Index to theShock and Vibration

Bulletins 36 Through 41

JANUARY 1972

A publication ofTHE SHOCK AND VIBRATION

INFORMATION CENTERNaval Research Laboratory, Washington, D.C.

Office ofThe Director of Defense

Research and Engineering

NATIONAL TECHNICALINFORMATION SERVICE

This document has been approved tfr publc re ,tce antu %atle: its di•,tribution is unlimted.

Index to theShock and Vibration

Bulletins 36 Through 41

JANUARY 1972

A Publication ofTHE SHOCK AND VIBRATION

INFORMATION CENTERNaval Research Laboratory, Washington, D.C.

Prepared byRudolph H. Volin

andHenry C. Pusey

Office ofThe Director of Defe"ne

Research and Engineering

Preface

The "Index to Shock and Vibration Bulletin Fos. 1 through 24" was publisned in October 1957and it was declassified and included as an appendix to the "Index to Shock and Vibration Bulletin25 through 35". Bulletins 36 through 41 were published in 43 parts between January 1967 andDecember 1970 and this volume provides a complete index to these Bulletins.

This index is divided into three parts. In Part I subjects are compiled in alphabetical order.Part H consists of a list of authors in the same way. Part III contains a reproduct ion of thecomplete table of contents for each of the Bulletins by number and part.

Each entry in Parts I and I1 is followed by a basic three-number set. The first numberidentifies the Bulletin, the second number the part, and the third number the page. The appear-ence of more than one three-number set, is an indic.a'ion of more than one reference for a singlelisting. The following -examples will serve as illustyations:'

_ _- Bulletin number

Part number

Mass matrices for piping systems 40-4-148

L Page number

Bulletin numbers

-_ _ Part numbersDamping in cylindrical shells 38-3.421, 39-1-155

-- Page numbers

Appendix A contains a c o mo l e t e list o. Bulletin 36 t h r o u g h 41 with their DDC accessicnnumbers where applicable. Instructioas for ordering Bulletins are contained in the same appendix.

Acknowledgement

Appreciation is expressed to Mrs. Katherine G. Jahnel for t y p in g the index cards and theauthor index, Mrs Margaret Farker and Mrs. Evelyn Starrett for their typing the indey cards andto Mrs. Barbara Szymanski, and Miss Patricia Fletcher for their typing of the manuscript.

'Ii

Table of Cont, ),'s

Preface iii

Part I - Subject Index - Shock ari '"ibt'ationBulletins 36 through 41 1

Part II - Author Inc9x - Shock j VidbrationBulletins 36 through 41 67

Part III - Tables of Contents - ,',ock and VibrationBulletins 36 through ', 77

Appendix A - Listing of Shock, Vibratio.iBulletins 36 thrc ir• 41 127

V

Part I

Subject Index

Shock and Vibration Bulletins36 Through 41

SUBJECT INDEX

A for gunfire environment on aircraft,

A7 aircraat 41-4-134

gunfire environment, 40-6-27, 41-4-133 for gunfire environment on helicopter,41-4-109

Acceleration at simulated launch vehicle spicecraftanalysis of data, 38-2-113 intertace, 40-3-87of beams with moving point loads, 41-6-55 for spherical structure, 41-7-97in damping collar, 40-5-161 from underground explosion, 41-6-80vs frequency

for electrohydraulic test system, Accelerometers40-5-249 base-strain, 37-2-48

ground shock base-strain sensitivity tests on, 37-2-44hydraulic pressure pulse from, calibration of, 37-2-17, 41-3-1

41-5-144 using Fourier integral transforms,gun setback 37-2-17

instrumentation for, 36-2-58 shock test facilities for, 40-2-205measurcment of, 36-2-53 standards for, 41-3-1

landing compensation of data from, 40-7-125attenuation of, 40-2-183 copper ball

limitations use of, 37-3-219as shock severity criteria, 40-2-31 design of, 41-3-17

limiting effect on structures, 41-3-6in vibration tests, 41-4-117 for environment of eggs, 41-- 3-11

linear and angular errors in, 37-2-43simultaneous tests, 41-3-155 using ferrofluid ultrasonic interferometer,

measurements 41-3-17on aircraft landings, 40-6-45 frequency response of, 41 -3-1on catapult launched aircraft, 40-6-47 high acceleration shock t. .. of, 40-2-205on railroad cars, 39-6-49, 41-4-154 for measirement of ground shock,40-7-133on simulator for human head impact, for meast rement of mobility matrix of

39-5-90 structures, 40-. 7-152response for measure'iernt of transportation

to air pulser impulse, 41-S-16 environments, 36-6-165as criterion for selection of normal for natural frequencies of plates, 41-7-41

modes, 40-7-170 nonlinear inertialon railroad cars, 40-6-115 affected by randnm vibration, 37-2-87of scale model hull, 41-S-18 oil damping in piezoresistive, 41-3-7

on tracked air cushion vehicles, 40-4-58 ringtransfer function stress concentration in, 37-2-43

for lumped parameter system, 38-2-108 vibration test using, 37-2-48use of, 36-3-20

and vibration, 36-3-119 Acceptance tests, see Qualification tests and

Acceleration probability density Quality Control Tests

for gunfire vibration in helicopters, Acoustic data, see Acoustic e.ivironment41-4-218

for vibration in hclicopters, 41-4-230 Acoustic environment

Acceleration pulse of airborne weapons, 39-S-16, 40-6-18,definition of energy density of, 39-5-83 41-S-34, 41-S-37on electrodynamic vibration exciters, of Apollo Applications Program payload,

40-2-176 39-3-61

Acceleration spectral density of Apollo Lunar Module, 37- 5-148,40- 3-163

for vibration of aircraft, 40-6-49 effect of airspeed on, 37-S-100on F-111B aircraft, 39-6-93

for vibration of avionics equipment, 40-6-52 in-flight vs laboratory test, 37-5-31Acceleration-time history instrumentation for, 36-7-93, 37-S-95

on drop test zhock machines, 41-5-59 of launch vehicle, 36-5-97, 36-7-89Fourier transIorm of predicted, 40-3-88 of OGO spacecraft, 36-7-91

Preceding page blank

of Phc.. xx Missile, 39-6-93 Acoustic Mobility/Imnedance Tr-nsducer(AMIT)predictioui of, 36-5-97, 41-4-168 description of, 40-4-198of RF-4C airplane, 37-S-95of re-entry vehicles, 40-3-33 Acoustic noise, see also Noiseresponse of structural components to, attenuation of, 38-3-109

36- 5-97 prediction of respc-.'se to, 41-4-87of Saturn V Launch Vehicle, 39-6-133spacecraft, 40-3- 52, 40-4-103 Acoustic powertest facility for low pressure, 41-3-207 prediction ofof UH-IF helicopter, 37-S-73 for VTOL Aircraft, 41-4-167of VTOL Aircraft, 41-4-161wind tunnel, 37-7-221 Acoustic radiation

from aircraft, 41-4-161Acoustic excitation resistance of cylindrical shells to, 40-3-23

of aerospace structures, 37-5-55, 41-7-1of airborne weapons, 39-S-15 Acoustic spectra, see also Power spectraof aircraft structures, 39-3-87 shaping of, 37-S-64combined with airblast, 39-3-65 for VTOL Aircraft, 41.4-164mathematical analysis of response to,

39-3-55 Acoustic test facilitiesprediction of flight vibration from, 36-5-85 for acoustic fatigue tests, 37-S-63of re-entry vehicl, s, 40-3-31 for aerospace '-ehicles, 37-5-1respouse to broad band random respr- ce for, 37-.0-21

Apollo Lunar Module, 40-3-172 calibration of, 37-5-147cylinders, 36-5-104 data analysis for, 37-S-35panel, 38-1-1, 40-3-57, 40-5-49 definition of noise field in, 39-2-87plates, 36-5-104 description of, 37- 5-33

of rocket motors, 41-6-115 design of, 37-S-17of shells, 40-3-23, 40-3-31 design of reverberation chamber for,of solar panels, 40-3-49 37-5-13during static firing tests, 39-6-135 instrumentation for, 37-5-19,37-5-42,and strain respoizse, 36-5-77 37-S-34structural damping during, 41-2-105 performance characteristics, 37-5-20,structural failure from, 39-3-65 37-S-17of structures, 36-5-89, 39-3-65, 41-1-13, performance of horn in, 37-5-46

41-6-211 scale model, 37-S-27vibration response to, 38-1-1 for si.-ulation of inflight noise, 37-S-64

sound ge,'erators for, 37-S-30Acowutic fatigue for spacecraft, 37-5-25

of boron fiber reinforced panels, 39-4- 101 vibration tests in, 37-5-8, 37-5-51of panels, 38-1-1susceptibility areas for, 37-S-19 Acoustic teststests of airborne weapons, 40-6-9

on aircraft stmctures, 37-S-63 of aircraft structures, 37-S-43facility for, 37-S-17 amp"'Lde distribution during, 38-1-4instrumentation for, 40-7-17 of Apollo Lunar Module, 37-5-109procedures for, 37-S-43, 40-5-54 of Apollo spacecraft, 37-5-25, 37-5-93,specimens for, 40-5-51 37-5-153viscoelastically damped panels, 40- 5-49 assembl7; level, 37- 5-117

of boron fiber reinforced panels, 39-4-101Acoustic filter compared to • ibration tests, 37-3-7, 37-3-21

helical coil as, 41-2-77 compa-ison of cpacecraft flight data with,36-3-44, 37-3-23

Acoustic generators, see Acco.th. test facilities of damped cantilever beams, 41-2-109data analysis for, 37-5-77

Acoustic impedance derivation of spectra for, 41-3-46in shock analysis of fluid systems, 40-2-67 of electronic equipment, 37-3-8, 40-S-78

establishing noise field for, 37-S-47Acoustic levels, see Boundary layer noise and failures, 37-5-170

Sound pressure levels. flight acoustic environment vs, 37-5-31

4

instrumentation for, 37-S-53 Aero-ipce atructu-weson Launcb Phase Simulator, 37-3-182 acou ,tic excitation of, 41-7-1low level acoustic test facility for, 37-5-1

to predict re.-pnase at high levels, damping of, 40-5-141-4-97 prediction of vibration of, 41-7-1

at low pressure&;, 41-3-.%07of models of spacecraft, 40-4-105 AH-1 Helicopter, 41-4-195of OGO spacecraft, 3?-3-2of panels, 39-4-103, 40-5-54 AH-56 helicopterprediction of response to, 41-.-87 ammunition conveyor system for, 40-4-115of propellAnt system, 41-7-155 response to blast of weapons, 40-1-70purpose of, 41-4-2as qualifization tests, 37-5-139. 27-5-167 AMM-4D missilereapnse of cylinder to, 37 ý-69 captive flighL environment, 37-1-125reverberation chamber ar, 39-2-87, data acquisition system for, 37-1-128

41-3-207 on F-4 aircraft, 39-1-195simulation ot vibration by, 37- 6-1,37-5-153 flight test vs system test, 39-1-217of spacecraft, S6-3-42, 37-5- 1, 40-3- INSof spacecraft conmponents, 36-3-39, 41-3-207 Airof upstage test vehicle, 41-6-19 as a damping mechanism, 36-4-75vacuum tests combined with, 37-5.- 175vibration t, simulate, 38-1-115, 40-3-252 Air blast, see also Blast

acoustic excitation combined with, 39-3-65Acoustic waves oi aircraft, 40-2-123

f ,orm vnderwarer explosions, 40-J .•5 charActeristics of, 57-1-81compared with underwater explosions,

Active vibration i&,lators, see awso 'Ahork 36-1-13 37-1-29oisolators and Vitbrati.on isolators damage to str':ctures from, e0-1-36

attenuaticn of •ibratior, in, 37-6-66 desigt forcharacteristc& of. 37-6-29 ,1 antennas, 3 7-• zdesign of, 37-6-3ý ol deck house. 39-1-107electrohydraulic, 39-4-141 drag loaf's from, 40-2-104for helicopters, 37-6,63 effects ofperformance of, Z7-G-,S-t cii zircraft carric-.s, 37-4..143shock response of, 37-6-69 on ;atennas, '±5-±-oi, 40-1-45transmissibUicy o:, 3V-6-45 oa performance of prin e movers,

:47-4-127Admittarnce, see Mechwdcz! impedance on protective structures, ý 8- 2-18"

on -.4hips. 36-1-13, 3,-l-1Advanced OrbiAng SoWar Olzservitory Space- emperimsntai vs predicted resi onse co,

craft (AOSO) 40-1-51. 4),1-03design for torsional stock, 36-7-63 field tent in an' ',nas, 37-4. 153qualification test requiremnents, 36-7-71 1'r•ue oi vev.icies to, 41-1-.35

'nteacdion v. !th structures, 3"-4-179Aerial delivery irernal loading o. structurcs by, 37-4-185

impact during, 41-3-,23 ()adis: 'ulation of, 97-3-19S. 41-3-223 on aisctcaft zomponents, 40-2-123

on above ground structures, 41-1-35Aerodynamnic drag 'ýn uitenna mast s*tuctures, 40-2.101

measurements o±, 40-2-63 on cyl•nders, 40-2-83&n deckhouse structure, 39- 1- 109

Aerodynamic loads effecta of sliding on, 37-4-193simulation of, 40-6-2 on laztc', type structure.s, 40-2-101

inathematical analyels of, 39-5-33Aerodynamic noise r , ships, 39,, 1- 95

tests, 37-S-l203 oa spheres, 39-5-29data analysin of, t3i.3-Z0• cn structures, *)7-4- 06, 37-4-193,ree:ults, 37-3-210 39-34.-5, 0-3,, 4,4-.45ot s "ale model Titan, 37-3-203 ox. vans. 37- 4--19,

K

nuclear airblast on, 40-2-123attenuation of ground shock from, elastic response to, 40-2-126

40-4-217 plastic response to, 40-2-128effects on above ground structures, catapult launchings of

37-4-213 acceleration measurements for,response spectra for, 41-S-4f 40-6-47shock pulse for, 40-4-219 compatibility with engine, 41-3-55

on open-frame structures, 38-2-117 crash loads on, 36-3-165plastic response of aircraft to, 40-2-128 mathematical analysis of, 38-'-166pressure time history for, 37-4-18r response of mathematical model for,propagation into structnres, 37-4-185 38-3-169response to simulation of. 41-3-133

of antennas, 37-4-151, 40-1-31, damping of radar antenna for, 38-3-5840-1-45, 40-1-75, 40-2-101 effect of flight parameters on captive

of blast closures, 40-2-133 flight vibration, 39-1-208of gas turbines, 40-2-147 gunfire environment inprediction of, 40-",-49 acceleration time history for, 41-4-134of re-entry vehicles, 39-1-223 isolation of recoil from, 39-4-251of shell Str'M.LZIs, 37-4-177 simulation of, 41-4-37of ships, 37-1-77 gun system forof structures, 37-4-169, 40-1-31, mathematical analysis of, 39-4-2Z5

40-2-101, 41-1-35, 41-S-45 landings ofupper and lower bounds for, 37-4-169 acceleration neasurements for,

test facilities 40-6-48for SAFEGUARD, 40-2-243 braking stops, 39-3-185shock tubes, 39-1-102, 39-5-41, vibration of landing gear, 39-3-179

39-5-53 modal surveys of, 36-3-55, 39-2-63tests mode tuning for, 36-3-67

on antennas, 37-S-14, 40-1-31, suspension system for, 36-3-6240-1-45, 40-1-80, 40-2-105 noise surveys of, 41-4-161

on gas turbines, 40-2-147 instrumentation for, 41-4-163structures

Air cushion vehicles acoustic excitation of, 39-3-87response of guideways to, 41-6-41 airL -- t load on, 40-2-125

response to pressure loads, 41-6-55 Clarkson's Method for prediction ofstress in, 39-2-8t'

Air drop, see Aerial delivery comparison of mtsa± ured and predictedstress in, 39-3-9:

Air guns, see Shock test facilities shock analysis of, 40-2-123

Air jets, see Acoustic test facilities Aircraftvibration of, 41-4-133

Air springs, see Pneumatic springs ribration icolation in, 39-4-157

Airborne equipment Aircr.tft carriers, see Shipsprediction of vibration of, 38-S-5

Aircraft seats

Airborne weapons, see also Captive flight czash simulator for, 41-3-133captive ilight environment on propeller

aircraft, 39-S-26 Amplitude, see Displacementcaptive flight vibration, 39-8-15cavity resonance in, 39-S-24 Amplitude control systemcriteria for qualification tests, 39-S-33 dynamic characteristics of, 36-3-1 0gunfire environment for, 39-S-27 response limitation of, 36-3-151laboratory vs flight vibration response,

39-S-33 Amplitude distributionduring acoustic tests, 38-1-

Aircraft, see also specific aircraft such as A-7,

C-130, C-133, F-4, F-111, RF-4C, and XB-70Ao Analog computers, see also Computers, Digitaletc., Computers and Hybrid computers

6

for analysis Command moduleof nonlinear systems, 36-3-43 impact attenuation for, 38-3-255of scale model launch vehicie, 40-3-208 yn.mic test program, 37-5-89, 39-2-105of shock data, 36-6-37 iquations of motion for, 37-5-59of shock spectra, 36-6-43 evaluation of flight vibration data for,

calculation of response spectra by, 36-6-37 37-5-100for damping calculations, 40- 3-151 flight vibration environment for, 37-5-90for estimation of fatigue damage, 41-3-60 Lunar modulefrequency stepping circuit for, 36-6-39 acoustic tests of, 37-5-109, 37-5-139for real-time analysis, 41-3-55 acoustic and vibration environments,for simulation of 37-5-139, 40-3-163

displacement, 39-6-53 engine induced vibration for, 37-5-107impact, 40-5-188 flight vibrati~xi vs ground test,motion of antenna booms, 36-6-197 40-3-174vacuum spring, 36-7.107 launch _%vironment V., s7-5-106vibration, 40-S-15 mathem. tical anwlysis of, 39-3-55

response te vibration and acousticAnalog/digital conversion excitation, 40-4- 172

data system, 36-6-56 structural response of, 31-5-150development of, 37-5-78 vibration of, &0-3-166

vibration tests, 37-5-105, 37-5-142Analysis, see subject of analysis or specific random vibration criteria for, 39-2-107

analyses such as Dynamic analysis Service Moduleresponse to pyrotechnic shock,

Analyzers 37-4-15for digital analysis of shock, 36-6-21 shock spectr, hr, 37-4-23for vibration, 36-6-49 vib,-ation test program for, 37-5-154

vibroacoustic test of, 36-3-39Anisotropic materials "Short-Stack"

analysis of, 39-3-201 combined environments test program,40-3-211, 40-7-99

Antennas Spacecraft Lunar Module Adapter (SLA)airblast tests of, 37-4-151, 37-S-14, vibration characteristics of, 37-5-58

40-1-31, 40-1-45, 40-1-75, 40-2-101 structural analysis of, 39-3-55Whip vibration qualification for components

analysis of, 40-1-47 of, 37-5-153criteria for materials for, 37-S-8 vibration test procedures for,damping of, 36-6-195, 39-4-1 39-2-110with extr.n~ible booms, 36-6-195design of simclatea, 40-2-104 Apparent weightdynsm'c analysis of, 37-4-159, 40-1-45, definition of, 37-3-62, 41-4-30, 41-4-110

40-1-VC and input force spectrum, 41-4-113paraboloiel simulation of, 36-3-47, 37-3-64

structu:i-l dynamics of, 41-6-103mat,,ematical model of, tl-6-104 Applications Technology Satellite (P TS)natural frequencies of, 4 '-6-110 combined environment tests oi,

predicted vs measured response to airblast, 37-5-17540-1-39, 40-1-49, 40-1-83 design and analys!s of, 36-7-41

shipboard, 3'7-4-151, 40-1-31, 40-1-45, natural frequencies of, 36-7- 5540-1-75 qualification test levels for, 36-7-58

Shock hardening of, 37- S- 1 response spectra for, 36-7-50simulation of motion bv analog computer, iibration characteristics of, 36-7-48

36-6-197twang test on, 40-2-108 Arches, see Hinged archwire rape

stress analysis of, 40-1-76 Armament .ystemsdesign of rei.oil adapters for, 39-4-251

Apoll. spacecraftacoustic test facility for, 37-5-25 Army equipmentacoustic test nrocedures for, 39-2-112 field tests of, 39-6-1

7

(

Asymptotic method cantileverfor determining response to vibration, dynamic analysis of, 39-3-130, 40-4-1

41-4-128 failure analysis of, 37-4-50finite elements for, 41-7-53

Atlas Booster influence coefficients for, 37-2-61dynamic analysis of cannister tethered to, lumped mass mathematical models

40-4-225 for, 41-7-55mechanical impedance of, 40-7-65

Atlas/Agena-D launch vehicle normal modes of, 39-3-134noise measurements op. 56-7-89 stresses in, 40-4-1

clamped- clamped, 36-4-10At-enuation, see Shock isolation and Vit ration composite

isoiation damping of, 36-4-37, 38-3-13, 41-2-133dynamic characteristics of, 36-4-28

Autocorrelation functions flexural vibrations in, 38-3-18from optical systems, 36-6-98 with compound sidebranch resonatorpower spectra and, 37-2-90 dynamic analysis of, 41-6-211

computer programs for, 38-1-76Automobiles conical

crash hazards for, 38-3-327 mathematical model of, 37-2-177dynamic tests of, 40-4-89 crack detection in, 38-1-55protective system for impacts of, 38-3-329 critical buckling loads for, 40-4-49response to dynamic tests, 40-4-94 cross-correlation analysis of cracks,safety criteria for, 38-3-325 38-1-55vibration isolation in, 38-3-317 damped

acoustic tests of, 41-2-109Auxiliary vibration table analysis of errors in calculations,

for electrohydraulic vibration exciter, 41-2-13541-3-113 dynamic analysis, 36-4-50

loss factors for, 38-3-8, 39-1-167Averaging method of Ritz, 40-5-262 meLhanical impedance analysis,

41-7-53Averaging techniques multilayer, 40-5-40, 41-2-121

for control of vibration tests, 36-3--39, symmetric and unsymmetric, 36-4-4337-3-75 unconstrained layer, 40-5-47

vibration of. 39-4-53B design charts for, 39-3-52

discrete models of, 41-6-163BaL~ncing dynamic analysis of, 38-1-67, 40-4-37,

of shafts, 41-6-204 40-4-81, 40-4-187, 41-6-47, 41-6-123,41-6-133, 41-6-163, 41-7-51

Ball peening tests, 37-2-41 failure analysis for, 37-4-43finite element analysis of, 38-1-10,

Base- strain sensitivity teo's 41-6-123, 41-7-51on accelerometers, 37-2-44 as foundations for machinery, 39-1-124

free-free, 37-3-93, 38-1-67, 40-4-35Bayesiai statistics holography for shock analysis of, 40-7-38

in structural reliability, 36-7-31 holography in study of vibration of, 40- 7-34laminated

Beam- columns analysis of, 36-4-81stiffness matrix of, 40-4-187 loss factors for, 36-4-83

mathematical analy. s of, 39-3-6Beams modal density of, 39. j- 1

r3ernoulll- Euler vibrations ol, 40-5.217frequency parameter tor, 3f-3-49 lumped mass matrix for, 41-6-123

oilinear hysteretic lumped parameter analysis of, 36-6-117mathematical model of, 41- 5-28 mathematical model, 38-2-13propagation of yielding in, 91-4-81 mcchanical impedance of, 38-2-222,response spectra for, 41-5-30 41-7-51

modal analysis of, 39-3-143, 40-4-50, of frames, 38-2-22041-6-136

modal effective nass of, 39-3-145 Bending momentsmode numbers of, 36-4-86 in beams with moving point lods, 41-6-55mode shapes of, 38-3-122, 41-6-164,

41-6-211, 41-7-51 Bibliographymoment curvature relationship for, on vibration equivalence, 39-2-190

41-6-147with moving point loads Blast, see also Air blast

forced vibration of, 41-6-49 from weaponsnatural frequencies of, 39-3-49, 40-4-2, effect on AH-56A hclicopter, 40-1-70

40-4-49, 40-5-277, 41-6-164, 41-6-211, effect on CH-47A helicopter, 40-1-6741-7-51 effect on UH-IB helicopter, 40-1-63

nonlinear, 41-5-29 helicopter response to, 40-1-61,non-uniform, 38-1-69 40-2-227pinned, 36-4-55 prediction )f field of, 34- 6-139reinforced concrete, 38-2-133 prediction of loads on helicopters,resonant 40-2-231

high acceleration vibration tests scaling laws for, 39-6-141using, 39-2-71

as tuned dampers, 39-4-19 Blast closuresresponse of full-scale and model valves

to moving prespure loads, 40-4-47 comparison of overpressures for,to shock, 40-4-3, 41-5-27 40-2-136static, 38-2-158 response to air blast, 40-2-133

root errors in frequencies for, 41-6-137scale model, 39-3-39 Blast Icadsshock loads on, 41-3-64, 41-6-147 stress analysis of submeiged structures,simply-supported, 36-5-77, 37-4-53, 40-7-203

38-1-11 on targets, 41-1.36Timoshenko, 40-4-2vibr2tion of, 38-3-13, 39-3-49, 40-2-40, Blast waves

40-4-47, 41-6-163 characteristics of, 41-1-26vibration analysis of, 40-5-P77 damage potential of, 41-5-1 1viscoelastic sandwich, 38-3-13, 39-4-117 drag coefficients for cylinders in,40-2-83wedge shaped, 41-6-139 interaction with helicopters, 40-2-228

Beam spring systems Bombscouplea bending and torsional vibration low dr',g

of, 36-6-121 flight vibration tests of, 41-S- 33

Bearings Boosters, see Launch vehicles and Missilesdynamic response of gas lubricatea,

38-3-221, 40-3-275 Bond strengthinstrumentation for dynamic tests of, of liquid squeeze-films, 39-2-77

40-3-277oil squeeze, 38-3-45 Boundary layer noise, see also Sound pressureprocedures for dynamic tests ox', 40-3-280 levelstest facility for, 38-3-222 for Apollo spacecraft, 37-5-28

comparison of sources of, 37-7-78Belleville spring, 41-2-37 correlation coefficients for, 37-5-63

joint acceptance for, 37-5-65Bending frequencies on launch vehicle, 36-5-97

of non-uniform shafts, 38-2-169 predictions of. 39-6-105, 41-7-4of railroad cars, 40-6-115 structural response to, 36-5-102, 40-3-C63

in weapons bay of F-111B aircralt,Bending modes, see also Modal characteristics 39-6-105

and Normal modesof beams, 38-1-67 Brake squealcomparison of test and theoretical,39- 2-139 in aircraft landing, gear, 39-3-179

9

Bridges instrumentation for vibration test for,dynamic analysis of, 41-4-99 40-6-15vibration tests of, 41-4-101 measurement of, 37-1-178, 37-1-195modal analysis of, 41-4-106 for Phoenix Missile, '19-6-77, 39-6-93

predicted vs measurec, 39-6-80,Buckling loads 39-S-27

on viscoelastic sandwich beams, 39-4-118 problems in simu2ation of, 40-6-61on propeller aircraft, 39-S-26

Buffel-,,g simulation in wind tunnel, 40-3-9of Titan MI models, 37-3-121 specification of vibration tests for,

39-1-212Buildings for Standard Antiradiation Missile

mass-spring model of, 38-2-190 (AR4), 4A-6-68for SUU-36 munitions dispenser,

13ullpup Missile 40-6-9rocket-propelled aled tests of, 39-1-179 for SUU-38 munitions dispenser,

41-5-89Bump tests vibration test, 40-S-48

of communications equipment, 39-6-15 vibrationdesign of machines for, 39-6-15 of airborne weapons, 40-6-9, 41-S-25,as a quality contr-'1 tool, 39-6-18 41-S-33

effect of aircraft flight parametersC on, 39-1-208

of FAE weapons, 40-S-47C-130 aircraft of helicopter trap weapons, 40-S-47

power spectral density on, 37-7-29 versus MIL-STD-810A, 37-S-115of missiles, 39-1-195, 40-S-67

C-133 aircraft panel discussion on, 40-S-83power spectral density on, 37-7-32

Captive tests, see Static firing testsCalculator

for critical damping, 38-3-89 Cargo, see Packaged equipment

Cailbration Catenary horns, see Acoustic test facilitiesof accelerometers, 37-2-17, 41-3-1od charge amplifiers, 36-6-212 Cavitationby comparison, 36-6-193 effects on response of hulls to underwater',f high-frequency microphone, 37-2-7 explosions, 41-S-50laser fur, 37-2-1 in underwater explosions, 41-S-49for laurch phase simulator, 36-6-207shock test facilities for 40-2-205 Cavity resonanceof vibration exciters 36-6-183 in captive airborne weapons, 39-S-24,

40-6-11Cantilever beams, see Beams

Centrifuges, see Launch-phase simulatorCaptive Air Space Craft (CASC)

concept of, 41-1-1 CH-47 helicopterdistribution of induced velocity on, 37-6-4

Captive airborne weapons, see AirbornL weapons reduction ot vibration in, 40-5-191and Captive flight response

to blast of weapons, 40-1-67Captive flight, see also Airborne weapons

environment CH-53 heliclpterAIM-4D missile, 37-:-125 compatibility of Lurbine engine withfor airborne weapons, 39-S-15 aibiaty o9-3-17data analysis of, 39-1-208 airframe, 39-3-17

of FAE weapon, 40-S-56of helicopter trap weapon, 40-S-54, Chaparral missile

40-S-58 transportation tests of, 39-2-37

10

Charge amplifiers criteria for vibration of, 37-7-200calibration of, 36-.-212 qualification by acoustic tests, 37-5-153,

37-S-43Chatter synthesis into mathematical model of

in aircraft landing gear struts, 39-3-179 structure, 38-2-198computer program for simulation of, vibration tests of, 37-5-4, 38-1-87,

39-3-188 39-2-71

Chladni figures Composite loss factorfor vibrating panels, 39-3-11 for space-damped structures, 38-3-32

Clarkson's Method Composite materialsfor prediction of stress in aircraft acoustic tests of, 39-4-101

structures, 39-3-88 dynamic characteristics of, 36-4-95predicteJ and experimental characteristics,

Columns 36-4-104mathematical analysis of, 39-3-248, shock wave propagation in, 41-5-69

41-6-2 vibration of fiber-reinforced, 39-4-81,parametric response to shock loads, 39-4-93

40-2-115parametric response spectra for, 39-3-247 Composite structuresparametric vibration of, 41-6-1 damping in, 38-3-24, 3e-3-57response to shock pulses, 40-2-117unstable regions for, 41-6-5 Compressed air launchers, see Shock test

facilitiesCombined environmental tests, see also Launch

Phase Simulator Computer programsof Apollo short stack, 40-3-211 for analysis of ground motion, SPECANAL,data acquisition for, 40-7-99 41-6-79facilities for, 36-3-119, 37-3-175, 40-2-51, for analysis of shipboard vibration,

40-3-293 36-6-115load control systems for, 40-3-225 for brake squeal simulation, 39-3-188use of regression analysis in, 36-6-83 for chatter simulation, 39-3-188of shipboard electronic equipment, 36-6-83 for combined environments test, 40-7-107of spacecraft, 37-5-175 for dynamic analysison subsystems of Orbiting Astronomical of antenna mnst, 40-2- 105

Observatory, 40-3-189 of gas turbine;;, 39-3-i 1of timers, 40-3-293 of shipboard equipmnt, 40-IR-2

of structures, 37-2-173, 40-7-178Combined en% Ironments Dynamic Design Analysis Method (DDAM),

effects on electronic equipment, 36-C-83 36-6-101, 39-1-61failure of structures from, 39-3-67 FAST

for evaluation of hardness of weaponCombustion Instability tests systems, 41-5-135

on the Saturn IB Satu-- launch vehicle, FORTRAN IV language, 36-6-105, 36-6-13140-4-109 for line solution method, 38-2-167

M•tARS, 37-2-190Complex structures for mechanical receptance, 38-2-242

analysis of mechanical impedance for, for modal combination, 38-2-13938-2-271 NASTRAN, 39-1-62, 41-6-203

dynamic analysiS of, 39-3-153 for normal mode analysis, 36-6-101stress waves in, 38 2-33 for on-line data analysis, 40-7-117vibration analyFis of, 39-3-99 for perturbation analysis (PTtrB),

40-7-179Component mode synthesis for pi opagation of shock waves, 40-4-135

theory of, 41-6-116 for response of panels to boundary layerfor vibration "nalys'- of rocket aotors,, noise, 40-3-63

41-6-115 for response of tower to ground shock,( DYNE), 41-6-82

Components, see also Electronic components for shock analysir, 36.6-131. 40-7-153

11

for sho.ck spectra, 36-2-12 point-to-pointfor structural analysis of sound pressure levels in

of beams, 38-1-76 reverberation chambers, 39- Ž-87of helicopters, 4A-2-238 in projectile - target interaction anal) s's,of compley, structures, 37-2-173 37-1-121

Structural Anal'ysib Matrix InterpretiveSystem (SAMIS), 38-2-139, 41-6-115 Cr:'elation analysis, 37-7-81

for study of isolation systems. 38-3-214,38-3-295 Correlation coefficients

for boundary laye: turbulence, 37-5-63Computers, see also Analog computers for reverberant acoustic ideld, 37-5-65

Digital computers and Hybrid computerscalibration of vibratit,, exciters using, Correlation lunctions

36-6-183 for panels, '.0-3- 59for dynamic analys's, 36-6-101flow L'iagrams for stiffness analysis on, Coulomb damping, see Damp.ing

17-6-22graphic techniques in analysis of Coupling, see also Cross-,.oupling and

structures, 40-4-41 Dynamic couplingoptimum shock isolators using, 39-4-185 in statistical energy analysis, 38-S-!1vibration test of, 37-3-78 theory of receptance, 38-2-240

Concrete Cr~clr detectiondynamic properties of, 39-4-201 in beams, 38-1-b5.properties of crushable, 39-4-202for shock isolation, 39-4-199 Crash

hazards for automobiles, 38-3-327Cones respoiise -, aircraft during, 38-3-165

stress-time history for truncated, 40-4-'31Crash energy dissipators, 39-4-236

Consistent mass matrixfor beams, 41-6-123 Crash injuries

design of an automobile for reduction of,Contained equipment, see Packaged equipment 38-3-325

Containers, see also Shipping containers Crash simulationmissile on scale model of aircraft fuselage,

snock test facility for, 37-4-137 38-3-171suspension systems for, 39-6-57 scale models for, 39-4-230

Continuous systems Crashworthinesstransient response of, 38-2-112 of automobiles, 38-3-325

test facility for aircraft seat, 41-3-133Control system

for transient waveforms on electrodynamic Creepvibration exciters, 40-2-160 of composite materials, 36-4-95

Co-p'hasors Critical dampingdefinition of, 37-2-77 calculator for, 38-3-89

Co quad analysis Critical flutter, see Gallopingdescription of, 41-3-37phase plotting for, 37-2-77 Critical speeds

damping for control of, 38-3-45Correlation, see also Cross correlation of propeller shafts, 36-6-121

Cook's theory of, 39-2-89 of shafts, 41-6-203effect of chamber geometry on noise

field, 39-2-93 Cross correlation, see also Correlationof flight vehicle vibration resporise, analysis of cracks in beams, 38-1-55

37-7-77 coefficien!

12

definition of, 39-2-90 shockfunctions criteria for structures, 40-2-31

definition of, 39-2-89 mechanisms for, 37-4-71for optical systems, 36-6-98 to shipboard equipment, 39-1-1between random vibration inputs, 39-2-51 of structures

probability for combited environments,Cross- coupling 39-3-65

between vibration exciters, 37-3-155 from underwater explosions, 37-4-71

C ross-motion Dampingcriteria in air versus a vacuum, 36-4-75

in vibration tests, 40-6-64 analog computer simulation of, 40-5-151reduction of, 39-2-157 analysis of multifrequency, 38-3-74

of antennas, 36-6-195, 39-4-1, 40-5-4,Cross-power spectral density, see also Power 40-5-147

spectral der sity of beamsdefinition of, 39-2-90 by constrained layers, 38-3-5.of generalized force, 40-3-60 38-3-13, 30 4-53, 40-5-40, 41-2-121,by recursive filtering, 36-6-65 41-9- 133

errors in calculation of, 38-3-25Crosstalk, see Cross-motion mathematical analysis of, 41-2-133

modelo for, 36-4-65Crushable structures, see also Yielding by unconstrained layers, 36-4-37,

structures and !ioneycombs 40-5-47design criteria for, 41-2-95 calculator for, 38-3-89scale models in study of, 39-4-227 characteristics of thrust bearing, 40-3-2P2as shock isolators, 39-4-1e9 corcept of single-particle impact, 39-4-1

crnsiderations for vibration test levels,Crystal accelerometers, see Accelerometers 39-2-153

for control of critical speeds, 38-3-45Cyclic deformation coulomb

energy absorption by, 38-3-255 effect of system response, 36-1-47in cylindrical shells, 38-3-121, 39-1-155

Cylinders effectair blast tests of, 40-2-83 on dynamic load factors, 41-S-4.1analysis of multilayered, 40-4-127 of errors on measurements, 38-3-153fluid induced vibrations in, 41-6-31 on response of loose systems toflutter of, 40-3-308 vibration, 41-6-39response of on response of mechanical systems

to acoustic excitation, 36- 5-104 with gaps, 41-6-42to boundary layer noise, 36-5-102 on upper and lower bounds of shock

self-excited vibrations of, 40-3-303, spectra, 40-2-22341-6-31 evaluation of coefficient, 36-4-69

stability analysis of, 41-6-33 extensionalvibration analysis of, 36-5-107 attenuation of acoustic noise using,

38-3-199Cylindrical shells dynamic properties of materials with,

Hamilton's Principle in dynamic analysis 38-3-202of, 40-3-134 in flight configuration of Upstage vehicle,

torsional vibration of, 36-5-115 41-6-23with grooved slider on rotating shaft,

D 38-3-112for helicopter rotor systems, 41-2-141

Damage, see also Fatigue damage at high temperatures, 36-4-25, 38-3-57boundaries for packaged equipment, impact, 39-4-3

40-6-127, 40-6-133 inelastic, 40-5-61to eggs during impact, 4'-1-11 of joints in structures, 36-4-1prediction for o, en-frai structures, at low temperatures, 36-4-25. 38-3-57

38-2-177 in machinery foundations, 36-4-81,from pyrotechnic shock, 41-5- 10 38-3-1, 39-1-143. 39-1-167

13

materials effects of frequency on, 38-3-156characteristics of, 40-5-1, 40-5-37 effects of temperature on, 38-3-156composite, 36-4-95 evalmution of effectiveness of, 40-5-105criteria for effectiveness, 38-3-200 at extreme temperaturus, 36-4-25,effect of test sample geometry on, 38-3-57, 41-2-125

40-5-109 of helicopter vibrations, 41-2-141evaluation of, 40-5-105 measurements of, 38-3-151stress-strain properties of, 40-5-62 multifrequency response of, 38-3-71

of multi-modal vibrations, 36-4-49 for multi-span structures with,nonlinear 36-4-49

absolute ,•isplacement transmissibility of radar antenna, 38-3-58for, 40-5-32 viscous

isolation of vibration with. 40-5-19 approximation of, 40-5-23in launch vehicle structures, 40- 5-261 using a mechanical system, 38-3-111shock isolation with, 41-2-21

in pipes, 39-1-143 Data acquisitionuse of oil for, 38-3-45, 41-3-7 for air blast tests, 40-2-105of plates, 39-4-63, 40-5-93, 41-2-106 of aircraft vibration, 37-1-A54for reactor fuel assembly, 36-4-72 of captive flight environments, S7-1- !Z5,relaxation, 40- 5- 203 39-6-93, 40-S-47in scale models, 36-4-1 for combined environments tests, 40-7-99in shim spring vibration isolator, 37-3-165 with constant bandwidth FM system,in ships, 40-S-7 37-2-109for silencing of ships, 41-2-151 for helicopter ground vibration survey,single frequency, 38-3-72 36-3-76nf sonar domes, 41-1-13 on-line digital computers for, 40-7-99spaced, 39-1-167 of transportation envirc iments, 36-6-163,of structures 40-7-45

during acoustic excitation, 41-2-105aerospace, 40-5-1 Data analysisanalysis of, 38-2-271 of acceleration data, 38-2-113comparison of evaluation systems for acoustic tests, 37-5-77, 37-S-35

for, 38-3-89 of aerodynamic noise, 37-3-208using constrained layers, 38-3-71 from air blast tests, 40-2-84effect of air on, 36-4-75 of boundary layer noise, 39-6-106effects on mechanical impedance, for combined environments tests, 40-7-99

40-3-236 digital systems for, 40-7-115, 41-5-39at extreme temperatures, 38-3-57 of dynamic en~ironments, 41-3-55by impact, 39-4-1 equipment for mapping of mode shapes,inelastic, 40-5-61 39-2-64in joints, 36-4-1 of flight data, 37-1-139by multi-layered treatments, 39-4-31, of gunfire environment, 37-7-206, 41-4-46,

39-4-53, 41-2-121 41-4-203, 41-4-210resonant beams for, 39-4-19 of helicopter noise, 37-S-74skin-stringer, 39-4-31 for high-force vibration tests, 37-3-143for sonic fatigue resistance, 40-5-49 of Mariner flight data, 37-4-5with stiff members, 38-3-29 for mechanical impedance, 41-5-54using vibration absorber, 40-5-147 on-line digital computers for, 36-6-57.viscoelastic materials for, 36-4-9, 40-7-99, 40-7-115

36-4-25, 36-4.49, 38-3-121, 38-3-139 using optical systems, 36-6-91of variable resonant vibration exciter, panel discussion on proposed standard,

38-S-3 39-6-7using vibration absorber, 37-6- 57 philosophy of, 41-3-81with viscoelastic materials of shock

of aerospace structures, 40-5-1 automated system for, 36-6-21using constrained layers, 38-3-37, desiderata for, 36-6-22

39-1-143, 39-4-53, 40-5-37, 40-5-93. on gun set-back acceleration, 36-2-5541-2-121, 41-2-133 pyrotechnic, 37-4-21

determination of properties, 36-4-37. on simulatoz for human head impact.39-4-11, 41-2-133 39-5-96

14

of tests on munitions dispenser, f-r vibration test fixtures, 36-3-10241-5-94

Af transportation environments, 37-7-19, Design philosophy39-6-34 for dynamic test facilities, 41-3-119

(4 vibrationsassemLly level tests, 37-5-129 Design procedure"during captive flight, 37-S-109, for shock is&, ation system, 41-2-68

39-1-208, 39-6-106, 40-8-47"--flow chart for, 40-7-230 Destroyers, see Ships

in hellcopters, 37-S-74from laigeelectrohydrau~ic test Detonations, see Gas detonations and Nuclear

system, 41-"3-115 detonationsmissiles, 37-7-98with on-line digital compter,. Digital computers, see also Analog computers,

36-6-57, 40-7-99 .. Computers, and Hybrid computersfrom pulsed random tests, 40-3-273 in analysis of fatigue damage, 36-5-17from Saturn tests, 36-6-55 for analysis of mechanical impedance,of shells, 39-3-107 41-5-53shipboard, 36-6-67 calculation of shock spectra by, 36-6-131on spacecraft in flight, 37-7-176 foi- control of waveforms of shock tests,techniques for, 36-6-47, 39-6-122 40-2-157

for wind tunnel test, 37-7-224 for design of shipboard equipment, 39-1-55,39-S-55

Data reduction, see Data analysis for determining mini-max response,36-5-71

Deceleration In dynamic analysis of antennas, 40-;-75of projectile during impact, 41-5-70 in dynamic analysis of helicopter

structures, 40-1-61Deceleration dei4ce for Dynamic Design Analysis Method

for protection of test specimen, 39-2-12 (DDAM), 36-6-101dynamic programming for, 36-5-74

Decks dynamic response of aircraft using,effect of equipment mass on shock motion, 38-3-169

40-1-1 for modal analysis of structures, 41-7-12on-line application for data analysis,

Deckhouses 36-6-57, 40-7-99, 40-7-115mathematical models of, 39-1-111 in optimization of structures, 39-1-63

programsDeflection, see Displacement for analysis of fatigue damage, 36- 5-25

comparison of, 36-5-65Delta launch vehicle for dynamic analysis, 36-7-45, 39-1-59

noise measurements on, 36-7-89 in shock analysis, 40-7-153, 41-5-39for simulation of overturning of structures,

Design, see specific lteits being designed 37-4-193for structural analysis, 38-2-139, 40-4-41,

Design c,'lteria 40-4-63for active vibration isolators, 39-4-159 for vibration analysis, 36-6-51, 36-6-115,for Advanced Orbiting Solar Observatory 37-2- 57, 38-3-295

(AOSO), 36-7-66for ATS-B spacecraft, 36-7-41 Digital recording systemsfor crushable structures, 41-2-95 for transportation environments, 36-6-163for deckhouse structure, 39-1-111for electronic components, 37-4-100 Dimensional analysisfor focal isolition system, 38-3-268 in scaling of performance of shock tubes,for Hawk suspension system, 41-2-160 39-5-55for impact limiters, 40-2-133for Inverting tube shock Isolator, 41-2-89 Dirac delta function. 36-5-119for Aldd isolators, 39-4-180for universal test fixture, 39-2-177 Direct stiffness methodfor unmanned spacecraft structures, for analysis oi structures with rotating

40-3-96 elements, 40-4-41

15

for dynamic analysis of continuum bodies, Dragon Missile36-5-55 vibration tests of, 40-3-268

in finite element analysis, 36-5-56in helicopter vibration analysis, 40-4-48 Drop ball testfor prediction of vibration, 37-6-20 impulse by, 37-2-21

Displacement Drop heightamplifier for shock, 41-3-149 effect of package size on, 37-7-14bounds for rigid plastic structure, 37-4-74 effect of package weight on, 37-7-13calculation from random vibration data, recorder for packages, 39-6-19

40-3-2 during rough handling, 37-7-4of composite panels, 39-3-191differential across structures, 40-2-1 Drop test machines, see Shock test facilitiesvs frequency for electrohydraulic test

system, 40-5-249 Drop testsof guideway structures for tracked air on different surfaces, 36-6-175

cushion vehicles, 40-4-57 rotational, 39-4-181of imperfect columns, 39-3-247isometric representation oi, 36-7-133 Ductslimiting device for vibration exciter, procedures for vibration tests of, 40-5-66

39-2-11mathematical analysis of railroad car, Duhamel integral

39-6-52 calculation of spectra using, 36-2-12measurement of

design of system for, 40-7-18 Dynamic analysis, see also Modal analysis,using holography, 41-3-63 Shock analysis, Mathematical analysis,using a multiple-beam interferometer, Structural analysis and Vibration analysis

37-2-13 of aerospace vehicles, 41-7-151proximity probes for, 40-7-17 of ammunition conveyor systems, 40-4-115

of shells, 38-2-84, 40-3-46 of anisotropic materials, 38-2-201test facility for simulation of large, of ballistic range models, 40-4-127

41-3-149 of beams, 41-6-211transfer functions for lumped parameter component mode synthesis for, 41-6-115

systems, 38-2-111 computer flow diagrams for, 37-6-22,40-IR-6

Displacement-time history of conservative systemsduring crash of vehicles, 39-4-231 Lagrange equations for, 41-6-87for Partial Full Scale Test Machine, Liapunov's functions for, 41-6-88

39-4-222 consideration of joints in, 37-2-182for sonar transducers, 41-1-30 cylinders, 41-7-93for spherical structures, 41-7-98 digital computer programs for, 36-7-45,of tower, 41-6-84 40-IR-2, 40-4-63, 41-6-203, 41-6-115

by direct stiffness method, 36-5-55Displacement transmissibility of driver section for shock tube, 37-4-131

for nonlinear vibration isolation system, Dynamic Substructure Method in, 39-1-5840-5-32 elasticity of launch rail in, 41-6-225

elastic-plastic, 37-1-25, 39-5-1, 40-4-67Distributed mass systems of electronic equipment, 37-4-97, 38-2-11,

response to base motion, 37-4-48 39-3-117of equipment, 40-2-215

Distributed parameter system of equipment-foundation system, 38-2-210calculation of modal response suppression finite element method, 38-1-7, 39-1-56,factor for, 38-2-277 39-3-129

flow path for, 41-6-179Drag coefficients of fluid-filled shells, 38-2-79

for cylinders in blast wave, 40-2-83 of fluid filled tubes, 41-7-144of foundations, 39-1-123

Drag loads of gas turbine, 39-3-21from air blast, 40-2-104 of grillages for ships, 40-7-207

16

of helicopter structures, 39-3-17, 40-1 -61 of control system for ,ibration tests,of hinged arches, 41-6-90 36-3-150improvement of mathematical model f'jr, comparison of using lumped parameter

36-5-1 method, 38-2-61of inertial guidance, 40-3-257 of composite beams, 36-4-28use of influence coefficients in, 36-6-101, of composite materials, 36-4-95

38-2-50 of crushable materiF.is, 41-2-98interface between stress analysis and, of gas turbine powered helicopters,

41.6-179 39-3-17of isolation system, 41-2-160, 41-5-129, measurement of

41-5-155 on equipment, 40-7-29of launch loads, 38-2-67 on structures, 40-7-51of launch vehicles, 40-3-205 of shock isolators, 41-2- 53of launch vehicles/spacecraft interface, of vibration test system with flexure

40-3-79 guides, 39-2-164line selution method, 38-2-163of lumped parameter systems, 38-2-57, Dynamic coupling

38-2-274, 39-3-153 between translation and rotation, 36-7- 135mass matrix in, 37-2-187mechanical impedance in, 38-2-8 Dynamic Design Analysis Method (DDAM),of nonconservative systems, 41-7-141 39-1-55, 40-1R-1of non-linear systems, 39-5-1 for analysis of motion of immersednormal mode method, 37-4-91, 41-2-105 solids. 40-1R-17of partially filled shells, 41-7-151 derivation and implications of, 37-4-41preliminary planning for, 38-2-1 in designproblems in, 41-2-1 of foundations, 39-1-40of railroad cars, 40-6-109 of shipboard equipment, 39-1-13,of re-entry vehicles, !9-1-223 39-1-25, 39-1-74, 40-7-144of rotor bearings, 40-3-281 digital computer programs for, 36-6-101,of scale model automobiles, 40-4-89 40-7-153of shafts, 40-4-163 use of dynamic substructure method for.of shipboard equipment, 36-7-129, 39-1-45, 38-2-12

39-1-84, 39-S-41, 40-7-165 flow chart for, 39-1-57, 40-7-166of shipping containers, 39-6-57 perturbation techniques for, 40-7-177of ship structures, 40-7-197 prediction versus full-scale shock testof single-degree-of-freedom systems, measurements, 36-1-1

41-S-45 review and approval of mathematicalsolids immersed in fluids, 40-IR-II models for, 39-1-45of sonar transducers, 41-1-21 selection of normal modes ior, 40-7-165spheres, 41-7-91 validation and derivation of inputs for,of spacecraft, 36-3-16 39-1-13of spring-mass ejection system, 41-6-93stiffness matrix in, 37-2-175 Dynamic environmentsfor strain response, 36-5-79 during arrested landings, 40-6-37use of structural damping in, 38-2-271 for cargoof structures, 37-2-173, 39-1-107, 39-3-99, on railroads, 39-6-47

39-3-129, 39-3-153, 40-2-57, 40-2-123, on trucks, 39-6-3140-2-227, 40-2-243, 40-4-25, 40-4-41, criteria for simulation of weapon-mount40-4-47, 40-4-63, 40-7-153, 41-5-27, interface, 41-5-5341-6-75, 41-7-9, 41-7-19, 41-7-81, data analysis for, 41-3-5541-7-89, 41-7-123, 41-7-131 derivation for propellant storage module

symmetry in, 38-2-6 for Sky Lab, 41-7-195of tethee•d systems, 40-4-225 effects ofof towed cables, 41-6-61 on field tests, 39-6-1of vibration test specimens, 41-4-79 on fragility of systems, 41-5-111of yielding structures, 36-2-10 on performance of gas lubricated

bearings. 40-3-275Dynamic characteristics of eggs, 41-3-11

of Advanced Orbiting Solar Observatory for ejected missiles, 40-6-1(AOSO), 36-7-66 measurements of, 39-6-27

17

prediction of Dynamic testsuse of flight vibration data in, 41-4-189 of gas lubricated rt.. rJngb, 40-3-275of mechanical impedance in, 38-2-249 general purpose fixt .., 39-2-175for spacecraft, 40-3-79 of plastic scale mod"., a9-3-39statistical energy analysis for, 41-6-9 of vehicles, 41-3-12,(

of railroad cars, 41-4-141for spacecraft, 41-4-3 Dynamics

discussion on, 41-2-1Dynamic equivalence of shock isolators, 39-4-213

of lumped parameter system, 39-3-157 of protective structures, 38-2-187

Dynamic excitationof damped structures, 38-3-71of immersed solids, 40-IR-II E

Dynamic loads Earthquakeson Atlas booster and tethered cannister, vibration test systems for simulation of,

40-4-226 41-3-109bounds for response of conservative

systems to, 41-6-87 Effective masson space vehicles from flight vibration definition of, 36-6-123

data, 40-4-171Effective modulus theory

Dynamic matrix in analysis of laminated layers, 41-6-188for structures, 37-2-190

Effective weightsDynamic models, see also Mathematical of reduced lumped parameter systems,

models, Models, and Scale models 39-3-158plastic materials for, 40-4-89scaling laws for, 39-4-228, 40-4-89, Eigenvalue problems

40-5-183 for fluid-filled shells, 38-2-86solution of, 38-3-98

Dynamic modulusof composite materials, 36-4-95 Eigenvector flowgraphs

for discrete systems, 38-1-104Dynamic overstress

criteria for in materials, 40-2-28 Elastic materialsmechanical properties of, 38-3-251

Dynamic response, see responseElastic medium

Dynamic similarity dynamic response in, 39-5-13criteria for scale model structures,

39-3-40 Elastic-plastic systemresponse to half sine pulse, 40-4-67

Dynamic stability respotse to a sawtooth shock pulse,of columns, 41-6-1 39-5-1

of conservative systems, 41-6-87of shells, 41-7-81 Elastic skid mountsof structures, 40-2-57 as shock isolators, 39-4-179

Dynamic Substructures Method Elastic strain energyIn dynamic analysis, 38-2-14, 39-1-58 in damped skin-stringer structures,

39-4-35Dynamic systems

equations of motion for, 40-5-137 Elastic wavemechanical impedance of, 40-5-135 propagation in helical coil, 41-2-77normal mode analysis of, 40-5-135

Elastome-s, see also Viscoelastic ,materialsDynamic stresses piezoelectric properties of, 3, 2-1

in sonar transducers, 41-1-31 as shock isolator, 41-2-57

18

r i

Elastoplastir qspouse Energy spectral densityof shelli to irpuluive 1oiids, 41-7-81 tor sum of two shock waves, 41-5-23

Electrodynamic shakers, sep Vibration exciters Engine cutoffvibration tests for, 37-4-60

Electromagnetic loudspeikers, see Acoustictest facilities Environmental data

measurement a.,d recording of, 36-6-163Electronic compooents, see also Components for rocket engines, 37-2-135

design criteria for, 37-4-100 from ships, 40-7-225vibration tests of, 40-5-IuI

Environmental factorsElectronic equipmert affecting latent information parameters,

acoustic tests of, 37-3-8 41-3-87dynamic analysis of, 37-4-97, 39-3-117effects of cumbined cvl-ir.mments on, Environmenta! tests

36-6-83 definiti-Ans of, 3q-2-124internal vibration oi, 3 ,-1-7 of e-/zosive weapons, 40-3-193qualifications of, 41-4-119relability testing of, 36-1-23 Environments, see specific environments suchshock response of cablitet for, 36-7-129 as Transportation environments, Vibrationshock tests of, 39-3-118, 39-5-79, environments and so forth

41-4-123vibration teets Jf, 3 1-3-14, 40-S-63, Equal annoyance contours

41-4-122 for vibrating humans, 41-2-16vibration tests for detecting loose parts,

36-6-73 Equalizationanalog system for, 36-3-49

Energy with low-frequency phase compensation,equivalence in components of, 41-3-83 36-3-51processing within a t ransducer, 41-3-92 for random -Abration tests, 41-4-79

Energy-absorbing steering column Equations of motioncharacteristics of, 37-4-82 for cyU idrical shells, 40-3-133

of helic ipter structures, 41-7-134Energy absorption for hen ispherical shells, 38-2-82

by cyclic deforma" n, 38-3-255 for lant ing gear, 39-3-182in hignway guard- rall structures, 40- 5-115 for later,.' displacement of columns,inverting tube for, 41-2-89 40-2-115materials for, 40-2-183 for lateral launch loads, 38-2-70using modified concrete, 39-4-199 for multicore sandwich beams, 40-5-280spherical crushable structures for, for non-uniform beams, 38-1-69

41-2-95 for open-frame structures, 38-2-183in vehicle structures, 39-4. 227 for plates, 38-1-46, 40-3-119

of sandwich plates, 39-4-76Energy analysis for sandwich shells, 40-3-70

of two coupled modes, 36-5-43 for spherical shells, 40-3-75for two-degree-of-freedom nonlinear

Energy balance systems, 39-3-162in multipanel structures, 37-2-101 for vibration isolators, 40- 5-22

Energy density Equipment, see specific equipments such asdefinition for transieni acceleration pulse, Electronic equipment, Shipboard equipment

39-5-83 and so forth

Energy-flow method Equivalencefor shock analysis, 37-4-65 bibliography on vibration, 39-2-190

in energy components, 41-3-83Energy methods of in'asured and predicted strains, 36-5-77

for vibration analysis of segmented rings, of mea wured and predicted vibrations,39-1-144 36-5-4i0

19

rr~

in power components, 41-3-83 due to air blast after acoustic loading,of test specimens, 36-2-63 39-3-68of transients, 36-2-101 in aircraft gas turbines, 39-3-18of vibratinn tests, 39-2-187 calculation of probability of, 41-5-141

Error auksls from combined environment,, 39-3-67

algorithm, 39-3-102 effect of qualification test 1 vels on,

in beam damping calculations, 3 8-1-25,41-2-135 in electronic equipm.mt, 36-6-73

of damping calculations, 38-3-153 of shell structures, 37-4-177

of instrumentation, 37-S-115 of spacecraft, 40-3-9

of measured properties of viscoelastic of weapon systems, 41-5-135

materials, 39-4-15 Fast Fourier Transform, see Fourier analysisof mechanical impedance measurements, and Fourier transform

39- 1-126of shock tube performance data, 39-5-59 Fatigue, see also Ace-ustic fptigde

Exploding wires of drcraft structures, 39-3-87, 40-5-49

simulation of shock waves by, 37-4-117 in the design of electronic equipment,40-4-97

Explosions Miner's Hypothesis for random vibration,of liouid propellants, 38-2-177 41-3-47

in shim spring vibration isolator, 37- 3-168Explosive shock, see Pyrotechnic shock of structural joints, 39-4-117

of structures, 40-5-61, 40-6-67Extensional damping, see Damping effect of air damping on, 36-4-75

F Fatigue damage, see also Damageanalog computer for, 41-3-60

F-4 Aircraft criteria for comparison of randomAIM-41) missile on, 39-1-195 vibration environments, 41-3-4.Q

digital comn.-luter program for, 36-5-25F-l11B aircraft energy summation in, 40-3-139

environment measurements on Phoenix gages for measurement of, 39-2-35Missile in, 39-6-93 to a multi-modal system, 36-5-17

predicted vs measured environment for from random vibration, 40-3-1missile in, 39-C-117

vibration of Phoenix missile in, 39-6-77, Fatigue failures39-6-4v3 criteria for, 36-5-19

Palmgren-Miner hypothesis for, 40-4-99FAE weapon reduction of, 40-4-97

captive flight vibration on UH-iE due to vibration, 36-4-75helicopter, 40-S-59

Fatigue gageFailure analysis description of, 39-2-35

of beams, 37-4-50of shells, 39-5-21 F-tigue life

effect of mean stress on, 40-4-99Failure criteria prediction of, 39-3-87, 40-6-67

for shipboard stri,-ares, 39-1-107for structural m =mbers, 38-2-183 Fatigue tests

for Chaparral missile, 39-2-37Failure modes failure modes of test specimens in,

in fatigue tests, 39-4-131 39-4- 131of v0icoelastic sandwich beams, 39-4-123

Failure rnte testsfor n~irisiles, 39-2-99 Ferrotluids

definition of, 41-3-18Failures

.,nder acoustic test, 37-5-170, 37-5-63, Field data, see specific data of interest such39-1-63 as Shock data and Vibration data

20

Field hadfling Flexibility matricesanalysis for Polaris missile, 36-7-145 for whip antennas, 40-1-.!9P 'eld of excitation Flexible structuresdefinition of, 37-3-77 experimental study of very long, 36-6-195

Field tests Flexural vibrationsof Army equipment, 39-6-1 considerations in composite beams,

38-3-18Finite Cosine transformdefinition of, 36-5-109 Flight dataF i ni e e e m e n m e h oda c q u i s itio n , 3 7 -1 - 1 3 7Finite element method for airborne electronic equipment, 40-S-66analysis by for Apollo spacecraft, 37-5-90of beams, 38-1-10, 41-6-123, 41-7-51 comparison of acouatic test with, 37-3-23of grillages, 40-7-212 comparison with vibration test criteria,of helicopter structures, 41-7-132 37-3-7of plates, 40-3-99, 41 7-41 during launch of OGO, 37-3-21of sells,A•1.-7-84of structlres, '1-7-123 Mariner, 37-4-5me.asurement of, 40-S-63for dynamic analysis, 39-1-56, 39-3-129 fo., SNAP 10A, 36-7-75extensin'n -, 36-5-55 Yo' spacecraft, 37-7-182mathematical anal:'qi, of sonartransducers, 41-1-21 Flight test

model of solar panels for, 38-2-149 of helicopters with active isolator, 37-6-75random vibration usine, 38-1-7 program for captive missile, 39-6-102for shock analysis, 38-2-11 vs system test response data, 39-1-217Fixed-base natural frequencies Flight vibrationdc :nition of, 38-2-209 vs acoustically ii duced vibration, 37- 5-160of experimental structures, 38-2-263 comparison of qualification test to,measured vs calculated, 38-2-268 41-n-47

for shipboard equipment, 38-2-209 data a. •lysis fo:, 37-7-176, 37-S-109use in shock design, 38-.2-261 dynami loaed. on space vehicles from,

40-4-171Fixtures vs flight acceptance test requirements,accelerometer error 39-6-129due to strain in, 37-2-47 vs ground vibration test, 37-7-173due to stress in, 37-2-43 at low altitudes and high speed, 39-4-158characteristics oi multimodal, 40-3-233 predicteddesign of from acoustic excitation, 36-5-85for floating shock platform, 37-4-85 vs measured for spacecraft, 39-6-128for resonant beam vibration tests, for missiles, 41-4-18939-2-72, 39-2-221 by statistical energy analysis, 41-6-9for shock tests, 38-2-95 probability of exceeding specifiedfor vibration tests, 36-3-101, 39-3-31, vibration test levels, 41-S-2840-3-231 procedures for measurement of, 39-6-121flexure guides for vibration tests, 39-2-157 simulation ofgeneral purpose, 39-2-175 for captive missile, 39-6-86parameters for selection of, 38-1-91 for helicopter, 41-3-121for vibration tests of composite panel, fur re-entry vehicle, 36-3..11339-3-192

for apacecraft, 39-2-147for vibration tests of elastomers, 39-2-4 for spacecraft, 37-5-28, 39-6-119, 40-3-9,for vibration tests of Saturn S-IVB, 40-3-16337-3-138 vs static firing tests, 39-6..133Flat plates Floating platforms, see also Shock testas underwater explosion model for hulls, facilities41-S-49 for shock tests, 37-4-85, 40-2-1

21

r"

Floors Force-node methodshock isolated, 41-5-155 for lumped parameter system, 38-2-292

Flow chart Force transducersfor method of indirect synthesis, 39-4-190 development of, 36-6-203

evaluation of, 36-3-9Flow diagram for variable resow.M vibration exciter,

for optimal design of shock isolators, 38-S-341-2-49

for vibration analysis of helicopters, Force transfer functions41-7-132 for lumped parameter systems, 38-2-111

Flowgraphs Forcing functionsstructural analysis using, 38-1-99 for helicopters, 40-S-48

for hydraulic shock inputs, 41-1-23Flko noise for mathematical models of railroad

reduction in water tunnels, 41-2-151 cars, 40-6-112for piping for steam systems, 39-1-155

Fluctuating pressure, see Boundary layer noise for re-entry vet icles, 40-3-36

Fluid damping FORTRAN IV computer language, 36-6-105,effect on motion of immersed solids, 36-6-131

40-1R-15Foundations, see also Machinery foundations

Fluid films, see Oil films for antenna mast structures, 40-2-103dig4tal computers for design of, 39-1-55

Fluid systems inputs to, 40-7-188shock analysis of, 40-2-67 motion of plates on, 40-4-220

for shipboard equipment, 39-1-39, 40-7-171Flutter stresses P.-id motions in, 40-4-219

of aircraft wings, 41-7-109 yielding p'operties o distributed, 40-4-82in combined flexure-torsion systi "*

40- 5-235 Fourier analysisof cylinders, 40-3-308, 41-6-31 of acceleratic, response of scale modelof hydrofoils, 41-7-205 hull, 41-S-lbmathematical analysis of, 41-7-111 for random vibration, 38-1-18of panels, 40-4-139 of shock data, 41-5-39root locus Aquations for, 40-5-237,

41-7-113 Fourier spctraof structures in fluid stream, 39-3-171 of complex shock transients, 36-6-9water tunnel facility for tests, 41-7-207 derivation of, 41-5-21

using Duhr.mel integral, 36-2-12FM multiplex system, 36-6-210 effect of digitizing detail on accuracy,

36-6-1Foams, see specific foams such as Polyurethane for hulls of submL 'nes, 39-S-44foams and Polystyrene foams for munitions ejection, 41-5-96

for shipboard equipment in submarsnes,Force-accepleration feedback 39-S-47

for control of input, 39-4-11 of s,,ock pulses, 40-2-175

Force- controlled shock tests Fourier transformsconcept of, 39-5-63 of acceleration-time histories 40-3-87

of air pulser output, 41-S-12Force-controlled vibration tests calibration of accelerometers using,

feasibility of, 36-3- 15 37-2-17on spacecraft, 36-3-15 for coherent optical systems, 36-6-96specification of, 36-3-1, 41-4-69 definition of, 41-5-40techniques for, 36-3-47, 37-3-61, 41-4-31 fast algorithm for computation of, 40-2-159

22

generating shoek pulses with modiLed, of piping systems, 40-4-19840-7-92 * plotting of, 36-6-37

in shock analysis of fluid systems, 40-2-67 of printed circuit boards, 40-3-113for transient functions, 38-1-18 of prototype automobile, 40-4-94trigonometric terms for, 41-5-45 of scale model automobile, 40-4.94

of vibration isolators, 40-6-40Fragility

definitions of categories of, 41-5-112 Frequency stepping circuit for analog computers,In design of structures, 41-5-130 36-6-39of equipment in hardened sites, 41-5-155of equipment in silos, 41-5-161 Fresnel-Kirchoff Diffraction formula, 36-6-94of hydraulic systems, 41-5-143of packaged equipment Friction

procedures for determinatibn of, effect of balance weight on vibration40-6-127, 40-6-133, 40-6-149 absorber, 36-7-124

shock tests for, 40-6-127, 40-6-133panel discussion on, 40-6-153 Frustumsprocedures for determination of, 41-5-119 propagation of stresswaves in, 40-4-127of shock isolation systems, 41-5-129standards for evaluation of, 41-5-111 Fuzes, see Mechanical fuzesof structures in hardened sites, 41-5-156of systems G

effect of dynamic environments on,41-5-111 Galloping

shock tests for, 41-5-121 of structures in fluid stream, 39-3-171vibration tests for, 41-5-123

Gas detonations, see also Nuclear detonationsFragmenting tubes for simulation of nuclear blast, 37-4-199

for attenuation of impact, 40-5-115force-time histories for, 40-5-128 Gas guns, see Shock test facilitiesm-iterials for, 40-5-117shock tests of, 40-5-116 Gas springs, see Pneumatic springs

Framesmat' ematical models of, 39-3-34 Gas turbinesmechanical impedance in analysis of, air blast tests of. 10-2-147

38-'-219 compatibility with helicopter airframe,mode shapes of, 38-2-225 39-3-17 *

natural frequencies of, 3P-2-225, 39-3-31Fraunhofer Diffraction p "ttern, 36-6-94 Gaussian pulse

properties of a, 37-2-21Frequency, see also Natural frequency

of zero crossings, 40-3-2 Geiger thick plate test method, 40-5-105errors in for beams, 41-6-126, 41-6-137 Gemini- Agena vehicle

Frequency analysis structural analysis of, 37-2-117of repetitive bursts of random vibration, test program for, 37-2-117

38-1-17Gemini-Titan vehicle

Frequency correction equations for mechanical ground wind-induced vibral.:.ns of,systems, 38-2-295 36-7-79

vibration tests on, 36-7-80Frequency parameter

for Bernoulli-Euler beams, 2J-3-50 General Bending Response Codefo': Timoshenko beams, 39-3-50 vibration analysis with, 39-S-60

Frequency response Ge , ralized massof accelerometers. 41-3-1 definition of, 38-2-274of microminiature amplifier, 36-6-220of nonlinear vibration isolation sysieas, Glass structures

40-5-26 shock analv.9is of, 40-5-176

23

Green's Theorem, 36-u-99 H

Grillages Half-sine pulse, see Shock pulsedynamic analysis of ships, 46J-7-207

h-ir.ilton - principle

Ground shock effect on protective structures in anialysis of shell-,, 40-3-134, 41-7-15238-2-187 in vibration analysis, 39-4-81, 39-4-93

instrumentation for, 40-7-133isolation of protective ',tructures froi.n, i'andling, see Ro-gh handling

39-4-199paramete.s of soils for 1,..', Hankel transform, 36-5-108

38-2-195respo;ise of plates to, 40-4-2it1 Hardened sites, see also .Q'Iosresponse of tower to, 41-6-82 analysis of, 38-2-187simulation of, 40-2-243. 41-3-149 fragility of equipment in, 4C-5-155

hydraulic systems for, 41- 5-143

Ground support equipment shock isolators for, 41-5-129, 41. 5-155shock isolation of, 37-4- 218

H,-.rdeningGrowid winds criteria for ship5. 39-1-65, 39-1 Jduring laura h, 38 -2- 70

Harmonic motion, see VibrationGuided missiles, see also Mi ,siles

environmental test program for, 39-2-195 Harmonic spikesenergy summation for, 40-3-149

Guidewaysresponse to air cushion vehicies, 41-6-47 Hawk missile

dynamic analysis of isolation system for,Guidirc environments 41-2-160

acceleration probability dens,'y for, dynamic environments for, 41-2-15941-4-21C

oh aircraft, 40-6-27, 41-4-1?3 Hawker-Sidde.ey P- 1127 aircraftfor captive airborne weapons, 39-S-27 acoustic environment of, 41-4-161data analysis of, 41-4-46, 41-4-203,

41-4-210 Heat shieldfield data, 37-2-32 pyrotechnic shock in, 36-2-63free field blast overpressure, 39-6-142free field side-on impulse, 39-6-146 helical coilon helicopters, 40-1-61, 40-2-227, for dispersal of sh(,ck loads, 41-2-77

41-4-195, 41-4-209of naval gun, 'M,-2-53 Helical c,,.l springdropagatUbn of blast waves from, 39-6-139 as shock isola:ors, 41-2-56for River Patrol Boat, 37-7-205shock spectra for, 41-4-204 Helicopters, see also specific helicopters suchsimulation of, 40-6-27, 41-4-37 as AH-1, All-56. CH-47., CH-53,, 011-4, and

UH-1Guns active vibration isolator for, 37-6-63

d:,.: amic analysis of recoil adapters, ammunition conveyor system for. 40-4-11539-4-251 balarring of rotors for. 36-7-113

i.solation of rteoil forces from, 39-4-2' 1 compatil;,"tv of gas turbi:,e with, 39-3-17simulation of rt:coil of, 41-3-187 computer programs for structural

analysis of, 4n--2-238Gul' loa,:s damnpinjg of iibration in. 41-2-141

ct: ]".anch vel,icles, 38-3-104 data acquisitic n system for vioration of,36-3-76

Gyrosc')pes .,:sign of fusel:.e, 3' 6-22as ,•%\nchronous vibration absorbers, dyn;imic analyst,, of. .0-4-43

37-r5-49 dynamic claracteristics of gas turbinevibration isolators for, 38-3-285 powered, 39-3-17

24

flight test of, 37-6-75 for high frequency vibration studies offocal isolation system for, 38-3-263 beams, 40-7-34ground vibration surveys of, 3t6-3-71, instrumentation using, 39-2-41, 41-3-64

39-3-23 for mode shapes of plates, 39-2-43,gunfire environment of, 41-4-195,41-4 .209 41-7-38mathematical model of, 38-3-282 in non-destructive tests, 41-3-63noise in, 41-4-221 for response to shock, 40-7-33prediction If ioads in rotor blo,'-, S4-6-6 for vibration measurements, 39-2-41,?redtction of response to blast, 40-2-231 40-7-43, 41-3-63prediction of vibration in, 37-6-19reduct'oii of vibration in, 36-7-113, 37-6-5, Honeycombs, see also Crushable sLructures

$?- 6-zql, 37 6-3d, 37-6-49, 37-6-63, and Yielding structuresS-5-191, 38-3-26: pulsed lasers for observing defects in,

response to blast 3f wapons, 40- 1-61, 41-3-7240-2. 227

simulation of flight vibration, 41-3-12i Hopkinson's Lawtransmission of vibration from rotors, for scaling of b ast pressure, 39-6-139

37-6-5vibration in, 37-6- I, 39-3-17, 40-4-48, Horns

40-5-t91, 41-4-19b, 41-4-209, performance in acot stic test facility,41-4-221, 41-7-131 37-5-46

vibration absorber for, 37-6-23, 40-5-191Hulls

Helicopter Trap Weapon (HTW) damage from underwater explosions,captive flight vibration of, 40-S-59 39-1-95

influence of characteristics on responseHigh acceleration shock test facility, 40-2-205 to air blast, 37-4-143

mathematical model for submarines,High imp2ct, see also Impact 40-7-186

of shells, 39-5-21 mathematical model for vibrations,38-1-126

High-impact shock machines, see also Shock response to underwater explosions,test machines 38-3-244, 40-7-185, 41-S-49

fixtures for, 38-2-95 vibration of, 38-S-1, 40-7-243mathematic- ',, model of, 38-2-97modified, 3o '-226 Humans

effect of shock on, 37-4-80, 39-5-89,High polymers 41-2-5

effect on diffuser flow noise, 41-2-151 effect of ,ibration on, 41-2-13equal annoyance contours for vibration.

High-shock loads 41-2-16foundations tor, 38-3-1 vibration isolators for. 39.4- 157simulation of, 40-2-205

Humping, see RailroadsHigh speed trains

measurement of vibration on Metroliner, Hybrid compute's, see also Analog cotoutei's,40-6- 93 Ctimputeis. and Digital computers

for high-specd analysis of vibration data,High temperature 36-6-55

damping at, 36-4-25, 38-3-57 for modal analysis. 41-3-25for vibration analysis of helicopter

Hieged arch structures, 41-7-131dynamic ana.) s s of, 41-6-90

Hydraulic flowHMS OBDURATE for simulating recoil of '.ins, 41- 3-187

shipboard sheok on, 37-1-1Hydraulic ý.hock

i.Llography forcing functiva ior, 41-1-21description of, 39-2-41. 41-3-31n mathematiial model for., '6-2-33

2,5

Hydrodynamic mass for determination of mechanical impedance,definition of, 40-IR-11 41-5-54

by drop ball test, 37-2-21Hydrofoils from gunfire, 39-6-146

flutter of, 41-7-205 in vibration tests of ships, 41-S-i

Hygens-Fresnel Principle, 36-6-91 Impulsive loads, see also Shock loadselastoplastic response of shells to,

Hysteretic damping, see also Damping 41-7-81in joints, 36-4-3 response of damped cylindrical shells to,

38-3-130I response of isolation system to, 40-5-206

vibration characteristics of ships from,Ignition shock, see also Shock 40-S-7

versus temperature, 37-2-168Indeterminate forms

Impact, see also High impact evaluation of, 38-1-36of airdropped material, 41-3-223attenuation for Apol o Command module, Indirect synthesis

38-3-255 definition of, 39-4-185attenuation for spacecraft, 40-2-183 flow chart for, 39-4-190combined with spin, 41-3-164 of shock isolators, 39-4-185co.)er ball accelerometer fo- measuring,

37-3-219 Inertial guidancedamage to eggs during, 41-3-11 dynamic analysis of, 40-3-257damping oy, 39-4-1design criteria for limiters, 40-2-183 Infinite stiffnessfragmenting tube for attenuation of, concept of, 37-2-184

40-5-115human response to, 41-2-5 Influence coefficientsinverting tube response to, 41-2-91 for cantilever beams, 37-2. 61lead targets for tests, 37-3-219 in dynamic analysis, 36-6-101, 38-2-50of nuclear fuel capsuZ-s, 40-2-193 quick check procedure fr,r, 38-2-205pads for modified slingsnot shock test for truss, 38-2-62

machine, 39-5-76on piping, 40-S-3 Input control, see also Force-controlledof projectiles on armor, 41-5-69 vibration testsprotective system for automobiles, by monitoring response spectra, 37-3-47

38-3-329pulse duration on different surfaces, Insertion factor

36-6-175 definition of. 38-S-20response to

of aircraft to ground, 38-3-165 Instrumentationof elartic half-space, 39-5-13 for acoustic eivironrannts, 36- 7-90,of helical coil, 41-2-80 37-5-19, 37-5-42, 37-5-168. 37-S-34,of structures, 37-1-115, 38-2-38 37-S-74, 37-S-95, 40-5-54. 40-7-17.

of scale model vehicles, 39-4-227 41-4-163, 1 1-4-221sensitivity of radioactive materials to, for captivw flight loads, 37-1-128, 40-6-15

41-3-194 for combined environments, 40-7-J02,of shells, 39-5-21 41-3-164of shipping containers. 39-6-65 for combustion irstability tests, 40-4-11,simulation of human head, 39-5-89 for dampA-ng evaluation, 38-3-90tests on hard landing payloads, 40-2-185 for dynamic tests, 37-2-132. 37-3-106,

37-4-3, 37-5-129, 38-3-221,. 39-2-1A4Impedanc... see Mechanical impedance for egg damai.,e 41-3-11

for ejection tests, 40-6-4Impulse error :nal. sis in. 37-S-115

calibration of accelerometers by, 37-2-21 for fixed-base natural ;requencics,designy ot exciter, 37-2-24 38-2-265

26

U

for flutter of hydrofoils, 41-7-207 Isotopesfor force input measurement, 36-3-114 shock test facility for, 41-3-194for gun setback acceleration, 36-2-58for gunfire environment, 37-7-206,

41-4-198, 41-4-210for handling of Polaris missile, 36-7-147 Jeepusing holography, 39-2-41, 41-3-64 shock and vibration in M-151, 37-7-39using a laser, 37-2-1for launch phase simulator, 36-6-207, Jet engine noise

37-3-184, 37-5-178 data analysis of, 41-3-55for mechanical impedance, 38-2-254,

40-4-200, 40-7-29, 40-7-65 Jointsfor mechanical signature analysis, 36-6-74 in structural analysis, 37-2-182for modal analysis, 36-3-86, 39-3-147 structural damping in, 36-4-1for model tests, 37-3-126, 40-4-93 with viscoelastic materials, 39-4-117for pyrotechnic shock, 37-4-17for response of bridges, 41-4-100 Joint acceptancefor rocket sled, 37-3-199, 41-7-3 for boundary layer turbulence, 37-5-65for shock, 37-4-106, 39-5-89, 40-1-10, transformation, 37-5-61

40-1-33, 40-5-256, 40-7-133, 40-S-22,41-3-175, 41-5-93, 41-6-147 K

for shock spectra, 36-2-18suppression of electrical noise in, 40-7-4 Keel shock factorterminology, 41-3-82 definition of, 39-1-8for transportation environmknt, 37-7-19, fo. HMS OBDURATE, 37-1-5

37-7-40, 40-6-91, 40-6-99, 4-4-142 for "iverine craft, 37-1-48for vibration, 37-2-118, 37-7-96,

37-7-176, 37-S-74, 37-S-95, 39-3-193, Kennedy-Pancu Method40-7-?9, 40-7-45, 40-7-225, 40-7-243, review of, 39-3-10840-S-66, 41-3-114, 41-4-221 for vibration analysis of shells, 39-3-107

for wind tunnel, 37-7-222Kinetic energy

Interface dynamic environments power dissipation of, 37-2-99mechanical impedance in prediction 6f,

38-2-249 L

Interferometer Lagrange's equationsin accelerometer design, 41-3-17 in analysis of towed cables, 41-6-62measurement of displacement with, for dynamic analysis of conservative

37-2-13 systems, 41-6-87in launch dynamics analyzer, 41-6-220

Isolation systems, see also Shock isolationand Vibration isolation Landing gear

for aircraft ground vibration survey, dynamic analysis of, 39-3-17936-3-62

for dynamic studies of launch vehicles, Lasers40-3-205 for observing defects in honeycombs,

for electronics cabinets, 40-S-29 41-3-72mathematical analysis of, 38-3-286 for vibration analysis, 37-2-1for missile containers, 39-6-57nonlinear springs for, 36-7-103 Latent information parametersfor railroad cars, 40-6-109 in measurements, 41-3-82with relaxation damping, 40-5-203for seismic mnss, 41-3-110 Lateral dynamic loadsfor static firing tests, 37-3-99 analysis of, 38-2-69

Isolators, see specific types such as Active Launch environmentsvibration isolators, Shock isolators, and for airborne weapons, .10-6-1Vibration isolators !or Apollo Lunar Moduie, 37-5-106, 40-3- 163

27

lateral response to, 38-2-67 Linear systemsrespons', of space vehicles to, 40-4-171 transfer functions for, 39-3-74simulation of, 36-3-119for SNAP 1OA, 36-7-73 Linearitytest fac'lity for, 39-I"-23Lieit of measurement system, 40-7-18

Launch phase simulator, see also Combinedenvironmental tests Liquid propellants

acoustic tests on, 37-3-182 explosions of, 38-2-177for combined acceleration and vibration

tests, 36-3-119hydraulic vibration exciter for, 39-2-23 L fquid springinstrumentation for, 36-6-207, 37-3-184 or shock Isolation, 41-2-57as qualification test facility, 40-3-183for spacecraft, 37-5-175 Liquid squeeze-films

mechanical properties of, 39-2-82Launch vehicles, see also specific launch for support of vibrating structures,vehicles such as Titan launch vehicle, Saturn 39-2-77launch vehicle, and Scout launch vehicle

acoustic environment of, 36-5-97, 36-7-89 Loading, see Dynamic excitationcombustion instability teats, 40-4-111criteria for scale models of, 40-3-205dynamic tests of, 37-3-99. 37-5-117 Loss factorsflight vibration time history for, 39-6-136 for damped beams. 38-3-8ground vibration test of, 39-2-135 for laminated beams, 36-4-83gust loads on, 38-3-104 for segmented rings, 39-1-150high-force vibration tests of, 37-3-137 of spaced-damped beams, 39-1-167inelastic damping of ducts, 40-5-61 in statistical energy analysis, 38-S-11interaction of spacecraft with, 38-2-239interface effects on subsystem response,

38-2-67 Loudspeakers, see Acoustic test facilitiesm-chanlcal impedance at interface,

40-3-79 Low temperaturemultimodal fixtures for, 40-3-231 damping at, 36-4-25, 38-3-57nonlinear damping in structural analysis,

40-5-261static firing tests, 39-6-133, 40-4-109 Lumped parameter systemsstiffness matrix for, 38-3-108 analysis of, 38-2-57, 38-2-274, 29-3-153,suspension system for dynamic studies 41-6-198

of, 40-3-205 in beam analysis, 36-6-117, 41-5-28,torsional shock from, 36- 7-63 41-6-123vibration analysis of, 38-3-95 'comparison of effective weights of,

39-3-158Lead targets comparison of natural frequencies of,

for impact tests, 37-3-219 39-3-158dynamic equivalence of, 39-3-157force-node method for, 38-2-292

Legendre's Polynomial, 38-2-83 forced response of, 38-3-95mobility matrix for, 40-5-137

Liapunov's functions reduction in mass points for, 38-2-57for dynamic analysis, 41-6-88 transfer functions for, 38-2-109

Lift-off, see Launch environments Lunar module, see Apollo spacecraft

Limits of allowable variation Lunar Orbitei spacecraftdefinition of. 37-3-77 flight acceptance test, 39-6-120

flight vibration of, 39-6-119Line solution method flight vibration vs flight acceptance test,

for stability analysis, 38-2-163 39-6-129for structural analysis, 38-2-157 vibration data analysis for, 39-6-122

28

M piezoelectric properties of rubberlike,39-2-1

M-151 Jeep propagation of stress waves, 39-3-201vibration in, 37-7-39 properties for scale models, 39-3-40

shock isolation properties of, 39-4-213Mach number

versus drag coefficients, 40-2-97 Mathematical analysis, see also Dynamicversus Reynolds number, 37-3-127 analysis, Structural analysis, Vibration

analysis and Shock analysisMachinery of acoustic excitation of solar panels,

gas-bearing, 38-3-221 40-3-49wear in, 41-4-51 of acoustic radiation resistance of shells,

40-3-24Machinery foundations, see also Foundations of air blast on structures, 39-5-29

design of damped, 36-4-81, 38-3-1, of ammunition conveyor feed system,39-1-143 40-4-118

mechanical impedance for, 38-S-19, of combined flexure-torsion flutter,39-1-123 40-5-236, 41-7-111

noise transmission of, 38-S-19 of combined torsional and translationalfor shipboard equipment, 38-3-1, 38-3-19 vibration, 39-3-172spaced damping of, 39-1-167 of damped beams, 38-3-14, 39-4-54.in submarines, 39-1-123 40-5-278, 41-2-133tests of, 36-4-88 of damped shells, 38-3-121uniform beams as, 39-1 123 of damping device for blade st ructures,vibration transmission of, 38-S-19 39-4-20

of deck vibration, 40-1-2Mariner spacecraft of ejection system, 41-6-94

dynamic analysis of, 38-2-139 of elastic-plastic system, 40-4-68electronic assembly for, 36-3-27 of fluid-filled shells, 38-2-79. 41-7-153instrumentation for, 37-4-3 of forced vibration, 38-3-95Mars 1969, 38-2-139, 39-2-123 of foundations, 39-1-136, 40-4-82modal analysis for, 38-2-143 of gun systems, 39-4-255modal survey of, 39-2-123 of impact of helical coil, 41-2-80shock spectra at separation, 37-4-8 of Inverting tube impact, 41-2-91transient response at separation, 37-4-1 of Isolators, 38-3-39, 38-3-286. 39-4-143,vibration tests of, 36-3-27, 38-2-151 40-5-204

of lumped parameter system, 39-3-154,Mass 41-6-197

effect of concentration on vibrating plates, of modal coupling. 39-3-10038-1-37 of nonconversative systems, 41-7-142

of nonlinear systems, 3 61. 40-5-263,Mass matrices 41-6-40

for beams, 38-1-12, 41-6-123 of panel fluttei. 40-4-140for bending of plates, 41-7-129 of paraboloidal antenna, 41-6-105comparisons of consistent, 39-3-129. of piping system, 40-4-148

40-4-1 of plates, 39-3-206, 39-3-234, 39-4-65,generalized, 39-2-127 39-4-74, 39-4-81, 39-4-93, 40-4-218,for piping system, 40-4-148 40-5-93, 41-7-30for plane stress, 41-7-126 of propulsion system for ships, 39-S-57in structural analysis, 37-2-187, 40-4-1 of protective atructures, 39-4-208translational, 40-4-194 of rail launching dynamics of missiles,

41-6-220Material damping, see Damping of scale model launch vehicle, 40-3-207

of segmented rings, 39-1-145Materials of shock bar, 40-2-211

criteria for dynamic overstr !ss in, of sonar transducers, 41-1-2140-2-28 of stress propagation, 40-4-128

for energy absorption, 40-2-183, 41-2-98 of torsional vibration, 40-4-163with extensional damping, 38-3-199 ot towed cables, 41-6-62

of underwater explosions, 39-S-42, Mean square amplit-'de40-7-186, 41-S-50 derivation of, 38-1-28

of vibration absorbers, 39-4-261Mechanical amplifiers

Mathematical models, see also Dynamic as shock test facilities, 40-2-205models, Models, and Scale models

of aircraft carrier, 37-4-144 Mechanical filterof aircraft structure, 40-2-123 for shock transducers, 37-2-37of antennas, 37-4-151, 40-1-47, 41-6-104for Apollo Applications Program Mechanical fuzes

structures, 39-3-57 shock tests on, 37-3-219, 41-3-155of Apollo Lunar Surface Experiment

Package, 38-2-47 Mechanical impedanceof beams, 40-4-48, 41-5-28, 41-6-212, analysis of weapon-mount interface,

41-7-55 41-5-53of conical beam, 37-2-177 of beams, 38-2-222, 41-7-51of deckhouse, 39- 1-111 for calculating transmission of vibration,of electronic equipment cabinet, 36-7-130 38-2-231, 38-S-19of fluid-filled shells, 38-2-79 for complex structures, 38-2-271of foundations, 39-1-40, 39-1-136, 40-4-81 for damping calculation, 38-3-89of heat shield, 36-2-64 data analysis for, 41-5-54of helicopter, 38-3-282, 40-2-236 definition of point force, 40-3-231of high-impact shock machine, 38-2-91 for determlning fixed-base naturalof isolation system, 40-5-204, 40-5-219 frequencies, 38-2-209of lumped mass beam, 38-2-13 in dynamic analysis, 40-2-215, 40-5-135of missile container, 39-6-57 effects of damping on, 40-3-236of missile handling system, 36-7-146 equivalence between modal shockof open cell foams, 40-5-292 parameters and, 41-7-59of open-frame structures, 38-2-181 of foundations, 39-1-123of plates, 40-2-235, 41-5-102 of frames, 38-2-219of propellant tank, 41-7-174 instrumentation for, 38-2-254, 40-7-29,of protective structures, 39-4-200, 40- 7-64, 41-5- 53

40-2-244 of piping systems, 40-4-199of radio telescope, 40-4-155 for prediction of dynamic environments,of railroad cars, 40-6-110 37-6-27, 38-2-249, 40-3-79of re-entry vehicles, 39-1-223, 40-3-34 of shells, 39-3-107of rigid frames, 39-3-34 in shock tests, 39-5-63of shock Isolator, 36-2-92, 38-3-213, simulation of, 40-3-233

39-4-218 of space-damped structures, 38-3-35of solar panels, 40-3-49 using structural equivalence, 36-2-63of sonar transducer, 36-2-33, 41-1-23 for vehicle isolation, 38-3-319of spacecraft, 36-3-16, 36-7-42 for vibration input control, 37-3-89,of submarine hull, 40-7-186 41-4-109of vibrating duct, 40-5-71of weapons skid, 36-1-27 Mechanical properties of elastic materials,

38-3-251Matrix, see Mass matrices and Stiffness

matrices Mechanical receptance coupling

Matrix analysis computer program for, 38-2-242

of helicopters, 40-4-43 in spacecraft system, 38-2-239

using mass and stiffness joiners, 40-IR-2 theory of, 38-2-240on a multi-modal system, 35-5-32

Mechanical Signature AnalysisMatrix flowgraphs, 38-1-1.00 of bearings, 41-4-173

of electronic equipment, 41-4-173Mean error instrumentation for, 36-6-74

in vibration analysis, 37-2-90 of microelectronic devices, 41-4-180

30

Mechanical systems simulation of captive flight environment,frequency correction equations for, 39-6-86

38-2-295 test facility for simulation of launchresponse ot, 38-2-107, 39-3-77 environment, 40-6-1vibration of, 39-3-73 vibration in, 37-1-150, 37-7-93, 40-4-163,viscous damping in, 38-3-111 41-4-190

vibration-induced errors in guidanceMethod of characteristics syi;tems, 37-2-87

for analysis of propagation of stress vibration qualification tests of, 40-6-67waves, 41-6-189

for analysis of splifn of structures, Mobile shelters40-4-127 shock isolators for, 39-4-179

Method co initial parameters, 38-2-157 Mobility, see Mechanical impedance

Microminiature amplifiers Modal analysis, see also Modal characteristics,frequency response oi, 36-6-220 Dynamic analysis, Shock analysis, Structuralspecifications for, 36-6-221 analysis, and Vibration analysisfor transducers, 36-6-215 of aircraft carrier, 37-4-146

automated system for, 41-3-25Microphones of bridges, 41-4-106

calibration of, 37-2-7 of focal isolation system, 38-3-265transfer function for, 37-2-9 Li foundations for shipboard equipment,

40-7-171Miner's hypothesis of frame structures, 40-7-172

use for random vibration, 41-3-47 of helicopters, 36-3-71use of hybric computers for, 41-3-25

Minuteman missile instrumentation for, 36-3-86measurement of vibration for, 37-7-93 of launch vehicle, 37-3-113summazy of vibration data for, 37-7-93 phase separation techniques in, 36-3-89vibration environment of, 37-7-98 of re-entry vehicles, 36-3-83, 40-3-31

of spacecraft, 38-2-143, 41-3-26Missiles, see also specific nmissiles such as of structures, 39-3-55, 39-3-99, 39-3-144,

AIM-4D missile, Bullpup missile, etc. 41-7-10bending of, 38-2-173 from test data, 38-2-271, 41-7-9captive flight environment of, 39-1-195,

39-6-77, 40-6-67 Modal characteristics of structures, 39-4-33components for

reliability of, 39-1-175 Modal combinationsimulation of flight environment for, computer program for, 38-2-139

40-3-293failure rate tests for, 39-2-99 Modal couplingflight test program for, 39-6-102 for Apollo Applicw.ions mathematicallaunch dynamics of, 41-6-219 model, 39-3-58launch environment for, 40-6-1 mathematical analysis of, 39-3-100predictad vs measured environment,

39-6-117prediction of dynamic environments for, Modal damping

41-4-189 effects of tuning on, 37-6-60prediction of fatigue life in, 40-6-67 loss factor from modal mass, 38-2-271response to ejection loads, 40-6-1 loss factor from vibration data,

response to ship loading, 37-7-68response to shock in tracked vehicles,

41-2-166 Modal densityrocket-propelled sled tests on, 39-1-175 of beams, 39-3-1shipping containers for, 39-6-57 of panels, 38-S-9, 39-3-1shock in, 39-S-1, 40-2-1 of printed circuit boards, 38-S-7shock isolation of, 36-2-89, 39-4-213, of shells, 40-3-69

39-6-59 of systems, 36-5-47shock spectra for shells, 38-2-43 of Upstage test vehicle, 41-6-15

31

Modal displacement ratio data analysis equipment for mapping of,versus mass ratio, 41-6-214 39-2-64of deck with simulated equipment, A-I-4

Modal effective mass for foundattons, 3F-3-172definition of, 39-3-143 of frames, 38-2-2 5measured vs calculated, 39-3-149 _, inertial referm.ce unit, 40-3-260measurement of, 39-3-147 from model tests, 37-3-128of structures, 39-3-143 of plates, 38-1-48, 39-2-43, 39-4-81,

39-4-93, 41-7-29, 41-7-37Modal mass of panels, 40-4-139

for calculation of loss factor, 38-2-271 effect of cavity on, 40-4-142determination from vibration tests, of radio teleacope, 40-4-156

38-2-271 of rings, 39-1-151of rocket motors, 41-6-119

Modal orthogonaity of Saturn I launch vehicle, 39-2-141discussion of, 41-3-38 of Saturn V dynamic test vehicle. 40-5-268

of scale model hulls, 41-S-23Modal response of shells, 38-2-79, 39-3-107

of elastic-plastic system, 37-4-73 of sonar transducers, 41-1-28of single resonator, 40-4-18 of Standard ARM, 40-6-80

of structures, 40-4-25, 40-7-33,Modal response suppression factor 40-7-207, 40-S-13, 41-7-9

for distributed parameter system, fron, test data, 41-7-938-2-277 of tubes, 41-7-148

relationship to modal mass, 38-2-271Mode tuning

Modal surveys for aircraft ground vibration survey,correlation of analysis and test, 39-2-129 36-3-67use of generalized mass matrix for,

39-2-127 Model teb.sof Mariner spacecraft, 39-2-123 for determination of strain response,of panels, 39-3-10 36-5-78of Saturn I, 39-2-135 instrumentation for, 37-3-126of scale models, 39-3-39 mode shapes from, 37-3-128of shells, 38-1-89, 39-3-107 Schlleren photographs from, 37-3-135

Modal synthesis Models, see also Dynamic models,for mode shapes of rocket motor, Mathematical models, and Scale models

41-6-119 of blast closure valves, 40-2-133for natural frequencies of rocket motor, digitally simulated, 38-2-119

41-6-119 for dynamic analysis, 40-4-P9of structures, 40-4-25 for evahlation of linear damping,

36-4-65Modal velocity of focal isolation systems

as criterion of severity of shock, 40-2-31 vibration tests of, 38-3. 268lumped parameter, 39-3-153

Modal weight criterion mass-spring of building, 38-2-190for selection of normal modes, 40-7-167 of shvck isolation systems, 41-2-58

for spacecraft reliability, 36-7-4Mode numbers of transducers, 41-3-91

of beams, 36-4-86 for wind tunnel tests, 36-7-80, 37-3-121

Mode shapes Modes, see Bending modes, Modalof aircraft from ground vibration tests, characteristics, and Normal modes

39-2-63antennas, 41-6-110 Modified Clarkson Method, 39-3-88for automobiles, 40-4-94beams, 36-4-55, 38-2-166, 40-5-283, lodular concept for shock and noise isolation.

41-6-163, 41-6-211, 41-7-51 38-3-243

32

Morn( at of Inertia of antenna, 41-6-110composite loss factor vs, 38-3-33 beams, 38-2-133, 40-4-2, 40-4-49,

40-5-277, 41-6-163, 41-6-211, 41-7-51Moment technique of box cars, 41-4-148

for system identification, 38-2-119 calibration of accelerometers, 41-3-3of decks, 40-1-4

Monte Carlo Method, 36-5-6 of frames, 38-2-225, 39-3-35of Inertial reference unit, 40-3-260

Moving loads of lumped parameter systems, 39-3-158response of structures to, 40-3-99, of panels, 39-3-191, 40-3-59, 40-4-139

40-4-47 of piping systems, 40-4-147of plates, 38-1-48, 39-4-73, 39-4-81,

Multi-nvds tests 39-4-93, 40-5-97, ;1-7-29, 41-7-37control of, 40-.4-185, 41-4-34 of printed circuit boards, 40-3-111for transportation vibrttion, 41-3-119 of radio telescope, 40-4-156for vibration of spacecraft, 40-3-179 oi re-entry vehicles, 40-3-40

of rings, 39-1-150Multiple-degree-of-freedom simulator of rocket motors, 41-6-119

for railroad car environments, 41-3-120 of rotor bearings, 40-3-286of scale models, 39-..-42

Multi-degree-of-freedom systems of shafts, 40-4-163, 41-6-208dynamic analogies for, 37-2-59 of shells, 38-2-79, 39-3-107, 40-3-131,dynamic analysis of, 40-1R-1 40-4-209, 41-7-151flutter in, 40-5-235 of ships, 38-1-125mathematical analysib of, 41-6-93 of solar pane- 1, 40-3-52mathematical model of, 36-5-1 of sonar trmnsducers, 41-1-29mechanical impedance analysis of, of suspension systems, 39-6-59

40-2-216 of structures, 40-4-25, 40-4-56, 40-7-207,response characteristics of, 39-3-161 40-S-13, 41-6-75, 41-8-103, 41-7-9Ritz averaging procedure for, 3P-3-162 of transmitters, 40-7-86shock spectra for, 40-4-17 tubes, 41-7-147zeros and poles of transfer functiov for,

40-2-219 Naval gunsenvir•.•ment frora, 6-2-53

Multimodal fixturesfor vibration tests, 38-1-120 Navigation ratio

as an indicatica of performance mal-..lti-modal system function, 39-2-100

fatigue damage to, 36-5-17 mneasurement of, 39-2-101matrix analysis of a, 36-5-32

NERVA Nuclear reactorMulti-point control shock tests on, 36-1-50

of vibration tests, 37-3-75, 41-4-33 vibration analysis of, 36-1-45vibration tests on, 36-1-50

Munson road tests, 37-7-44New York Slate Safety Sedan, 38-3-325

Myklestad's Method

for coupled flexure-torsion vibration, Natural vibration modes, see Modal analysis41-7-109 and Modal characteristics

derivation of, 41-7-119Nike-X missile

N shock test facility for, 37-4-127

NASTRAN computer program Nimbus Spacecraftfor analysis of critical speeds of shafts, vibration tests on, 40-3-243

41-6-206Noise, see also Acoustic noise

Natural frequency, see also Frequency classification of sources, 36-5-97of ammunition conveyor system, 40-4-120 comparison with spacecraft vibrationof anisotropic miterial, 39-3-201 spectra, 36-7-97

33

damping treatments for attenm..m of, of plates39-1-159 holography for identificatica cf,

defluftion of field in acoustic test facility, 40-7-3637-S-47, 39-2-87 of piping systems, 40-4-147

in heUcoptc rs, 41-4-221 of re-entry vehicles, 40-3-40Interaction with structures, 36-5-48 selection ofIsolation of, 38-3-243 for Dynamic Design Analysis VM AhodlIqttd flow in water, 41-2.151 (DDAM), 40-7-165from machinery, 39-1-167 NRL criterion for, 40-7-166measurements of, 37-S-74 of shipboard equipment, 39-1-25, 39-1-55,in piping systems, 39-1-155, 40-4-197 39-3-117, 39-S-41prediction levels of, 36-5-86 of solar panels, 40-3-49iwduction of, 38-3-243, 40-4-103 of shells, 39-1-155, 41-7-151response to, 36-5-99 of structures, 38-3-13 1 ")-3-99, 39-4-31,simulation in acoustic test facility, 40-3-49, 40-7-165, 41-z-105, 41-6-103,

37-S-64 41-7-135Eimulation at reduced pressures, 41-3-207 of tanks, 41-7-164transmission through foundations, 38-S-19,

39-1-167 Nuclear detonations, oee also Gas detonationseffects on submarines, 39-1-98

Noise generators, see Acoustic tefA lacilities simulation of shock loads from, 40-2-243,41-5-167

Nomograph free field environments for, 41-5-137for resonant frequencies of ducts, 40-5-72 analysis of response of systems to,for response of ducts, 40-5-77 41-5-140

Non-destructive tests Nuclear fuel capsulesholographic interferometry in, 41-3-63 impact of, 40-2-193

shells for, 39- 5-21Nonlinear damping

transient response V. mounting system Nuclear power plantwith, 41-2-34 SNAP 10A, 36-7-73

Nonlinear springs Nuclear weaponscharacteristics of, 36-7-105 simulation of effects of with detonablein suspension systems, 36-7-103 gas explosions, 37-4-199

shock environment for, 37-4-97, 39-1-93Nonlinear syst ms

analog comrrters in study of, 36-6-43 Nyquist plotmathematic il analysis of two degree of of co-quad phasors, 37-2-80

freedom, 39-3-161shock in, 39-5-1 0

Nonlinear vibration OH-4A helicopter, 38-3-263of plates, 40-3-119 performance evaluation of vibration

isolator for, 38-3-272Normalization

at structural mode shapes, 39-2-63 OH-6 helicopterresponse to gunfire, 40-1-66

Normal mode methodfor shock analysis, 36-7-129, 37-4-9 1, OV-10 aircraft

38-2-11 vibration of weapon, 40-S-47

Normal modes, see also Bending modes, and Oil filmModal characteristics as a mechanism for damping, 38-3-45

of beams, 38-1-69, 40-4-50, 40-7-34computer program for analysis of, Open cell foam

36-6-101 dynamic analysis ot, A0-5-291of dynamic systems, 40-5-135 predicted vs experimental dynamicof panels, 40-3-60 c.- ,tcteristics of, 40-5-303

34

F

prediction of force-time history for, Packages40-5-300 drop height recorder for, 39-6-19

as shock isolator, 40-5-291 effect of size on drop height, 37-7-14as vibration isolator, 40-5-291 effect of weight on drop height, 37-7-13

measurement of transportationOperation Prairie Flat, 40-1-31, 40-1-45, environments for, 39-6-19

40-1-75, 40-2-83, 40-2-101 rough handling environment of, 37-7-1vibration environment within, 37-3-16Operation Sailor HaL

shear force measurements in deckhouse, Palmgren- Miner hypothesis39-1-117 for prediction of fatigue failure, 40-4-99

Optical systems Panelsdata analysis using, 36-6-91 acoustic fatigue of, 38-1-1Fourier transforms in, 36-6-96 acoustic excitatior of, 40-3-57, 40-5-49

compositeOrbiting Astrono.mical Observatory (OAO), acoustic tests of, 39-4-101

40-3-179 modal densities for, 39-3-12analysis of flight dynamic loads, 40-3-181 natural frequencies of, 39-3-15,combined environmental tests on, 39-3-191

40-3-189 properties of, 39-3-191criteria for dynamic environment for, strain response, 39-4-104

40-3-180 structural analysis of, 39-3-1qualification tests of, 40-3-179 vibration of, 39-3-1, 39-3-191structural qualification loads for, correlation functions for, 40-3-59

40-3-182 dynamic analysis of, 40-4-139test facility for qualification of, 40-3-182 effect of cavity on vibration, 40-4-142

modal densities of, 38-S-9Orbiting Geophysical Observatory (OGO) natural frequencies of, 40-3-59, 40-4-139

arcoustic environment of, 36-7-91 normal modes of, 40-3-60, 40-4-139zcoustic tests of, 37-3-21 prediction of flutter speeds in, 40-4-139response to random vibration, 37-3-21 response ofvibration absorber for, 37-6-57 to boundary layer noise, 40-3-63

to rocket propelled sled environments,Ordnance 41-7-1specification for shock hardening of, strain response of, V^8-1-241-5-80 vibration of, 40-5-49

Overlkad protection Paracril-BJduring vibration tests, 39-2-11 properties of, 38-3-61, 38-3-157

Overpressures Parametric analysisfree field blast from gunfire, 39-6-142 of spacecraft, 39-2-149for full-scale and model blast closurevalves, 40-2-136 Parametric excit•ation

of structures, 40-2-57

Overtestcriteria for, 36-3-6 Parametric vibrationof columns, 39-3-247, 41-6-1elimination of using force control, 36-3-5 of plates, 40-3-119

p Partial full scale shock test machinedisplacement time history for, 39-4-222

Packaged equipment as shock test facility, 39-4-216damage boundaries for, 40-6-127,

40-6-133 Perissogyrodesign procedures for, 40-6-135 as vibration absorber, 37-6-49fragility of, 40-6-127, 40-6-133repeated shock tests of, 39-6-15 Perturbation analysissimulated drop test of, 40-6-139 equations for, 40-7-178

35

for multi-mass systems, 40-7-177 vibration transmission for, 40-4-204PTURB computer program for, 40-7-179 vibration of, 39-1-155, 40-4-197

Phase control system Plasticsdynamic characteristics of, 36-3-150 for scaie models, 39-3-39response limitation of, 36-3-151

PlatesPhase plotting composite

for vibration tests, 37-2-77 damping of, 40-5-93dynamic analysis of, 39-4-73,

Phase separation techniques 39-4-81, 39-4-93, 40-5-93in modal analysis, 36-3-89 mode shapes of, 39-4-81, 39-4-93

natural frequencies of, 39-4-73,Phoenix Missile . 39-4-81, 39-4-93, 40-5-97

acoustic excitation of, 39-6-93 stresses in, 39-4-73captive flight environment for, 39-6-77, vibration of, 39-4-73, 39-4-81,

39-6-93 39-4-93, 40-5-93environmental measurements in F-111B damping in, 39-4-67, 40-5-93, 41-2-106

aircraft, 39-6-93 deformation by exploding projectile,flight vibration of, 39-6-93 37-1-97prediction of captive flight environment deformation as a function of thickness,

for, 39-6-77 37-1-104shock in, 39-6-93 on distributed foundations, 41-5-102

dynamic analysis of, 38-1-45, 39-3-205,Photography 39-4-73, 39-4-81, 39-4-67, 39-4-93,

for studying motion of structures, 40-3-99, 40-3-119, 40-5-93, 41-5-101,36-6-197 41-7-29, 41-7-41

on elastic half space foundations. 43-4-21GPhysiological effects on elastoplastic foundations, 40-4-221

from shock, 41-2-5 finite elements of, 40-3-100from vibration, 41-2-16 mass matrix for bending, 41-7-129

mathematical analysis of, 39-3-197,Plczoelectric accelerometers, see 39-3-206, 39-3-234, 39-4-65, 39-4-74Accelerometers mathematical model of, 40-2-235

mode shapes of, 39-2-43, 39-4-81,Piezoelectric properties 39-4-83, 41-7-29, 41-7-37

of elastomers, 39-2-1 natural frequencies of, 39-4-73, 39-4-81,of polymers, 39-2-1 39-4-93, 40-5-97, 41-7-29, 41-7-37

parametric response of, 39-3-205,Piezoresistive accelerometer3, see 39-3-233, 40-3-119Accelerometers response of

to acoustic excitation, 36-5-104Piping to boundary layer noise, 36-5-102

shock resistance in for ships, 40-S-1 to moving loads, 39-3-233, 40-3-99shock tests of supports, 40-S-4 to ,nock, 39-4-63, 40-4-217,damping in, 39-1-143 41-3-64, 41-5-101

dynamic analysis of, 40-4-147 to traveling pressure pulses,effects of impact on, 40-S-3 40-4-217fluid flow through, 40-2-70 shock wave propagation in, 39- 5-13fluid structure coupling in, 40-4-197 statistical energy analysis of, 36-5-4Gforcing functions for, 39-1-155 stiffness matrix for bending, 41-7-126frequency response, 40-4-198 stresses in, 39-4-73, 40-7-204mass mnatrix for, 40-4-148 vibration of, 38-1-37, 38-1-45, 39-3-197,mc .,anical impedance for, 40-4-199 39-3-205, 39-4-73, 39-4-81, 39-4-93,MIL-S-901C shock tests, 40-S-1 40-3-119, 40-5-93, 41-7-31, 41-7-37natural frequencies of, 40-4-147 vibration tests of, 39-3-210noise in, 39-1-156, 40-4-197normal modes of, 40-4-147stiffness matrJx for, 40-4-149 Pliers eventstress waves in, 40-5-157 shock loads in tower during, 41-6-75

Pneumatic springs for ST'OL aircraft, 40-6-96

mathematical analysis of, 41-3-181 for vibration of Metroliner, 40-6-95as shock Isolators, 41-2-57for testing of projectiles, 41-3-175 Power transmission linesfor variable resonant vibration exciter, galleping of, 39-3-175

38- -3 Prediction, see environment or effect predicted

Polaris missilefield handling, 36-7-145 Pressure pulsesshock during ship loading, 37-7-67 in hydraulic systems, 41-5-143

Polyethy'ene foam Pressurescharacteristics of, 384-177 acoustic tests at low. 41-3-207

Polymers Pressure time historypiezoelectric properties of, 39-2- for air blast, 37-4-188

for underwater explosions. 3i-1-4, 40-1-10Polystyrene foam

characteristics of, 38-3-179 Pressure vesselsshock analysis of, 40-IR-7

Polyurethane foamproperties of, 36-2-90, 38-3-177 Prime moversshoca' isolation with, 36-2-89, 40-5-285 shock tube farility for, 37-4-127vibration isolation with, 40- 5- 285

Printed circuit boardsPc!yvinylchloride-acetate (PVC-A) modal density of, 38-S-7. 38-S-11

properlies of, 40-4-90 xibration response of, 38-S-5

Polyvinylchloride foam Project PYRO, 38-2-177properties of, 38-3-179

Project Sure Fire. 37-2-117Poseidon missile

shock isolation system for, 39-4-214 Projectilesdeformation of steel plates by. 37-1-97

Potential flow model hard-wire instrumentation on, 41-3-175for cylinders. 41-6-32 impact on armor. 41-5-69

inteiaction with target, 37-1-116Power penetration of. 37-1-115

equivalence in components of, 41-3-83 pneumatic spring for testing of, 41-3-175simulation of firing. 41-3-175

Power dissipation test facility for. 41-3-175of kinetic energy, 37-2-99

Propeller shaftsPower spectra, see also Acoustic spectra critical speeds of, 36-6-121

and autocorrelation function, 37-2-90P rot ective structures

Power spectral deas.ty, see alto Cross-power effects of air blast, 38-2-187spectral density effect ot Iound shock on, 38-2-187

on air suspension trtcks, 37-7-21 mathematical analysis of. 39-4-208,definition of, 39-2-90 40-2-243versus dynamic pressure, a, " mathematical model of,39-4-200, 40-2-244of firing pulse of thruster, 40-3-269 shock isolation systems for, 39-4-199high speed computation of. 36-6-47 shock loads for. 40-2-2,14f* mechanical systems. 39-3-75 shock tests c-f equipment in, 40-2-243for multiple square wave shock pulses,

39-5-85 Proximity probesfor railroad cars. 40-6-113 vs accelerometer, 40-7-22in rocket engines. 37-2-121 caliliration of. 40-7-22with selective bandwidth, 36-6-63 for neasurement of dispiacement.for space vehicles. 40-4-!71 40-7-17

37

Pulsed random vibration tests, 40-3-267 Radomespulse gating, 36-6-40 for antennas, 40-1-32

Pyrotechnic devices Railroad carsfor ejection of munitions, 41-5-89 dynamic analysis of, 39-6-52, 40-6-109flight events by, 41-5-I simulation of displacement of, 39-6- 53shock spectra for, 41-5-2 simulator for environments c', 41-3-120shock tests with, 41-5-11 suspension systems for, 40-C .09

vibration of, 40-6-109Pyrotechnic shot:,

attenuatio-, of, 36-2-79, 37-5-40, 41-5-4 Railroadscriteria for prediction of, 41-5-1 effect of track roughness on cargo, 39-6-47damage from, 41-5-10 transportability criteria for cargo, 40-6-85data, 37-2-30, 41-5-1, 41-5-9 transportation environment for, 39-6-47data analysis for, 37-4-21definition of problem of, 40-2-21 Random vibrationin heat shield, 3OA-2-63 of aircraft equipment. 41-S-25in honeycomb st i uctures, 37-4-15 analysis of. 37-2-89instrumentation for, 37-4-17 by finite element method, 38-1-7mass leading effects on, 41-5-13 mean error in. 37-2-90in miss les, 39-S-I, 40-2-21 using optical systems, 36-6-91response spectra for. 36-2-73 of beams. 37-3-93shock spectra for. 41-5-2. 41-5-10 calculation of displacement. 40-3-2simulation of, 36-2-71, 41-5-9 computations of, 38-1-27in structures, 40-2-21, 41-5-9 cross correlation between multiple inputs.in SUU-38 munitions dispenser, 41-5-89 39-2-51

effects on humans. 41-2-130 energy summation for. 40-3-143

environments. 41-3-43Quad phasors, 37-2-77 errors in guidance systems from, 37-2-87

fatigue damaige froi.). 36-4-76. 40-3-1Qualification levels of flight vehicles, 41-6-9

for vibration tests, 37-7-176 Fnurier analysis olf 38-1-18frequency analysis of repetitive buists.

Qualification tests, see also Oualitv Control 38-1-17tests frequencv of zero crossings. 40-3-2

acoustic tests for, 37-5-139. 37-5-167 identification of system parameters.of captive airborne weapons. 39-S-33 38-2-122comparison to flight vibration, 41-3-47 of inertial accelerometers. 37-2-87(a missiles, 40-6-67 of integtrated svstems, 37-3-151of solar panels. 39-2-127 isolation of. 38-3-285on spacecraft, 36-7-1. 40-3-20, 40-3-179 kinetic enerNy of., 40-3-139vibration and st ructural ,eliabilitv. mechanical inipedaihce for predic'ion of.

36-7-1 40-3-79of missiles in capt ie flight,. 39-1- 195

Quality cont ,ol tests.. see also Qualification non-stationamy. 40-4-174tests of panels, 40-5-49

for missiles, 39-2-199 paiametric response of plates t-o.. 40-3-119of payloads in ,hells, 40-3-45l prediction of response to, 37-3-61response

Radar ant enna of plates, 39-3-205, 40-3-119of danmping, 38-3-58 of isolation systems, 40-5-210

of linear sy'stems. 37-3-89, 39-3-73Radioactive maiterials of mechanical sy'stems., 39-3-77

air gun for testing, 41-3-194 of single-degree- o- reedom .vst ems.impact sensitivity otf, 41-3-194 39- 3- 73

ofl shells. 40-3-45. 40-4-209Nadio Ast 'onomy Explorer satellite. 36-6-195 shock tests '.m,. 39-5-83

38

IN

for simulation of engine cutoff, 37-4-62 Reliabilityversus sinusoidal vibration on humans, of components, 39-1-175

41-2-16 determination of, 36-7-9, 36-7-29of spacecraft, 39-6-119 improvement of, 41-2-141specifications analysis, 38-2-52 of spacecraft,stationary, 40-4-172 analysis of, 40-3-11and strain response, 36-5-81 effect of qualification tests on, 36-7-1,of structures, 39-3-55, 41-2-105, 41-6-197, 40-3-20

41-7-195 model for, 36-7-4system identification under, 38-2-120 tests

tests of electronic equipment, 36-7-23,control of, 36-3-1 5, 36-3-47, 37-3-47, 41-4-123

37-3-81, 37-3-89, 41-4-77 of propulsion systems, 36-7-21mechani I 1 ipedance for control of, of warheads, 39-1-177

37-3-8l8with multiple shakers, 36-3-92, Residual thrust oscillation

36-3-153, 37-3-89, 37-3-151, 39-2-51 definition )f, 40-4-171specification of, 41-4-109

transfer function for, 36-5-88 Pesor-.'cetransmission through structures, 38-2-231 of composite panels, 39-3-15, 39-3-195

of ducts, 40-5-72Range of variation of reinforced concrete beams, 38-2-133

definition of, 37-3-77 tests of re-entry vehicles, 36-3-83

Payleigh distribution Resonant frequency, see Natural frequencyto derive peak exceedwnce curve, 41-3-44

Resonant systemsRayleigh's Principle effect of sweep rate on, 41-4-95

in vibration analysis, 40-7-210Response

Rayleigh-Ritz Method, 38-2-169 to acoustic excitationof beams, 33-5-77

RC averaging error, 41-4-93 measurement of, 37-S-53of panels, 38-1-1, 39-4-101

Reactor fuel assembly prediction of, 41-4-87damping model for, 36-4-72 of re-entry vehicles, 40-3-38

of solar panels, 40-3-49Real-time analysis of spacecraft. 36-3-42

analog computer for, 41-3- 55 of structures, 36-5-89. 36-5-97,36-4-49, 39-3-55, 40-3-57

Reciprocity calibration to aerodynamic loadsof probe for vibration, 40-7-:,0 of re-entry vehicles, 39-1-223of vibration exciterr, 36-6-185 to air blastrecoil simulation of. 41-3-187 of antenna, 37-4-151, 40-1-31, 40-1-45in small arms. 41-5-53 of gas turbines, 40-2-147

of hulls, 37-4-143Re-entry vehicles of re-entry vehicles, 39-1-223

acoustic excitation of. 40-3-31 of shells. 37-4-177aerodynamic icads lor, 39-1-223 of structures. 37-4-169, 37-4-177flight vibration tests of, 36-3-113 of target., 41-1-40modal analysis of, 36-3-83, 40-3-31 upper and lower bounds for, 37-4-169natural frequencies of. 40-3-40 of aircraft to crash loads. 38-3-165fIvrotechnic shoc, tests of,. 36-2- 71 characteristics of two-degree-of-freedomresonance tests of. 36-3-83 systems, 39-3-161structural model of., 37-4-67 comparison of shock and vibiation. 36-7-66

digital computers for determining mini-max.,Regression analysis 36-5-71

in combined environment tests, 36-6-83 to dvnanic loadsior prediction of vibration, 37-7-81. of beams, 3j-3-39

39-6-122 of stiffened plates, 39-3-233, 40-3-102

39

of structural elements, 38-2-157 of structuresof two degree of ireedom nonlinear calculations for, 38-2-3, 38-2-157,

systems, 39-3-161 40-3-1effect of Coulomb damping on, 36-1-47 digital computer for analysis of,effect of temperature on, 40-5-4 37-4-171errors in prediction of, 36-1-7 upper and lower bounds of totalof helicopter structures to gunfire, impulse, 37-4-173

41-4-195 to vibration,to launch environments, 38-2-67 of airborne weapons, 37-S-107,limitation of amplitude control system, 39-S-27, 40-6-9, 40-S-59

36-3-151 of boron-epoxy plates, 39-3-205,limitation of phase control system, 39-4-81, 39-4-93, 41-7-30

36-3-151 of bridges, 41-4-99of missiles to ship loading, 37-7-68 of damped structures, 36-6-115.optimization for railroad cars, 40-6-117 41-2-105, 41-4-99to shock of ducts, 40-5-61

of bilinear system, 36-6-45 of dynamic systems, 36-5-69of columns, 40-2-115 of elastomers, 39-2-1of continuous systems, 38-2-112 of flight vehicle. 37-7-77of crash energy dissipators, 39-4-236 of focal isolation systems, 38-3-265,of cylinders, 36-5-106 39-4-144, 40-5-205distributed mass systems, 37-4-48 of humans, 41-2-13of elastic half-space, 39-5-13 of hydrophones, 37-2-52of electronic equipment, 36-7-129, of inertial reference unit, 40-3-260

37-4-98 of launch vehicles, 38-3-104of fluid in gauge system, 40-2-67, of linear systems, 37-3-89, 39-3-73

41-7-192 of lumped parameter systems,of forced draft blower, 38-2-103 38-3-95of fragmenting tubes, 40-5-128 of mechanical systems, 41-4-130,of glass structures, 40-5-175 41-6-42of hard landing payloads, 40-2-187 of payload in shells, 40-3-45of humans, 41-2-5 of printed circuit boards. 38-S-5,of isolation systems, 40-5-206, 40-3-111

41-2-27 of propellant gauge system. 41-7-190of liquid filled tubes, 41-7-149 of rectangular plates. 39-3-205of mechanical systems, 38-2-107 of reinforced concrete beams,of missile stowage system, 40-2-8 38-2-133of missiles, 37-1-115 of rotor bearings, 40-3-283of nuclear reactor of shafts in water, 39-2-217of optimum isolation eystem, 40-5-208 of shells, 38-3-121of plates, 36-5-106, 39-4-63 of spacecraft, 36-5-50of protective structures, 38-2-187, of target acquisition system, 40-S-63

39-4-199 of test specimens, 36-3-48, 38-1-136of rsonators, 40-4-20 of viscoelastic dampers, 38-3-71of rotor bearings, 40-3-286 to underwater explosionsof second-order systems, 36-6-37 of shells, 40-1-15of shells, 38.3-121 of shipboard equipment, 39-1-55of ship decks, 40-1-1 of structures, 41-7-89of ships, 39-1-21 of submarine equipment. 39-S-41of single-degree-of-freedom systems,

39-5-1, 41-S-46 Response functionsof sonar transducer, 36-2-31,, 37-1-67 transformation of, 36-4-105of spacecraft, 37-4-1of structures, 38-2-38. 3o-4-5, Response spectra

40-2-1, 40-5-175 of airborne weapons dispenser,. 40-5-11of shock isolator to foundation velocitN', for bilinear hysteretic beam., 4 1-5-Ao

38-3-216 for blade-like structures, 39-4-26of small arms to recoil, 41-5-53 calculation by analog computer. 36-6-37oi spacecralt from subsystem tor columnns,. 39-3-247. 40-2-115

characteristi(s, 38-2-239 concept of, 36-7-64

40

I'

in control of vibration tests, 37-3-47 Road testsof cylinder during acoustic test, 37-5-69 simulated for tracked vehicle. 41-3-124for nuclear airblast. 41-S-46for pyrotechnic shock, 36-2-71 Road vehiclesfrom random inputs, 39-2-51 vibi'ation isolation of. 38-3-317for remote compass transmitter, 40-5-14 vibration tests of. 41-3-124for shock in plates, 41-5-101of spacecraft electronic assembly, Rocket engines

36-3-30 acoustic excitation of. 41-6-115of structures excited by underwater combustion instability in. 40-4-110

explosions, 40-7-190 environmental data for, 37-2-135for swept sinusoidal vibration, 38-1-133 power spectral density for. 37-2-121for torsional shock, 36-7-64 shock test of, 37-2-129for torsional vibration, 36-7-65 vibration tests of, 37-2-129

vibration analysis of. 41-6-115Reverberant acoust.,c field

correlation coefficients for, 37-5-65 Rocket Motors, see Rocket engines

Reverberation chamber Rocket Propelled sledsacoustic tests in, 39-2-87, 41-3-207 instrumentation for tests, 37-3-199.

41-7-3Reynold's number test data for prediction of response of

critical, 39-2-217 panels. 41-7-1versus Mach number, 37-3-127 tests on missiles. 39-1-175

RF-4C aircraft Pocket vehicles., see Missilesvibration and acoustic environments for,

37-S-95 Rodsvibration of equipment in, 37-S-103 longitudinal vibrations of, 40-2-39

lumped parameter mathematical modelsRigid body of, 41-7-62

damped vibration of elastically-supported.36-7-135 Root locus equations

for binary flutter. 41-7-113Rigid body modes

for helicopter structures, 41-7-135 Root locus methodin extension of binary flutter models.

Riyng spring, 41-2-56 41-7-109mathematical analysis of, 41- 7-120

Ringscomposite loss factor for, 39-1-150 Rotary inertiamode shapes of, 39-1-151 definit-on of. 39-3-49natural frequencies of, 39-1-150 effects on vibrating beams. 38-3-13.vibration analysis of. 39-1-144 39-3-49

Ritz averaging procedure Rotating shaftfor multi-degree-of-freedom systems. danipirg of. 38-3-112

39-3-162Rotor blades

Ritz Method balancing of. 36-7-113in vibration analysis, 39-4-81, 39-4-93 mathematical model of. 40-2-237

vibration isolation of., 38-3-263Riverine craft

shock data for, 37-1-48 Rough handlingshock hardening of, 37-1-35 drop height duri,.g. 37-7-4shock isolation for equipment, 37-1-55 efhect of distribution system on, 37-7-8shock isolation for personnel. 37-1-56 ufVI ronmetnts for caro. 37- 7-1

durinm loadine of slhis. 37-7-67River Patrol Boat MtCASUtreel' t of., 36-6-173

dvyamic environment for, 37-7-205 shock recordt r to., 39-6-19

41

shock spectra for, 37-7-16 S-IVB stagetransportation environments during, assembly level vibration tests,

37-7-1 37-5-121data analysis for vibration tests,

Rough road tests 37-2-109comparison to MIL-STD-810A, 37-7-63 high force vibration tests, 37-3-137

test criteria for vibration, 37-3-139S vibration of propellant in, 41-7-169

vibration environment of, 39-6-133Safeguard facility equipment vibration tests of scale models, 38-2-25

shock tests on, 40-2-243Sawtooth pulse, see Shock pulse

Safety criteria for automobiles, 38-3-3z5Scalar flowgraphs, 38-1-100

Safety factorsderivation for spacecraft equipment, Scale models, see also Dynamic models and

40-3-94 Mathematical models, and Modelsfor design of spacecraft structures, correlation factors for natural frequencies,

40-3-89 39-3-42for crash simulation, 39-4-230

SAM-D Missile in crash tests of aircraft fuselages,rail launch dynamics of, 41-6-219 38-3-171

in crashworthiness studies of vehicles,Sandwich panels, see Panels 39-4-227

data from wind tunnels, 37-7-221Sandwich plates, see Plates for dynamic analysis of structures,

40-4-89Satellitev, see Spacecraft for dynamic studies of launch vehicles.

40-3-205Saturn launch vehicles properties of materials for, 39-3-40

acoustic environment of, 39-6-133 for shock analysis of structures, 40-1-1dynamic test vehicle, 40-5-261 for stress in blast closures, 40-2-138fixture for component vibration tests, vibration of beams, 39-3-39

38-1-87prediction of dynamic characteristics, Scaling

40-5-268 for blast of weapons, 39-6-141S-1B stage of damping, 36-4-1

bending modes for, 37-3-113 for dynamic models, 39-4-228combustion instability tests, 40-4-109 for shock tests, 39-5-41data from dynamic tests, 37-3-115 for shock tubes, 39-5-41, 39-5-53dynamic tests, 37-3-99 for Titan Ill models, 37-3-125isolation system for dynamic test of vibration data, 36-5-85

stand, 37-3-101measured versus predicted modes, Schlieren photographs

39-2-139 from mo t esmodal survey, 39-2-135 from model tests, 37-3-135structural analysis, 39-2-136

S-IC stage Scout launch vehicleacourtic tests on fin structures, prediction of flight vibration, 36-5-85

37-5-167engine cutoff vibration, 37-4-59 Seismic massreliability program for, 36-7-19 isolation system for, 41-3-110

S-I1 stage for variable resonant vibration exciter,acoustic vs mechanical excitation for, 38-S-3

37-5-135analysis of data from, 36-6-47, 36-6-55 Self synchronizationassembly level vibration tests, of vibrating machinery, 41-6-159

37-5-121launch vibration environment, Sensitivity analysis

37-5-117 of shock isolators, 41-2-51

42

Sensitivity of humans to vibration, 41-2-13 structural analysis of, 38-1-87, 38-2-79,39-3-107, 39-5-21, 40-3-23, 40-3-31,

Separation shock, see Pyrotechnic shock 40-3-69, 40-3-131, 40-4-209, 41-7-151vibration of, 3U-1-155, 39-3-107, 40-3-31,

Shafts 40-3-69, 40-3-131, 40-4-209critical speeds of, 38-3-45, 41-6-203 as vibration test fixtures, 38-1-87in studies of bending vibrations of

missiles, 38-2-169 Shillelagh Missilein studies of torsional vibrations of shock test facility for components,

missiles, 40-4-163 37-4-103, 37-4-111torsional natural frequencies of, 40-4-164vibration analysis of, 39-2-217 Shipboard environmentvortex shedding of towed, 39-2-218 simulation of, 40-2-51

versus floating platform shock tests and,Shakers, see Vibration exciters 37-1-71

Shear deformation effects on vibrating beams, Shipboard equipment38-3-13, 39-3-49 analysis of response to underwater

explosions, 39-S-41Shear modulus combined environment tests of, 36-6-83,

measurement of, 36-4-85 40-2-51criteria for shock inputs to, 39-1-80

Shells damage of, 37-1-2, 39-1-1, 39-1-96acoustic excitation of, 40-3-23, 40-3-31 DDAM prediction versus response, 36-1-1attenuation of noise in, 39-1-159 design for underwater explosions, 39-1-65correspondence theorem for, 38-3-122 dynamic analysis of, 36-7-129, 38-2-11,criterion for impact failure, 39-5-21 39-1-13, 39-1-25, 39-1-33, 39-1-45,damping of, 38-3-121, 39-1-155 39-1-74, 39-1-80, 39-3-117, 39-3-41,dynamic stability of, 41-7-81 40-1R-1, 40-7-165, 40-7-177, 40-7-197eigenvalue distributions in, 40-4-209 Dynamic Design Analysis Method (DDAM)eigenvalue problem for, 38-2-86 for, 39-1-13, 39-1-25elasto-plastic response to impulse loads, effect on shock response of decks, 40-1-1

41-7-81 fixed-base natural frequencies for,equations of motion for, 40-3-75 38-2-209finite element analysis of, 41-7-84 foundations for, 38-3-1, 39-1-39, 40-7-171Hamilton's principle in modal analysis, Fourier spectra for, 39-S-47

41-7-152 information needs for dynamic analysisKennedy-Pancu Method for vibration of, 40-7-141

studies of, 39-3-107 mathematical models of, 39-1-45, 39-1-86,impact of, 39-5-21 40-IR-5kinetic energy of, 40-3-134 normal mode analysis of, 39-1-13,mathematical analysis of, 38-3-123 39-1-25, 39-1-55, 39-S-41mathematical model of, 38-2-79 problems in application of DDAM,mechanical impedance of, 39-3-107 40-7-144modal densities of, 40-3-69 shock environment, 37-1-1, 40-S-29mode shapes of, 38-2-79, 39-1-161, shock hardross, 39-1-1, 39-1-13, 39-1-25,

39-3-107, 40-3-31, 40-3-131, 41-7-151 40-7-143mode surveys of, 39-3-107 shock isolated vs hard mounted. 40-S-40natural frequencies of, 38-2-79, 39-3-107, shock isolation of, 37-1-25, 39-1-83,

40-4-209, 41-7-151 40-7-233, 40-S-29for nuclear fuel capsules, 39-5-21 shock response, 40-2-1optimized damping treatments for, shock spectra for, 39-1-15

39-1-163 shock tests of, 37-1-69, 38-2-95,radial motion of spherical, 36-5-114 38-3-221, 39-1-70, 39-1-84, 40-7-145response to underwater explosions, sources of shock data for, 36-1-2

40-1-15 stress analysis of, 39-1-42shock spectra for, 38-2-43 two-stage isolators for, 40-7-233stress waves in, 38-2-38 velocity spectra for, 39-S-48stresses in, 40-3-43 vibration isolation of, 40-7-233

43

Shipboaro personnel DD421shock isolation of, 37-4-79 capsize boundaries of, 37-1-87

design of machinery for, 39-1-33Shipboard shock design of propulsion systems, 39-S-55

effect on humans, 41-2-5 DLG-16, 39-1-107elastic-plastic analysis of, 37-1-25 capsize boundaries of, 37-1-87evolution of design techniques for, 37-1-23 dynamic analysis of boilers, 39-1-26on HMS OBDURATE, 37-1-1 effects of airblast on, 36-1-13, 37-1-77,information needs for design requirements, 37-4-143, 39-1-1

40-7-141 effect of underwater explosions on,motions of decks, 40-1-1 36-1-13, 37-1-1, 39-1-1, 39-1-65protection of equipment from, 39-1-100 on shipboard humans, 41-2-5response of missile stowage system to, electronic equipment for, 39-3-117

40-2-8 environmental data from, 40-7-225shock isolators for, 38-3-246 foundations for machinery, 38-S-19survey of progress in, 37-1-15 HMS OBDURATE, 37-1-1tests on shock isolators, 40-S-35 use of keel shock factor for, 39-1-8on 21B weapons skid, 36-1-23 predicted vs measured shock response,

39-1-21Shipboard vibration rough handling during loading, 37-7-67

automated recorder for, 40-7-225 shock analysis for, 40-1-1, 40-7-65computer program for analysis of, 36-6-115 shock data for, 36-1-14, 37-1-1data analysis of, 36-6-67 shock loads on, 39-1-3, 39-1-13, 39-1-33,instrumentation for, 40-7-243 39-1-65, 39-1-93, 40-7-141, 40-7-153,response of structures to, 36-6-115 40-S-1, 41-1-1vibration exciter for, 38-S-1 shock resistance of piping, 40-S-1

shock tests of boilers, 39-1-30Shipping containers, see also Containers specifications for shock inputs, 39-1-13

dynamic analysis of, 39-6-57 underwater explosions tests on, 39-1-67,for missiles, 39-6-57 41-1-1recorder to measure drop height, 36-6-173 USS ATLANTA, 36-1-3, 36-1- i3shock during handling, 37- 7- 2 USS FULLAM, 36-1-3shock tests of, 39-6-65 velocity time histories at different decksimulation of tipover, 39-6-65 levels, 39-1-7

vibration in, 38-1-125, 39-S-55, 40-S-13Ships vibration analysis of, 36-6-67, 36-6-115,

airblast environment for, 36-1-16, 39-1-95 38-S-1, 39-S-55aircraft carriers vibration characteristics from impulse

analog computer program for loads. 40-S-7vibration, 40-S-16 vibration tests )f, 41-S-1

catapult excited vibrations on, 40-S-13effects of air blast on, 37-4-143 Shock, see also specific types such as Groundmathematical model of, 37-4-144. shock and Pyrotechnic shock

40-S-16 as criteria for severity acceleration,modal analysis for, 37-4-146 40-2-31

antennas for, 37-4-151, 40-1-31, 40-1-45, attenuation of40-1-75 in glass structures, 40-5-175

balanced protection for, 39-1-97 in missiles, 39-S-1calculations of natural frequencies for, by yielding structures, 3P -255

38-1-125 in avionics during arrested lari.i: gs,CVAN 65 40-6-37

capsize boundaries for, 37-1-87 challenging problems in. 36-2-1criteria for shock hardening, 39-1-65, complexity of, 36-2-5

39-1-93 criteria for shipboard structures, 39-1-39daunping from anchor drop tests, 40-S-8 damage to eggs, 41-3-11damping of foundations for machinery, damage mechanisms for, 37-4-71

39-1-171 designdamping treatments for silencing, 41-2-151 of electronic equipment,, 37-4-98damping from vibration generator tests, use of fixed-base natural frequencies

40-S-9 in, 38-ý-261

4;

of shipboard equipment, 39-1-13, in ships, 39-1-1, 39-1-13, 39-1-33,39-1-25, 39-1-77 39-1-65, 39-1-93, 40-7-141, 40-7-153,

of shipboard structures, 39-1-39 40-S-1, 41-1-1of ship boilers, 39-1-25 problems in dissemination ofin submarines, 38-3-243 information, 39-1-81use of vibration for, 41-4-119 sources in structures, 40-2-22

displacement amplifier for, 41-3-149 spectral analysis of, 36-6-2in electronic equipment, 40-7-85, 40-S-73 in submarines, 39-1-93, 39-S-41, 41-S-49environment transient waveform control of, 40-2-164

from guns, 39-6-139 in trucks, 39-6-31isolation of gunfire, 39-4-251 velocity spectra as descriptor of, 40-2-32for nuclear weapons, 37-4-97, 39-1-93

equivalence with vibration, 41-4-124 Shock analysis, see also Dynamic analysis,from 5 in./54 Naval gun, 36-2-53 Mathematical analysis, Modal analysis,during handling of shipping containers, Structural analysis, and Vibration analysis

37-7-2 of aircraft during ground impact, 38-3-166human tolerance to, 37-4-80, 41-2-5 analog computers in, 36-6-37inputs for shipboard equipment, 39-1-50 computer programs for, 36-6-131in M-151 jeep, 37-7-39 of cylindrical shells, 40-1-17measurements digital computers in, 40-7-153

on ships, 39-1-5 of elastic-plastic systems, 39-5-2,on structures, 40-2-3 40-4-67

in missiles, 39-S-1 of elastoweric shock isolators, 39-4-216during shiploading, 37-7-67 of electronic equipment, 39-3-117, 40-7-85,

modal velocity as criteria for severity, 40-S-3140-2-31 energy-flow method for, 37-4-65

in nonlinear structures, 41-5-27 finite element method for, 38-2-11in non-linear system, 39-5-1 of fluid systems, 40-2-67parametric response to, 40-2-115 of force transmitted to armor, 41-5-72performance of gas bearings during, of gas spring, 41-3-181

38-3-221 of high-impact shock machine, 38-2-95physiological effects from, 41-2-5 of impact damping, 39-4-3prediction of transmission, 37-4-65 of impact limiters, 40-2-185protection of spacecraft during landing, of inverting tube for, 41-2-89

41-2-89 of machinery for ships, 39-1-35protection of above-ground structures, mathematical models for, 36-6-131

37-4-213 normal mode method for, 38-2-11response to of open cell foams, 40-5-291

of beams, 40-4-3, 41-5-27 of pressure vessels, 40-IR-7of bearings, 40-3-275 of propagation of shock wave, 39-5-14

of electronic equipment to, 37-4-98 of propagation of stress waves, 38-2-34of fluid systems, 40-2-67 of rotational drop test, 39-4-182of fragmenting tubes, 40-5-128 of shipboard equipment, 39-1-33, 39-1-45,of glass structures, 40-5-175 39-3-117, 40-1R-1, 40-7-177holography for, 40-7-33 of ships, 39-1-13, 40-7-165of hulls, 40-7-185 of ship's decks, 40-1-1of missiles on tracked vehicle, shock spectra in, 37-4-43

41-2-166 of shock tubes, 39-5-42of multi-degree-of-freedom systems, of sonar transducers, 41-1-21

40-4-17 of structures, 36-6-131, 40-1-1, 40-2-31,of plates, 39-4-67, 41-5-101 40-2-123, 40-5-176, 40-7-185, 40-7-197,of ship decks, 40-1-1 41-7-89of shipboard equipment, 40-2-1 of suspension systems, 39-6-60, 40-5-218,

response spectra 41-2-60for columns, 40-2-115 of test facility for damping collar, 40-5-16r,for plates, 41-5-101 time sharing computer program for,

rough hanldling, 37-7-16 40-7-153on shipboard equipment, 37-1-1, 40-S-29 of tipover of shipping containers, 39-6-68on shipboard machinery, 39-1-34 of vacuum tube launchers, 40-2-194

45

Shock analyzer design of attenustor strut ior, 38-3-256design of, 37-2-65 of equipment in mobile shelters, 39-4-179digital, 36-6-21 of ground support equipment, 37-4-218

from high frequency effects, 41-2-53Shock barges, see Floating shock platforms for impact on structures, 40-5-115

with nonlinear damping, 41-2-21Shock data open cell foama for, 40-5-291

analysis of, 36-2-55, 40-7-115 with polyurethane foam, 36-2-89automated system for, 36-6-21 properties of elastomeric materials,desiderata for, 36-6-22 39-4-213digital, 36-6-21 of recoil forces from guns, 39-4-251fast Fourier transforms in, 41-5-39 for riverine craft equipment, 37-1-55proposed standard for, 39-6-7 for riverine craft personnel, 37-1-56

comparison for full-scale and model blast of shipboard equipment, 37-1-25closures, 40-2-143 of shipboard personnel, 37-4-79

interpretation from ship shock tests, systems40-2-1 analysis of, 40-5-218, 41-2-60,

presentation of, 39-6-7 41-5-129for riverine craft, 37-1-48 design of, 41-2-55, 41-2-68, 41-5-155during rough handling, 37-7-2 for equipment in hardened sites,sampling and digitalization of, 41-5-0ý 41-5-155on ships, 37-1-1 for equipment platforms, 41-5-129

from air blasts, 36-1-16 fragility of, 41-5-129from underwater explosions, 36. 1-14, interactive optional design of,41-2-47

40-1-11 modeling of, 40-5-218, 41-2-58on simulated ship structures, 40-2-10 for Frotective structures, 39-4-199sources for shipboard equipment, 36-1-2 viscoelastic materials for, 40-5-175on submarines, 36-1-4 yielding structures for, 41-2-89

of weapons skid 21B, 36-1-23Shock design numbers

comparison of, 39-3-117 Shock isolators, see also Active vibrationisolators and Vibration isolators

Shock effects annularon isotopes, 41-3-194 dynamics of, 39-4-213on sonar transducers, 36-2-31 effect of air flow on spring rate of,

39-4-226Shock hardening mathematical mod.l of, 39-4-218

of antennas, 37-S-1 for avi'nics equipmentof hydraulic systems, 41-5-143 during arrested landing, 40-6-37of ordnance, 41-5-77 polyurethane foams As, 40-5-285of riverine craft, 37-1-35 computer-aided design of, 41-2-47of shipboard equipment, 39-1-1, 39-1-13, crushable structures as, 39-4-199

39-1-2.5, 40-2-147, 40-7-143, 41-5-35 damped, 38-3-215of shipbcard structures, 39-1-107 dynamic characteristics of, 41-2-53of sonar transducers, 37-1-65 double actingof submarines, 39-1-93 analysis of, 38-3-214of weapon systems, 41-5-135 performance of, 38-3-219

elastic skid mounts as, 39-4-179Shock inputs elastomeric, 41-2-57

for shipboard equipment, 39-1-80 analysis of airflow in, 39-4-216properties of, 39-6-58

Shock isolation for electronics equipment, 40-S-31for aircraft crashes, 41-3-133 energy-absorber steering columns as,of avionics components, 40-5-285 37-4-79of ballistic missiles, 36-2-89, 39-4-213 for equipment in hirdened sites, 41-5-129combined with ship silencing, 38-3-243 failure models for, 41-5-130computer-aided design, 39-4-185 flow diagram for, 41-2-49concepts, 37-4-214 gas dynamic effects in, 39-4-213concrete for, 39-4-199 high performance, 41-2-53crushable structures for, 41-2-95 high rate loading of, 40-5-218

46

data acquisition for, 40-5-256 from gins, 36-2-85test facility for. 40-5-245 half sine

tests of, 40-5-223 crushable honeycomb response to,indirect synthesis of, 39-4-180 40-4-74inverting tube u, 41-2-89 elastic-plastic system response to,linear versus nonlinear, 41-2-34 40-4-67load deflection characteristics of, on elecUtodynamic vibration exciters,

40-7-235, 40-8-31 36-2-21mathematical models of, 38-3-213, 41-2-65 shock spectra for, 36-2-23, 37-2-73for missile stowage system, 40-2-10 yielding structures response to,for mobile shelters, 39-4-179 40-4-81optimum, 36-5-73, 39-4-185 input for microphone, 37-2-7open cell foams as, 40-5-291 rectanguIsVperformance of comphnsation for, 40-7-130

conventional, 40-7-234 response of bilinear system to,o( crushable, 39-4-23- 36-6-45

polyurethane foam, 36-2-92 /aesponse of columns to, 40-2-119relaxation damping for, 40-5-203 requirements for full-sine, 40-2-178sensitivity analysis of, 41-2-51 response of columns to longitudinal,for shipboard equipment, 38-3-246, 40-2-115

39-1-83, 40-7-233, 40-S-29 sawtoothshock tests on, 40-5-171, 40-5-246, compensation for, 40-7-130

40-7-235, 40-S-35 on electrodynamic vibration exciters,shortcomings of conventional, 38-3-213 36-2-24, 40-7-94soil as, 37-4-182 iesponse of elastic-plastic systemspecifications for, 41-2-54 to, 39-6-1stress waves in, 40-5-157 response of resonator to, 40-4-20surging in, 40-5-217 shock spectra for, 36-2-22, 37-2-74system identWf'-lon in design of, 39-4-188 shapingtransmlisslbility of, 41-5-157 by drop test techniques, 41-5-65vacuum spring as, 36-7-103 shock spectra for triangular, 37-2-75

square wave,Shock loacs, see also Impulsive loads power spectrum for, 39-5-85

on beams, 41-6-147 synthesis of, 39-5-69on blast closure valves, 40-2-135 trapezoidal,on composite materials, 41-5-69 response to, 36-5-119design for high intensity, 40-7-85 shock spectra for, 36-5-124dispersal of, 41-2-77measurement of, 41-3-64 Shock recordersparametric response of columns to, design requirements for, 36-6-175

40-2-115 for rough handling of packages, 36-6-173,in plates, 41-5-101 39-6-19respnJmwe of secoWd-urdE i" svstmn. to, test shipments with, 39-6-30

36-6-37 for transportation environments, 36-6-163,on scale mocels, 3U- 4 - 26 1 36-6-173, 39-6-19, 40-3-99ships, 39-1-3simulation of, 40-2-243 Shock response, see responseon structures, 40-2-3, 40-2-57, 40-2-115,

40-2-243, 41-6-75, 41-6-187, 41,7-89 Shock spectrafor tests of spacecraft, 36-2-97 analysis of, 37-4-43, 11-3-75vibration absorbers for, 39-4-261 by analog computer, 36-6-43

ana!yzers for, 37-2-66, 41-3-78Shock pulse calculation of

analog analysis of, 38-1-19 by digital computer, 36-6-131compensation for haversine, 40-7-126 using Duhamel integral, 36-2-12editing of, 36-6-23 comparison for various pulse shapes,on electrodynamic vibration exciters 40-6 134

procedures for generating, 40-7-96 of complex shock transients, 36-6-9synthesis of multiple, 39-5-83 computer program for, 36-2-12

Fourier spectra for, 40-2-175 definition of, 41-3-75, 41-5-18

47

derivation of, 41-5-19 for sirmulation ofin design of equipment, 40-2-215 air blast, 39-1-102for dynamic analysis of shipboard human head impacts, 39-5-89

equipment, 39-1-15 underwater explosions, 37-4-137effect solid-propellant guns as, 36-2-83

of damping on, 40-2-223 for submarine hull penetrations, 39-1-73of digitizing detail on accuracy, vacuum tube launchers as, 40-2-193

36-6-1 for zero impedance tests, 39-5-64of separation of frequencies on dip,

40-2-225 Shock test machines, see also High-impactof signal error on analysis, 37-2-38 shock machines

of gunfire on helicopters, 41-4-207 capabilities of modified slingshot, 39-5-76for half-sine pulse, 36-2-23, 37-2-73 drop test, 37-2-32instrumentation for, 36-2-18 acceleration-time histories on,lower and upper bounds to, 40-2-220 41-5-59for missile shells, 38-2-43 shock tests on, 39-5-73, 41-5-59as a measure of damage potential,41-5-17 dual mode, 37-4-137for munitions ejection, 41-5-96 ,forw< mulation of container tipover,practical upper frequency limit of, 37-4-43 39-6-65for pyrotechnic shock, 41-5-2requirements for transmitter, 40-7-86 Shock testsfor rough handling shocks, 37-6-16 of aerial-delivered material, 41-3-223for sawtooth pulse, 36-2-22, 37-2-74 of attenuator struts, 38-3-257for shock isolated equipment, 41-5-167 of beams, 41-6-147using sinusoidal pulse technique, 38-3-211 of bearings, 40-3-280for slow sweep vibration tests, 38-3-208 by directional, 37-2-33for spacecraft, 39-5-67 on blast closure valves, 40-2-133in specifications, 39-5-85, 40-2-245 of boilers for ships, 39-1-30for structures, 40-4-17 compared to normal mode structuralfor trapezoidal shock pulse, 36-5-124 analysis, 39-3-117for triangular pulse, 37-2-75 with compressed air launchers, 40-S-21for underwater explosions, 39-S-41 control of waveforms by digital computers.for weapons skid 21B, 36-1-26 40-2-157yielding effects on, 36-2-9 for design of equipment, 40-2-215

0 .on drop test shock machines, 39-5-73,Shock test facilities 41-5-59

air guns as, 37-2-32, 37-3-219, 37-4-103, versus Dynamic Design Analysis Method37-4-111, 41-3-194 (DDAM), 36-1-1

for calibration of accelerometers, with electrodynamic shakers, 36-2-17,40-2-205 36-3-91, 39-5-67, 39-5-83, 40-2-157,

compressed air launchers as, 40-S-21 40-2-173, 40-7-93, 41-3-149detonable gas explosions as, 37-4-199 of electronic equipment, 39-3-118,electrodynamic vibration exciters as, 39-5-79, 40-7-85, 41-4-123

39-5-67, 39-5-83, 40-2-157, 40-2-173 of equipment in protective structures.exploding wires as, 37-4-121 40-2-243, 41-5-167floating shock platform as, 37-1-69, using exploding wires. 37-4-119

37-4-85, 39-1-82, 40-2-1 for failure loads on railroad cargo,gas guns as, 41-3-155 40-6-87mechanical amplifiers as, 40-2-205 floating shock platform versus shipboardfor missile containers, 37-4-137 environment, 37-1-71partial full scale test machine as, 39-4-216 fixtures for, 38-2-95, 39-2-175for prime movers, 37-4-127 force-controlled, 39-5-63for qualification to MIL-S-901C, 37-4-85, on foundations. 38-3-2

39-1-71 for fragilityfor repeated shocks, 39-6-15 of packaged equipment, 40-6-127.Servo-hydraulic vibration exciters as, 40-6-133

40-2-243 of systems, 41-5-121shock tubes as, 37-4-127, 39-5-41, of fragmenting tubes, 40-5-116

39-5-53, 40-2-133, 40-2-147 on fuzes, 41-3-155shock tunnel as, 37-3-203 of gas-bearing machinery, 38-3-221

48

with gas guns, 41-3-155 Shock tubes, see Shock test facilitiesof glass spheres, 40-5-178on gas turbines, 40-2-152 Shock velocitywith head impact simulator, 39-5-96 from scaled data, 39-5-56of helical coils, 41-2-79high acceleration, 40-2-205 Shock waves, see also Blast wavesof humans, 41-2-5 fluid-structure interaction, 39-1-63on hydraulic systems, 41-5-145 propagation ofof isolation systems, 41-2-61 in composite materials, 41-5-69limitations on present methods, 39-5-63 in elastic half-space, 39-5-14mechanical amplifications of stress waves in elastic plates, 39-5-13

for, 40-2-205 kinetic energy absorbed hi, 40-7-135mechanical impedance in, 39-5-63 weasurement uf, 40-7-134on modified floating shock platform, through structures, 40-2-21

37-1-69 in soilswith modified slingshot shock test pulse x-rays for study of, 36-6-225

machine, 39 5-71 in structures, 36-2-66, 39-5-13, 40-2-21of nuclear zuel capsules, 40-2-193of perkaged equipment, 39-6-15 Sidewinder Missile (AIM-9D)of pipit g, 40-S-1 power spectral density vs dynamic pressure,pyzi'technic 37-S-111

with explosive charges, 36-2-71of a re-entry vehicle, 36-2-71 Signal error

with pyrotechnic ae'ices, 41-5-11 elfect on shock spectra analysis, 37-2-38for railroad transportability of cargo, sources in transducers, 37-2-29

40-6-86on rocket engines, 37-2-129 Silencing, see Submarineson scale model vehicles, 39-4-227shipboard, 37-1-21, 37-1-69 Silicones

interpretation of data from, 40-2-1 characteristics of, 38-3-177of a missile stowage system, 40-2-5 damping properties of, 38-3-64

of shipboard equipment, 37-1-69, 38-2-95,38-3-221, 39-1-70 Silos, see also Hardened sites

panel discussion oi , 'Q-'-77 fragility of equipment in, 41-5-161problems in, 39-1-34, 40-7-145 hydraulic systems for, 41-5-143

of shipping containers, 39-6-65 shock isolators for equipment in,of shock isolators, 39-4-217, 40-5-171, 41-5-129, 41-5-155

40-5-246 sho',k tests uf equiprment in, 41-5-167with shock tubes, 39-5-41, 39-5-53with solid-propellant-powered guns, Simuladon, see effect ur environment simulated

36-2-83on soni.' transducers, 37-1-63 Simultdeon spacecraft, 39-5-67 i'. shock tubes, .%-6-57specialized facilitiea for, 37-4-103, Simile-degree of-freedom systems

3 7 -4 -1 1 1 , d y n a m ice a n a log- f o m 3 7 -2 -5 8specifications for, 36-2-107, 39-5-63, dynamic analoyses for, 37-2-58

39-5-67, 39-5-85, 40-2-164, 40-2-241, dynamic analysis of, 40-4-67, 41-5-4541-5-77 response of

vacuum tube launchers for, 40-2-193 to random vibration, 39-3-73to verify mathematical model of foams, to sawtooth shock pulses, 39-5-140- 5-300 to trapezoidal shock pulses, 36- 5-119

40-5-300shock in non-linear, 39-5-1of weapon ejection mechanisms, 41-5-89 transfer functions for, 39-3-75zero impedance, 39-5-63

design of shock test facilities for, Sinusoidal pulse39-5-65 shock spectra using, 38-3-211

for vibration tests, 38-3-207Shock transients

Fourier spectra of, 36-6-9 Sinusoidal vibrationshock spectra of, 36-6-9 calibration for, 37-2-23

49

damping in plates during, 41-2-106 Sonic fatigue, see Acoustic fatigueerror as a function ol amplitude, 37-2-88fatigue damage from, 36-4-76, 36-5-17 Sound generators, see Acoustic test facilitiesfragility of resolver for, 41-5-114isolation of, 38-3-285 Sound pressure levels, see also Boundarykinetic energy of, 40-3-139 layer noiseresonant response to swept-notched, contours for VTOL Aircraft, 41-4-165

41-4-130 point-to-point correlation of, 39-2-87response to

of damped cylindrical shells, 38-3-132 Spacecraft, see also specific spacecraft suchof humans, 41-2-13 as Apollo spacecraft, Mariner spacecraft,of spacecraft, 41-4-127 and Lunar Orbiter spacecraft

response spectra for swept, 38-1-133 acoustic environment for, 40-3-52to simulate engine cutoff, 37-4-60 acoustic excitation of solar panels, 40-3-49to simulate spacecraft flight loads, acoustic test facility for, 37-5-25

39-2-147 acoustic tests of, 37-5-1, 40-4-105,and strain response, 36-5-81 41-3-207transmission through structures, 38-2-231 components, 36-3-39

application of mechanical impedance to,Mkds 38-2-239, 38-2-249, 40-3-86

design criteria for, 39-4-180 attenuation of impact for, 40-2-183load-deflection characteristics of, combined environment tests on, 37-3-188

39-4-180 criteria for vibration of, 37-7-202design criteria for, 40-3-96

Sky Lab dynamic environments of, 40-3-12, 41-4-3dynamic environment, 41-7-195 flight data versus acoustic tests, 36-3-44

flight vibration of, 37-7-173, 40-3-9Slosh interaction with launch vehicles, 38-2-239

modes, 41-7-181 launch induced failures, 40-3-9in propellant tanks, 41-7-169, launch phase simulator for, 37-5-175

41-7-185 mathematical model of, 36-3-16in rigid tanks, 41-7-164 modal analysis of, 41-3-26

of propellant noise reduction in, 40-4-103equivalent mathematical model of, notched random test spectra for, 36-3-15

41-7-169 parametric analysis of, 39-2-149predicted vs experimental, 41-7-176 prediction of dynamic environments for,scaling laws in equivalent models for, 40-3-79

41-7-170 protection during landing shock, 41-2-89reliability of, 40-3-11

Snap buckling analysis of, 40-3-11of structures, 41-6-89 effect of qualification tests on, 36-7-1

model for, 36-7-4Snap 1OA response of

crltcria for structural design of, 36-7-74 to sinusoidal vibration, 41-4-127flight vibration data for, 36-7-75 from subsystem characteristic,,

Soil 38-2-239

analysis of ground shock in, 38-2-19t safety factors for, 40-3-89as isolator of stress waves, 37-4-182 shock loads in, 36-2-97

y36-6-225 shock spectra for, 39-5-67shock tests on, 39-5-67

Solar panels structural analysis of, 36-3-16finite element models of, 38-.2-149 structural qualification, 39-2-147normal modes analysis for, '0-3-49 synthesis of analytical model of, 39-2-153qualification tests of, 39-2-127 transient loads in, 36-2-97response to acoustic excitation, 40-3-49 transportation environment for, 37-7-19

Sonar S, ,tem AN'BQS-6B, 39-3-117 vibration analysis of, 41-4-128using the statistical energy method,

Sonar transducers 36-5-41mathematical models of, 36-2-33 vibration tests of, 40-3-9.ahock in, 36-2 1, 37-1-67 fixtures for, 40-3-231

50

force-controlic 1, 36-3-15 Stabilityto simulate flight loads, 39-2-147 of active vibration isolstion systems,

39* 4-16L5Spzed-dampin

W4-6

application of, 38-3-34 Standard Antiradiation Missile (ARM)of structures, 3e-3-31 captive flight environment for, 40-5-68

spectral analysis of bending moment for,Spalling 40-6-81

of strucnwres, 40-4-127Standards, see also specifications

Specifications, see also Staniards for calibration of accelerometers, 41-3-1analysis of, 38-2-52, 39-6-151 for evaluation d fragility, 41-5-111of combined environmental tests, 37-5-176for microminiature amplifiers, 36-6-221 Static analysisMIL-E-5400, 40-6-37 of anisotropic material, 39-3-201MIL-S-901C, 37-1-69, 38-2-95, 41-5-77MIL-STD-810B Static firing tests

for shock tests, 40-2-173 for launch vehicles, 37-3-99, 39-6-133,for vibration tests, 40-3-151 40-4-109

MIL-T-5422, 40-647 isolation system for, 37-3-99safety factors for spacecraft structures,

40-3-89 Statistical analysisfor shock hardening oa ordnance, 41-5-30 of multi-degree of freedom systems,of shock inputs to ships, 39-1-13 40-4-17for shock isolators, 41-2-54of shock tests, 36-2-107, 39-5-63, 40-2-45 StatisLiCal enErgy analysis

using shock spectra, 39-5-85 coupling f ictors in, 38-S-i lshock and vibration fundamentalb if, 38-6-2, 41-6-10

review of panel discussions on, loss factors in, ,8-9-1139-6-151 of multipanel structiares, 37-2-99

versus standardE, 39-6-151 for vibration analysis of spatcecrait,for vibration tests, 41-4-30. 41-4-69 36-5-41

41-4-109 for prediction of dynamic environments,force and motion in, 38-1-109 38-S-5, 41-6-9shortcomings of, 37-3-1

for zero impedance shock tests, 39-5-66 Statistical shock analysisof missile on transporter, 41-2-167

Spectral analysisof gunfire, 41-4-135 Stiffness matrixfor input control of vibration tests, 37-3-53 'or beams, 38-1-11, 40-4-187of shock, 36-6-2 for columns, 40-4-187

computation of, 39-3-130Spectral analyzer joiner matrix for, 40-IR-4

optical, 36-6-98 for landing gear, 39-3-190for shock, 37-2-65 for launch vehicles, 38-3-108

for mechanical shock model, 36-2-47Spheres for piping system, 40-4-149

air blast loads on, 39-5-29 for plane stress, 41-7-124shock tests on glass, 40-5-178 for plates. 41-7-126structural analysis of, 39-5-29 reduced, 40-4-2vibration analysis of, 36-5-107 in structural analysis, 37-2-175,

40-7-177Spring mass systems for triangular elements, 41-7-123

effect of looseness on performance,41-6-39 STOL aircraft

vibration environment of, 40-6-91Sprint Missile

shock data for, 39-S-3 Stowage systemvibration data for, 39-S-7 shock tests of, 40-2-5

51

Strain Strouhal numberin beams, 36-5-77 definition of, 40-3-303in panels, 38-1-2, 39-4-108 for vortex shedding about cylinders,

41-6-31Strain gage

as berding moment transducer, 36-6-199 Structural analysis, see also Dynamic analysis,as fatigue gage, 39-2-35 Mathematical analysis, Modal analysis,microminiature amplifier for, 36-6-218 Shock analysis, and Vibration analysis

of air blast resistance structures,Stranded wire spring, 41-2-56 37-4-180

of antennas, 37-4-159, 40-1-45, 40-1-76,Stress 41-6-103

in aircraft structures, 39-3-87 of Apollo Lunar Surface Experimentin beams, 39-4-120, 40-4-1 Package (ALSEP), 38-2-50Clarkson's method for prediction of, automated, 39-3-31

39-3-88 of beams, 36-4-50, 37-4-50, 38-1-67,combination of modal, 40-4-3 39-3-1, 40-4-1, 40-4-81, 40-5-277,correlation with velocity, 40-2-38 41-6-47, 41-6-123, 41-6-133, 41-6-1 1,determination from random vibration 41-7-51

data, 40-3-1 of bridges, 4i-4-99distribution from vibration, 36-7-6 of columns, 39-3-247, 40-2-115, 4) -6-1measured versua predicted, 39-3-90 consistent mass matrices for, 40-4-1in plates,'39-4-73 digital computers in, 38-2-139, 40-4-163in scale model blast closures, 40-2-138 digital computer programs for, 36-7-45.in shells, 40-3-43 38-2-139, 40-2-105, 40-2-238of antennas, 40-1-76 using dynamic substructures, 38-2-14of electronics equipment, 39-3-118 of fixtures, 38-2-95, 39-2-158of glass structures, 40-5-183 J frames, 38-2-219of plates, 40-7-204 of grillagesof shipboard equipment, 39-1-42 by folded plate method, 40-7-216of stratified medium, 41-6-187 by orthotropic plate method, 40-7-208

Rayleigh's Principle in, 40-7-210Stress concentration under ring accelerometers, of guideways, 41-6-47

37-2-43 of hardened sites, 38-2-187of helicopters, 40-2-238

Stress-strength concept line solution method for, 38-2-157in structural reliability, 36-7-2 lu:..ped parameter method in, 38-2-D7,

39-3-153Stress-time history mechanica. mipedance in, 38-2-219

for cones, 40-4-131 of missiles, 38-2-173o1 panels. 39-3-1, 40-4-139

Stress waves o pipinpg system, 40-4-147attenuation of, 40-5-157 of plates. 36-5-46, 38-1-45, 39-3-205,mechanical anmplifications of 40-2-205 39-3-233. 39-4-73,. 39-4-81, 39-4-93,in piping, 40-5-157 40-3-99, 4C-3-119, 41-5-101,41-7-29propagation of ol radio telescope, 40-4-155

through anisotropic materials, ol recoil adapters, 39-4-25139-3-201 ol re-entry vehicles, 39-1-223

analysis of, 38-2-34 of shells, 36-5-109. 37-4-178, 38-1-87,.cylinders, 40-4-127 39-3-107. 39-5-21,, 40-3-23, 40-3-31,in frustums, 40-4-127 40-3-69, 40-3-131. 40-4-209mathematical analysis of, 40-4 -128 e1 sphei'es, 39-5-29method of characteristics for, (il submarine htlls,. 36-6-115

41-6-183 of trusses, 38-2- 1,:39-3-157,.41-6-197in shells, 38 -2-38in shock isolators, 40- 5-157 Structural Analysis Matrix Interpreti\euse of soil as isolatur, 37-4-182 SN stem (S.\MIS, computr program, 38-2-139

in solids, 41-6-1.39in structures,. 38-2-33, 41-(,-18'; Structural daUnpiiw-, see Damping

32

S.

Structural damage, see Damage of structures air blast loads on, 37-4-169, 37-4-185,38-2-177, 39-1-109, 37-4-193, 39-3-65,

Structural design 39-5-29, 40-1-31, 40-1-45, 40-2-101,loads for 41-1-35

analytical versus experimental, air blast propagation into, 37-4-18536-7-56

of machinery fourdations, 36-4-88 Structuresmini-max response problems in, 36-5-69 air blast resistant, 37-4-180viscoelastic materials in, 36-4-9, 33-3-37 air blast shock tests on, 39-5-41

aircraftStructural dynamics acoustic tests of, 37-S-43

of Apollo Lunar Surface Experimental fatigue resistance of, 40-5-49Package (ALSEP), 38-2-47 prediction of stress in, 39-3-88

philosophy of tests, 41-4-1 aircraft carrierscardboard models in studies of,

Structural equivalence 40-S-14using mechanical impedance, 36-2-63 antennas

air blast loads in, 40-2-101Stru .turai fatigue, see Fs tigue of structures design of foundation for, 40-2-103

design of masts. 40-2-104Structural members impact damping of, 39-4-1

criteria for failures of, 38-2-183 attenuation of impact on, 40-5-115dynamic response of, 38-2-157 beam-plate, 37-4-67reduction of vibration in, 38-3-71 blade-likevibration analysis of, 38-2-219 damping of, 39-4-19

response spectra for, 39-4-26Structural models vibration of, 39-4-19

of re -entry vehicles, 37-4-67 class of loadings for, 37-4-170synthesized, 38-2-201 combined environmental tests of, 40-3-211for vibration tests, 38-2-26 computer graphic techniques for, 40-4-41

cylindrical, 41-7-93Structural relationships damage from air blast, 40-1-36

in dynamic analysis, 38-2-2 damping of, 36-4-49, 36-4-75. 38-3-29,38-3-121, 38-3-133, 39-1-167, 39-4-1,

Structural reliability 39-4-19, 39-4 31, 39-4-53, 40-5-2.analysis of, 36-7-29 40-5-49, 40-5-Cl. 40-5-147, 40-5-261,Bayesian statistics in, 36-7-31 41-1-13, 41-2-105, 41-2-121

difficulties in determining, 36-7-27 deck, 40-7-218panel discussion on, 36-7-27 deckhouseof spacecraft, 36-7-1 air blast environment for, 39-1-109stress-strength concept in, 36-7-2 design criteria for, 39-1-11vibration qualification tests for, 36-7-1 degradation in, 39-2-35

differential d' placement across, 40-2-1Structural synthesis digital computers in analysis of, 37-4-171,

fundamentals of, 39-3-32 37-4-193, 40-1-61, 40-4-41dynamic analysis of, 36-5-41, 36-7-130,

Structures, see also specific types such as 37-2-173, 38-2-1, 38-2-11, 38-2-57,Aircraft structures, Bridges, Hardened sites, 39-1-107, 39-3-129, 40-1-66, 40-2-57,Protective structures, and Shipboard 40-2-123, 40-2-227, 40-3-99, 40-3-257,structures 4u-4-1, 40-4-31, 40-4-41, 40-4-47,

above-ground 40-5-183, 40-7-153, 40-7-197, 41-5-27,shock protection techniques in 41-3-75, 41-6-197, 41-7-9, 41-7-19,

37-4-213 41-7-81, 41-7-89,, 41-7-123, 41-7-131acoustic excitation of, 37-5-167 43, computer programs for, 36-C-.105,

39-3-55, 39-3-65, 40-3-51, 4. , 40-4-64, 40-7-17841-7-195 scalt models for, 40-4-89

acoustic fatigue of, 40-5-49 stiffness matrix in, 40-7-177aerospace dynamic characteristics of, 40-7-51

lesigii of, 41-6-179 dynanic response of, 38-2-157

,53

to air blast, 41-1-35 from test data, 41-7-9calculations of, 38-2-3 modal characteristics of, 39-4-33to transient loads, 41-7-19 modal effective mass of, 39-3-143

dynamic stability of, 40-2-57 modal enrichment of, 40-3-236effect of accelerometers on, 41-3-6 modal synthesis of, 40-4-25effect of phase shift on response, 41-5-22 mode shapes of, 40-4-25, 40-7-207,equivalent static loads for, 41-6-197 41-7-9externally redundant, 36-6-105 multipanel, 37-2-99failure of multi-span, 36-4-49, 38-3-139

due to acoustic excitation, 39-3-65 natural frequencies of, 38-2-209, 38-2-261,from combined environments, 39-3-67 40-4-25, 40-7-207, 41-6-75, 41-6-103,

fatigue of, 39-3-87, 40-5-49, 40-5-161 41-7-9, 41-7-21fin, 37-5-167 near resonant vibration tests, 38-2-23finite element analysis of, 41-7-123, normal modes of, 39-3-99, 40-3-49,

41-7-132 40-7-165, 41-6-103fixed-base natural frequencies of, 38-2-209, optimization of, 39-1-63

38-2-263 parametric excitation of, 40-2-57flutter of, 39-3-171, 40-5-235, 41-7-109 prediction of responsefragility of, 41-5-129 to blast of weapons, 40-2-234frame scale models for, 40-4-89

air blast on, 38-2-177 pyrotechnic shock in, 40-2-21, 41-5-4,effect of liquid propellant explosions 41-5-9

on, 38-2-179 radio telescope, 40-4-158mathematical analysis of, 38-2-183, reduction of vibration in, 38-3-57

40-7-172mathematical models of, 38-2-181 Structures

free-free, 40-4-31 reliability of warhead, 39-1-177future requirements for, 41-2-1 responsegalloping of, 39-3-171 to acoustic excitation, 39-3-55,glass 40-3-57

analysis of stress in, 40-5-183 to air blast, 37-4-169, 40-1-31,attenuation of shock in, 40-5-175 40-2-101

for helicopters, 40-1-161, 40-2-227, to blast from weapons, 40-1-61,41-7-131 40-2-227, 41-1-195

gunfire vibration of, 41-4-195 to blast waves, 40-2-229, 41-5-17highway guard-rail to combined environments, 39-3-65

energy absorption of, 40-5-115 to dynamic excitation, 38-3-71honeycomb to moving loads, 40-3-99, 40-4-47

pyrotechnic shock loads in, 37-4-15 to transient loads, 41-7-22response to half sine pulse, 40-4-74 to underwater explosions, 40-1-15.

ideal size of, 36-7-32 40-7-197, 41-7-89identification of complex, 38-2-23 upper and lower bounds, 37-4-173impact damped, 39-4-1 rigid plastic, 37-4-75inertial rei,ýrence unit, 40-3-260 Ritz averaging method for, 40-5-262interaction of control system wit.i, with rotating elements, 40-4-41

40-3-205 safety factors for, 40-3-93interaction of noise with, 36-5-48 scale modellinear elastic, 36-6-131 dynamic similarity criteria for,load restraint for, 40-3-221 39-3-40mathematical analysis of, 38-3-121, vibration tests of, 40-4-89

39-3-55, 39-3-172, 40-3-257 shellmathematical models of, 36-6-131, air blast loads on, 37-4 -177

39-3-57, 41-7-19 failure of, 37-4-180mechanical impedance of, 38-2-285, modal survey of, 38-1-89

38-3-35, 39-3-143, 39-1-123, 40-3-236, shock in, 39-5..,29, 40-2-1, 41-6-7540-7-51 shock analysis of, 36-6-131, 40-2-31,

missile 40-7-185, 41-7-89response to high impact, 37-1-115 shock loads on, 41-b-187

modal analysis of, 39-3-55, 39-3-99 shock measurement on, 40-2-3flow charts for, 41-7-12 shock response of, 40-2-10

54

I'

shock wave propagation in, 36-2-66, isolated modules for, 38-3-24340-2-21 replenishment of Polaris missiles for,

shock spectra for, 40-4-17 36-7-145shipboard shock in, 36-1-4, 39-1-93, 39-S-41,

dynamic analysis of, 40-7-197 41-S-49failure criteria for, 39-1-107 shock hardness of, 38-3-243, 39-1-93shock criteria for, 39-1-39 shock test facilities for, 39-1-73shock hardness of, 39-1-107 silencing, 38-3-243

simulation of capsize of, 37-4-193 USS George Washington, 36-6-115on single non-rigid supports, 38-2-261 velocity spectra for bulkheads of, 39-S-44skin-stringer

analysis of energy in, 39-4-35 Subsystemsnormal mode analysis of, 39-4-31 dynamic analysis of, 38-2-67

slosh modes of, 41-7-181 modal coupling of, 39-3-99snap buckling of, 41-6-89spacecraft Surging

safety factors for, 40-3-91 in hydraulic systems, 41-5-143test program for, 39-2-147 in shock isolators, 40-5-217

spheresdynamic analysis of, 41-7-91 Suspension systems, see Isolation systems

sources of shock in, 40-2-22static vs dynamic loads in, 41-6-197 SUU 36 munitions dispenserstatistical energy analysis of, 37-2-99 captive flight of, 40-6-9stiffened plate, 41-2-105stress analysis of, 41-6-191 SUU-38 munitions dispenserstress wave propagation in., - 2-4Z, shock tests of, 41-5-93

41-6-187submerged SV-5D re-entry vehicle, 36-3-83, 36-3-113

pressure loads on, 40-7-199shock analysis of, 40-7-197 Sweep rateshock loads in, 41-7-89 effect on resonant systems, 4t-4-95

sysicu identification of, 38-2-23torsional and translational vibration of, Symmetry

39-3-171 in structural analysis, 38-2-6transmission of loads through, 37-4-65,

38-2-231 Synthesisunderground in designing isolators, 39-4-186

shock isolation systems for, 39-4-199vehicleenergy absorption in, 39-4-227 System identification

in design of shock isolators, 39-4-188vibra-acoustic transfer function for, moment technique for, 38-2-119

40-3-63 of stroictures, 38-2-23vibration of, 38-1-99, 39-4-19, 40-4-41, theory of, 38-2-24, 38-2-121

40-7-207, 41-6-1, 41-6-47, 41-6-103, vibration tests for, 38-2-27, 38-2-12041-7-19, 41-7-131, 4L7-195 identification of

vibration analysis of, 36-5-41, 39-3-55, for digitally simulated models,40-4-25, 40-5-277, 41-6-197 38-2-119

vibration tests of, 38-1-115, 39-4-41, from random vibration input, 38-2-12240-4-89, 41-7-95 from sinusoidal vibration input,

fixtures for, 39-2-157, 40-3-221 38-2s-126with viscoelastic materials, 39-4-117yielding, 36-2-10, 40-4-81

Systems, see also specific systems such asSubmarines Multi-degree-of-freedom systems and

damage from underwater explosions, Isolation systems39-1-99 for analysis of vibration data, 36-6-47,

foundations for machinery in, 39-1-123 37-2-109hulls for dynamic phase plotting, 37-2-77

Fourier spectra for, 39-S-44 elastic-plastic, 37-4-73structural analysis, 36-6-115 equipment-foundation, 38-2-210

55

for generating and measuring combined transonic wind tunnel as, 37-3-123environments, 40-3-297 for tri-axial vibration, 41-3-121

lumped parameter, 39-3-153 for wheel/rail dynamic studies, 41-3-127modal coupling of, 39-3-100nonconservative, 41-7-141 Test fixtures, see also fixture

for combined acceleration and vibrationT tests, 40-3-293

design criteria for, 39-2-177

TALOS missileflight vibration of, 41-4-189 Test programs

for missile environments, 37-2-117,Tanks 39-2-195

gun recoil on, 41-3-187 for verifying integrity of spacecraftstructures, 39-2-147

TAT/Agena-D launch vehiclenoise measurements on, 36-7-89 Test specimens

equivalence of, 36-2-63Temperature protection of, 39-2-11

effecton damping, 38-3-156, 41-2-125, Test system

41-2-145 definition of, 37-3-77on high polymer viscoelastic materials,

38-3-175 Test techniquesignition shock versus, 37-2-168 for simulation of earthquakes, 41-3-116

Test criteria. Tests, see also specific types such as Acousticdevelopment of, 39-2-196 tests, Dynamic tests, Environmental tests,

Shock tests, Vibration tests

Test facilities, see also Acoustic test facilities, combined environment for shipboardand Shock test facilities equipment, 40-2-51

air drop, 41-3-223 cross-country, 41-2-163for aircraft seat crashworthiness,41-3-133 of gun recoil on tanks, 41-3-187for combined environmental tests, handling of Polaris missiles, 36-7-147

37-3-175, 40-2-51, 40-3-293 laboratory vs field, 39-2-35for cross-country tests of vehicles, of machinery foundations, 36-4-88

41-3-215 in shock tubes, 39-5-58design of, 40-2-52, 40-5-245, 41-3-119 simultaneous linear and angulardisplacement amplifier as, 41-3-149 accelerations, 41-3-155clectrohydraulic vibration exciters as,

41-3-109 Thunderpipe tests, 36-5-2for elements of shock isolators, 40-5-245for explosive weapons, 40-3-201 Time-sharing computersfor fuzes, 41-3-155 calibration of vibration exciters using,for gas bearings, 38-3-222 36-6-183for high rate loads on shock isolators,

40-5-245 Timoshenko beamsfor impact tests of isotope fuels, 41-3-195 frequency parameters for, 39-3-50for large displacements, 41-3-149for launch environments of missiles, 40-6-1 Tipofffor launch environments of spacecraft, mathematical analysis of, 41-6-224

39-2-23, 40-3-183LaunL "hase Simulator, 40-3-183 Tipoverfor la', .-hing and recovering projectiles, of shipping containers, 39-6-65

41-3, 175for low pressure acoustic environments, Titan launch vehicle

41-3-207 scale models offor noise reduction studies in spacecraft, aerodynamic noise test on, 37 203

40-4-105 wind tunnel acoustic data on,for recoil simulation, 41-3-187 37-7-221resonant beam, 39-2-72 wind tunnel tests of, 37-3-121

56

wind-induced vibration tests of, 36-7-81 for measurement ofbending moment, 36-6-199

TNT egg damage, 41-3-11for simulation of propellant explosions, force, 36-6-203

38-2-179 ground shock, 40-7-136of shock, 37-2-29

Torpedoes vibration, 40-7-244underwater explosion tests on, 40-1-9 microminiature amplifiers for, 36-6-215

response to environment, 40-7-1Torsional natural frequencies seismic, 40-7-123

upper and lower bounds for shafts,40-4-164 sonarfinite element analysis of, 41-1-21

Torsional shock mathematical models for, 36-2-33,design of spacecraft for, 36-7-63 36-2-39prediction of response to, 36-7-67 optimization of design, 36-2-41

response to shock, 36-2-31, 37-1-67Torsional vibration shock hardening of, 37-1-65

coupled bending and, 36-6-121 shock tests on, 37-1-63of missiles, 40-4-163 vibration requirements for, 37-2-51response spectra for, 36-7-65of shells, 36-5-115 Transfer functionc,

for active vibration isolation systems,Total impulse 39-4-170

upper and lower bounds from air blast, development of, 38-2-11537-4-173 Fourier transform for, 38-1-18

for linear systems, 39-3-74TOW missile for lumped parameter systems, 38-2-109

effect on UH-1B helicopter, 40-1-64 for microphones, 37-2-9transportation environment for, 37-7-39 for nonlinear vibration isolation systems,

40-5-27Towers for prediction of flight vibration, 36-5-85

response to ground shock, 41-6-75 for single-degree-of-freedom systems.TDYNE computer program for, 39-3-75

41-6-82 for two-degree-of-freedom systems,40-2-216

Tracked air cushion vehicles vibra-acoustic, 40-3-63response of guideway structures to,

40-4-47 Transf( r impedance, see Mechanical impedance

Tracked vehicles Transfer matrix method. 38-2-157cross-country tests of, 41-2-163simulated road tests of, 41-3-124 Transforms, see Fourier transformsvibration isolation for, 41-2-159

Transient dataTracking filter to improve mathematical models, 36-5-1

for averaging, 36-3-142Transient loads, see Shock loads

Transducers, see also Accelerometers andForce transducers Transient response, see Response

calibration Transient testsaccelerometers, 41-3-1 T rans it ofs sby comparison, 36-6-193 for fragility of systems. 41-5121laser for, 37-2-1 Transients

compensation for distortion, 40-7-123 simulation with i lbration tests. 39- 3-207curve fitting technique for, 40-7-124

conceptual models of, 41-3-91 Transmissibilityenergy processing within, 41-3-92 of active vibration isola.ors, 371-6- 'U.errors in, 37-2-29 37-6-45factors influencing response, 40-7-2 effect of looseness in mechanical svstenisinfluence of environment on, 40-7-3 on, 41-6-42

57

of foam materials, 38-3-193 Two mass systemsof foundations, 39-1-123 perturbation analysis for, 40-7-180of isolators with nonlinear damping,

40-5-22 Uof missile suspension systems, 39-6-60of pneumatic active isolators, 40-7-241 UH-1 helicopterfor railroad cars, 40-6-112 acoustic environment on, 37-S-73of shock isolated floors, 41-5-157 distribution of induced velocity on, 37-6-7of shock isolators, 40-7-234, 41-5-157 environment for on-board weapons,of two stage isolators, 40-7-238 40-S-47of vibration isolators, 37-3-167, 40-5-28, response to TOW missile overpressures,

40-7-236 40-1-64of viscoelastic isolators, 38-3-40 vibration of, 37-S-73

weapons blast effects on structure of,Transmission matrices 40-1-62

definition of, 41-7-61derivation from continuum theory, 41-7-76 Underground explosionspower series expension of, 41-7-73 acceleration-time history from, 41-6-80theory of, 41-6-133 response of tower to, 41-6-75

rransportation environments Underground structures, see Hardened sitescriteria for, 40-6-85 and silosdata for, 37-6-19data acquisition for, 36-6-163, 40-7-45 Underwater explosionsdata analysis of, 37-7-19, 39-6-36 acoustic wave-shell interaction theoryinstrumentation for, 37-7-19, 37-7-40, for, 40-1-15

39-6-31 airblast compared with, 36-1-13, 37-1-29for loose cargo on trucks, 39-6-18 cavitation in, 41-S-49on M-151 Jeep, 37-7-39 correlation of velocity change with forcingfor packages, 39-6-19 function for, 40-1-9of railroad cars, 39-6-47, 40-6-91 damagerecorders for measurewent of, 36-6-163, nlalysis of, 37-4-71

36-6-173, 39-6-19, 40 -6-99, 40-7-45 to shipboard equipment, 39-1-96during rough bandling, 37-7-1 to submarine equipment, 39-1-99simulation of, 39-6-15, 41-3-119, 41-3-215 design of shipboard equipment for,for spacecraft, 37-7-19 39-1-33, 39-1-65for STOL aircraft, 40-6-91 dip in shock spectrum for, 39-S-41,survey of, 37-7-1 40-7-1F,5for trucks, 39-6-31 effect on humans, 41-2-5

environment, 39-1-65, 37-2-30, 39-1-4,Traveling waves. 40-7-99

analysis N, 35-2-66 eqiAvalent static pressure from, 40-7-198instrumentation Lr, 40-1-10

Trucks pressure data from, 40-1-10transportation environments for, 37-7-1, pressure-1,ime history for, 39-1-4, 40-7-99

37-7-19, 3a-6-3i response toof rulls, 38-3-244, 40-7-185, 41-S-49

Truncated cones oi cylindricl shells, 40-1-22response to strain pulse, 40-44130 of shipboard equipment, 39-1-55,

39-S-.41Trusses of ships, 36-1-13, 37-1-1, 39-1-1

dynamic analysis of, 38-2-61, 39-3-157, of structures, 40-1-15, 40.7-197,41-6-199 41-7-89

RoyO Canadin Navy criteria for,Tuning 40-S-30

effects on modal damping, 37-6-60 shock data from, 40-1-11shock test facility for, 37-4-137

Twanig tcst testson antenna masts, 40-2-108 on decks, 40-1-5

i

on scale model captive air spacecraft, distribution of41-1-6 in CH-47 helicopter, 37-6-8

on ships, 39-1-67, 41-1-1 in UH-1 helicopter, 37-6-7on torpedoes, 40-1-9 measurements of human head impact,

velocity change from, 40-1-9 39-5-93velocity response spectra for, 41-S-58 recorder to measure impact, 36-6-173velocity time-history for hulls, 41-S-52

Velocity changeUnit impulse function correlation with underwater explosion

properties of, 38-2-107 forcing function, 40-1-9

Upstage test vehicle Velocity gagesacoustic test of, 41-6-19 for measurement of ground shock,40-7-133flight vibration of, 41-6-9mudal density for, 41-6-15 Velocity responsesources of vibration for, 41-6-24 in selection of normal modes, 40-7-169

U. S. Army Combat Development Command Velocity spectramission of, 39-6-1 for bulkheads of submarines, 39-S-44

cavitation effects on, 41-8-58V as descriptor of shock, 40-2-32

for equipment in submarines, 39-S-48I Vacuumdamping in, 36-4-75 Velocity-time history

for spherical structures, 41-7-98Vacuum spring

as a shock and vibration isolator, 36-7-103 Velocity transfer functionssimulation on analog computer, 36-7-107 for lumped parameter systems, 38-2-111

Vacuum tests Vibra-acoustic environmentcombined with acoustic tests, 37-5-175 criteria for simulation of, 37-5-1

of external aircraft stores, 41-S-33Vacuum tube launchers

for shock tests, 40-2-193 Vibrating beam test methodfor damping in materials, 40-5-106

Vansair blast loads on, 37-4-194 Vibration, see also specific types such as

Flight vibration, Random vibration, andVariation spectra, 36-6-9 Shipboard vibration

and acceleration, 36-3-119Vehicles acoustically induced

active isolation of, 38-3-317 flight vibration vs, 37-5-160crash environment, 39-4-231 in aerospace vehicles, 37-5-2crashworthiness of, 39-4-227 aircraft, 37-7-35, 41-4-133cross-country tests of, 41-3-215 acceleration spectral density curvescrushable shock isolators for, 39-4-231 for, 40-6-49dynamic tests of, 41-3-127 from gunfire, 40-6-27response of bridges to, 41-4-102 from motion of towed cables,scale model 41-6-61

impact of, 39-4-227 power spectral density for STOL,prediction of response to impact for, 40-6-96

39-4-242 sources of, 37-S-97stabilization system for, 38-3-317 versus airspeed, 37-S-100

on aircraft carriers, 40-S-13Velocity of aircraft landing gear, 39-3-179

correlation of stress with, 40-2-38 amplitude by optical method, 37-2-13as criteria for asymptotic method for determining

measurement of wear, 41-4-53 response to, 41-4-128severity of shock, 40-2-23 automated recorder for, 40-7-225severity of vibration, 40-2 -?'7, 41-4-53 of automobiles, 40-4-94

59

II

of avionics equipment, 40-6-37, 40-8-63 fixtures for amplification of, 39-2-221,acceleration spectral density curves 41-3-149

for, 40-6-52 flow-inducedof beams, 38-3-13, 39-3-49, 39-4-53, in cylinders, 40-3-304, 41-6-31

40-2-40, 40-4-47, 40-5-277, 41-6-133, of shafts, 39-2-21741-6-163 of structures, 41-7-205

identification of damping models in, of fluids, 41-7-18136-4-65 of grillages for ships, 40-7-207

with moving point loads, 41-6-49 of guideways, 41-6-48of blade-like structures, .9-4-19 in helicopters, 37-6-1, 37-6-7, 39-3-17,of bearings, 38-3-221, 40-3-275 40-4-43, 41-4-195, 41-4-209, 41-4-221of bombs, 41-S-34 high-speed analyzer for, 36-6-49of box cars, 41-4-155 of hul.-*of captive airborne weapons, 37-S-107, code for measurements ot, 40-7-243

39-6-78, 39-S-15 characteristics of, 38-S-1challenging problems in, 36-2-1 mathematical model for, 38-1-126of columns, 39-3-247 as indicator of wear, 41-4-51complexity of, 36-2-5 of launch vehicles, 39-6-135criteria of loose mechanical systems, 41-6-39

for helicopters, 40-5-194 mathematical analysis offor severity, 40-2-27 forced, 38-3-95for spacecraft, 37-7-202 torsional and translational, 39-3-172

damage potential of, 41-3-43 of mechanical systems, 39-3-73damping in missiles, 38-2-74, 39-S-1, 39-2-196

of elastically-rigid bodies, 3$-7-135 multi-axis tests for, 41-4-34in helicopters, 41-2-141 multi-modal, 36-4-49in pipes, 39-1-143 of munitions dispenser, 41-S-37in plates, 39-4-63, 40-5-93 use of Myklestad's method for, 41-7-109in structutres, 36-4-49, 38-3-1, of nonconservative systems, 41-7-141

38-3-57, 38-3-71, 39-4-1, 39-4-19, nonlinear39-4-31, 40-5-49, 40-5-61 of panels, 39-3-191

of deck structures, 40-1-2, 40-7-218 of spring-mass systems, 41-6-39as a diagnostic tool for shock design, of two-degree-of-freedom systems,

41-4-119 39-3-161in multipanel structures, 37-2-99 of one-dimensional continuum, 41-7-61of ducts, 40-5-71 in packages, 37-3-16effects of panels, 3U-3-1, 39-3-13, 39-3-191

on fatigue damage to structures, parametric, 39-3-20536-5-17 physiological effects from, 41-2-16

on humans, 41-2-13 of piping, 39-1-143, 39-1-155, 40-4-197electrically generated in elastomers, of plates, 38-1-37, 38-1-45, 39-3-197,

39-2-1 39-3-206, 39-4-63, 39-4-73, 39-4-81,of electronic equipment, 37-3-7 39-4-93, 40-5-93, 41-7-29, 41-7-37environment prediction

for captive .Jrborne weapons, 39-8-16 for aerospace structures, 36-5-41,of high speed trains, 40-6-91 36-5-85, 36-5-97, 38-S 5, 39-6-77,of STOL aircraft, 40-6-91 39-6-119, 40-6-67, 41-6-9, 41-7-1,

of equipment 41-7-195in aircraft, 37-S-103 far airborrie equipment, 38-S-5from gunfire, 40-6-27 direct stiffness method for, 37-6-20

equivalence of for helicpters, 37-6-5, 37-6-19energy summation in, 40-3-1?9 for missiles, 39-6-77measured and predicted, 36-5-90 mobility in, 37-6-27shock with, 41-4-124 for propellant storaie module shelf,

failures of spacecraft from, 40-3-9 41-7-196feedback control signal averaging of, regression analysis technique for,

36-3-139 39-6-122of fiber-reinforced composite materials, statistical energy method for,

39-4-81, 39-4-93 36-5-41, 38-S-5, 41-6-9

'i0

of propellant, 41-7-169 Vibration

of propellant storage module of structures, 37-2-99, 38-1-99, 38-2-57,sources of, 41-7-195 39-3-171, 39-4-19, 39-4-31, 40-4-41,

proposed standard for data analysis of, 40-4-155, 40-5-49, 40-7-207, 40-S-13,39-6-1 4i-6-1, 41-6-47, 41-6-103, 41-7-19,

of radio telescopes, 40-4-155 41-7-131, 41-7-205of railroad cars, 40-6-95, 40-6-109, as a substitute for acoustic tests, 38-1-115,

41-4-141 40-3-252reduction of systems with self synchronized rotors,

by active isolators, 37-6-66 41-6-159in helicopters, 36-7-113, 37-6-5, techniques for data analysis of, 36-6-47

37-6-49, 37-6-63, 40-5-191, torsional and translational, 39-3-17141-1-141 transient

with viscoelastic materials, 36-4-9, of multi degree of freedom systems,36-4-49, 37-3-19, 38-3-1, 38-3-13, 40-4-1738-3-29, 38-3-37, 38-3-57, for simulation of engine cutoff,38-3-71, 38-3-175, 39-4-19, 37-4-5939-4-31, 39-4-53, 39-4-63, 39-4-73, for simulation of nuclear detonation40-5-1, 40-5-37, 40-5-49, 40-5-93, shock, 41-5-16741-5-105, 41-5-121, 41-5-141 transmission

response in foundations, 38-S-19, 39-1-123of bearings, 40-3-275 from helicopter rotors, 37-6-5of bridges, 41-4-99 mechanical admittance for calculating,of ducts, 40-5-61 38-2-231effect of sinusoidal sweep on, 38-1-134 by polyurithande-isolator, 40-5-288of focal isolation system, 38-3-265 through structure, 39-6-135of helicopters, 41-7-131 of trucks, 37-7-28,,39-6-31of hydrophones, 37-2-52 of two degree of freedom systems,of plates, 38-1-37, 38-1-45, 39-3-197, 39-3-161, 39-3-171

39-3-206, 39-4-1.4. 39-4-81, walking, 40-4-16039-4-93, 40-5-93, 41-7-29, 41-7-37 of weapons

of printed circuit boards to, 38-S-5, on aircraft, 40-S-47, 41-S-3340-3-111 on helicopters, 40-S-47

of shells, 39-1-155, 39-3-107, 40-3-69,40-3-131 Vibration absorbers

of River patrol boat, 37-7-205 active, 38-3-235of rocket motors, 41-6-115 analysis of synchronous, 37-6-49of rods, 40-2-39 for attenuation of brake squeal, 39-3-186rotor-induced, 36-7-113 damping using, 37-6-57, 40-5-147of rotors, 41-6-159 definition of. 38-3-235of scale models, 39-3-39 dynamic mounting requirements for,self-excited, 40-3-303, 41-4-194, 41-6-31 36-7-122sensitivity of humans to, 41-2-13 flight tebts of, 40-5-199of shafts in analysis of missile bending, gyroscopes as synchronous, 37-6-49

36-2-169 for helicopters, 36-7-113, 37-6-23,with NASTRAN analysis, 41-6-203 40-5-191

of shells, 39-1-155, 39-3-107, 40-3-69, mathematical analysis of, 39-4-261,40-3-131 41-7-135

in ships, 38-1-125, 39-S-55, 40-S-13 performance of, 36-7-116, 38-3-237simulation of, 41-4-29 for spacecraft antennas, 40-5-148

by acoustic tests, 37-5-1, 37-5-153 for transient shock loads, 39-4-261analog computers in, 40-S-15 tuning of, 39-4-265, 40 ;-191vs flight of captive missiles,

39-6-86 Vibration analysis, see also Dynamic analysis,gunfi. e induced, 41-4-37 Mathematical anal•,•is, Modal analysis,during launch, 39-2-23 Shock analysis, and Sti ,ctural analysisshort burs.:;t 4W,-$-267 of aircraft braking f,,cp, 39-3-185

of sonar transducers, 37-2-51 of beams, 38-3-13of spacecraft, 37-7-176, 40-3-179 61 coluryns, 39-3-248stress distribution from, 36-7-6 co-quad, 37-2-77

61

of cross correlation effects on test presentation of, 39-6-7results, 39-2-51 scaling of, 36-5-85

of cyl~nders, 36-5-107 for spacecraft, 37-7-173digital computers in, 38-3-295 in structural analysis, 38-2-271of ducts, 40-5-71of eigenvector errors, 39-3-102 Vibration distributionflowgraphs in, 38-1-99 measurement of, 37-2-102of gas turbines for helicopters, 39-3-17General bending response code for, Vibration equivalence

•9-S-60 monograph on, 39-2-189Hamilton's principle in, 39-4-81, 39-4-93for helicopters, 37-6-7, 41-7-131 Vibration excitershybrid computers in, 41-7-131 air pulser as, 41-S-1of inertial reference units, 40-3-257 force-time history for, 41-S-11isolation systems, 37-6-44, 38-3-285 amplification of output of, 39-2-221,of landing gear, 39-3-179 4: ! 49of launch vehicles, 38-3-95 calibration ofof liquid squeeze-films, 39-2-78 by reciprocity method, 36-6-185for mini-max response, 36-5-69 with a time-sharing computer,of nuclear reactors, 36-1-45 36-6-183of panels, 39-3-191 for calibration of accelerometers, 41-3-3of plates, 39-3-197 for combined environment test facilities,of propellant quantity gauge system, 40-2-51

41-7-182 cross-coupling between, 37-3-155of propulsion systems for ships, 39-S-55 displacement limiting device for, 39-2-11of railroad cars, 39-6-52 driving by prerecorded tapes, 37-3-152of resonant fixtures, 39-2-221 electrodynamicRitz method in, 39-4-81, 39-4-93 control techniques for, 40-2-157,of self synchronization of rotors, 41-6-160 41-4-183of shafts, 39-2-217, 41-6-203 protection of test specimens on,of shells, 39-3-107 39-2-11of spacecraft, 36-5-41, 41-4-128 shock testing by, 36-2-17, 39-5-67,of specifications for random vibration, 39-5-83, 40-2-157, 40-2-173,

38-2-52 40-7-93, 41-7-149of spheres, 36-5-107 for simulation of control forces ofof stabilization systems for vehicles, launch vehicle, 40-3-206

38-3-319 electrohydraulic, 41-3-109statistical energy method for, 36-5-41 control system for, 39-2-26of structures, 36-5-41, 38-2-23, 39-3-39, on launch phase simulator, 36-3-119,

41-6-197, 41-7-131 39-2-23survey of techniques for, 41-4-1 flexure- guided, 39- 2-159of synchronous vibration absorbers, for launch phase simulator, 36-3-119,

37-6-49 37-3-182, 39-2-23of systems with dynamic coupling, 36-7-135 multipleof traveling waveb, 36-2-66 control stabilization of, 37-3-155of vibration absorber for spacecraft random vibration tests with, 39-2-51

antenna, 40-5-148 servo-hydraulicof viscoelastic dampers, 38-3-72 as shock test facility, 40-2-243of wear in machinery, 41-4-65 for shipboard tests, 38-S-1, 41-S-1

variable resonant, 38-S-1Vibration data

analysis of, 40-7-115 Vibration isolationfacility for, 36-6-47 active systems for, 37-6-29hybrid computer for, 36-6-55 displacement mobility ,f, 39-4-174one-third octave vs narrow filter dvnamic response of, 39-4-166

bandwidth, 41-S-30 performance t-I's of, 39-4-163determination of stress from, 40-3-1 response to shock, 37-6-69modal damping loss factor from, 38-2-289 stability of, 39-4-165modal response suppression factor from, transfer functions for, 39-4-170

38-2-271 vehicles, 38-3-317

62

active-passive systems for, 3.-6-39 on avionics equipm-nt, 40-S-63in aircraft, 39-4-157 data analysis for, 37-S-74of avionic components, 40-5-285 on captive airborne weapons, 37-S-107,computer programs for, 38-3-295 40-S-47, 39-1-195, 39-6-93electrohydraulic systems for, 37-6-32, on engines, 37-2-118

39-4-141 on freight cars, 41-4-141local systems for, 38-3-263 on helicopters, 37-S-73, 41-4-209,in helicopters, 37-6-29, 37-6-39, 38-3-263 41-4-221hybrid systems, 37-6-44 on high speed trains (Metroliner),40-6-93hypothesized gyroscope for, 38-R-289 instrumentation for, 37-2-118, 37-S-74,on M-754 tracked vehicle, 41-2-159 37-S-95, 40-7-45, 40-7-225nonlinear systems for damping in, 40-5-19 lasers fo,. 37-2-1

frequency response for, 40-5-26 holography for, 39-2-41, 40-7-33resonance characteristics of, 40-5-31 on M-151 (jeep), 37-7-39transfer functions of, 40-5-27 on missiles, 37-7-93

parametric analysis of systems for, on munitions dispenser, 40-6-2138-3-235 on printed circuit boards, 38-S-5, 40-3-111

of ro6ad vehicles, 38-3-317 probe for, 40-7-29of systems with relaxation damping, on River patrol boats, 37-7-205

40-5-205 on ships, 40-7-231on sonar transducers, 37-2-51

Vibration isolators, see also Active vibration on STOL aircrift, 40-6-95isolators and Shock isolators on trucks, 37-7-21, 39-6-31

active, 38-3-317, 39-4-141, 39-4-157 on vehicles, 40-7-48design criteria for, 39-4-159 velocity transducers for, 40-7-244development of, 39-4-160

active-passive, 37-6-76 Vibration modes, see Modal analysisfor avionics equipment, 40-6-37

polyurethane foams as, 40-5-285 Vibration response, 3ee Responsefor combined shock and vibration isolation, Vibration spectra

40-7-233 for antennas, 40-5-4effects on safe levels for rotor bearings, for hiters, 41-4-2

40-3-290 for helicopters, 41-4-228electrohydraulic, 39-4-141 for missiles, 41-4-190

characteristics of, 39-4-146 for spacecraft, 36-7-97mathematical analysis of, 39-4-143 Vibration tests

force-deflection characteristics for, acceleration limiting in, 41-4-11740-7-236 . acoustically-induced, 36-3-39

frequency 'edponse of, 40-6-40 of aircraft equipment, 41-S-25for gyroscope, 38-3-285 allowable cross-motion in, 40-6-64for helicopters, 37-6-39, 37-6-69, 38-3-263 for Apollo lunar surface experiment,hysteresis loop characteristics for, 38-2-52

40-5-21 areas of controversy on equivalence of,nonlinear 39-2-188

performance of, 40-5-19 assembly-level, 36-3-27transmissibility for, 40-5-22 control of, 37-3-49

open cell foams as, 40-5-291 data analysis for, 37-5-129perfomance of conventional, 40-7-236 of launch vehicles, 37-5-117polyurethane, 40-5-286 of avionics equipment, 40-S-63, 40-6-32for protection of humans, 39-4-157 qualification levels for components,relaxation damp! ng for, 40-5-203 40-S-76response to shipboard shock, 40-7-236 of bearings, 40-3-280shim spring as, 37-3-163 of bombs, 41-S-33for shipboard equipment, 40-7-233 of bridges, 41-4-101static load characteristics of, 40-3-287 of calibration propellant storage modules,vacuum spring as, 36-7-103 41-7-200

for captive flight environment,Vibration measurements, see also Vibration 39-1-212, 40-S-48

data combined with temperature and humidity,on aircraft, 37-7-28, 37-S-95 36-6-83

63

h | • . .. . . .. ... .... . . . . . .. . .... .. . . . . .. .. . . . . . .. .. ... . . . . . .... . .j.. .

compared with of launch vehicles, 36-7-80, 37-2-109,acoustic tests, 37-3-7, 37-3-21 39-2-135field data, 37-3-1 of scale models of, 38-2-25, 41-7-171flight vibration, 37-7-173 levels for, 39-2-153vibration analysis, 36-1-45 of a LOX vent duct, 36-3-91

comparison of fatigue damage potential mechanical impedance in, 38-2-234,of, 40-3-153 41-4-109

of components for mechanical signature analysis,problems in, 37-5-4 36-6-73, 414-174qualification levels for, !"7-7-176 of missiles, 39-2-197, 40-3-268

of computer programmt R A7-3-78 for modal surveys of aircraft, 36-3-55control of monitoring of, 36-3-1

averaging techniques for, 36-3-139, multimodal fixtures for, 40-3-231,38-1-12037-3-47, 37-3-75 multiple-axis, 39-2-23, 41-3-119

assembly-level, 37-349 with multiple vibration exciters, 36-3-55,base-strain in accelerometers, 36-3-71, 36-3-91, 38-1-115

37-2-48 control techniques for, 36-3-147,for multiple vibration exciters, 41-4-183

36-3-147, 41-4-183 importance of cross correlation in,criteria, 41-S-25 39-2-51

for captive airborne weapons, 39-S-15 of large structures, 38-1-115comparison of flight data with, 37-3-7 multi-point control of, 37-3-75, 41-4-33for launch vehicles, 37-5-119 of munitions dispensers, 41-S-37

design for shock, 41-4-119 wind tunnel vs laboratory excitationfor detecting loose parts, 36-6-73, for, 40-6-22

41-4-173 near resonantdetermination of modal mass from, for identification of complex

38-2-271 structures, 38-2-23determination of bond strength of liquid on nuclear reactors, 36-1-50

squeeze-films from, 39-2-80 of oil squeeze beari.ng damper, 38-3-48of ducts, 40-5-66, 40-5-75, 40-5-88 outer loop control for, 41-4-183dynamic analysis of systems for, 41-4-79 overload protection during, 39- 2-11for earthquakes, 41-3-109 phase plotting for, 37-2-77of elastomers, 39-2-4 of plates, 39-2-197, 39-3-210, 39-4-83of electronic components, 40-3-111 practical approach to, 37-3-4of electronic equipment, 37-3-14, probabilistic approach to, 41-S-25

41-4-122 pulsed random, 40-3-267energy summation in, 40-3-151 control system for, 40-3-270equivalence of, 37-3-1, 39-2-187 analysis of data for, 40-3-273of explosive weapons, 40-3-196 as quality assurance tool, 36-6-73,for fixed-base natural frequencies, 41-4-173

38-2-209, 38-2-261 realism of, 37-3-2, 39-2-195, 41-4-29fixtures for, 36-3-101, 38-1-120, 39-3-31, reduction of spectrum levels for,41-S-27

39-2-72, 39-2-157, 39-2-175, 39-3-192, of re-entry vehicles, 36-3-11340-3-231 response limiting in control of, 41-4-183

flexure guides as fixtures for, 39-2-157 response outside of sweep range during,focal isolation systems, 38-3-268 38-1-136for fragility of systems, 41-5-123 ring accelerometers for, 37-2-48of gas-bearing machinery, 38-3-221 of road vehicles, 41-3-124on helicopters, 36-3-71, 39-3-23 of rocket engines, 37-2-129high acceleration, 39-2-71 of scale model hulls, 41-S-3high-force of segmented shells, 38-1-87

control of, 37-3-139 of shafts, 41-6-207data analysis for, 37-3-143 sinusoidal pulse technique for, 38-3-207

on humans, 41-2-13 sinusoidal sweep in, 36-2-102, 38-1-133,on immersed solids, 40-IR-17 38-3-207of impact damped structures, 39-4-4 for slosh modes in propellant tanks,instrumentation for, 41-3-114 41-7-169of isolation systems, 38-3-268, 40-6-40 of spacecraft, 36-3-27, 37-3-21, 38-2-151,of isolators, 40-6-39 40-3-9, 40-3-183

64

criteria for, 37-5-156 strength characteristics of joints with,fixtures for, 40-3-231 39-4-117

procedures for, 39-2-110 for structural damping, 36-4-9, 36-4-25,programs for, 37-5-109, 37-5-154 36-4-49, 38-3-121, 38-3-139qualification levels for, 37-7-175 in structural design, 36-4-9, 38-3-37of scale models of, 40-3-243 for tuned damping, 38-3-151

specifications for, 36-3-1, 38-1-109, vibration parameters for, 38-3-7540-6-42, 40-6-62, 41-4-30, 41-4-69

of structures, 38-1-115, 39-4-41, 41-7-195 Vortex sheddingof scale models of, 40-4-89 for cylinders, 40-3-303, 41-6-31

survey of techniques for, 41-4-1 for towed shafts, 39-2-218sweep rate effects in, 41-4-95for system identification, 38-2-27 Wtracking filters in, 40-6-64of viscoelastic damper, 38-3-76 Walleye missileof viscoelastic foam materials, 38-3-190 dynamic analysis of shipping container,of weapons, 40-3-267 39-6-57wind-induced, 36-7-81

WaterhammerViscoelastic materials, see also Elastomers in fluid systems, 40-2-67

for attenuation of shock, 40-5-175chetiiorheological study of, 38-3-175 Water tunnelscomplex stiffness of, 39-4-11 measurement of low noise in, 41-2-152damping with, 36-4-25, 36-4-49, 38-3-37,

38-3-71, 41-2-121 Waveform synthesizersat extreme temperatures, 38-3-57 shock pulse shaping by, 39-5-67 4

of plates, 39-4-63, 40-5-93of structures, 40-5-1, 40-5-37 Waveformsof vibration, 41-2-141 controL of transient, 40-2-157

dynamic modulus versus temperature, reproduction of, 36-3-4736-4-33

effect on fatigue of joints, 39-4-117 Weapons skid, 21Beffects of specimen geometry on Young's analysis of, 36-1-23

modulus, 38-3-154 design shock spectra for, 36-1-26endurance life of, 41-2-147high polymer, 38-3-175 Weber transform, 36-5-108load carrying capacity of structures with,

39-4-117 Wind tunnelsloss factor versus temperature, 36-4-30 acoustic data from, 37-7-221for machinery foundations, 38-3-1 captive flight vibration tests in, 40-6-12mathematical analysis of test system for, data from scale model in, 37-7-221

39-4-13 instrumentation for tests in, 37-7-422performance at extreme temperatures, tests of missiles in, 36-7-80, 37-3-121

36-4-25 transonic, 37-3-123properties of, -4-37, 38-3-1, 38-3-151,

38-3-175, 39-4-11, 39-4-67, 40-5-38, Wings40-5-50, 40-5-105, 41-2-125, 41-2-133 flutter of aircraft, 41-7-109

Geiger thick plate test for, 40-5-112techniques for determining, 39-4-15 Xfrom vibrating composite beam test,

40-5-112for reduction of shock in plates, 39-4-63 XB-70A aircraftfor reduction of vibration, 36-4- 9, modal survey on, 36-3-55

36-4-49, 37-3-19, 38-3-1, 3P-3-13,38-3-29, 38-3-37, 38-3-57, 38-3-71,38-3-175, 39-4-19, 39-4-31, 39-4-53, X-rays39-4-63, 39-4-73, 40-5-1, 40-5-37, experiments with, 36-6-2.9040-5-49, 40-5-93, 41-5-105, 41-5-121, field emission type, 36-6-23341-5-141 for research in soils, 36-6-225

response to vibration, 39-4-11 in soil dynamics, 36-6-228

65

Y propagation in beams, 40-4-81

Yielding structures, see also CrushableYielding structures and Honeycombseffects on shock spectra, 38-2-9 shock attenuation by, 38-3-255, 41-2-89

66

Part II

Author Index

Shock and Vibration Bulletins36 ThroLugh 41

67

AUTHOR INDEX

A B Berge, G. E., 39-2-99

Abdulhadi, F., 39-4-73, Bachman, R. E., 41-6-75 Berkman, H. R., 37-3-75

40-5-93, 41-2-133 Baganoff, D., 38-1-55 Bernstein, M., 37-5-105

Ablowitz, M., 39-3-73 Baganoff, F., 38-1-55 Berry, E., Jr., 41-7-123Abstein, H. T., Jr., 41-4-37 Bahn, M. M., 38-2-47 Bert, C. W., 39-3-107,

39-3-191, 40-5-277Ach, J. T., 37-S-73, 41-4-221 Baird, E. F., 37-5-105Bezler, P., 40-4-147Addonizio, N. R., 39-1-39 Bajan, R. L., 3 Bezle, P., 41-3-63

Agnew, D. R., 39-6-65 Baker, W. E., 36-5-55,

Agrawal, B. N., 41-4-127 37-1-77, 40-2-227, 40-1-61 Bickle, L. W., 39-5-41

Alcone, J. M., 41-2-89 41-7-19 Biehl, F. A., 39-3-179

Ali, H. B., 38-1-125 Baker, W. J., 36-6-225 Bies, D. A., 37-6-39

Allen, H. C., 41-7-195 Balcerzak, M. J., 37-4-199 Binder, R. C., 37-2-7,Alle, H C. 417-15 BakeR. ., 8-326337-4-117, 39-2-99,Alley, T. L., 40-4-225 Balke, R. W., 38-3-263 39-3-171, 40-2-67,

Bangs, W. F., 41-5-9 40-5-235, 41-2-151,Alma, H. F., 38-1-125, 41-7-205

40-S-7 Baran, A. S., 36-2-17

Ames, V. G., 40-3-293 Baratono, J. R., 37-7-221 Bishop, G. W., 38-2-205,39 -1-33

Andersen, W. F., 39-4-213 Barclay, R. G., 40-5-147 Blasingame, W., 36-4-81,

Andersun, J. D., 39-4-81 Barnett, P., 37-4-1 39-1-143

Anderson, R. H., 37-4-151 Barnoski, R. L., 38-1-37 Blenner, D. R., 38-3-199,

Anderson, T. L., 40-2-115 Barrett, S., 39-2-157 40-5-105

Angelopulos, N., 37-2-117 Basdekas, N. L., 41-7-29 Bliven, D. 0., 40-2-123

Apgar, J. W., 37-1-97 Basye, C. B., 40-4-115 Block, D. L., 38-2-33

Aprahamian, R., 41-3-63 Bathke, E. A., 41-5-59 Boers, B. L., 36-4-65

krcas, N., 39-3-87 Baum,, C., 41-6-123 Bohs, C., 39-5-73

Arcilesi, C. J., 37-3-175 beck, C. J., Jr., 37-5-167, Bclds, P. G., 41-4-22139-6-133 Bort, R. L., 39-1-13

Arone, R. A., 36-3-147,41-3-119 Beckett, R. E., 41-6-39 Bost, R. B.. 36-5-85

Arthur, W. E., 40-5-285 Beecher, W. C., 39-2-175 Bouche, R. R., 41-3-i

Arthurs, T. D., 38-2-139 Bell, A. W., 38-2-57, Bouclin. P., 40-S-63

Arya, S. C., 39-4-199 Bowie, G. E.. 40-5-61

Ashley, C., 41-2-13 Bell, R. L., 40-2-205 Bozich, D. J., 36-6-55,Belsheim, R. 0., 36-1-1 37-5-77, 39-4-227Ashton, J. E., 39-4-81, 39-1-13 Bramme~er, G. F.,

39-4-93 BaiieG .

Avila, J. H., 36-6-101 Benson, A. S., 41-7-151 40-5-261

Benson, D. A., 37-S-1 Bratkowski, W. V.,Avis, A. J., 36-71-*5 36-6-215Avre, R. S, 41-5-27 Benton, M D., 37-2-173 Brauchli, H., 41-6-87

Preceding page blank

Britt, F. A., 37-4-151 Coalsoa, C. G., 41-3-223 Davis, H. J., 37-3-219Britton, W. R., 36-2-71 Coffey, C. G., 40-2-147 Davis, S., 36-7-63, 38-3-325Brock, P. A., 36-3-147 Cohen, E., 37-4-213 Deckard, C. E., 41-3-119Brown, C. R., 36-7-145, Cole, H. M., 40-S-21 DeClue, T. K., 41-3-119

37-7 -67 Colopy, F. H., 36-7-'3: Delchamps, T. B., 39-6-151Bruns , G. H ., 36-4-49 Colonna, R. A., 37-5-89 Della Rocca, R. J., 39-1-39Burack G. D., 36-1-45 Colt, J. G., 37-3-151 Demas, L. J., 37-5-175Burnet, R. R., 3Compton, W. A., 40-5-61 Dembo, M. M., 40-2-243Conley, W. R., 40-1-75 Denton, K. D., 41-5-89Burton, B. E., 41-5-27 Conticelli, V. M., 38-2-177 Derby, T. F., 40-5-19,Butt, L. T., 37-4-71 Cook, L. L., Jr., 39-2-11 40-5-203

C Cornelius, K. T., 36-1-13, DeVost, V. F., 37-2-2938-3-213 Dick, A. F., 36-1-1Caba, D. W., 39-6-133 Corrao, P., 41-2-5 Dickerson, J. R., 37-2-173Calcaterra, P. C., 37-6-29, CsT . 923

39-4-157, 40-5-203 Cost, T. B., 39-2-35 DiTaranto, R. A., 36-4-81,Campos, P. E., 38-2-67 Courtney, W. J., 41-3-187 39-1-143

Cannon, C. M., 38-3-151, Covert, M., 41-2-95 - Dodge, F. T., 41-7-16a39-4-31 Cox, P. A., Jr., 40-2-227 Doll, R. W., 39-4-179

Carlson, A. D., 36-2-31 40-1-61 Donaghy, R. G., 37-4-127Carrell, T., 40-5-285 Crist, S. A., 41-6-61 Dorland, W. D., 37-5-25,Carter, D. A. E., 40-3-193 Critchfield, M., 36-4-95 37-5-139, 40-3-163

Carter, R. R., 37-2-i Crites, R. C., 41-3-55 Douglas, B. E., 38-3-89,Cartr, . R. 372-139-1-155Catherines, J. J., 40-6-91 Cronin, D. L., 38-1-133, Downing, B. N., 40-6-6741-7-9

Cerasuolo, D., 41-3-149 Cronkhite, J. D., 41-7-131 Dreher, J. F., 37-S-95,Chajes, A., 37-4-143 39-S-15, 41-S-25,

Crum, J., 41-5-167 41-S-33Chalmers, R. H., 40-2-31 Cunniff, P. F., 36-2-9 Drischler J. A., 36-5-77Chandiranani, K. L., Curciiack, H., D., 41-3-i65 Dudek, T. J., 38-3-199.

36 -5-97Chaump, L. E., 40-3-31 Curreri, J. R., 39-2-51, 40-5-105Chap, S ., 4 0-3-341 39-3-161, 40-4-147 Dunham, T. D., 38-3-235Chen, S., 41-7-141 Curtis, A. J., 37-3-47, Durling, B. J., 40-6-109Chi, M., 41-7-29 39-6-77, 41-4-37 DuWaldt, F. A., 37-6-5Childs, W., 39-6-15 Curwen, P. W., 38-3-221,Chin, J., 41-3-149 40-3-275 Dzialo, F. J., 37-4-143

Chirby, A. E., 39-2-105, Cyphers, H. D., 36-6-207,41-7-195 39-2-23 E

Christiansen, H. N., 39-3-31 Earls, D. L., 38-S-541-6-115 D41-S-25

Chung, T. J., 11-7-81 Daly, J. M., 36-5-55 Ebner, S., G.. 41-G-1Cinelli, G., 36-5-107 Damle, S. K., 40-3-99 Eckblad, D. M., 41-5-143Citipitioglu, E., 39-6-57 Davidson, L. C.,. 40-4-197 Edelberg A. Y.., 40-3-9Clevenson, S. A., 39-6-119 Edelman, S.,, 39-2-1

Egle, D. M., 38-3-235, Fritz, R. J., 40-1R-11 Hagglund, R. R., 41-5-6939-3 -107 Frohrib, D. A., 38-3-37 Haile, W. B., Jr., 41-6-103Eidson, R, L., 41-7-81 Frost, A., 38-3-221 Hammer, J. G., 41-7-89Eldred, K. McK., 37-5-1,37-5-25, 37-5-139 Fuss, R. E., 36-1-13 Hancock, R. N., 40-6-27

Elliott, W. A., 40-4-89 G HanLs, B. R., 36-4-1,39-2-77Ellison, J. A., 36-6-203 Gaberson, H. A., 40-2-31, Hanners, R. J., 39-1-123

Elmore, N., 41-1-1 41-5-39 Hal, F. D., 40-3-23,Elsen, W. G., 37-3-21 Gaffney, J. S., 38-2-67 40-4-209Engblom, J. J., 40-5-135 Galef, A. E., 41-7-9 Haskell, D. F., 39-5-21Epstein, H., 40-5-291 Gambucci, B. J., 40-3-205 Hasselman, T. K., 36-7-129Erickson, L. L., 39-3-1 Gardner, L. B., 41-5-53 Hawkinc, J. T., 37-4-79Eshleman, R. L., MO-5-217, Garner, D., 40-2-173 Hayek, S. I., 40-3-131

41-2-53 Garza, L. R., 41-7-169 Hayes, C. D., 37-2-7Everett, W. D., 37-4-137 Gaugh, W. J., 38-2-139, Healy, J. J., 37-4-127Everitt, J. M., 37-5-117 39-2-123 Hedrick, W. L., 41-5-143

F Gebhart, C. E., 37-4-193 Heer, E., 38-2-239Fagan, J. R., 36-2-17, Gelman, A. P., 36-7-73 Heinrichs, J. A., 36-3-15

36-4-75, 39-5-83 Gemind'.r, R., 40-2-10136-4-75,, 39-5-831-

Favour, J. D., 37-2-17, Gerks, I. F., 39-2-217 Heise, R. J., 31-140-2-157 Gertel, M ., 36. -6-1, 37-4-43 Hel mueg, J. G., 4 1 56-Helmuth, J. G., 37-3-i55,Feeser, L. J., 39-3-233, Gesswein, J., 41-2-5 41-4-183

40-3-99 Gilbert, W. E., 40-1-45 Henderson, F. M., 36-6-115Feng, C. C., 38-1-99, Go, J. Chi-Dian, 39-5-13 41-6-16339-3-99

Fine, H. A., 41-5-69 Godino, V. D., 41-1-21 Henderson, J. P., 39-4-31,FineR. A, 415-6940-5-1Fischer, E, G., 37-7-67 Goff, J. W., 40-6-127 4 ,51Fitzgerald, E. A., 38-3-139 Goldberg, J. L., 37-2-13 Henley, C ., J,-2-4Fitzgerald. T. E., 37-4-59 Goldman, R. J., 36-2-63 Henryks, W., 41-4-Henry, A. 3., 38-1-27Flamnctiy, W. G., 37 -6-63, Gordon, L. A., 39-1-4538-3.-11 Gossard, M. L., 41-6-103 Herre a , G., 40-2-57Floyd, C. J., 39 3-117, Grant, R. L., 41-5-155,41-4-119 41-5-IG7 HershiId, D. J.,. 36-6-195Fluent, S. L., 41-3-175 Gray, T). M., 39-1-25 Herzberg, R. J., 41-4-1

Fogelson, S,. 36-5-17 Gray, H. P., 41-S-45 Herzing, K. A., 40-6-9,Fogelon, _ 365-1741-5-89Foley, J. T., 39-6-31 Grishani, L. R., 39-2-1 HmnF.89Foster, W. P., 40 S-7 Grootei,hi-s, PF., 40-5-37

Fotieo, G.,, 39-S-1 Grui,,cy, A. H., 41-4-51 Hiecen, M. H., 41-3-20 7

Foxwell, V. M., Jr., 40-6-37 Gurdo, A. F., 37-S-I Higginbotham, H. H. 37-1-69Higham, C., 40-3-193

Franken, P. A., 36-3-27 H Higney, J. T., 41-6-123Freeland, R. E., 39-2-123 Hagen,. A., 40-S-13 Hill, L. R., Jr., 40-l-31Frericks, D. E., 41-5-53 Himelblau, H.,, 37-4-15

71

Hinegardner, W. D., 37-S-95 Isada, N. M., 40-2-123, Kapur, K. K., 38-1-7Hines, D. E., 41-6-9 40-3-111, 41-3-215, 41-3-133 Kartman, A. E., 41-4-189Hirsch, A. E., 37-4-79 Ishino, B. M., 40-3-257, Kazmierczak, F. F., 41-3-4341-2-151

Hobbs, G. K., 37-2-173 Keeffe, R. E., 41-5-59

Hofer, K. E., 40-5-245 Keegan, W. B., 40-3-179

Hoffman, D., 41-5-77 Jackman, K. P., 39-2-195 Kennedy, D. R., 37-5-167Holbeck, H. J., 38-2-139 Jacobs, B. R., 37-3-99 Kennedy, R., 40-6-85Holland, R., 36-6-1, 37-4-43, Janetzko, L. G., 40-S-63 Kennedy, R. P., 41-6-75

41-4-195 Janza, F. J., 36-6-225 Kimsey, R. D., 39-1-175Holley, F. J., 36-6-163, Jaszlics, L J., 39-3-99 Kipp, W. L, 39-5-8936-6-207

Hollis, W. W., 39-6-1 Jenkins, J. F., 41-7-81 Kirchman, E. J., 37-3-175Holt, H. L., 39-2-195 Jenks, A., 41-6-123 Kirsch, A., 39-1-223Hooper, W. E., 36-7-113 Jensen, F. R., 41-6-115 Kiwior, T. M., 39-6-93Hord, J. E., 39-2-135 Jewell, R. E., 39-3-55 Klepl, M. J., 40-5-235Hornbuckle, J. C., 41-7-109 Johnson, C. D., 37-1-63, Knauer, C. D., Jr., 37-1-125,39-2-41 37-4-15Hou, S., 40-4-25, 40-4-17139 -43741Houston, A. D., 40-4-7 Johnson, M. R., 37-4-199 Koegler, R. K., 40-2-123Houstn, A. D., 37-3-1, Johnson, R. L., 41-3-63 Kohler, B. A., 39-2-71Howard, E. P., 36-5-1,38-1-7 Johnston, J. D., Jr., 37-5-25 Kolb, A. W., 37-S-17Howlett, J. T., 36-2-.97, 40-3-163 Koronaios, N., 37-2-9938-3-207, 40-2-183 Jones, D. 1. G., 36-4-9, Kozin, C. H., 38-2-119Huang, C. C., 40-2-243 36-4-49, 38-3-139,

38-3-151, 39-4-19, 39-4-31, Kozin, F., 38-2-119Huang, H., 40-1-15 40-5-1, 41-2-105 Krach, F. G., 38-2-133Huffington, N. J., Jr., 36-2-63 Jones, G. K., 36-2-71, Kraft, D. C., 38-3-71Hughes, P. S., 36-2-53, 37-6-57, 40-3 -79 D37-2-29 Jones, L W., 39-4-63 Krajcinovic, D., 40-2-57Humphrey, P. W., 40-5-147 Jones, P. J., 38-3-285, Kula, L. C.. 37-4-59Hunter, N. F., Jr., 36-3-47, 41-6-197 Kulasa, L. V., 39-3-3937-3-61, 37-3-155 Jones, R., 37-6-63 Kulina, M. R., 38-3-45,Hupton, J. R., 39-1-167 Jones, T. B., Jr., 40-2-51 40-1R-1

Hurt, D. M. C., 40-S-1 Kunieda, H., 40-3-69K

Hutchinson, J. A., 40-6-27, L41-4-133 Kacena, W. J., II, 41-6-197 LaBarge, W. L.. 39-4-117,Hwang, C., 38 1-87 Kachadourian, G., 37-7-173 40-5-49Hwang, C. M., 36-7-129 Kadman, Y., 39-3-65 Laier, R. L., 39-4-179

Kalinowski, A. J., 39-4-185 Laird, W. M., 39-3-39Kampfe, W. R., 37-3-193 Lake, R. M., 41-3-11

Ip, C., 36-5-1, 36-6-91, Kao, G. C., 38-2-177, L'ikin, E. D., 39-S-1538-1-7 39-4-22738-1- 39--227Lambert, W. H., 36-7-79Irick, J. T., 37-1-77 Kaplan, S. M., 36-7-41, Lamoree, M. D., 39-4-117,

Isaacson, C. C., 39-2-63 39-2-147, 40-3-89 40-5-49

72

I

LeBrun, J. M., 40-2-157 Masri, S. F., 39-4-1 Morrow, C. T.. 39-2-87.Lee, H., 41-7-51 Massey, G. A., 37-2-1 39-5-63.41-5-17Lee, K., 37-4-C3 MWsters, A. E., 41-7-81 Morse, R. E., 37-7-93

Lee, R. H., 41-1-35 Mathur, P. N., 40-4-217, Moser, J. R., 40-2-173

Lee, S. E., 36-6-67, 38-S-1 41-1-35 Mueller, A. W., 40-4-103

Lee, S. K., 39-3-201 Matrullo. M., 36-3-113 Mvirhead, J. C., 40-2-147

Lee, T. N., 40-3-57 Maurer, 0. F., 37-S-43 Mullen, J. F., 38-3-45

Leffer, N. A., 37-2-87 Mayberry, B. L., 39-3-191 Murdock, 3. W., 41-1-35Mayer, G. M., 37-1-63, Murfin, W. B., 36-6-21,

Lemley, C. E., 40-4-139 37-2-51, 39-2-41 37-4-177, 38-1-109Lester, G., 41-4-183 Mays, J. R., 40-4-81, 41-5-101 Murray, F. M., 37-5-13Liang, S. T. W., 39-S-55 McCaa, R., 36-3-113 Muskat, R., 41-6-93

Liber, T., 40-5-291 McCafferty, R. M., 41-3-109 Musson, B. G., 41-4-133Lifer, C. E., 38-1-87 McCann, R. F., 36-3-71Lipeles, J. L., 41-5-77 McCarty, J. L., 40-2-183 NLoewy, R. G., 36-2-1 McConnell, K. G., 39-4-11,Long, B. R., 38-1-45 40-S-13 Nagy, J. A., 37-2-43Long, J. V., 40-5-61 McCoy, R. G., 40-2-133 Nashif, A. D., 36-4-9,

36-4-37, 38-3-57, 38-3-151,Luebke, R. W., 41-4-141 McFarland, S. L., 41-4-161 39-4-19, 39-4-53, 40-5-1,Lund, D. M., 39-1-65 McGrath, M. B., 41-5-1 41-2-121

Lutes, L. D., 38-2-239 McGrattan, F. J., 36-2-31 Naylor, C., 40-2-147Lyon, R. H., 36-5-97, 40-4-17 McHorney, P. E., 37-1-125, Nelson, F. C.. 38-3-5

37-4-15 Nelson, J. E.,. 41-5-101

M hrcIntosh, V. C., 41-4i-209 Nemergut, P. J., 41-7-37

],'cNabb, J. W., 36-1-23 Neubert, V. H., 41-6-147,Macinante, J. A., 40-4-155 41-7-51Mac~tosh A. ., 3-1-1Mebane, W. W., 37-2-65Macintosh, A. M., 37-1-1 Melichar, F., 37-4-185 Nevrincean, G., 40-2-133Mack, T. H., 36-3-27 Newbrough, D. E., 37-5-89,Macy. M. J., 39-1-45 Meilsen, S. B.. 40-2-83 37-5-105

Maddux, G. E., 41-7-37 Melodia, A. C., 36-6-131 Newman, R. K., 38-3-71

Magrath, H. A., 37-S-17 Mentzer, W. R., Jr., 36-2-9 Nicholas, T., 38-3-13,

Maguire, A. F., 36-1-45 Merchant, J. K., 40-3-31 39-4-53, 41-2-121

Mains, R. M., 38-2-1, Merkel, R. W., 39-2-63 Nielsen, R., 38-2-157.

39-3-129, 40-4-1, 41-4-79 Meyer, E. B.. 38-2-231 40-4-63

Mair, R. W., 37-S-1 Miller, D. F., 36-1-45 Nirsehl, J., 40-5-285

Mandich, R. P., 39-1-195 Miller, D. K., 40-4-209 Nissel, N. B., 38-3-32539-6-93 Miller, H. T., 38-3-29, Noiseux, D. U., 38-2-231

Manning, J. E., 37-4-65 39-1-167 Nokes, D. S., 38-3-5Marcus, D., 41-4-195 Mok, Chi-Hung, 40-2-.215 Noonan, W. E., 37-3-89,

Mard, K. C., 39-3-17 Mol'tar, A. J., 37-7-67 38-1-17

Marsh, E. G., 3V.2-51 Monanan, J., 41-7-37 North, R. G., 36-3-55

Martin, D. J., 38-3-207, Moody, M. L., 39-3-247. Novak, M. E., 40-4-4141-6-203 40-2-115. 41-6-1 Nunez, H. W., 40-2-193

73

0 Peoples, J. R., 41-S-1 Razziano, A.. 39-2-6iGden, J. T., 41-7-81 Perry, C. H., 40-6-1 Reade, R., 41-3-187

Oed,,, R. J* 39-893 Perry, E. S., 39-4-199 Redford, D. F., 313-3-91,O'Hara, G. J., 38-2-209, Petak, L. P., 38-2-209 37-2-109

.9-1-13, 39-3-143 Pe' rs, F. W., 37-3-121 Reed, R. S., 37-7-205

Ohno, J. M., 38-3-175 Pettit, E. A., Jr., 39-3-31 Regillo, D. A., 39-5-67O'Leary, J. J., 40-5-191 Peverley, R. W., 36-3-39, Remmers, G. M., 38-2-261,

Oleson, M. W., 40-2-1 37-5-153 39-3-143

Olmsted, G. W., 41-3-207 Phelps. H. N., Jr., 41-1-13 Rich, H, L., 37-1-15, 39-1-93

Olsen, J. R., 37-4-15 Phelps, W. D., 37-7-19 Rich, R. L., 36-7-19,Olson, J. N., 41-3-207 Pierce, S. R., 40-6-127 Riggen, C. L., 36-3-83

On, F. J., 38-2-249, 40-3-79 Pilkey, W. D., 36-5-69, Rimer, M., 41,7-18137-4-169, 38-2-157, Riparbelli, C., 37-1-115

O'Neill, J. P., 40-5-157 39-4-185, 40-4-63, 41-2-47Osgod, . C. 40Roach, C. D., 37-6-1Osgood, C. C., 40-3-1 Pittman, P. F.. 36-6-215

Robb, E. A., 36-7-13Ostrem, F. E., 37-7-1 Platus, D. L., 38-3-255 Roberts, J. A., 36-7-19O'Sullivan, D. J., Jr., 39-6-19 Pollard, W. G., 41-3-75 Roberts, P. V., 40-S-29,Ottis, J. V., 36-3-47, 37-3-61, Pomonik, G. M., 37-7-39 41-2-15941-4-29 Poppitz. J. V.. 38-2-187 Roberts, W. H., 37-7-77,Owens. F. S., 36-4-25 Port, R. J.. 41-5-129 39-S-1,340-2-21

P Porter, 0. H., 37-1-35 Robertson, K. D., 36-7-103

Paoich, R. J., 37-2-57 Potter. J., L., 41-2-141 Robinson, F., 36-6-83Rocke, R. D., 39-4-1,Padu,,,an. J. A., 39--161 Powell, A., 36-2-5 41-6-133, 41-7-61

Painter, G. W., 36-3-1 Prendergast, F. X.. 36-6-37 Rodeman, R., 41-4-109Pakstys, M., Jr., 38-2-11, Prothro, B. E.. 39-6-47 Rodkin. S., 37-4-10338-3-243, 39-1-55 Pulgrano.. L. J., 39-3-73 Rodriguez, A. M., 40-4-217Pal, D., 41-5-39 Pursifull, L. J., 39-6-47. Rovers, D. M.. 41-1-35Pan, K. C., 41-6-39 40-6-99

Roos,, C. H., 41-4-173Parker, G. HR., 41-6-9 Putman, T. H.. 38-3-317 Root, L. W., 38-1-27,Parker, W. S., 40-4-109 Putukian, J. H.. 37-4-97 39-2-187, 39-5-73. 40-4-97Parks, J. G., 41-3-17 Q Rosenberb, G. S., 36-4-65Parmenter, W. W., 37-S-107, Rosenfield, M. J., 38-2-177

40-S-47 Quinn, T. L., 39-4-251Roske, V. P., Jr.. 40-5-277Parrish, T. V., 40-6-109 R Ross, D. H., 37-3-203

Patel, M. C., 40-3-131 Rader, W. P., 41-5-9 Rossmiller, R.. 41-3-187

Payne, B. F., lb-6-183 Raftopoulos, D. D., 41-S-49 Roth, S. C.. 39-2-1

Rao, P. N., 40-5-217, Rountree, R. C., 41-5-111Paz, M., 39-6-57, 41-6-159, 40-5-245 Rowan, W. H., 41-5-13541-7-123

Ranney, J, P., 36-2-97, Roy., R., 41-6-133Pearson, J.. 40-3-205 38-2-23Rubinstein,, N., 38-2-169,Peete, W. F., Jr.,. 40-1-9 Ravenscraft. J. R., 41-6-211 40-4-163

Penrod, D. D., 41-6-39 Rav, J., D.., 39-3-107 Rucker,. C. E., 38-1-1

74

.udder, F. F., Jr., 39-3-49 Sewall, J. L., 40-6-109 Steier, M., 40-4-63Runkle, C. J., 40-3-23 Sharma, M. G., 36-4-95 Stein, P. K., 41-3-81Rupert, C. L., 39-4-101 Shear, J. C., 40-3-111 Stephens, D. G., As 1-1,Ruzicka, J. E., 39-4-141, Shpway, G. D., 40-3-211 41-7-181

40-5-19 Siwy .D,4--1Shupe, W. 1., 41-3-11 Sterk, M. W., 36-6-203

Shurtleff, W. W., 36-3-139 Stevens, R. A.. 39-2-105.i 41-7-195

Safford, F. B., 37-4-117, Shyu, T. P., 40-3-11941-5-111 Sierakowski. R. L., 41-7-109 Stevens, R. W., 37-4-M3I

Sallet, D. W., 39-4-261, Sgillito. V. G., 38-2-19, Stevewton, J. R., 36-3-5540-3-393, 41-6-31 40-4-163Stewart, H. L., 40-3-267

Salter, J. P., 37-3-1 Silver, R. L., 39-3-205 St. Lawrence, W. F.. 36-4-95Salyer, H. A., 41-3-25 Silverman. S., 37-1-77. StrickI 1, G. E., Jr.,

40-2227 40--6139-5-29Sanchez, L., 37-4-213 40-22L., 40-1-1ISapetta, L, P., 39-4-73 Simmons, D. R., 39-4-31 Stroeve, A., 40-3-49

SSincavage, J., 39-5-83 Sugarman, R. C., 41-3-215•_ Sardella, G., 36-3-83

Saunders, H., 36-5-Wji Singhvi, G. M., 39-3-233 Sub, N. P., 41-2-7739-1-2.23, 40.4-187 Skolka, E. J., 36-3-119 Sullivan, J. R., 39-1-65

Saunders, P. D., 38-2-95 Smallwuod, D. 0., 41-4-87 Sussman, E. D., 41-3-215$cavuzzo, R. J., 39-S-41, Smart, T. E., 37-2-77 Sutphin, H. C., 41-6-219

41-S-49 Smith, A., 40-S-29 Sutton, J. F., 39-2-23Scharton, T. D., 36-3-27,

36-5-41, 38-1-115, 40-3-231 Smith, D. L., 41-4-161 Swanson, W. L., 40-3--7

Schell, E. H., 40-6-153 Smith, E. F., 41-6., Sylvester, R. J., 36-5-1

Scheller, B. R., 40-4-115 Smith, F. A., 37-7..':21, T38-3-285, 39-3-55Schock, R. W., 37-5-117 Smith, J. E.. 39-1-123, Tai, C. L., 38-2.7ý

Schlue, J. W., 37-7-19 40-4-197 Tait, j. N.,.40-3-139Schoessow, T. D., 38-1-37 Smith, L. G., 37-3-137 Tereniak, W. B., 36-7-89Schrader, C. G., 37-4-85 Snowdon, .1, C., 41-2-21 Terkun, V., 36-7-41Schubert, D. W., 37-6-29, Soifer, M. T., 38-2-57. Thomas, C. F , 37-S-73,39-4-141, 39-4-157 39-3-153 41-4-209Schulz, M. W., 36-6-73 Somerset, J. H.. 39-3-205, Thomas, E. V., 36-4-81,Schwantes, S. N., 40-6-9 40-3-119 38-3-1, 38-S-19, 39-1-155

41-5-89 Soroka, A. J., 39-2-147 Thompson, J. N., 39-4-199Sciarra, J. J., 37-6-19 Soulant, H., 38-S-I Thornton, E. A., 40-I-ISearnons. L. 0., 36-2-83, Sowers, J. D., 38-3-95 Timmerman, K. M., 37-3-193

41-3-195 Spalthoff, W. G.. 39-1-195 Tinling, N. G._ 39-6-77.Seat, J. R., 37-5-117 Spencer, P. R., 40-3-275 41-4-37Seigel, A. E., 40-4-127 Srinivasan, A. V.. 37-6-49 Tirman. C. J., 40-5-157Sellers, W., H., 37-2-57 Stadter, J. T., 38-2-169, Tolle, E. A., 39-S-15Sevin, E., 36-5-69, 37-4-169, 40-4-163 Tolleth, F. C.. 36-3-101

39-4-185 Stable.. C. V., Jr., 36-7-1 Tomassoni, J. E.. 36-7-79Sevy, R. W., 38-S-5

75

Trull, R. V., 41-4-95 Walton, W. C., Jr., 41-6-203 Winquhtt, A. A.. 40-2-67

Tryon, H. B., 40-3-275 Wambsganss, M. W., Jr., Witt, E. F., 40-2-133

Tuckerman, R. G., 36-6-67 36-4-65 Witte, A. F., 38-1-67,

Tustin, W., 40-6-61 Wang, E. H., 36-6-225 41-4-109, 41-4-69

Wang, Shou-ling, 39-1-107 Wohltmann, M., 39-5-1,U Wang, Y. F., 40-1-15 40-4-67, 41-6-219

Uchiyama, J. T., 37-3-121 Ward, H. H., 39-1-65 Wood, W. R., Jr., 39-2-105,

Uchlyam a, S., 28-2-79 W ard, T. A ., 41-7-205 W1 , W E 4 - 1Woolam, W. E., 40-5-115

Ungar, E. E., 36-5-41, Warkulwiz, V. P., 38-2-107 Wren, i. J., 37-5-25,

37-2-99, 39-3-65, 41-7-1 Warnaka, G. E., 39-1-167 37-5-139

V Warner, R. W., 41-2-95 Wrenn, B. G., 41-4-1

Vagnoni, L. A., 36-2-53 Waters, D., 37-S-1 Wright, P. M., 38-1-99

Van Bibber, V. H., 41-1-1 Weatherstone, J. D., 36-6-47 y

van der Heyde, R. C. W., Weber, J. D., 38-3-16537-S-63 Weinberger, F., 37-1-35, Yang, J. C. S., 4U-4-127,

Wein40e5-1r5 41-63-1187Van Gulick, L. A., 41-6-219 39-1-1 40-5-175, 41-6-187

Yang, T. M., 37-6-39,Varney, R. F., 41-4-99 Weissman, S., 37-4-213 38-1-115

Vatz, I. P., 38-2-271, Welch, W. P., 38-2-95 Yorgiadis, A., 39-2-15741-6-179 Wells, C. R., 39-2-135 Young. D., 40-2-227,

Venetos, M. A., 36-6-173 West, J. R., Jr., 37-4-15, Young. D. 40-2-227

Verga, J., 38-2-219, 37-5-89 Y39-2-221 Westine, P. S., 39-6-139, Young, R. K., 41-5-53

Vigil, M. G., 39-5-41, 40-1-61 z39-5-53 White, M. P., 37-4-143

Viner, J.: G., 41-4-99, 41-S-1 Mhite, R. P., Jr., 37-6-5 Ziegra, G. A., 38-3-243,41-1-21

Vogel, W., 41-6-147 White, R. W., 37-5-55 Zimmerman, N. H., 40-4-139

Volz, W. A., 36-2-89 Whitehill, A. S., 39-4-251 Zonars. D., 41-2-1

von Hardenberg, P. W., Wiland, J. 41-4-19539-3-17 J Zwibel, H. S., 41-7-89

Williams, L. A., 33-7-89W Wilson, J. F., 40-4-47,

41-6-47Wallerstein. L., Jr.,

37-3-163 Wilson, J. P., 40-IR-1

76

\i

Part III

Tables of Contents

Shock and Vibration Bulletins36 Through 41

77

Bulletin 36Part I

DYNAMIC DESIGN ANALYSIS METHOD PREDICTION VERSUS TEST MEASUREMENT OFSHIPBORNE EQUIPMENT RESPONSE ......................... .; ........ I

R. 0. Belsheim and A. F. Dick, Naval Research Laboratory, Washijigton,:D.C,

COMPARISON OF SHOCK MOTIONS INDUCED BY AIR BLAST 'AND UNDERWATER EXPLOSIONS .................................... 13

Robert E. Fuss and Kenneth T. Cornelius, David Taylor Mod,.l Basin, Washingt6n. D.C.

ANALYSIS OF 21B WEAPONS SKID FOR VERTICAL SHOCK .................... 23John W. McNabb, Northern Ohio University. Ada. Ohio

NERVA NUCLEAR REACTOR VIBRATION ANALYSIS AND TEST PROGRAM WITHEMPHASIS ON NONLINEAR RESPONSES ................................. 45

R. D. Burack, D. F. Miller, and A. F. Maguire, Westinghouse ElectricCorporation, Pittsburgh, Pennsylvania

RECENT SOVIET RESEARCH IN SHOCK, VIBRATION, AND NONLINEAR MECHANICS ...David B. Singer, Aerospace Corporation, San Bernardino, California

DISTRIBUTION ......................... ......................... 55

Bulletin 36

Part II

Opening Session

THF CHALLENGE OF THE SECOND HALF OF THE DECADE ....................It. G. Loewy, Utiiversity of Rochester, Rochester, New York

SHOCK AND VIBRATION - A PERSPECTIVE .......... ............................. 5Alan Powell, David Taylor Model Basin, Washington, D.C.

Shock

YIELDING EFFECTS ON SHOCK SPECTRA ..................... .......................... 9William R. Mentzer, Jr., Bowles Engineering Corporation, Silver Spring, Maryland,and Patrick F. Cunniff, University of Maryland, College Park, Maryland

SHOCK SPECTRA OF PRACTICAL SHAKER SHOCK PULSE ........................ ... 17John R. Fagan and Anthony S. Baran, Radio Corporation of America,Princeton, New Jersey

TRANSDUCER SHOCK STUDY ................... ................................. 31Arthur D. Carlson and Robert J. McGrattan, General Dynamics, Electric Boat Division,Groton, Connecticut

DIRECT MEASUREMENT OF 5"/54 GUN SETBACK ACCELERATION ....... ........... 53Peter S. Hughes and Luigi A. Vagnoni, Naval Ordnance Laboratory,Silver Spring, Maryland

':lThis manuscript was not available at the time this part of the Bulletin went to press. It is hopedthat the paper will be published at a later date,

Preceding page blank 79

SIMULATION OF HEAT SHIELD PYROTECHNIC SHOCK IMPEDANCE ......... .. 63Norris J, Huffington, Jr., and Rober. -.. Goldman, The Martin Company.Baltimore, Maryland

PYROTECHNIC SHOCK TESTING OF A FULL-SCALE REENTRY VEHICLE ............. 71W. R. Britton and G. K. Jones, The Martin Company, Baltimore. Maryland

SHOCK TESTING WITH SOLID-PROPELLANT-POWERED GUNS.................. 83Larry 0. Seamons, Sandia Corporation, Albuquerque, New Mexico

APPLICATION OF POLYURETHANE FOAM TO SHOCK ISOLATION OF LARGESILO-BASED MISSILES ............ ................................. .. 89

W. A. Volz, Westinghouse Electric Corporation, Sunnyvale, California

NEW APPROACH FOR EVALUATING TRANSIENT LOADS FOR ENVIRONMENTALTESTING OF SPACECRAFT ............................... 97

James T. Howlett and John P. Raney, NASA Langley Research Center,Hampton, Virginia

SPECIFICATION OF SHOCK TESTS - PANEL SESSION ................................ 107

DISTRIBUTION - ............ ......................... .......... 121

Bulletin 36Part III

Vibration Testing

USE OF FORCE AND ACCELERATION MEASUREMENTS IN SPECIFYING ANDMONITORING LABORATORY VIBRATION TESTS . ............... . .I

G. W. Painter, Lockheed-California Company, Burbank, California

FEASIBILITY OF FORCE-CONTROLLED SPACECRAFT VIBRATION TESTINGUSING NOTCHED RANDOM TEST SPECTRA ............ .......................... 15

Joseph A. Heinrichs, The Martin Company, Baltimore, Maryland

COMPARISON OF MARI4ER ASSEMBLY-LEVEL AND SPACECRAFT-LEVELVIBRATION TESTS .................................... ....... ..... 27

Peter A. Franken and Terry D. Scharton, Bolt Beranek and Newman Inc., Van Nuyk,California, and Thomas H. Mack, Jet Propulsion Laboratory, Pasadena, California

ACOUSTICALLY INDUCED VIBRATION TESTING OF SPACECRAFT COMPONENTS .,. .. ,. 39Richard W, Peverley, General Electric Company, Houston, Texas

REPRODUCTION OF COMPLEX AND RANDOM WAVEFORMS AT VARIOUS POINTSON A TEST ITEM . . ..................... . ................ .. 47

John V, Otts and Norman F. Hanter, Jr., Sandia Corporation, Albuquerque, New Mexico

MULTIPLE SHAKER GROUND VIBRATION TEST SYSTEM DESIGNED FOR XB-70A ., .. 55R. G. North and ,. R. Stevenson, North American Aviation, Inc., Los Angeles,California

THE HOW OF HELICOPTER VIBRATION TESTING.......... ,........... 71Ronald F., McCann, The oeing Company, Morton, Pennsylvania

RESONANCE TESTING OF , LIFTING BODY REENTRY VEHICLE .................... 83G. Sardella and C. L. R ggen, The Martin Company, Baltimore, Maryland

SHOCK AND VIBRATION TESTING USING FOUR-SHAKER SYSTEM .. .............. .

Dean F. Redford, Thiokol Chemical Corporation, Brigham City, Utah

80

DESIGN TECHNIQUES FOR HORIZONTAL DRIVER:....................Fred C. Tolleth, Nc-.-th -American Aviation, Inc.. Autonetics ..isn An.aheim.California

FLIGHT LEVEL VIBRATION TESTING OF A LIFTING BODY REENTRY VEHICLE . . .R. McCaa and M. Matrullo, The Martin Company, Baltimore, Maryland

HYDRAULIC EXCITER COMBINED ENVIRONMENT TESTS.............. .. .. .. .. . . .....Edwin J. Skolka, NASA Goddard Space Flight Center, Greenbelt, Marylimnd

AVERAGING FUNDAMENTAL VIBRATION CONTROL SIGNALS:A THEORETICAL STUDY........................ .. . . ..... . . ....... .. .. .. .. .. ....

W. W. Shurtleff, Sandia Corporation. Albuquerque. New Mexico

CONTROL TECHNIQUES FOR MULTI-SHAI:ER VIBRATION SYSTEMS .. .. . ..........Richard A. Arone, Wyle Laboratories. Huntsville. Alabama. and Paul A. Brock:Sine Engineering Company, Granada Hills, California

Bulletin 36Part IV

D~amiping

MECHANISMS AND SCALING OF DAMPING IN A PRACTICAL STRUCTURAL JOINT . . . .Brantley R. Hanks and David G. Stephens, NASA Langley Research Center,I-Lrnptoni, Virginia

DAMPING OF STRUCTURES BY VISCOELASTIC LINKS.......... . . ... . .. .. .. .. .. ....David 1. G. Jones. Air Force Materials Laboratory, Wright- Patterson Air Force Base,Ohio. and Ahid D, Nash&f Univers,.ty of D~ayton, Dayton, Ohio

ELASTOMERS FOR DAMP3ING OVER WIDE TEMPERATURE RANGES.......... .. .. .. ....F. S. Owtvvis, Air Force Materials Laboratory, Wright- Patterson Air Force Base. Ohio

NEW MIETHO0D FOR DETERM0INING DAMPING PRtOPERTIEs OF VISCOELASTICMATERIALS. .. ............................................... . . .. . ..... .. .. .. .......

Ahid D. Nasqhif, University o f Dayton, Dayton, Ohio

EFFFCT Or TUNED) VISCOELASTIC DANIPEWS ON RESPONSE OF MULTI-SPANSTR1UCTURES .*..... ................ .............. ............ .............. ..... ......

David 1. G. Jo)ne~s and George H4. Brians. Air Force Nlatt*"mals Laboratory,/WrighL- Patterson Air Force Base. Ohio

METHOD101 FOR IDENTIFYING AND) EVALUATING I.INF.M( DAMPING MODELS INBEAM VIBRATIONS .. .. ............................................. . . ... . .. .. .. .. ....

M. W. Wainbsganss, Jr.. B . L. Boe rs., and G. S. Rosenberg, Argonne NationalLaboratory, Argonne, Illinois

EFFECT OF AIR DAMPING ON STrRUCTURAL FATIGUE FAILURE........ . .. .. .. .. ....John R. Fagan, Radio Corporation of Amnerica, Princetoni, Nevw Jersey

D)EVELOPMENT OF DAMPED MJACHINERY FOUNDATIONS.............. ... . .. .. .. .. ....W. Blasingaine and E. V. Thomnas, Navy Marine Enigineering Laboratory.Aminapolhs, Maryland, and R. A. DiTaranto, Pennsylvania Military Colle-ges.Chester, Pennsylvania

D)YNAMIC MECHANICAL. STUDIES OF A COMPOSITE MATEIAl . .. .. ....... .. .. .. ....M. G. Sharnia, M. Critchfield. and W. F. St, Lawrence, The Pennsylvania StateUniversity, University Park, Pennsylvania

81

Bulletin 36Part V

Analysis and Prediction

METHOD FOR IMPROVING A DYNAMIC MODEL USING EXPERIMENTALTRANSIENT RESPONSE DATA ......... ................................

Ching-u Ip, Eli P. Howard, .nd Ric nard J. Syivester, Aerospace Corporation,San Bernardino, California

DIGITAL AN ,LYSIS OF FATIGUE DAMAGE TO A MULTI-MODAL SYSTEM SUBJECTEDTO LOGARITHMICALLY SWEPT SINUSOIDAL VIBRAT.ON SPEG.LA ...... .......... 17

Seymour Fogelson, The Marquardt Corporation, Van Nuys, California

ANALYSIS OF VIBRATION DISTRIBUTIONS IN COMPLEX STRUCTURES ........... 41Eric E. Ungar, Bolt l1eranek and Newman Inc., Cambridge, Maqsachusetts, andTerry D. Schae'ton, Bolt Beranek and Newman Inc., Van Nuys, California

DYNAMIC ANALYSIS OF CONTINUU.i BODIES BY THE DIRECT S1 IFI'•N;•SS METHOD. . . 55W. E. Baker, Rocketdyne, Division of North American Aviation, McGregor, Texas,and J.M. DaLy, Arde Engineering Company, Asheviile, North Carolina

MIN-MAX RESPONSE PROBLEMS OF DYNAMIC SYSTEMS AND COMPUTATIONAlSOLUTION TECHNIQUES ....... .................................... 69

Eugene Sevin and Walter Pilkey, IIT Research Insttitute, Chiago, Illinois

STRAIN RESPONSE OF SIMPLY SUPPOIr rED BEAMS TO POINT AND ACOUSTIC LOADING 77Tony L. Parrott and Joseph A. Drischler, NASA Langley Research Center,Langley Stltion, Hampton, Virginia

PREDICTION OF FLIGHT VIBRATION LEVELS FOR THE SCOUT LAUNCH VEHICLE . . . 85Robert B. Boat, LTV Aerospace Corporation, LTV Astronautics Division, Dallas, Texas

RESPONSE OF STRRUCTURAL COMPONENTS OF A LAUNCH VEHICLE TO IN- FLIGHTACOUSTIC AND AERODYNAMIC ENV!RONMENTS ........... ...................... 97

Khushi L. Chandiramani and Richard H. Lyon, Bolt Beranek and Nev%&man Inc.,Cambridge, Massachusetts

DYNAMIC VIBRATIONS OF THICK-WALLED ELASTIC ANISOTROPIC CYLINDERS ANDSPHERES WITH INTERNAL DAMPING ............... ........................... 107

Gabriel Cinelli, Argonne National l.aboratory, Argonne, Illinois

EFFECT OF ASYMMWTRICAL TRAPEZOIDAL PULSF ON SINGLE- DEGREE-OF-FRitEEDOMSYSTE:MS .S..................................... .......................... .119

H. Saunders, General Electric Cupany, Philadelphia, Pennsylvania

Bulletin 36Part All

Data Analysis and Instrumentation

EFFECT OF DIGITIZING DETAIL ON SHOCK AND FOURIiR SPECTRUMCOMPUTATION OF FIELD DATA .....................................

hi. Gertel and R. Holland, Allied ReseirLh Asociates, Inc., Con~ord, Massachusetts

AUTOMArED DIGITAL SHOCK DATA REDUCTION SYSIEM .......... .......... .. .. 21Waiter B. Murfin, Sindia Corporation, Albuquerque, New Mexico

82

AUTOMATED ANALOG METHOD OF SHOCK ANALYSIS .................. 37F. X. Prendergast, Bell Telephone Laboratories, Whippany, New Jersey

VIBRATION DATA REDUCTION TECHNIQUES AS APPLIED TO SATURNS-II VEHICLE 47

Joseph D. Weatherstone, North Am~erican'A'viatiodn,D~owney,'Caaifornia .........

DIGITAL ANALYSIS OF SATURN ENVIRONMENTAL TEST RESPONSE DATA ........... 55Daniel J, Bozich, Wyle Laboratories, Hurtsville, Alabama

USE OF A LOW-FREQUENCY SPECTRUM ANALYZER ...................... 67S. E. Lee and R. 0. Tuckerman, David Taylor Model Basin, Washington, D.C.

DETECTION CF LOOSE PARTS AND FREE OBJECTS IN "EALED CONTAINERS ..... ... 73M. W. Schul-t, General Electric Research and Development Center,Schenectady, New York

COMBINED ENVIRONMENT TESTING OF SHIPBOARD ELECTRONIC EQUIPMENTAND UTILIZATION OF REGRESSION ANALYSIS ........... ...................... 63

F. Robinson, Navy Electronics Labc "atory, San Diego, Califorria

ANALYSIS OF RANDOM VIBRATION WITH AID OF OPTICAL S'kSTEMS ............... 91Ching-u Ip. Aerosoace Corporation, San Bernardino, California

COMPUTER eROGRAM FOR DYNAMIC DESIGN AiNALYSIS METHOD ............... 101John H. Avila, David Taylor Model Basin, Washington, D.C.

COMPUTER PROGRAM FOR GENERAL SHIP VIBRATION CALCULATIONS ............. 115

Francis M. Henderson. David Thy-nr Model Basin, Washington, D.C.

MATHEMATICAL MODEL AND COMPUTER PROGRAM FOR TRANSIENTSHOCK ANALYSIS ................... ....................................... 131

Anthoryr C. Melodia. David Taylor Model Basin. Washington, D.C.

TRANSPORTATION ENVIRONMENTAL MEASUREMENT AND RECORDING SYSTEM . .. 163Frank J. Holley, NASA Goddard Space Fhght Cvnter. Grecnbvit, M\tryland

DEVELOPMENT OF VELOCITY SHOCK RECORDER FOR MP \-,ULJRMENT OFSHIPPING ENVIRONMENTS ............................ . ............ 173

Matthew A. Venetos, U.S. Army Natick ,!.boraturis, Natick, .. laachusetts

ABSOLUTE CALIBRATION OF VIBRA',ON GENERATORS WITH TIME-SHARINGCOMPUTER AS INTF.GRAL PART OF SYSTEM ....... ...................... .... 183

B. F. Payie, National Bureau o' St..ndards, Washington, D.C.

EXPERIMENTAL TECHNIQUEN FOR OBSERVING MOTIO.N OF LXTENDIBLEANTENNA BOOMS, ..... .................. ............... 195

Donald J. Her- ifeid, N -,A GoddardSpace Fhght Center, Greenbelt, Maryl."nd'

DEVELOPMENT OF LOW-COST FORCE TRANSDUCER ....... ................... .. 203Marlyn W. Sterk, Sandia Corporation, Albuquerque, New Mexico, andJames A. Ellison, California Institute of Tecnnology, Pasadena, California

AUTOMATIC CALIBRATION AND ENVIRONMENTAL MEASUREMENT SYSTEMFOR LAUNCH PHASE SIMULATOR ....... ............................. ...... 07

Harry D. Cyphers and Frank J. Holley. NASA Goddard Space Flght Center,Cirvenbelt, Maryland

MICROMINIATURE INSTRUMENTATION AMPLIFIERS .......................... 215W. V. Bratkowski and P. F. Pittman, Westinghoube Research and DevelopmentCenter, Pittsburgh. Pennsylvania

INVESTIGATION OF PULSE X-RAY TECHNIQUES FOR STUDY OF SHOCK-WAVE-INDUCED EFFECTS IN SOIL .............. ................................. 225

Warren J. Baker. Frank J. Janza, and Eric H. Wang, Civil Engine•riag ',esearchFacility, University of New Mexico, Albuquerque, New, Mexico

!8

DISTRIBUTION . ................ ........................... 237

Bulletin 3(Part VII

Structural Reliability

ESTIMATE OF EFFECT OF SPACECRAFT VIBRATION QUALIFICATION TESTINGON RELIABILZTY ................................................. I

Clyde V. Stahle. Jr., The Martin Company, Baltimore, Maryland

S-IC RELIABILITY PROCRAM FROM STRUCTURAL LIFE VIEWPOINT .......... 19Roy L. Rich and James A. Roberts, The Boeing Company, New Orleans, Louisiana

STRUCTURAL RELIABILITY - PANEL SESSION ........... ....................... 27

Design Data and Methods

DYNAMIC ANALYSIS OF ATS-B SPACECRAFT ........................ 41Saul M. Kaplan and Victor Terkun, Hughes Aircraft Company, El Segundo, California

SPACECRAFT DESIGN FOR ATLAS TORSIONAL SHOCK TRANSIENT ........... 63Sol Davis, Fairchild Hiller, Republic Aviation Division, Farmingdale, Long Island,New York

COMPARISON OF PREDICTED AND MEASURED LAUNCH LOADS FOR SNAP 10A .... 73Everett A. Robb and A, P. Gelman, Atomics International, Canoga Park, California

GROUND- WIND-INfnUCED OSCILLATIONS OF GEMINI-TITAN AIR VEICLE ANDITS ERECTOR .. ......................................... 79

John E. Tcrmassoni and William H. Lambert, The Martin Company, Baltimore, Maryland

NOISE LEVEL MEASUREMENTS FOR IMPROVED DELTA, ATLAS/AGENA-D, ANDTAT/AGENA-D LAUNCH VEHICJ.ES ... ............................. 89

Lloyd A. Williams and William B. Teremak, NASA Godca.d Space Flight Center,Greenbelt, Maryland

THE "VACUUM SPRING" . ............ ................................... . . .. 103K. D. Robertson, U.S. Army Materials Research Agency, Watertown, Massachusetts

SELF-ADAPTIVE VIBRATION BALANCING DEVICE FOR HELICOPTERS ........ . . .. 113W. Eua-• 'oopeh, The Boeing Company, Morton 'Pt, ii ylvania

SHOCK RESeONSE OF ELECTRONIC EQUIPMENT CABINETS BY NORMALMODE METHOD ...................................................... 129

T. K. Hasselman and C. M. Hwang, TRW Systems, Redondo Beach, Cahfornia

DAMPED VIBRATIONS OF ELASC'ICALLY SUPPORTED RIGID BODY WITH COUPLINGBCTWEEN TRANSLATION AND ROTATION ....... ......................... ..... 135

Francis H. Collopy, ITEK Corporation, Lexington, Massachusetts

MISSILE HANDLING ANALYSIS ........... ................................. .... 145C. R. Brown and Alex J. Avis, Westlnghouse Ele,.tric Corporation, Sunnyvale, California

DISTRIBUTION ................ .......................................... . ... 53

84

Bulletin 37 IPart I

RECENT WORK ON SHOCK AT N. fC.R.E ...................................A. M. MacIntosh, Naval Constrv'-tion Research Establishment, Dunfermline,Fife, Scotland

STATE OF SHOCK IN THE NAVY, 1967 .................................. 15H. L. Rich, Naval Ship Research and Development Center, Washington, D. C.

NAVY DYNAMIC DESIGN ANALYSIS METHOD -- PANEL SESSION ..... :................. 33

SHOCK HARDENING RIVERINE WARFARE CRAFT FOR VIETNAM .................... 350. H. Porter and F. We'nberger, Ne 1 Ship Research and Development Center,Washington, D. C.

SHC'•< i'ESTING OF SONAR TRANSDUCERS-A STATUS REPORT ............... 63•,. M. Mayer and C. D. Johnson, Navy Underwater Sound ! *" iratory, New London,Connecticut

AN EXPLOSION SHOCK-TESTING METHOD FOR iHIPBOARD EQUIPMENT .......... 69R. R. Higginbotham, Naval Ship Research and Development Center, Portsmouth,Virginia

RIGID BODY RESPONSE OF NAVAL SURFACE VESSELS TO AIR BLAST ............. 717J. T. Irick, AVCO Corporation, Lowell, Massachusetts, S. Silverman and W. E. Baker,Southwest Research Institute, San Antonio, Texas

REACTION OF MILD STEEL TARGETS TO EXPLODING MUNITIONS .................. 97J. W. Apgar, Ballistic Research Laboratories, Aberdeen Proving Ground, Maryland

RESPONSE OF A MISSILE STRUCTURE UNDER HIGH VELOCITY IMPACT ... .:..... 115C. Riparbelli, General Dynamics/Pomona, Pomona, California

AIM4D/F4 CAPTIVE-FLIGHT VIBRATION LOADS AND ENVIRONMENTALMEASUREMENTS PROGRAM ......................................... 125

C. D. Knauer, Jr. and P. E. McHorney, Hughes Aircrpft Company, El Segundo,California

Bulletin 37Part II

Instrum.ntatiun and Analysis

PORTABLE LASER INSFIRUMENT FOR VIBRATION ANALYSIS ANDrRANSDUCER CALIBRATION ....... . ......... . ............ I .... ... .'., .- . . . I

G. A. Massey and R.: R. Carter, Sylvania Electronic Systems, Mountain View, California

IIIGH-1- REQUENCY MICROPHONE CALIBRATION USING A SUPERSONICFREE-FLIGHIT RANGF ..... ..... .. . . ". ... , .e . ....... ..... ... ... ... ý, 7, 1 • . 7

C. D. hlayes, Jet Propulsion Laboratory, Pasadena,. California, and R., C. BinderUniver• ity of Southern California. Los Angelus, California

METHOD OF MEASURING VIBRATORY DISPLACEMENTS IN TERMS OF ALIGIiT WAVELENGTH . . .,,. . , ... ..... . . ... .I , 1 ., . 1. . e ....... I . 13

J., L. Goldberg, National Standards Laboratory,, Sydn-y,: Australia

85

CALIBRATION OF ACCELEROMETERS BY IMPULSE EXCITATION AND FOURIERINTEGRAL TRANSFORM TECHNIQUES .................................. 17

J. D. Favour. The Boeing Company. Seattle. Washington

13IDIRECTIONAL S11OCK AND HIGH-IMPACT EFFECTS ON S;IOCK TRANSDUCERS .... 29V. F. De*Vost and P. S. Hughes. Naval Ordnance Laboratory. Silver Spring. Maryland

INFLUENCE OF FIXTURE STRESS CONCENTRATIONS ON RING ACCELEROMETERS .. 43J. A. Nagy and C. E. Henley, Jr.. NASA Goddard Space Flight Center.Greenbf.It, Maryland

SONAR TRANSDUCER VIBRATION REQUIREMENTS AND MEASUREMENT TECHNIQUES. 51G. M. Mayer and E. G. Marsh, Navy Underwater Sound Laboratory, New London,Connecticut

AU'TOMATED VIBRATION ANALYSIS .............. 57R. J. Pabich and W. H. Sellers. Raytheon Company. Bedford, Massachusetts

A COMPACT. LOW-COST SHOCK-SPECTRUM ANALYZER ..................... 65W. W. Mebane, Naval Ordnance Laboratory, Silver Spring, Maryland

DYNAMIC PHASE PLOTTING ................... 77T. E. Smart, Sandia Corporation. Albuquerque. New Mexico

RANDOM-VIBRATION-INDUCED ERRORS IN A MISSILE CAUSED BY NONLINEARINERTIAL ACCELEROMETERS ....................................... 87

N. A. Leifer, Bell Telephone Laboratories, Inc., Whippany. New Jersey

VIBRATION DISTRIBUTIONS IN MULTIPANEL STRUCTURES: COMPARISON OFMEASUREMENTS WITH STATISTICAL ENERGY PREDICTIONS ................. 99

E. F. Ungar and N. Koronajos. Bolt Beranek and Newman Inc., Cambridge.Massachusetts

CONSTANT BANDWIDrIH FM DATA SYSTEM DESIGNED FOR SATURN S-IVB/VVIBRATION TESTrS .. .......................................................... 109

D. F. Redford, Thiokol Chemical Corporation. Brigham City. Utah

DYNAMICS PORTION OF GEMINI AGENA TARGET VEHICLE ENGINE MODIFICATIONAND TEST PROGRAM (PROJECT SURE FIRE) ................................... 117

N. Angelopulos, Lockheed Missiles & Space Company, Sunnyvale, California

DYNAMIC ANALYSIS OF COMPLEX STRUCTURES ............................ 173M. D. Benton, G. K. Hobbs. Hughes Aircraft Company, El Segundo, California, andJ. It. Dickerson, University of Texas. Austin. Texas

Bulletin 37

Part IIIReproduced frombost available copy.

A)VANCES IN NU'MI:REOI.Oc',, .. . . . . . . . . .. .ll~t~ h ';td .•l.,•,nt. . . ..., ,... ... ... . . . ..'J. P-. Salt(vr. Roy-al Arm.,.-,' s.-..,h.ai . .- t yti,-;.t j.st-tblishm, nt. IOrt

INTIERNAL VIBRATION (MF I':;.VCI .'I- !C 1 -. '.l|I- U.N; .(I 'iL7 L.TING FROM ACOUSTICSI IAK INDUC-'.D i IxciND UL CE.....................................................

A. 1). 1lhuston, L dcl-heed Z'ii..ii -. S,,c, Ca.i.,,av. ".. * .l,', C;1Iii,.)r1a

RANDOM-VIBRAtION R- I*SPONS!.% IA. A :-'Ud .11l I. i, 011E•O-, I'YSICAL OISERVA-TOR Y: ElI.AGH1T. AGOUSTIC. .i' \'D VI RA LItNX I I..'[ . ...... ................. 2 1

WV. G. I'1lse;, NA.-% Idd rd " . ilit C.'rtt ,,r .. t. rylan8

86

RANDOM-VIBRATION TEST LEVEL CO•'£rPOL USING INPUf" AND TEST ITEMRESPONSE SPECTRA. *. .: ,.. .. . , ....... . .. .... ,.: ............. ... 47

A. J. Curtis and J. G. fierrera, Ilughc s A. r, raft Company, Culver City. California

RANDOM-FORCE VIBRATION TESTING. ................................ 61J, V. Otts and N. F. Hunter. Jr., Sanidii Curpo.ration, Albuquerque, New MeXico

CONTROL POINT AVERAGING FOR LAiRCE SPECIMEN VIBRATION TESTS ......... 75H. R. Berkman, Litton Systern3, Inc.,: Van Nuys.: California

VIBRATION ME'IHODS FOR MULrIPLF, RANDOM EXCIIATION................ ........ 89W. E. Noonan, McDonnell Comnpany, St. Louis, Missoiri

DYNAMIC TESTING OF FULL-SCALE SATURN LAUNCH VEHICLES .... . 99B. R. Jacobs, Northrop Nortronics. Huntsville, Alabama

BUFFET RESPONSE MIEASUREME•,NS 01' A SEVEN PERCENT AEROELASTICALLYSCALED MODEL OF VARIOUS TITAN III CONFIGURATIONS ............... 121

J. T. Uchtyama and F,, W. Peters, %I,., rt i-M•.rietta Corporation, Denver.: Colorado

HIGH-FORCE VIBRATION-TESTING OF I'tE SATURN S-IVB STAGE........... .. ... 137L. G. Smith,; McDonnell Douglas Corporatiiun, Huntington Beach, California

SIMPLIFIED METHOD OF CONDUCI'ING A DUAL RANDOM-VIBRATION INTEGRATEDSYSTEM TEST .... , , . . . . . ,., . ...... . . ,. ... ..... 151

J, G. Colt, Radio Corporation of America, Burlington,: Massachusetts

CONTROL STABILIZATION FOR MULI'IPLE SHAKER TESTS.......... ........ :. 155N. F. Hunter, Jr., Sandia Corporation,: Albuquerque. New Mexico, and J. 0. Helmuth,:Chadwick -Helnuth Company, Inc.. Monrovia, Caliturnia

THE SH1-*M SPRING IS9)LATOR . .. .. , ... .. ,.... ... 1t3L., Wallerstein,, Jr., Lord Manufacturing Company. Erie, Pennsylvania

rest Fc•ciities

ADVANCED COMBINED ENVIRONMENTAL TEST FACILITY . ........ ..: 175E. J, Kirchman and C., J., Arcilesi, NASA Goddard Space Flight Center,:Greenbelt, Maryland

DEVELOPMENT OF SIMULATED AIRCRAFT DELIVERY USING A ROCKET SLED ,,. 193W. R• Kampfe and K. M. Timmerman, Sandia Corporation, Albuquerque, New Mexico

AERODYNAMIC NOISE INVESTIGATION IN A SHORT-DURATION SHOCK fUNNEL...... 203D. 1• oss, Aerospace Corporation, El Segundo, Ctlifornia

IMPACT'ESTING WITH A FOUR-I::CH AIR GUN AND LEAD TARGETS ......... s..... 19H., J. D~vis, Harry Diamond Laboratories, Washington, D. C,

Bulletin 37

Part IV

Shock Analysis and Simulation

MEASUREMENT AND ANALYSIS OF SPACECRAFT SEPA.rZiTION TRANSIENTRESPONSE FOR MARINER-TYPE SPACECRAFT .... .. . ...... .., ............. . . . .I

P. Barnett, Jet Propulsion Laboratory, Pasadena, California

MECHANICAL SHOCK OF HONEYCOMB STRUCTURE FROM PYROTECHNICSEPARATION .....................-.................. . .. . .15

J. R. Olson, J. R. West, Jr., H. Himelblau, North American Rockwell Corporation,Los Angeles, California, C. D. Kniauer, Jr., and P. E. McHorney, Jr., Hughes AircraftCompany, El Segundo, Californ-a

87

SIMPLE STRENGTH CONCEPT FOR DEFINING PRACTICAL HIGH-FREQUENCYLIMITS OF SHOCK SPECTRUM ANALYSIS .................................. 43

M. Gertel and R. Holland, Allied Research Associates, Concord, Massachusetts

TRANSIENT VIBRATION SIMULATION ...... ................................. 59T. E., Fitzgerald and L. C. Kula, The Boeing Company, New Orleans, Louisiana

PREDICTING MECHANICAL SHOCK TRANSMISSION ........ . .................... 65J. E. Manning and K Lee, Bolt Beranek and Newman Inc., Cambridge. Massachusetts

SHOCK DAMAGE MECHANISM OF A SIMPLE STRUCTURE ........................ ,... 71L. T. Butt, Naval Ship Research and Development Center, Portsmouth, Virginia

GENERAL MOTORS ENERGY-ABSORBING STEERING COLUMN AS A COMPONENTOF SHIPBOARD PERSONNEL PROTECTION .... ............................. 79

J. T. Hawkins and A. E. Hirsch, Naval Ship Research and Developmeat Center,Washington, D.C.

DESIGN OF HEAVY WEIGHT SHOCK TEST FACILITIES ............................ ... 85C. G. Schrader, San Francisco Bay Naval Shipyard, San Francisco. California

DERIVATION AND IMPLICATIONS OF THE NAVY SHOCK ANALYSIS METHOD.......... 91F. J. Heyrnann, Westinghouse Electiic Corporation, Lester., Pennsyl, Ania

DYNAMIC ANALYSIS OF A TYPICAL ELECTRONIC EQUIPMENT CABINETSUBJECTED TO NUCLEAR-WEAPON-INDUCED SHOCK ........................... 97

J. H. Putukian, Kaman Avidyne, Burlington, Massachusetts

DEVELOPMENT OF A ZERO-G COAST PHASE AIR GUN .......... ,..... .... 103S., Rodkin, General Electric Company, Philadelphia, Pennsylvania

DEVELOPMENT OF A MISSILE LAUNCH SHOCK TEST FACILITY FOR SHILLELAGH... I1IR. W. Stevens, Martin-Marietta Corporation, Orlando, Florida

USE OF EXPLODING WIRE APPARATUS FOR LABORATORY SIMULATION OFSHOCK WAVES ....... ............................................ 117

F., B. Safford, Mechanics Research Inc., El Segundo, California, and R. C. Binder,,University of Southern California, Los Angeles,. California

NIKE-X SHOCK TUBE FACILITY .. ................. ....... .... 127R. G. Donaghy and J, J. Healy, Office of the Chief of Engineers, Department of theArmy, Washington, D. C.

DESIGN AND PERFORMANCE OF DUAL MODE SHOCK MACHINE ,.: ...... ........ 137W. D.: Everett, Na'al Missile Center, Point Mugu, California

Air Blast and Ground Shock

INFLUENCE OF SHIP MOBILITY ON INTERNAL FORCES PRODUCED BY BLAST ........ 143A. Chajes,. F J. Dzialo, and M. P. White, Department of Civil Engineering,:University of Massachusetts, Amherst,: Massachusetts

DYNAMIC BEHAVIOR OF SHIPBOARD ANTENNA MASTS SUBJECTED TO BLAST-GENERATED OVERPRESSURES .......•. . . ......... .................... , 151

F., A., Britt and R. H, Anderson,, Mechanics Research,, Inc.,, El Segundo,: California

*HARDENED ANTENNA TECHNOLOGYD.ý A. Benson, A. F. Gurdo, R, W. Mair and D, J. Waters,, Rome Air Development Center,:Griffiss AFB., New York

ABSOLUTE UPPER AND LOWER BOUNDS FOR THE CRITICAL BLAST LOADINGENVIRONMENT OF TARGET ELEMENTS AND SYSTEMS ... .E ........ 169

E., Sevin and W., D, Pilkey, lIT Research Institute, Chicago, Illinois

*This paper appears in Shock and Vibration Bulletin 37, Supplement.

88

ELASTIC-PLASTIC COLLAPSE OF STRUCTURES SUBJECTED TO A BLAST PULSE .... 177W. B. Murfin, Sandia Corporation, Albuquerque. New Mexico

INTERNAL LOADING OF STRUCTURES BY BLAST WAVES .............. . .. ........ 185J. F. Melichar, Ballistic Research Laboratories, Aberdeen Proving Ground, Maryland

EFFECTS OF SLIDIITG ON BLAST LOADS REQUIRED TO OVERTURN STRUCTURES ... 193C. E. Gebhart, liT Research Institute, Chicago, Illinois

USE OF DETONABLE GAS EXPLOSIONS FOR BLAST AND SHOCK STUDIES ............. 199M. R. Johnson and M. J. Balcerzak, General American Research Division, Niles, Illinois

INCORPORATION OF SHOCK PROTECTION IN EXISTING ABOVEGROUND CYLINDRICALSTRUCTURES SUBJECTED TO NUCLEAR BLAST ........................... 213

E. Cohen, S. Weissrman and L. Sanchez, Ammann and Whitne-,, New York, New York

Bulletin 37

Part V

Large Tibroacoustic Test Facilities

VIBROACOUSTIC ENVIRONMENTAL SIMULATION FOR AEROSPACE VEHICLES ........K. McK. Eldred, Wyle Laboratories, El Segundo, California

"*RTD SONIC FATIGUE FACILITY, DESiGN AND PERFORMANCE CHARACTERISTICSA. W. Kolb and H., A.. Magrath, Air Force Flight Dynamics Laboratory, Wright-PattersonAFB., Ohio

OPERATIONAL CHARACTERISTICS OF A I00,000-CUBIC-FOOT ACOUSTIC REVER-BERATION CHAM BER ..... - . . -. .,,. . ., .. "......., I I,., , 1 .; 1 .. 1. ,.ý .: ,. I. . ",. . " . • ., . 13 '

F, M. Murray,, Wyle Laboratories, Huntsville, Alabama

CONCEPT, DESIGN, AND PERFORMANCE OF TIHE SPACECRAFT ACOUSTICLABORATORY ....................... ....... .. ,. .. ..... .. 25

R. J. Wren, W. D. Dorland, J. D. Johnston, Jr., NASA Manned Spacecraft Center,Houston, Texas,: and K., McK., Eldred,, Wyle Laboratories, El Segundo,: California

THEORETICAL STUDY OF ACOUSTIC SIMULATION OF IN-FLIGHT ENVIRONMENTS :... 55R. W. White, Wyle Laboratories, Huntsville, Alabama

DATA HANDLING METHODS FOR LARGE VEHICLE TESTING ........ .. ,77D.: J., Bozich,: Wyle Laboratories, Huntsville, Alabama

DEVELOPMENT AND VERIFICATION OF THE VIBRATION TEST REQUIREMENTSFOR THE APO- LO COMMAND AND SERVICE MODULES.: -, , - e e ...... 89

r. E. Newbrough, General Electric Company, Houst-in, Texas,, R. A. Colonna, NSAManned Spacecraft Center, Houston, Texas,, and J. 1%. West,, Jr., North American RockwellCorporation, Downey, California

DEVELOPMENT AND VERIFICATION OF THE AOOLLO LUN R MODULE VIBRATIONTEST REQUIREMENTS ...... .:... ..... . ......., ,. ,- ".1 .. .,. , ,, . . . ,. . ... ,,.• 1, 05D,, E Newbrough, General Electric Company, Houston, Texas,, M., Bernstein and

E., F.ý Baird,, Gruirman Aircraft Ergineering Company,, Bethpage,, New York

*'This paper appears in Shock and Vibration Bulletin 37, Supplement,

89

SATURN S-Il, S-IVB, AND INSTRUMENT UNIT SUBASSEMBLY AND ASSEMBLYVIBRATION AND ACOUSTIC EVALUATION PROGRAMS ........................ 117

R. W. Schoc , J. M. Everitt, NASA Marshall Space Flight Center, Huntsville. Alabama,and J. R. Stt, Brown Engineering Company, Huntsville, Alabama

DEVELOPMENT OF ACOUSTIC TEST CONDITIONS FOR APOLLO LUNAR MODULEFLIGHT CERTIFICATION ............................................ 139

W. D. Dorland, R. J. Wren, NASA Manned Spacecraft Center, Houston, Texas, andK. McK. Eldred, Wyle Laboratories, El Segundo, California

*FACILITY SONIC FATIGUE PRCOF TESTING0. F. Maurer, Air Force Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio

VIBROACOUSTIC TEST MET, )S TOR VIBRATION QUALIFICATION O' APOLLOFLIGHT HARDWARE ... ....................... I., ........ 153

R. W. Peverley, General Electric Company, Houston, Texas

ACOUSTICAL QUALIFICATION OF S-IC FIN STRUCTURES ....................... 167C. J. Beck, Jr., The Boeing Company, Huntsville, Alabama, and D. R. Kennedy, BrownEngineering Company, Huntsville, Alabama

*SIMULATION OF ACOUSTIC FATIGUE FA.. URE IN THE WIDEBAND NOISE TESTFACILITY OF THE AIR FORCE FLIGHT DYNAMICS LABORATORY

R. C. W. van der Heyde, Air Force Flight Dynamics Laboratory, Wright-PattersonAFB, Ohio

REAL-TIME COMBINED ACOUSTIC-VACUUM TESTING OF SPACECRAFT ............ 175L.; J. Demas, NASA Goddard Space Flight Center, Greenbelt, Maryland

Bulletin 37

Part Vi

lelitcopte r Env roaments

HELICOPTER VIBRATIONS . . .. ..... ........C. D. Roach, U.S., Army Aviation Materiel Laboratories. Fort Euistis. Virginia

IIELICOPTER VIBRATION -- A MAJOR SOURCE., IFS PRED)ICIION AND AN AIPPROACIITO ITS CONTROL ....... . ....... .. ......... ............... .... . .... ....

R, P. White,, Jr., and F.. A. DuWa!dt,: Cornell Aeronautical Laboratory. Inc..Buffalo, New York

*"IN-FL1GIIT VIBRATION AND ACOUS'IC STUDY ON l1IF- U|l-IF lIELICOPIERC. E., Thomas and J. T., Ach, Air Force Flight Dynamics Laborat,)ry,, ' right-Patterr•onAFB,, Ohio

HELICOPTER FUSELAGE VIBRATION PREDICTION BY SI IFFNESS MOBILI I Y SMIE1 IODS.. I 9J. J, Sciarra,, The Boeing Company,: Morton, Pennsylvania

ISOLATION OF IIELICOPIER RO FOR-INDUCED VIBRA rIONS USING ACTIVE EI.EMEN I'S .. 9P.. C., Calcaterra and D. W., Schubert,, Barry Research & Development,,Watertown,, Massachusetts

HYBRID VIBRATION-ISOLATION SYSTEM FOR ItELICOPI'ERS .............D, A.: Bieb and T. M, Yang,ý Bolt Beranek and Newman Inc., Los Angvls,, California

"'This paper appears in Shock and Vibration Bulletin 37.: Supplement.,

90

RECENT ADVANCES IN THE STUDY OF SYNCHRONOUS VIBRATION ABSORBERS ...... 49A., V. Srinivasan. Kaman Corporation, Bloomfield, Connecticut

OPTIMIZING THE DYNAMIC ABSORBER TO INCREASE SYSTEM DAMPING ........... 57G, K. Jones, NA!A Goddard Space Flight Center, Greenbelt., Maryland

APPLICATION OF THE DYNAMIC ANTIRESONANT VIBRATION ISOLATOR TOHELICOPTER VIBRATION CONTROL ........................ ...... 63

R. Jones and W. G. Flannelly, Kaman Corporation, Bloomfield, Connecticut

Bulletin 37Part VII

Environmental Data

SURVEY OF THE CARGO-HANDLING SHOCK AND VIBRATION ENVIRONMENT.......... IF. E. Ostrem, General American Research Division, Niles., Illinois

A NEW LOOK AT TRANSPORTATION 'vIBRATION STATISTICS . .......... . 19J. W., Schlue and W. D. Phelps, Jet Propulsion Laboratory,, Pasadena, California

RECENT SHOCK AND VIBRATION MEASUREMENTS ON THE M-151 (JEEP) VEHICLE .. .: 39R. D. Brunnemer and G. M. Pomonik, Hughes Aircraft Company, Canoga Park, California

LATERAL IMPACT SHOCK DURING SHIP LOADINC OF THE A3 POLARIS MISSILE .,.. 67E. G., Fischer, C. R. Brown, and A. J., Molnar, Westinghouse Electric Corporation,Pittsburgh,, Pennsylvania

*FF-4C VIBRATION AND ACOUSTIC ENVIRONMEN£ STUDY

J., F., Dreher, Air Force Flight Dynamics Laboratory,, and W. D, Hinegardner., SystenEngineering Group, Wright -Patterson AFB,, Ohio

EMPIRICAL CORRELATION OF FLIGHT VEHICLE VIBRATION RESPONSE. .2 .. ........ 77W. H. Roberts,, Martin-Marietta Corporation, Orlando, Florida

VIBRATION DATA SUMMARY OF MINUTEMAN WING VI FLIGHT TEST MISSILES .,. .. 93R. R. Burnett and R., E. Morse, TRW Systems, Redondo Beach,. California

SPACECRAFT VIBRATION, COMPARISON OF FLIGHT DATA AND GROUND TEST DATA .. , 173G. Kachadourian,: Gene'al Electric Company, Philadelphia, Pennsylvania

MEASUREMENT AND ANALYSIS OF GUN FIRING AND VIBRATIC' , ENVIRONMENTSCF THE RIVER PATROL BOAT ........ 2)5

R. S. Reed, Naval Ordnance Laboratory,. Silver Spring,, Maryland

*RESPONSE OF THE AIM-9D (SMflEWINDER) MISSILE TO CAPTIVE-FLIGHT VIBRATIONW. W., Parmenter. N=•ai bv'? ipons Center, China Lake, C;.hifornia

SCALE-MODEL WIND-TUVNEL ACOUSTIC DATA.......... ........ . ........ .......... 221J., R. Baratono and - A. Smith, Martin-Marietta Corporation,: Denver,2 Colorado

A

"Thiis paMper aLppeadrs in Shock and Vibration B4ulletin 37, Supplenaent.

91

II

Builetin 38Part I

Vibration Analysis

VIBRATION RESPONSES OF. SIMPLE CUJRVED PANELS TO HIGH INTENSITYRANDOM AND DISCRETE FREQUENCY NOISE .....................................

C. E. Rucker, NASA Langley Research Center, Hampton, Virginia

RANDOM VIBRATION USING FINITE ELEMENT APPROACH . ,. .......... ,.......... 7K, K. Kapur, Ching-U Ip and E., P. Howard, Aerospace Corporation,San Bernardino, California

FREQUENCY ANALYSIS OF REPETITIVE BURSTS OF RANDOM VIBRATION ............. 17W. E. Noonan, McDonnell Company, St., Louis, Missouri

SIMPLIFIED RANDOM VIBRATION COMPUTATIONS ............................... ,.27LaVerne W., Root and A. S. Henry, Collins Radio Campany, Cedar Rapids, Iowa

CONCENTRATED MASS EFFECTS ON THE VIBRATION OF CORNERSUPPORTED RECTANGULAR PLATES ................................... 37

R., L. NBarnoski, Measurenyent Analysis Corporation, Los Angeles, California,aad T., D. Schoessow, ,-erospace Corporation, El Segundo, California

VIBRATION OF ECCEN'IRICALLY STIFFENED PLATES ......... .......... 45B. R, Long, Defence Research Establishment Suffield, Ral.iton, Alberta, Canada

CRACK DETECTION IN A STRUCTURAL BEAM THROUGH CROSS-CORRELATION ANALYSIS ................................ 55

F., Biganoff, Baganoff Associates, Inc., St. Louis, Missouri, andD. Baganoff, 3tanford University, Stanford, California

A THEORETICAl MODAL STUDY FOR TH. -,L I'ERAK-. VIBRATIONS OF BARSHAVINC VARIABLE CROSS SECTION AND FREE END CONDITION. ,.,. . ._ ........ ,. . .. , 67

A. F. Witte, Sandia Corporation, Albuq,,erque, New Mexico

*VARIABLE RESONANT VIBRATION GENERATOR FOR EXPERIMENTA 1,VIBRATIONAL, ANAL'.'SIS OF STRUCTURES

H, Soulant and S. lee, Nav'i Ship Research and Development Center, Washington, D.C.,

*THE PREDICTION OF INTERNAL VIBRATION LFEVEIS OF FLIGHTVEHICLE EQUIPMENT

R. W. Sevy and D. L. Earls, Air Flbrce Flight Dynamics Laboratory,Wriglt-Patterson AF!3, Ohio

SATURN V COMPONfNT VIBRATION TESTS USING l EGMENTED SIIELISPECIMENS ....... 87C. livang, Northrop Corporation,. Norair Division, Hawthorne, California, andC., E., Lifer, NASA, Marshall Spact Flight Center, Huntsville, Alabama

AN APPLICATION OF FIOW(RAPHS TO TIlE FREE VIBRATION OF STRUCTURES .... 99P. M., Wright, Univers.itV of Toronto, Toronto, Canada, andC., C. Feng, University of Colorado, Boulder, Colorado

DUAL SPECIFICATIONS IN: VIBRATION TESTING .,. ... 109W. B., Murfin, Sandia Corporation, Albuquerque, New Mexico

SUBSTITUTE ACOUSTIC TESTS . , ...... .. ...... , c ....... . , . 15T. D. Scharton and T., M. Yang, Bolt Beranek and Newman Inc., Van Nuys, California

*This paper appears in Shock and Vibration Bulletin 38, Supplementt

92

SIMPLIFIED METHOD OF CALCULATING NATURAL FREQUENCIES ANDNORMAL MODES OF VIBRATION 1."1 -'l2IPS ............ 125

H. B. Ali and H. F. AlrA.. Naval ý,, :p Research and Development Center,Washington, D.C.

RESPO4SE SPECTRA FOR SWEEPING SINUSOIDAL EXCITATIONS .................... 133D. L. Cronin, TRW Systems Group, Redondo Beach. California

BuUflein 38Part 11

Structural Analysis

AN OVERALL VIEW OF STRUCTURAL DYNAMICS ....................... • • .,.. . .....

R. M. i.'.ains, Washington Universi'.y, St. Louis, Missouri

DYNAMIC SUBSTRUCTURES NIETHO ) F OR SHOCK ANALYSIS ...... ........

M. Pakstys, Jr., General Dynamic s, Electric Boat Division, Groton, Connectict

IDENTIFICATION OF COMPLEX ýTRUC1J'ES USING NEAR-RESONANCE TESTING......... 23J. P. Raney, NASA Langley Reibearch Center, Hampton, Virginia

PROPAGATION OF LONGITUDINAL STRESS WAVES IN 2. COMPLEXBAR-TYPE STRUCTURE .................... ....... • .. .......... 33

D. L. Block, Martin Marietta Corporation, Orlando, Florida

ALSEP SYSTEM STRUCTURAL DYNAMICS STUDY ............................. 47M, M. Bahn, Aerospace Systems Division, The Bendix Corporation,Ann Arbor, Michigan

REDUCING THE NUMBER OF MASS POINTS IN A LUMPED PARAMETER SYSTEM 57"M. T. Soifer and A. W. Bell, Dynamic Science, "'onrovia, California

LATERAL DYNAMIC RESPONSE OF LARGE SUBSYSTEMS DURINGLAUNCH TRANSIENT CONDITIONS ..... . . . .. ... .... •.. 67

J. S. Gaffney and P., E. Campos, Atlantic Research Corporation,Costa Mesa, California

A NEW APPROACH TO rHE INTERACTION PROBLEMS OF FLUID-FILLEDELASTIC MEMBRANE SHELLS. . e..................' ......... . ... .. 79

C. L. Tai and S. Uchiyama, Space Division, North American Rockwell Corporation,Downey. California

STRUCTURAL. AND VIBRATION ANAI,YSIS OF NAVY CLASS HIGH IMPACT,MEDIUM WEIGHT SHOCK TESTS e. . .. e . . ..... .. ...... ,, ..... .. . ... . .e, e, 95

W. P. Welch and P, D., Saunderq, Westinghouse Electric C3rporation,Sunnyvale, California

TRANSIENT RESPONSES OF A LINEAR MECHANICAl, SYSTEM BY US' OFEXPERIMENTALLY DETERMINED UNIT IMPULSE RESPONSES . • .,., . .e.......... :.: 1-. 107

V. P. Warkulwiz, General Electric Company, Valley Forge SpaceTechrology Center, Pennsylvania

A MOMENT TECHNIQUE FOR SYSTEM PARAMETER IDENTIFICATION .......... :.: ..... 119F. Kozin and C. H. Koin, Midwest Applied Science Corporation,West Lafayette, Indiana

REINFORCED CONCRETE BEAM RESONANCES, . : . .. . .. ,•.. 133F. G. Krach, Barry Control,, Division, Barry Weight Corporation,Watertown, Massachusetts

93

STRUCTURAL DYNAMIC ANALYSIS OF THE MARINER MARS '69 SPACECRAFT ........... 139H. J. Holbeck, Jet Propulsion Laboratory, Pasadena. California, andT. D. Arthur* and W. J. Gaugh, Northrop Systems Laboratory.Northrop Corporation. Hawthorne, C Jlifornia

LINE SOLUTION TECHNOLOGY AS A GENERAL ENGINEERING APPROACH TO THESTATIC, STABILITY, AND DYNAMIC RESPONSE OF STRUCTURAL MEMBERS ANDMECHANICAL ELEMENTS ................. 157

W. s). Pilkey, HT Research Institute, Chicago. ilinois, and R. Nielsen, Jr.,'iepartr,,ent of Transportation. Washington, D.C.

UPPER AND LOWER BOUNDS TO BENDING FREQUENCIES OF NONUNIFORM SHAFTS,AND APPLICATIONS TO MISSILES ...................................... 169

N. Rubinstein, V. G. Sigillito and J., T. Stadter, Applied Physics Laboratory,The Johis Hopkins University, Silver Spring, Maryland

DAMAGE PR, DICTION FOR OPEN-FRAME STRUCTURES SUBJECT TOLIQUID PRt PEI.LANT EXPLOSIONS ................................ I.......... 177

G. C. Kao ind V. M. Conticelli, Wyle Laboratories, Huntsville, Alabama, and"M. J. Rose ifielc:, U.S. Army Corps of Engineers. Ohio River DivisionLaboratori -s, Cincinnati, Ohico

SIMPLIFIED DYNAMICS OF HARDENED BURIED BUILDINGS,.: ......... 1...... 1873. V. Poppitz, Bell Telephone Laboratories, Inc., Whippany, New Jersey

INFLUENCE "OEFFICIENT MATRIX QUICK-CHECK PROCEDURE............,............ 205G W,. Bishop, Bishop Engineering Company, Princeton, New Jersey

Mechanical Impedance

DETERMINATION OF FIXED BASE NATURAL FREQUENCIES OF DUAL FOUNDATIONSHIPBOARD EQUIPMENTS BY SHAKE TESTS .......................... 209

L. P. Petak and G., J. O'Hara, Naval Research Laboratory, Washington, D.C.

*VIBRATION TRANSMISSION METHODS FOR FOUNDATION STRUCTURESE., V. Thomas, Annapolis Division, Naval Ship Research and Developmint Center,Annapolis, Maryland

VIBRATION ANALYSIS OF A STRUCTURAL. FRAME USING THE Mr TIOD OF MOBIITY,, , ,19J.: Verga, Har.eltine Corporation, lattle Neck, New York

APPlICABIIITY OF MECHANICAL ADMITTANCE TECHINIQUES .:. .. .. 2.1....... .. ... 1D. U. Noiseiix and E, B, Meyer, Bolt Btranek and Newman Inc.,Cambridge, Massachusetts

APPIICATION OF THlE MECHANICAL, RECEP rANCE COUPLING PRINCIPIETO SPACECRAFT SYSTEMS.. ......... .... 9

F. Heer, Jet Propulsion 1,tl oratory, Pasadena, California, andL,. D..Ctites, Rice University,, Ilouston, Texas

A VERIFICATION OF TIlE PRACTICAl.ITY ,'i" PREDICTING IN rERFACE DYNAMICAL,ENVIRONMENTS BY THE USE OF IMPEDANCE CONCEPTS ................. . ...... 249

F, J., On, NASA, Goddard Space Flight Center, Greenbelt, Maryland

EXPERIMENTAL I'ECIINIQUE FOR DETERMINING FIXED-BASE, NATURAL FREQUENCIESOF STRUCTURES ON SINGl,E NONRIGID ATTACHIMIENT POINrS ........... 2. ,

G, M.- Remmers, Naval Research l.aboratory, Washington, D.C.,

DETERMINATION OF MODAI. MASS FROM rEST DATA ............ , ...... 2711, P. Vatz, Brown Engineering, A Teledyne Company, Huntsville, Ali.mint

"*This paper appears in Shock and Vibration Eulletin 18, Supplement.,

94

Builetin 38Pat III

Dampaing and Isolation

DESIGN OF A DAMPED MACHINERY FOUNDATION FOR HIGH-SHJCK LOADING ........E. V. Thomas, Annapolis Division, Naval Ship Research and Development Center,Annapolis, Maryland

CONSTRAINED LAYER DAMPING WITH PARTIAL COVERAGE........ 5..... ...... ......

D. S. Nokes and F. C. Nelson, Tufts University, Medford, Massachusetts

THE EFFECTS OF ROTATORY INERTIA AND SHEAR DEFORMATION ON THEFLEXURAL VIBRATIOnS OF A TWO-LAYERED VISCOELASTIC-ELASTIC BEAM ........... 13

T., Nicholas. Air For,.e Materials Laboratory, Wright-Patterson AFB, Ohio

METHODS OF DAMP'NG VERY STIFF STRUC rURAL MEMBERS . ...., . ....... : *......... 29H. T. Miller, Lord Manufacturing Company, Erie, Pennsylvania

THE OPTIMUM DESIGN OF FIVE-PLY VISCOELASTIC ISOLATION FLEXURESFOR POINT4INERTIA LOADING 37

:. A. Frohrib, University of Mmnnesota, Minneapolis, Minnesota

APPLICATION OF DAMPING DEVICE FOR CRITICAL SPEED CONTROL ............ . 45J. F. Mullen and M, R, Kulina, Curtiss-Wright Corporation, Wood-Ridge, New Jersey

DEVELOPMENT OF PRACTICAL TUNED DAMPERS TO OPERATE OVERA WIDE-TEMPERATURE RANGE. ........................................ 57

A. D. Nashif, Univer-'.v of Dayton Research Institute, Dayton, Ohio

MULTIFREQUENZ'7. (ESPONSE OF VISCOELASTIC DAMPERS........ ............... ..... 71BR, K. Newman and D. C, Kraft, University of Dayton, Dayton, Ohio

THE CRITICAL DAMPING CALCULATOR AND A COMPARISON OF SELECTEDSTRUCTURAL DAMPING EVALUATION SYSTEMS .. e ................. . . 89

B. E. Douglas, Annapolis Division. Naval Ship Research and Development Center,Annapolis, Maryland

FORCED RESPONSE OF LUMPED-PARAMETER SYSTEM WITH APPLICATIONS TOMISSILE DYNAMICS .................. . ...... , .. . .... ..... .... .. ...... q5

J. D. Sowers, Chrydler Corporation Space Division, New Orleans, Louisiana

A NONFLUID VELOCITY DAMPER .. .................... IllW. G. Flannelly, Kaman Aircraft Division,, Kaman Corporation,, Bloomfield,: Connecticut

THE DYNAMIC RESPONSE OF LINEARLY VISCOEI.ASTIC CYL.INDRICAL SHELLSTO PERIODIC OR TRANSIENT LOADING ......................................... 121

E. A. Fitzgerald, Missile and Space Systems Division,: McDoy,nell Dougla.•Corporation, Santa Moni; a, California

DAMPING OF MUI.TISPAN STRUCTURES BY MEANS OF VISCOLI.ASI IC LINKS I I •D. IL G. Jones,, Air Force Materials Laboratory, Wright-Patterson AFP Ohio

DAMPING MEASUREMENTS ON SOFT VISCOEIASTIC MArERIAIS USINGA TUNED DAMPER TECHNIQUE ....................... .............. 151

C, M, Cannon and A. D. Na,;hif, University o0 Dayton, Diyton,: Ohio, andD. I. G.. Jones, Air Force Materials l.aboratory, Wright-Pattv r.,on AFB,- Ohio

AIRCRAFT S'JRUC rURAl. RESPONSE DUE FO GROUND IMPACT ........... ....... 165J. D, Weber, Convair Division of General Dynami.s,: San Diego California

95

EFFECT OF TEMPERATURE ON THE VISCOELASTIC HIGH POLYMER MATERIALS .... 175J. M. Ohno, Aerc, ipace Systems Division, The j3endix Corporation,Ann Arbor, Michigan

BROADBAND EXTENSIONAL DAMPING MATERIALS ............................. 199D. R. Blenner and T., J. Duaek, Lord Manufacturing Comp-kiy, Erie, Pennsylvania

A SINUSOIDAL PULSE TECHNIQUE FOR ENVIRONMENTAL VIBRATION TECTIN ........ 207J. T. Howlett and D, J. Martin, NASA, Langley Resear"h -,enter, Hampton, Virginia

Isolation

A STUDY OF THE PERFORMANCE OF AN OPTIMUM SHOCK MOUNT ............ 213K. T. Cornelius, Naval Ship Research and Development Center, Washington, D.C.

AN INVESTIGATION OF THE PERFORMANCE OF GAS-BEARING MACHINERYSUBJECTED TO LOW-FREQUENCY VIBRATION AND SHOCK......................... 221

P. W. Curwen and A., Frost, Mechanical Technology Inc., Latham, New York

AN EXPERIMENTAL INVESTIGATION OF AN ACTIVE VIBRATION ABSORBER..... ..... .236T. D. Dunham, Southwest Research Institute, San Antonio, Texas, andD., M., Egle, University of Oklahoma, Norman, Oklahoma

INTEGRATED SHOCK AND ACOUSTIC MODULAR DESIGN CONCEPTlOR SUBMARINE, . .... .......... 243

M., Pakstys, 'r. and G.. A., Ziegra, Electric Boat Division of General Dynamics,

Groton, Connecticut

CYCLIC DEFORMATION CREW ATTENUATOR STRUTS FOR THEAPOLLO COMMAND MODULE .. . . ....................... 255

D. L. Platus, Mechanics Research, Inc., El Segundo, California

DEVELOPMENT OF THE KINEMATIC FOCAL ISOLATION SYSTEM FORHELICOPTER ROTORS ........ . _ .. ......... 263

R. W, Balke, Bell Helicopter Company, Fort Worth, Texas

A TOOL FOR PARAMETRIC ANALYSIS OF COMPLEX ISOLATION SYSTEMS .......... •.285P. J. Jones and F. A., Smith, Martin Marietta Corporation, Denver, Colorado

AN ACTIVE STABILIZATION SYSTEM FOR VEHICLES AND OTHER MASSIVE BODIES.,.... 317T., H., Putmar., Westinghouse Research Laboratories, Pittsburgh, Pennsylvania

CRASH CONSIDERATIONS IN THE DESIGN OF THE NEW YORK STATE SAFETY SEDAN .. , 325S., Davis and N. B., Nissel, Fairchild Hiller, Republic Aviation Division,Farmingdale, L.I., New York

Bulletin 39Part I

AN INTRODUCTION TO THE BASIC SHOCK PROBLEM ....................F. Weinberger and R. Heise, Jr., Naval Ship Research and DevelopmentCenter, Washington, D.C.

DESIGN INPUT DERIVATION AND VALIDATION .............. ...................... 13R. 0. Belsheim, G. 3 O'Hara and R. L. Bort, Naval Research Laboratory,Washington, DC.

SHOCK DESIGN OF NAVAL BOILERS ..................................... .5D. M. Gray, Combtistion Engineering, Inc., Windsor, Connecticut

96

MACHINERY DESIGN FOR SHIPBOARD UNDERWATER SHOCK .............. 33G. W. Bishop, Bishop Engineering Company, Princeton, New Jersey

SHOCK DESIGN OF SHIPBOARD STRUJCTURES ...... ........................ ..... 39R. 3. Delia Rocca and N. R. Addonizio, Gibbs and Cox, Inc., New York, New York

REVIEW AND APPROVAL OF DYNAMIC ANALYSIS ............ .................... 45M. J. Macy and L. A. Gordon, Supervisor of Shipbuilding, Conversion and Repair,USN, Brooklyn, New York

COMPUTER AIDED DESIGN - ANALYSIS FOR SHIPBOARD UNDERWATER SHOCK . . . 55M. Pakstys, Jr., General Dynamics, Electric Boat Division, Groton, Connecticut

CURRENT NAVY SHOCK HARDENING REQUIREMENTS AND POLICY ................. 65J. R. Sullivan, H. H. Ward and D. M. Lund, Department of the Navy,Naval Ship Syste.ms Command Headquarters, Washington, D.C.

SHOCK DESIGN AND TEST QUALIFICATION OF SHIPBOARD SYSTEMS/COMPONENTS- PANEL SESSION ............ .............................. 71

':'HARDENING OF SURFACE SHIPS AND SUBMARINES FOR ADVANCED SEA-BASED DETERRENCE .................................... 93

H. L. Rich, Naval Ship Research and Development Center, Washington, D.C.

TOWARD A MORE RATIONAL BLAST-HARDENED DECKHOUSE DESIGN ..... ........ 101Shou-ling Wang, Naval Ship Research and Developme.nt Center, Washington, D.C.

COMPUTATION OF THE MOBILITY PROPERTIES OF A UNIFORMBEAM FOUNDATION .................. .. .......... ................. ... 123

J. E. Smith and R. J. Ha'ners, Naval Ship Research and Development Center,Annapolis, Maryland

AN ANALYTICAL INVESTIGATION OF THE DAMPING OF RADIAL VIBRATIONSOF A PIPE BY CONSTRAINED VISCOELASTIC LAYERS USING AXIAL STAVES 143

R. A. DiTaranto, PMC Colleges, Chester, Pennsylvania, and W. Blasingane,Naval Ship Research and Development Center, Annapolis, Maryland

*DAMPED CYLINDRICAL SHELLS AND DYNAMIC SYSTEMS EFFECTS ...... ..... 155B. E. Douglas and E, V. Thomas, Naval Ship Research and Development Center,Annapolis, Maryland

APPLICATION OF SPACED DAMPING TO MACHINERY FOUNDATIONS .............. 167J. R. Hupton, General Dynamics, Electric Boat Divisiun, Groton, Connecticut,H. T. Miller and G. E, Warnaka, Lord Manufactiring Company, Erie, Pennsylvania

*ROCKET SLED TESTS OF THE AGM-12 "BULLPUP" MISSILE ............... 175Robert D. Kimsey, Naval Missile Center, Point Mugu, California

AIM-4D FLIGHT MEASUREMENT PR.)GRAM ........ ......... ................... 195R. P. Mandich and W. G. Spalthoff, Hughes Aircraft Company, Canoga Park, California

*AEROELASTIC ANALYSIS OF A FLEXIBLE RE-ENTRY VEHICLE: ...... ....... .. . IH. Saundirs and A. Kirsch, General Electric Company, Re-Entry SystemsDepartment, Philadelphia, Pennsylvania

*This paper not presented at Symposium.

97

Bulletin 39Part H1

Vibration

ELECTRICAL GENERATION OF MOTION IN ELASTOMERS ................. IS. Edelman, S. C. Roth and L. R. Grisham, National Bureau of Standards.,Washington, D.C.

CONTROLLED DECELERATION SPECIMEN PROTECTION SYSTEMS FORELECTRODYNAMIC VIBRATION SYSTEMS ............. .......................... 11

Lawrence L. Cook, Jr., NASA Goddard Space Flight Center, Greenbelt, Maryland

CONTROL TECHNIQUES FOR SIMULTANEOUS THREE. DEGREE-OF-FREEDOMH'.DRAULIC VIBiATION SYSTEM ............... ............................... 23

H. D. Cyphers and J. F. Sutton, NASA Goddard Space Flight Center, GremnbeIt, Maryland

"qNITIAL REPORT ON EQUIVALENT DAMAGE MEASUREMENT BY UTILIZINGS/N FATIGUE GAGES ................... ...................................... 35

Thomas B. Cost, Naval Weapons Center, China Lake, California

HOLOGRAM INTERFEROMETRY AS A PRACTICAL VIBRATION MEASUREMENTTECHNIQUE .................... ........................... ............ 41

Cameron D. Johnson and Gerald M. Mayer, Navy Underwater Sound Laboratory,Fort Trumbull, New London, Connecticut

RESPONSE OF AN ELASTIC STRUCTURE INVOLVING CROSS CORRELATIONSBETWEEN TWO RANI6OMLY VARYING EXCITATION FORCES ...... ................. 51

A. Razziano, Grumman Aircraft Engineering Corporation, Bethpage, New York, andJ. R. Curreri, Polytechnic Institute of Brooklyn, Brooklyn, New York

AUTOMATIC NORMALIZATION OF STRUCTURAL MODE SHAPES ............ ...... ... 63C. C. Isaacson and R. W. Merkel, Engineering Laboratories, McDonnell AircraftCompany, St. Louis, Missouri

"v'RESONANT BEAM HIGH "G" VIBRATIO,' TESTING .... .. .................. . . . .. 71B., A. Kohler, International Business MachinL, Corporation, Federal SystemsDivision, Owego, New York

THE USE OF LIQUID SQUEEZE-FILMS TO SUPPORT VIBRATING LOADS ...... . 77Brantley R. Hanks, NASA Langley Research Center, Langley Station,Hampton, Virginia

POINT-TO-POINT CORRELATION OF SOUND PRESSURES IN REVERBERATIONCHAMBERS .............. .................... . ....... 87

Charles T. Morrow, LTV Research Center, Western Division, Anaheim, California

ENVIRONMENTAL LABORATORY MISSILE FAILURE RATE TEST WITHALRODYNAMIC FUNCTION SIMULATION ........... ............. ......... ... 99

Raymond C. Binder and Gerald E. Berge, Naval Missile Center,Point Mugu, California

APOILLO CSM DYNAM12 TEST PROGRAM ....... ....... ... ........ . ....... ... 105A. E. Chirby, R. A. Stevens and W. R.ý Wood, Jr., North American RockwellCorporation, Downey, California

MODAL SURVEY RESULTS FROM THE MARINER MARS 1969 SPACECRAFT ......... 123R. E. Freeland, Jet Propulsion Laboratory, California Institute of Technology,Pasadena, California, and W. J. Gaugh, Northrop Systems Laboratories,Northrop Corporation, Hawthorne, California

".This paper not presented at Symposium.,

98

r

UPRATED SATURN I FULL SCALE DYNAMIC TEST CORRELATION .. ............ 135Charles R. Wells and John E. Hord, Chrysler Corraration Space Division,New Orleans, Louisiana

AN APPROACH FOR DUPLICATING SPACECRAFT FLIGH7-INDUCED BODY FORCESIN A LABORATORY ............ ...................................... .... 147

S, M. Kaplan and A. J. Soroka, General Electric Company, r•-hiladeiphia, Pennsylvania

FLEXURE GUIDES FOR VIBRATION TESTING ............... ....................... 157Alexander Yorgiadis and Stanley Barrett, North Am, -tcan Rockwell Corporation.Downey, California

A COMPRESSION-FASTENED GENERAL-PURPOSE " ¾.ATION AND SHOCK FIXTURE . 175Warren C, Beecher, Instrument Division, Lear , -r., Inc., Grand Rapids, Michigan

VIBRATION EQUIVALENCE: FACT OR FICTION? .................... 187LaVerne Root, Collins Radio Company, Cedar Rain , Iwa

PROVIDING REALISTIC VIBRATION TEST ENVIRC rPAENTS TO TACTICALGUIDED MISSILES ...................... . .................................... 191

K. R. Jackman and H. L. Holt, General Dynamic- Pomona, California

*THE REDUCTION OF THE VIBRATION LEVEL 011 A CIRCULAR SHAFT MOVINGTRANSVERSELY THROUGH WATER AT THE (.'ITICAL REYNOLDS NUMBER ..... ... 217

Irvin F. Gerks, Honeywell Inc., Seattle, Washib 'ton

*ANALYSIS AND DESIGN OF RESONANT FIXTUI, -* TO AMPLIFY VIBRATOROUTPUT .......... ... .... ..................... . ... .... . ............ 2

J. Verga, Hazeltine Corporation, Little Neck. w York

Bu:lefin 39Part III

Structaral Analysis

MODAL DENSITIES OF SANDWICH PANELS: THEORY AND EXPERIMENT ................ 1Larry L. Erickson, NASA Ames ResevTch Center, Moffett Field, California

TURBINE ENGINE DYNAMIC COMPATIBILITY WITH HELICOPTER AIRFRAMES ........... 17Kenneth C. Mard and Paul W. von Hardenberp, Sikorsky Aircraft Division of UnitedAircraft Corporation, Stratford, Con'Aecticut

SYNTHESIS OF RIGID FRAMES BASED ON DYNAMIC CRITERIA ....... ................ 31Henry N. Christiansen, Associate Professor, Department of Civil Engineering Science,Brigham Young University, Provo, Utah, and E. Alan Pettit, Jr., Engineer,Humble Oil Company, Benicia, California

DYNAMIC RESPONSE OF PLASTIC AND METAL SPIDER BEAMS FOR 1/9THSCALE SATURN MODEL ...................................... 39

i.0 V. Kulasa, KPA Computer Techniques, Inc., Pittsburgh, Pennsylvania, and W. M. Laird,University of New York, Fredonih, New York

"'CHARTS FOR ESTIMATING THE EFFECT OF SHEAR DEFORMATION AND ROTARYINZ-"TTA ON THE NATURAL FREQUENCIES OF UNIFORM BEAMS. ............... 49F. F. Rudder, Jr., Aerospace Sciences Research Laboratory, Lockheed-Georgia

Company, Marietta, Georgia

*This paper not presented at Symposium.

99

ACOUSTIC RESPONSE ANALYSIS OF LARGE STRUCTURES ................... 55F. A. Smith. Martin Marietta Corporation, Denver Division, Denver, Colorado,and R. E. Jewell, NASA Marshall Space Flight Center, Huntsville, Alabama

*ESTIMATION OF PROBABILITY OF STRUCTURAL DAMAGE FROM COMBINEDBLAST AND FINITE-DURATION ACOUSTIC LOADING ......... ..................... 65

Eric E. Ungar and Yoram Kadman, Bolt Beranek and Newman Inc.,Cambridge. Massachusetts

*THE RESPONSE OF MECHANICAL SYSTEMS TO BANDS OF RANDOM EXCITATION .... 73L. J. Pulgrano and M. Ablowitz, Grumman Aircraft Engineering Corporation,Bethpage, New York

*PREDICTION OF STRESS AND FATIGUE LIFE OF ACOUSTICALLY-EXCITEDAIRCRAFT STRUCTURES .......................................... 87

Noe Arcas, Grumman Aircraft Engineering Corporation, Bethpage, New York

VIBRATION ANALYSIS OF COMPLEX STRUCTURAL SYSTEMS BY MODALSUBSTITUTION . .............. ........................................... 99

R. L. Bajan, C. C. Feng, University of Colorado, Boulder, Colorado, andI. J. Jaszlics, Martin Marietta Corporation, Denver, Colorado

THE APPLICATION OF THE KENNEDY-PANCU METHOD TO EXPERIMENTALVIBRATION STUDIES OF COMPLEX SHELL STRUCTURES ..... .................. ... 107

John D. Ray, Charles W. Bert and Davis M. Egle, School of Aerospace andMechanical Engineering, Uriversity of Oklahoma, Norman, Oklahoma

*NORMAL MODE STRUCTURAL ANALYSIS CALCULATIONS VERSUS RESULTS ............ 117Culver J. Floyd, Raytheon Company, Submarine Signal Dikision, Portsmouth. Rhode Island

COMPARISONS OF CONSISTENT MASS MATRIX SCHEMES ......... ................... 129R. M. Mains, Departmcnt of Civil and Environmental Engineering,Washington University, St. Louis, Missouri

MEASUREMENT OF A STRUCTURE'S MODAL EFFECTIVE MASS .................. ... 143

G. J. O'Hara and G. M. Remmers, Naval Research Laboratory, Washington, D.C.

SIMPLIFYING A LUMPED PARAMETER MODEL . . . ................ 153Martin T. Soifer and Arlen W. Bell, Dynamic Science, a Division of MarshallIndustries, Monrovia, California

STEADY STATE 3EHAVIOR OF TWO DEGREE OF FREEDOM NONLINEAR SYSTEMS . . 1J. A. Padovan and J. R. Curreri, Polytechnic Institute of Brooklyn, Brooklyn, New York,and M. B. Electronics, New Haven, Connecticut

THE FLUTTER OR GALLOPING OF CERTAIN STRUCTURES IN A FLUID STREAM. . . . 171Raymond C. Binder, University of Southern California, Los Angeles, California

*AIRCRAFT LANDING GEAR BRAKE SQUEAL AND STRUT CHATTER INVESTIGATION. . 179F. A. Biehl, McDonnell Douglas Corporation, Long Beach, California

EXPERIMENTAL INVESTIGATION OF NONLINEAR VIBRATIONS OF LAMINATEDANISOTROPIC PANELS .................................... 191

Bryon L. Mayberry and Charles W. Bert, School of Aerospace and MechanicalEngineering, University of Oklahoma, Norman, Oklahoma

*STRUCTURAL DYNAMICS ANALYSIS OF AN ANISOTROPIC MATERIAL ...... .......... 201S. K. Lee, General Electric Company, Syracuse, New York

*EXPERIMENTS ON THE LARGE AMPLITUDE PARAMETRIC RESPONSE OFRECTANGULAR PLATES UNDER IN-PLANE RANDOM LOADS ........ .............. 205

R. L. Silver and J. H. Somerset, Department of Mechanical and Aerospace Engineering,Syracuse University, Syracuse, New York

*This paper not presented at Symposium.

100

*RESPONSE OF STIFFENED PLATES TO MOVING SPRUNG MASS LOADS ... ...... 233Ganpat! M. Singvi. Schutte Mochon, Inc., Milwaukee. Wisconsin, and Larry J. Feeser,University of Colorado, Boulder, Colorado

*PARAMETRIC RESPONSE SPECTRA FOR IMPERFECT COLUMNS ................ .... 247Martin L. Moody, University of Colorado, Boulder, Colorado

Bulletin 39Part IV

Damping

*APPLICATION OF A SINGLE-PARTICLE IMPACT DAMPER TO ANANTENNA STRUCTURE .................... .................................... 1

R. D. Rocke, Hughes Aircraft Company, Fullerton, California, and S. F. Magri,University of Southern California, Los Angeles, California

A PROPOSED EXPERIMENTAL METHOD FOR ACCURATE MEASUREMENTS OFTHE DYNAMIC PROPERTIES OF VISCOELASTIC MAT-JUIALS . . -. '...... ........... II

Kenneth G. McConnell, Associate Professor of Engineering Mechanics,Iowa State University, Ames, Iowa

DAMPING OF BLADE-LIKE STRUCTURES ................ .......................... 19David I. G. Jones, Air Force Materials Laboratory, Wright-Patterson Air Force Base,Ohio, and Ahid D. Nashif, University of Dayton, Dayton, Ohio

MULTI-LAYER ALTERNATELY ANCHORED TREATMENT FOR DAMPING OFSKIN-STRINGER STRUCTURES .................. ................................ 31

Captain D. R. Simmons, Air Force Institute of Technology, Wright-Patterson AirForce Base, Ohio, J. P. Henderson, D. I. G. Jones, Air Force Materials Labora° #ry,Wright-Patterson Air Force Base, Ohio, and C. M. Cannon, University of Dayton,Dayton, Ohio "

AN ANALYTICAL AND EXPERIMENTAL INVESTIGATION OF A TWO-LAYERDAMPING TREATMENT ................ .................................. .... 53

A. D. Nashif, University of Dayton, Dayton, Ohio, and T. Nicholas, Air ForceMaterials Laboratory, Wright-Patterson Air Force Base, Ohio

DAMPING OF PLATE VIBRATIONS BY MEANS OF ATTACHED VISCOELASTICMATERIAL ...... ................................... ...................... 63

I. W. Jones, Applied Technology Associates, Inc., Ramsey, New Jersey

VIBRATIONS OF SANDWICH PLATES WITH ORTHOTROPIC FACES AND CORES ........ 73Fakhruddin Abdulhadi, Reliability Engineering, IBM Systems DevelopmentDivision, Rochester, Minnesota, and Lee P. Sapetta, Department of MechanicalEngineering, University of Minnesota, Minneapolis, Minnesota

THE NATURAL MODES OF VIBRATION OF BORON-EPOXY PLATES ...... ........... 81J. E. Ashton and J. D. Anderson, General Dynanices, Fort Worth, Texas

'NAý URAL MODES OF FREE-FREE ANISOTROPIC PLATES ......... ................ 93J. E. Ashton, General Dynamics, Fort Worth, Texas

ACOUSTIC TEST OF BORON FIBER REINFORCED COMPOSITE PANELSCONDUCTED IN THE AIR FORCE FLIGHT DYNAMICS LABORATORY'SSONIC FATIGUE TEST FACILITY ............ .............................. .... 101

Carl L. Rupert, Air Force Flight Dynamics Laboratory, Wright-P-tterson AirForce Base, Ohio

*This paper not presented at Symposium.

101

!

STRENGTH CHARACTERISTICS OF JOINTS INCORPORATING VISCOEIAST'CMATEn IALS ................................................ 117

W. _. LaBarge and M. D. Lamoree, Lockheed-California Company, Burbank, Calif',rnia

Isolation

RECENT ADVANCES IN ELECTROHYDRAULIC VIBRATION ISOLATION .......... 141Jerome E. Ruzicka and Dale W. Schubert, Barry Controls, Division of Barry WrightCorporation, Watertown, Massachusetts

ACTIVE ISOLATION OF HUMAN SUBJECTS FROM SEVERE AIRCRAFT DYNAMICENVIRONMENTS ......................................... .............. 157

Peter C. Calcaterra and Da.e W. Schubert, Barry C'etrols, Division of BarryWright Corporation, Watertown, Massachusetts

ELASTIC SKIDMOUNTS FOR MOBILE EQUIPMENT SHELTERS ........... .............. 179R. W. Doll and R. L. Laier, Barry Controls, Division Barry Wright Corporation,Burbank, California

COMPUTER-AIDED DESIGN OF OPTIMUM SHOCK-ISOLATION SYSTEMS ............ 185E. Sevin, W. D. Pilkey and A. J. Kalinowski, UT Research Institute, Chicago, Illinois

ANALYTIC INVESTIGATION OF BELOWGROUND SHOCK-ISOLATING SY3TEMSSUBJECTED TO DYNAMIC DISTURBANCES ........ ............................ 17')9

3. Neils Thompson, Ervin S. Perry and Suresh C. Arya. The University of Texa-at Austin, Austin, Texas

GAS DYNAMICS OF ANNULAR CONFIGURED SHOCK MOUNTS ........ ............... 213W. F. Andersen, Westinghouse Electric r.orpn:•.tion. Sunnyvale, California

A SCALE MODEL STUDY OF CRASH ENEP.GY DISSIPATING VEHICLE STRUCTURES . . 227r. J. Bozich and G. C. Kao, Research Staff. Wyle Laboratories, Huntsville, Alabama

DESIGN OF RECOIL ADAPTERS FOR ARMAMENT SYSTEMS ................... . . 251A. S. 'WVhitchill and T. L. Quinn, Lord Manufacturing Company, Erie, Pennsylvania

*A DYNA lIC VIBRATION ABSORBER FOR TRANSIENTS ...... .................. . .. 261Dirse W. Sallet, University of Maryland, College Park, Maryland and Naval OrdnanceLaboratory, White Oak, Silver Spring, Maryland

Bulletin 39

Part V

Shock

DYNAMIC RESPONSE OF A SINGLE-DEGREE-OF-FREEDOM ELASTIC-PLASTICSYSTEM SUBJECTED TO A SAWTOOTH PULSE ...... .............. .. .......

Martin Wohltmann, Structures and Mechanics Department, Martin MariettaCorporation, Orlando, Florida

*TRANSIENT DYNAMIC RESPONSES IN ELASTIC MEDIUM GENERATED BYSUDDENLY APPLIED FORCE ............ ................................ ..... 13

Dr. James Chi-Dian Go, The Boeing Company, Seattle, Washington

IMPACT FAILURE CRITERION FOR CYLINDRICAL AND SPHERICAL SHELLS .......... 21Donald F. Haskell, Hittman Associates, Inc., Columbia, Maryland

*This paper not presented at Symposium.

102

*THE EXCITATION OF SPHERICAL OBJECTS BY THL PASSAGE OiF PRESSUREWAVES........................................;...........14;; ...... 29

Got-on E. Strickland, J.., Lo~ckheed 1631 siles and Space Compay P 0oAlo

THE PERFORMANCE CHARA4CTER1STICS OF CONCENTRATED- CHARGE,EXPLOSIVE- DRrEN SHOCK TUBEts. .. .......... ........ ........ ........ ........... 41

L. W. ffickle and M. G. Vigil, Sandia Laboratories, Albuquerquae. New Mexico

*PRIMACORD EXPLOSIVE-DRIVEN SHOCK TUBES AND BLAST WAVE PARAMETERSIN AIR, SULFURHEXAFLUORIDE AND OCTOFJ.UOROCYC LO BUTANE (FREON-C318) 53

M. G. Vigil, Sandia Laborilories, Albvnuerque. Nev Mexico

ZERO IMPEDANCE SHOCK TESTS, A cAst FoR SPECIFY!NG THE MACHINE........... 63ChaA~es T. Morrow, LTV li-:.-Aivh C ".cec. Wesiern Division, A..aheirn. California

SHOCK TESTiNG WITH ANE EI.ECTRODYVNALMIC EXCITER AND WAVEFORMSYNTHESIZER.........................................................67

Dabia A. Regillo, Massachuset s !nstituWŽ of Techno~ogy. Lincoln Laboratory,

SL~INGSHOT SHOsCKTESTING ......... t... ......................................................

La~ene Wot na arlBohie, Coilina Radio Company, Cedar Rapide. IowaSHCKTETIG NDANALYSIS: A NEW LABORATORY TECHNIQUE.................83

J. Fganavi J.Sinava.-., CA Astre- Electrorlco tPlvision. Princeton, Now Jersey

*INTRUENTT.'N FR AfiIuMA'4 OCCUPANT SIMULATION SYSTEM............ 8W. .Kpp Mj~teevResearch Lab~oratory, inc.. onterery, California

;;uIletin 39

Part V1I

Introductory Papersu

THE IMPACT OF A DYNAMIC ENVtRONMENT ON FLELD E;XPER9AlENTATP'!O .....Walter W, Hollis, U.6 Army Combat Vovelopmrnit~ Coi~rmaAi, Exp-,rimentationCommand, Fort Ord. Czlifornia

TRANSCRIPT OF PANEL DISCUSSION~ O7 PRLCPOSJt') USASI 3'7ANDA. D ONMET3UODS FCR ANALi.YSIS AND PRF.SENTAT,,)N 'r O SH~OCK AND ViBRATION rATA * 7

Julius S. Bendat, Measurement Analysia Corptratior., ?,oa Angecl.,5. Catlifornia,and Alien J. Curtio, aH-ers Aircraft Corporatitm, Cuiver City, Cailtio'nia

TrAnisportation and Packagjnot

THE BUMP TEST!NCI OF MILITARY SIGNALS EQUiPMENtT INI THEUNITED YKINGPOM.. .. ...... ........ ........ .......... ... .. ...... ........ ........ 15

W. Chiidu, Signals JRefeaeirch and Developmem~ Eut:,blittlhvijent, Ministry ofTechnology, Un~tcd Kuvgdfcr-.

NLABS SHIPPING HAZAi'ýDS kECORDw.R SrA'rU;: ANtr' FUTURE PLANS.......... ...... 19Dcunni J. O'Sullivan, rr,, U 2. At-my Natick Libozat-wic,, 'faticK, Massachusetts

*This paer' tot pre'sen~ted at Syrnuotirtrn.

NORMAL AND ABNORMAL DYNAMIC ENVIRONMENTS ENCOUNTERED JNTRUCK TRANSPORTATION ..................................... 31

J. T. Foley, Sandia Laboratories, Albuquerque, New Mexico

DEVELOPMENT OF A RAILROAr ROUGHNESS INDEXING AND SIMULATIONPROCEDURE ..... ................ 47

L. J. Pursifull and B. E. Prothro, U.S. Army Transportation Engineering Agency.Military Traffic Management and Terminal Service, Fort Eustis, Virginia

AN APPROXIMATE METrfOD OF DYNAMIC ANALYSIS FOR MISSILECONTAINER SYSTEMS ................... 57

Mario Paz, Associate Professor, mnd Ergin Citipitioglu, Associate Professor,University of Louisville, Louisville, Kentucky

SIMULATED MECHANICAL IMPACT TEST EQUIPMENT ........................ 65D. R. Agnew, Naval Air Development Center, Johnsville, Warminster, Pennsylvania

Environmental Measurements

SUCCESS AND FAILURE WITH PREDICTION AND SIMULATION OF AIRCRAFTVIBRATION ......................................................... 77

.J. Curtis and N. G. Tinling, Hughes Aircraft Company, Culver City, California

PHOENIX ENVIRONMENTAL MEASUREMENTS IN F-IIIB WEAPONS BAY ............T. M. Kiwior, R. P. Mandich and R. J. Oedy, Hughes Aircraft Company,Canoga Park, California

LUNAR ORBITER FLIGHT VIBRATIONS WITH COMPARIS )NS TO 'LIGHTACCEPTANCE REQUIREMENTS! AND PREDICTIONS BASED ON A NEWGENERALIZED REGRESSION ANALYSIS ............................. I9

S.,erman A. Clevenson, NASA Langley Research Center, Langley Station,Hampton, Virginia

VIBRATION AND ACOUSTIC ENVIRONMEi' r CHARACTERISTICS OF THE SATURNV LAUNCH VEHICLE .................... ...................................... 133

Clark J. Beck, Jr. and Donald W. Caba, The Boeing Company, Huntsville, Alabama

THE BLAST FIELD ABOUT THE MUZZLF OF GUNS ........... .................... 139Peter S. Westine, Southwest Ret -arch Institute, San Antonio Texas

SPECIFICATIONS: A VIEW FROM THE MIDDLE .......... ........................ 151T. B. Delchamps, Bell Telephone Laboratories, Inc., Whippany, New Jerse)

SUPPLEMENT

SHOCK AND VIBRATION CHARACTERISTICS OF AN ADVANCED HYPERSONICMISSILE INTERCEPTOR ............. .....................................

George Fotieo and V, liiam H. Roberto., Structures and Mechanics Department,Martin Marietta Corporation, Orlando, Florida

VIBRACOUSTIC ENVIRONMENT AND TEST CRITERIA FOR AIRCRAFT STORESDURING CAPTIVE FLIGHT .......................................... 15

J. F. Dreher, Air Force Flight Dynamics Laboratory; E.. . Lakin, AeronauticalSystems Division, and E. A. Tolle, Air Force F"'oht roynamics Laboratory,Wright-Patterson Air Force Base, Ohio

SPECTRUM DIP IN SUBMARINE UNDERWATER SHOCK ...... .................. .... 41R. J. Scavuzzo, The University of Toledo, Toledo, Ohio

*DESIGN AND VIBRATION ANALYSIS OF A NAVAL SHIP PROPULSION SYSTEMWITH A DIGITAL COMPUTER ................... ................................ 55

Stephen T. W. Liang, Naval Ship Research and Development Center, Washington, D.C.

*This paper not presented at Symposium.

1C4

Bulletin 40Part I

EFFECT OF EQUIPMENT MASS ON THE SHOCK MOTIONS OF DECKS ..................E. A. Thornton, Naval Ship Research and Development Center, Portsmouth, Virginia

CORRELATION OF A RESULTANT VELOCITY CHANGE TO AN UNDERWATEREXPLOSION FORCING-FUNCTION ............................. .9

W. F. Peete, Jr., Naval Undersea Research and Development Center, Pasadena,California

PREDICTION OF THE TRANSIENT RESPONSE OF A CYLINDRICAL VjASTIC SHELLTO SPHERICAL UNDERWATER SHOCK WAVES BY THE ACOUSTIC vAVE-SHELLINTERACTION THEORY ....... ................................ 15

H. Huang and Y. F. Wang, Naval Ship Research and Development Laboratory,Annapolis, Maryland

STRUCTURAL EVALUATION OF SHIPBOARD WEAPON SYSTEMS-NSRDCPARTICIPATION IN OPERATION PRAIRIE FLAT ............. .......... 31

L. R. HiH, Jr., Naval Ship Research and Development Center, Washington, D.C.

THE RESPONSE OF WHIP ANTENNAS TO AIR BLAST ....................... 45W. E. Gilbert, Naval Ship Research and Development Center, Washingtc , D.C.

SHOCK LOADING AND RESPONSE OF HELICOPTER STRUCTURES DUE TOWEAPON BLAST ....... .................................. . 61

P. A. Cox, W. E. Baker, S. Silverman, and P. S. SWstine, Southwest ResearchInstitute, San Antonio, Texas

THE RESPONSE OF LONG WIRE ROPE AINTENNAS TO AIR BLAST ....... ........ 75

Bulletin 40

Part H1

Shock

AN EXPP'RIIAENTAL APPROACI (TO UNDERSTANDING SHOCK RESPONSE ..........M. W. Oleson, Naval Researcr Laboratory, Washington, D. C.

EXPLOSIVE SHOCK .................................................. 21W. H. Roberts, Martin Marietta Corporation, Orlando, Florida

MODAL VELOCITY AS A CRITERION OF SHOCK SEVERrIY ...................... 31H. A. Gaberson, Naval Civil Engineering Laboratory, Pt. Hueneme, California,and R. H. Chalmers, Naval Electronics Laboratory Center, San Diego,Califo:nia

THE SIMULTANEOUS APPLICATION OF TRANSIENT AND STEADY STATEDYNAMIC EXCITATIONS IN A COMBINED ENVIRONMENT TEST FACILITYSIMULATING SHIPBOARD ENVIRONMENTS ......................... ....... 51

T. B. Jones, J;., Hughes Aircraft Company, Fullerton, California

1iY)

*PERIODIC SHOCK EXCITATION OF ELASTIC STRUCTURES ...................... 570. Krajcinovic, Ingersoll-Rand Research Inc., Princeton, New Jersey, andG. Herrmann, Northwestern University, Evanston, Illinois

SHOCK ANALYSIS OF FLUID SYSTEMS USING ACOUSTIC IMPEDANCE AND THEFOURIER TRANSFORM: APPLICATION TO WATERHAMMER PHENOMENA ............ 67

A. 4. Winquist, Norton AFB, San Bernardino, California, and R. C. Binder,University of Southern California, Los Angeles, California

.RAG ON FREE FLIGHT CYLINDERS IN A BLAST WAVE ........ ................. 83S. B. Mel!sen, Defense Research Establishment Suffield, Alberta, Canada

ANALYTICAL AND EXPERIMENTAL RESULfTS OF LATTICE TYPE STRUCTURESSUBJECTED TO A BLAST LOADING ...................................... 101

R. Geminder, Mechanics Research, Inc., Los Angeles, California

*LATERAL RESPONSE OF SLIGHTLY CURVED COLUMNS UNDER I )NGITUDINALPULSE LOAD ..................................................... 115

T. L. Anderson, University ef Idaho, Moscow., Idaho, and M. L. M ody,University of Colorado, Denver, Colorado

RESPONSES OF AIRCRAFT STRUCTURES SUBJECTED TO BLAST LOADING ......... .. 123N. M. Isada, R. K. Koegler and D. 0. Bliven, Cornell Aeronautical Laboratory,Inc., Buffalo, New York

PREDICTION OF BLAST-VALVE RESPONSE USINC MODELS ......................... 133R, G. McCoy, G. Nevrincean and E. F. Witt, Bell Telephone Laboratries,

44i1ppany, New Jersey

*TESTING THE RESPONSE OF GAS TURBINES TO AIR BLAST ........................ 147J. C. Muirhead, R. Naylor and C. G. Coffey, Defense Reseh.rch EstablishmentSuffleld, Alberta, Canada

TRANSIENT WAVEFORM CONTROL OF ELECTROMAGNETIC -1IBRATION TESTEQOiPM ENT ....................................................... 157

J. D. Favour and J. M. LeBrun, The D"Ging Company, Seattle, Washington,and J. P. Young, NASA Goddard Space Flight Center, Greenoelt, Maryland

AN IMPROVED ELECTRODYNAMIC SHAKER SHOCK TECHNIQUE ................... 173J, R. Moser and D. Garner, Texas Instruments Inc., Dallas, Texas

PROTUBERANCE ,F.SCT' ON LIMITER-EQUIPPED HARD LANDINGPA"LOAWS ........... ............................................ 183

J. L. McCarty and J. T. 1lnwiet'.,N ASA Larg'ey Research Center, Hampton,Virginia

IMPACT TESTS OF NUCLEAR 01UEL MATRICES USING A VACUUM TUBELAUNCHER .............................. ............................... 1 .,3

N. W. Nunez, Sadia Corporation, Albuquerque, New Mexico

DEVELOPMENT OF 100,000 G TEST FACILITY ............................. .. 205R. L. Bell, Endevco Corporation, Passdena, California

*ON THE INTERPRETATION AND APPLICATIONq OF SHOCK TEST RESULTS INENGINEERING DESIGNS . .,... . ......................... 215

Chi-Hung Mok, Gr.neral Electric Comnpay,. Philadelphia, Pennsylvania

S"T i7paperniiotpresented at Syniposit-',-..

I ff

I

METHODS OF COMPUTING STRUCTURAL RESPONSE OF HELICOPTERS TOWEAPONS' MUZZLE AND BREECH BLAST ............................... 227

W. E. Bzker, S. Silverman, P. A.. Cox, Jr., and D. Young, Southwest ResearchInstitute, San Antonio, Texas

SHOCK TESTING FOR EQUIPMENT IN PROTECTIVE STRUCTURES ................ 243M. M. Dembo and C. C. Huang, U. S. Army Engineer Division, Huntsville,AlaLama

Bulletin 40Part III

Vibration

ANALYSIS OF RANDOM RESPONSES FOR CALCULATION OF FAT!GUE DAMAGE ....

C. C. Osgood, RCA Astro-Electronics Division, Princeton, New Jersey

VIBRATION TRENDS ANALYSIS .............. I , .... ... ...

A. Y. Edelberg, The Boeing Company, Washington, D. C.

THE RADIATION RESISTANCE O -P%,LINDRICAL SHELLS EXUIBITINGAXISYMME"RIC MODE SHAPES )I ....................... 23

C. J. Runkle, Chentsttand Reseai~ch Center, Durham, North Carolina, andF. I. Hart, North Caro.hia State University, Raleigh, North Carolina

MODAL SENSIT[VITY STUDY OF A CONICAL REENTRY VEHICLE TOAERODYNAMICALLY INDUCED ACOUSTIC LOADING ....................... .. 31

L. E. Chaump and J. K. Mer'hant, General Electric Company, Philadelphia,Pennsylvania

ACOUSTIC RESPONSE OF A SPACECRAFT SOLAR PANEL USING NORMAL MODEMETHOD ....... ... ....... ................ I ..................... ..... . 49

A. Str~j,.,e, TRW Systems Croup, Redondo Beach, Californi,

COMPUTER PROGRAMS FOR PREDICTION OF STRUCTURAL VIBF 4,TIONS DUE TOFLUCTUATING PRESSURE ENVIRONMENTS ............................. . 57

T. N. Lee and W. L. Swanson, Chrysler Corporation Space Division, Huntsville,Alabama

MODAL DENSITIES OF SPHERICAL SHELLS ........ e ............. ... . . 69H. Kunieda, NASA Ames Research Center, Moffett Field, California

PREDICTION OF INTERFACE RANDOM AND TRANSIENT ENVIRONMENTS 7HROUGHTHE USE OF MECHANICAL IMPEDANCE CONCEPTS 7? • ......... • . . . . .

G. K. Jones and F. J. On, NASA Goddard f"pace Flight Center, Greenbelt, Maryland

*FACTORS OF SAFETY FOR UNMANNED SPACECRAFT STRUCTURES ...... ..... 89S. M. Kaplan, General Electric Company, PhIladelphia, Pennsylvania

*RESPONSE OF RECTANGULAIR PLATES TO MOVING LOADS BY A FINITEELEMENT PROCEDURE ..... ,, .. ... ;........ . . ............ 99

S. K. Damle, Tiriversity of Baroda, Barodi, India, and L. J, Feeser,University of Coiorado, Bouhhlr,, Colorado

*This paper not presented at Symposium.

107

r

*VIBRATORY RESPONSE OF PRINTED CIRCUIT BOARDS ................. ....... III

N. M. Isada, State University of New York, Buffalo, New York, and J. C. Shear,Eastman Kodpk Company, Rochester, New York

*NONLINEAR PARAMETRIC RESPONSE OF PLATES UNDER RANDON, LOADS ............ 119

T. P. Shyu and J. H. Somerset, Syracuse University, Syracuse, New Y irk

*VIBRAT!ON OF CELLULAR CYLINDRICAL SHELLS ...................... 13,IWZ, C. Patel, Brown Engineering Company, Huntsville, Alabama, and S. I. Hayek,Pennsylvania State University, University Park, Pennsylvania

*ANALYSIS OF SINUSOIDAL AND RANDOM VIBRATION ENERGIFS ...... .............. 139J. N. Tait, Naval Air Development Center, Johnsville, Pennsy.vania

APOLLO LUNAR MODULE VIBRATIONS DURING FLIGHT AND GROUNDTESTS ............................................................... 163

W. D. Dorland and J. D. Johnston, Jr., NASA Manned Spacecraft Center,Houston, Texas

STRUCTURAL QUALIFICATION OF THE ORBITING ASTRONOMICAL OBSERVATORY . . 179

W. B. Keegan, NAbA Goddard Space Flight Center, Greenbelt, Maryland

THE ENVIRONMENTAL TESTING OF EXPLOSIVE STORES IN THE UNITEDKINGDOM .............. ............................................ 193

C. Higham, Ordnance Board, London England, and D. A. E. Carter,Environmental Test Center, Foulness, England

A UNIQUE MODEL, SUSPENSION, AND EXCITATION SYSTEM FOR LAUNCHVEHICLE DYNAMICS STUDIES ............ .................... 205

J. Pearson and B. J. Gambucci, NASA Ames Research Ceiitur, Moffctt Field,California

LOAD APPLICATION AND CONTROL SYSTEMS UTILIZED TO SIMULATECOMBINED LOADS ENVIRONMENT FOR SATURN V - APOLLO SPACECRAFT . . ., .: . 211

0. D. Shipway, Wyle Laboratories, Norco, California

IMOPEDANCE SIMULATION VIBRATION TEST FIXTURES FOR SPACECRAFT TESTS . . . 231T. D. Scharton, Bolt Beranek and Newman Inc., Van Nuys, California

VIBRATION ANALYSIS OF AN INERTIAL REFERENCE UNIT....................... 257B. M. Ishino, Autonetics, Anaheim, Cal!fornia.

*PULSED-RANDOM VIBRATION TESTING . .. ............ 267

H. L. Stewart, McDonnell Aircraft Company, St. Louis, Missouri

*AXIAL RESPONSE OF A HIGH-SPEED, GAS-LUBRICATED, ROTOR-BEARING

ASSEMBLY TO SHOCK AND VIBRATION ......... ... .................. .. 25P. R. Spencer and P. W. Curwen, Mechanical Technology, Inc., Latham,New York, and H. B. Tryon, NASA Lewis Research Center, Cleveland, Ohio

MULTI-ENVIRONMENT TEST SYSTEM FOR SEQUENTIAL TIMERS .... W........ . 29oV. G. Ames, U. S. Army Frankford Arsenal, Philadelphia, Pennsylvania

*ON THE SELF EXCITED VIBRATIONS OF A CIRCULAR CYLINDER IN UNIFORM

FLOW ......... ....................... . ... ..... 303D. W. Sallet, University of Maryland, Co!',He Park, Maryland

_Thi-•Ta paernot presented at '-mposium.

1)8

Bulletin 40

Part IV

Dynamics

FURTHER COMPARISONS OF CONSISTENT MASS MATRIX SCHEMES ....................R. M. Mains, Washington University, St. Louis, Missouri

SHOCK SPECTRA FOR STATISTICALLY MODELLED STRUCTURES ................... 17R. H. Lyon, Bolt Beranek and Newman Inc., Cambr'dge, Massachusetts

REVIEW OF MODAL SYNTHESIS TECHNIQUES AND A NEW APPROACH ................ 25S. Hou, Bellcomm, Inc., Washington, D. C.

ROTATING ELEMENTS IN THE DIRECT STIFFNESS METHOD OF DYNAMICANALYSIS WITH EXTENSIONS TO COMPUTER GRAPHICS ......................... 41

M. E. Novak, The Boeing Company, Vertol Division, Philadelphia, Pennsylvania

DYNAMIC RESPONSE OF BEAMS TO MOVING PRESSURE LOADS AS RELATED TOTRACKED AIR CUSHION VEHICLES .................................... 47

J. F. Wilson, Duke University, Durham, North Carolina

*THE DESIGN OF A STRUCTURAL MEMBER ANALYSIS PROGRAM FOR ANINTERACTIVE COMPUTER SYSTEM ............................. ........ 63

W. D. Pilkey, University of Virginia, Charlottesville, Virginia, and R. Nielsenand M. Steier, COM/CODE Corporation, Washingtun, D. C.

*Dv 4AMIC RESPONSE OF A SINGLE-DEGREE-OF-FREEDOM ELASTIC-PLASTICSYSTEM SUBJECTED TO A HALF SINE PULSE ............................. 67

M. Wohltmann, Martin Marietta Corporation, Orlando, Florida

*PROPAGATION OF YIELDING IN A BILINEAR HYSTERETIC BEAM ANDDISTRIBUTED FOUNDATION UNDER DYNAMIC PULSE LOADING ................. 81

J. R. Mays, University of Colorado, Denver, Colorado

PLASTIC MODELS FOR DYNAMIC STRUCTURAL ANALYSIS ..................... 89W. A. Elliott, Chevrolet Division, GMC, Detroit, Michigan

" iGUE DESIGN OF ELECTRONIC EQUIPMENT ............................ 97.

L. W. Root, Collins Radio Company, Cedar Rapids, Iowa

MODEL STUDIES TO DETE"MINE LOW-FREQUENCY NOISE REDUCTION OFSPACECRAFT .................................................... ''103

A. W. Mueller, NASA Langley Research Center, Har-,,,on, Virginia

*COMBUSTION INSTABILITY TESTS OF THE S/ti URN IB FIRST STAGE ................ 109W. S. Parker, Ch'ysler Corporation, New Orleans, Louisiana

DYNAMIC ANALYSIS OF A HIGH-SPEED LINKLESS AMMUNITION CONVEYORSYS" M .......... .......................... . .... ..... 115

C. B. basye and B. R. Scheller, Emerson Electric Company, St. Louis, Missouri

STRESS WAVES IN MULTILAYERED CYLINDERS AND CONICAL FRUSTUMS ......... 127J. C. S. Yang ati A. F Seigel, N;,val Ordnance Laboratory, Silver Spring,Maryland

'TFhi-•paer riot presented at Symposi mi

109

CAVITY EFFECT ON PANELu -'- UTTER - JUST HOW SIGNIFICANT? ............... 139N. H. Zimmerman and C. E. Lemley, McDonnell Aircraft Company, St. Louis,Missouri

AN EIGENVALUL PROBLEM SOLUTION OF A THREE-DIMENSIONAL PIPINGSYSTEM ......... o. .......... o............... o .............. 147

P. BezIer, Brookhaven Naticial Laboratory, Upton, New Yor., and J. R. Curreri,Polytechnic Institute of Broo, lyn, Brooklyn, New York

DESIGN MODEL BASED ON OBSERVFJ) MODES OF VIBRATION OF AUSTRAL.ANCSIRO 210-FT RADIO TELESCOPE ....................................... 155

J. A. Macinante, CSIFJ, National Standards Laboratory, Syt:cey, Australia

UPPER AND LOWER PJUNDS TO TORSIONAL FREQUENCIES OF NONUNIFORMSHAF'i q AND APPLICATIONS TO MISSILES ..................................... 13

N Rubinstein, V. G. Sigillito and J. T. Stadter, Applied PLysics LAboratory, JHU,Silver Spring, Maryland

*DETERMINATION OF DYNAMIC LOADS AND RESPONSE OF A SPACE VEHICLEUSING FLIGHT DATA ... ........................................... 171

S. Hou, Bellcomm, Inc., Washington, D. C.

*STIFFNESS MATRIX OF A BEAM-COLUMN INCLUDING SHEAR DEFORMATION ......... 187H. Saunders, Generzl Electric Company, Pniladelphia, Pennsylvanid

*LIQUID-STRlUCTURE COUPLING IN CURVED PIPES ......................... 197L. C. Davidson and J. E. Smith, Naval Ship Research and DevelpmentLaboratory, Annapolis, Maryland

*DISTRIBUTION OF EIGENVALUES IN CONICAL SHELLS .......................... 209D. K. Miller and F. D. Hart, North Carolina State Universi t y, Paleigh,North Carolina

*DYNAMIC RESPONSE OF STRUCTURAL SHIELD TO A TRAVELING PRESSUREPULSE .......... . ............................................... 217

A. M. Rodriguez and P. N. Mathur, Aerospace Corporation, San Bernardino,California

*ANALYSIS OF THE RELATIVE MOTION OF THE PEM MOD-IV TETHEREDCANISTER AND THE ATLAS BOOSTER ................ ioý ................... 225

r. L. Alley, Aerospace Corporation, San Bernardino, California

Bulletin 40

Part V

Damping and Isolation

REDUCTION OF VIBRATIONS IN AEROSPACE STRUCTURES BY ADDITIVEDAMPING .......................... :.e. • ,* . . ......... . . ... ..

D. 1. G. Jones and J. P. Henderson, Air Force Materials Laboratory, Wright-Patterson AFB, Ohio, and A. D. Nashif, University of Dayton, Dayton, Ohio

VIBRATION ISOLATION WITH NONLINEAR DAMPING ............. ,.... 19J. E., Ruzicka and T. F. Derby, Barry Controls, Watertown, Massachusetts

-This paper not -presented at Symposium.

110

THE CONTROL OF VIBRATIONS WITH VISCOELASTIC MATERIALE ................... 37P. Grootenhuls, Imperial College of Science and Technology, London, England

SONIC FATIGUE RESISTANCE OF STRUCTURES INCORPORATING A CONSTRAINEDVISCOELASTIC CORE .............................................. 49

M. D. Lamoree and W. L. LaBarge, Lockheed-California Compan,, Burbank,California

EXPERIMENTS ON INELASTIC DAMPING OF SPACE VEHICLE DUCTS ................. 61G. E. Bowie, W. A. Compton and J. V. Long, Solar Division of InternationalHarvester Company, San Diego, California

TRANSVERSE VIBRATIONS OF LAMINATED PLATES vITH VISCOELASTIC LAYERDAMPING ...................................................... 93

F. Abdulhadi, IBM Corporation, Roche'iter, Minnesota

COMPARISON OF THE GEIGER THICK PLATE TEST AND THE VIBRATINGCOMPOSITE BEAM TEST FOR THE EVALUATION OF THE EFFECTIVENESSOF VIBRATION DAMPING MATERIALS ................................ 105

D. R. Blenner, Lord Manufacturing Company, Erie, Pennsylvania, andT. J. Dudek, General Tire and Rubbe. Cn'mpany, Akron, Ohio

AN AEROSPACE ENERGY ABSORBER APPLIED TO HIGHWAY SArETY ................ 115W. E. Woolam, Southwest Research Institute, San Antonio, Texas

*DETERMINATION OF THE COMPLEX MOBILITY AND IMPEDANCE MATRICESFOR DAMPED LUMPED PARAMETER LINEAR DYNAMIC SYSTEMS.................. 135

J. J. Engblom, Hughes Airrraft Company, Culver City, California

'WAGGING TAIL' VIBRATION ABSORBER ............................... ... 147R. G. Barclay and P. W. Humphrey, ITASA Godd-.rd Space Flight Center,Greenbelt, Maryland

A SIMPLE DEVICE FOR ATTENUATION OF LONGITUDINAL ELASTIC STRESSW AVES ........................... ............................ 157

J. P. O'Neill and C. J. Tirman, TRW Systems Group, Redondo Beach, California

ANALYSIS OF SHOCK MITIGATION FOR GLASS SUBMERSIBLES ..................... 175J. C. S. Yang, Naval Ordnance Laboratory, Silver Spring, Maryland

REDUCTION IN VIBRATION OF THE CH-47C HELICOPTER USING A VARIABLETUNING VIBRATION ABSORBER ......................................... 191

J. J. O'Leary, The Boeing Company, Philadelphia, Pennsylvania

RESPONSE AND OPTIMIZATION OF AN ISOLATION SY;STEM WITH RELAXATIONTYPE DAMPIN G ................................................. 203

T. F. Derby and P. C. Calcaterra, Barry Controls, Watertown, Massachusetts

THE RESPONSE OF MECHANICAL SHOCK ISOLATION ELEMENTS TO HIGH RATEINPUT LOADING ......................................... .. .. 217

R. L. Eshleman and P. N. Rao, lIT Research Institute, Chicago, nlinois

RATIONAL ANALYSIS OF A TWO-DEGREE-OF-FREEDOM FLEXURE-TORSIONSYSTEM FOR REDUCTION OF CERTAIN TYPES OF FLUTTER ..................... 235

M. J. Klelp, North American Rockwell Corporation, Los Angeles, California,and R. C. Binder, University of Southern California Los Angeles, California

*This paper not pres.ented at Symposium.

111

,r

DESIGN AND DEVELOPMENT OF A SHOCK ISOLATION EVALUATION SYSTEMFOR HIGH RATE INPUT LOADING ..................................... 245

P. N. Rao and K. E. Hofer, IT Research Institute, Chicago, illinois

*A STUDY OF AMPLITUDE FREQUENCY PLOTS WITH NONLINEAP DAMPING ........ 261G. F. Brammeier, Brown Engineering Company, Huntsville, Alabama

VIBRATIONS OF MULTICORE SANDWICH BEAMS ............................. 277V. P. Roske, Jr., Air Force Missile Development Center, Holloman AFB,New Mexico, and C. W. Bert, University of Oklahoma, Norman, Oklahoma

*THE USE OF POLYURETHANE FOAM FOR SHOCK AND VIBRATION ISOLATIONOF AVIONICS COMAPONENTS ......................................... 285

W. E. Arthur and T. Carrell, North American Rockwell Corporation, LosAngeles, California, and J. Nirsebl, U. S. Army Electronics Command,Ft. Monmouth, New Jersey

*THE ANALYTIC MODELING OF OPEN-CELL FOAMS AS SHOCK AND VIBRATIONELEMENTS ..................................................... 291

T. Liber, UIT Research Institute, Chicago, illinois, and H. Epstein, Universityof Minnesota, Minneapolis, Minnesota

Bulletin 40

Part VI

Trans2ortation

SIMULATION OF DYNAMIC LOADS ON EJECTED MISSILES .......................... 1C. R. Perry, The Boeing Company, Seattle, Washington

WIND TUNNEL SIMULATION OF FLIGHT VIBRATION AND ACOUSTIC LEVELS ON•N EXTERNAL STORE .......................... ............................... 9K. A. Herzing and S. N. Schwantes, Honeywell Inc., Hopkins, Minnesota

A METHOD TO SIMULATE GUNFIRE INDUCED VIBRATION ENVIRONMENT ............. 27J. A. Hutchinson and R. N. Hancock, LTV Aerospace Corporation, Dallas, Texas

THE SHOCK AND VIBRATION EXPERIENCED BY NAVAL AVIONICS DURING .ARRESTED LANDING .............................................. 37

V. M. Foxwell, Jr., Westinghouse Aerospace Division, Baltimore, Maryland

A SURVEY OF PRACTICAL PROBLEMS ENCOUNTERED IN REPRODUCING THECAPTIVE FLIGHT ENVIRONMENT BY MAEANS OF SHAKERS AND SHiOCK TESTMACHINES ................ ..... o ............................ 61

W. Tustin, Tustin Institute of Technology, Inc., Santa Barbara, California

STANDARD ARM CAPTIVE CARRY LIFE EXPECTANCY PREDICTION ANDV11RATION QUALIFICATION TESTING .................................. 67

B. N. Iowning, General Dynamics Corporation, Pomona, California

RAILROAD TRANSPORTABILITY CRITERIA ................................ 85R. Kennedy, U. S. Army Transportation Engineering Agency, Ft. Eustis, Virginia

*This pqper not presented at Symposium.

112

ME LSURED VIBRATION RIDE ENVIRONMENTS OF A STOL AIRCRAFT AND A!r., GH-SPEED TRAIN .............................. o ................. 91

J. J. Catherines, NASA Langley Research Center, Hampton, Virginia

THR',?SHOLD-TYPE RECORDERS .............................. _...... ......... 99L. J. Pursifull, U. S. Army Transportation Engineering Agency, Ft. Eustis,%tirginia

RATL VEHICLE DYNAMIC STUDIES ........................................ 109J. L. Sewall, R. V. Parrish and B. J. Durling, NASA Langley Research Center,Hampton, Virginia •

A PROCEDURE FOR DETERMINING DAMAGE BOUNDARIES .......... ....... 127J. W. Goff and S. R. Pierce, Michigan State University, School of Packaging,East Lansing, Michigan

EVALUATION OF A FRAGILITY TEST METHOD AND SOME PROPOSALS FORSIMPLIFIED METHODS ............. o ................................ .... 133

E. H. Schell, Shock and Vibration Information Center, Washington, D. C.

PANEL DISCUSSION ON FRAGILITY o ..... o .................. ...... 153

Bulletin 40

Part ViI

Instrumentation and Data Analysis

THE RESPONSE OF TRANSDUCERS TO THEIR ENVIRONMENT: THE PROBLEMOF SIGNAL AND NOISE ...... .......................................

P. K. Stein, Arizona State University, Tempe, Arizona

A SIMPIFIED METHOD FOR MEASURING STATIC AND DYNAMIC DISPLACEMENTOF VIBRATING SYSTEMS ...................................... ........ 17

P. T. JaQuay, Air Force Flight Dynamics Laboratory, Wright-Patterson AFB,Ohio

INSTRUMENTATION FOR MEASUREMENT OF VIBRATORY MOTION AND MECHANICALIMPEDANCE WITHIN ASSEMBLED AEROSPACE EQUIPMENT ......................... 29

C. T. Morrow, LTV Research Center, Anaheim, California

APPLICATIONS OF HOLOGRAPHY TO HIGH-FREQUENCY VIBRATIONS ANDTRANSIENT RESPONSE ..... ..................................... .... 33

H. Apk'ahaminn and D. A. Evensen, TRW Systems Group, Redondo Beach, California

LOW-FREQUENCY PORTABLE VIBRATION MEASURING AND RECORDING SYSTEM .... 45S. A. Clevenson, D. J. Martin and A. C.- Dibble, NASA Langley Research Center,Hampton, Virginia

MEASUREMENT OF THE TOTAL STRUCTURAL MOBILITY MATRIX ................ 51J. E. Smith, Naval Ship R•search and Development Laboratory, Annapolis,Maryland

113

*DEVELOPMENT OF A SMALL TRANSMITTER FOR HIGH INTENSITY SHOCKENVIRONMENT ........ .......................................... 85

E. L. Kirkley, Radiation Inc., Melbourne, Florida

PREDICTABLE SHOCK PULSE BY MODIFIED FOURIER TRANSFORMS ................... 93C. W. Young, Johnson-Williams Division, Bacharach Instrument Company,Mountain View, California

ON-LINE COMPUTER APPLICATIONS FOR THE APOLLO 'SHORT-STACK'COMBINED ENVIRONMENTS TEST PROGRAM ............................. 99

D. J. Bozich, Wyle Laboratories, Huntsville, AlabamaDYNAMIC DATA ANALYSIS SYSTEM ............ ......................... 115

M. 0. Michellich, The Boeing Company, Seattle, Washington

*A DYNAMIC DATA COMPENSATION TECHNIQUE FOR SEISMIC TRANSDUCERS ....... 123G. L. Schulz and W. E. Baker, University of New Mexico, Albuquerque,New Mexico

AIR DAMPED HIGH-G ACCELEROMETER AND WIDE BAND VELOCIMETER FORSHOCK STUDY IN FREE MASS UNDER SEVERE AIR BLAST ........................ 133

Y. T. Li and S. Y. Lee, Massachusetts Institute of Technology, Cambridge,Massachusetts

Ship Shock

A SURVEY OF THE INFORMATION NEEDS OF INDUSTRY IN DESIGNING TO MEETNAVY SHIPBOARD SHOCK REQUIREMENTS .................................. 141

H. C. Pusey, Shock and Vibration Information Center. Washington, D. C.

A CONVERSATIONAL TIME SHARING COMPUTER PROGRAM FOR DYNAMICSHOCK ANALYSIS ................. .................... ................. :.. '53

B. A. Bott. General Electric Company, Groton. Connecticut, and R. G. Gauthier,General Dynamics Corporation, Groton, Connecticut

CRITERIA FOR MODE SELECTION IN THE DDAM PROCEDURE ............ ... 165M. Pakstys, Jr., General Dynamics Corporation. Groton, Connecticut

APPLICATION OF PERTURBATION TECHNIQUES TO THE NAVY'S DYNAMICDESIGN ANALYSIS METHOD ............................. . .. .. . •.. ..... 177

J. T. Higney, Gibbs & Cox. Inc., New York, New York

AN ANALYSIS OF SPECTRUM DIP IN UNDERWATER SHOCK ....................... 185R. J. Scavuzzo and D. D. Raftopoulos, The University of Toledo, Toledo, Ohio

DYNAMIC ANALYSIS OF SUBMERGED SHIP STRUCTURE AND EQUIPMENT ............. 97D. B. Ehrenpreis. David Ehrenpreis Consulting Engineers. New York, New York

DYNAMIC BEHAVIOR OF PARTIALLY CONSTRAINED SHIP GRILLAGES ...... .,., .. 207C. S. Smith. Naval Construction Research Establishment, Dunfermline, Fife.Scotland, and D. Faulkner, British Navy Staff, Washington. D. C.

*AN ENVIRONMENTAL VIBRATION RECORDER.............. . ........... 225R. E. Schauer and W. P. Foster, Naval Ship Research aind l)vvlopment Ce(uter,Washington, D. C.

*This paper not presented at Symposium.

114

*2K SYSTEM APPROACH FOR VIBRATION AF0'O SHOCK PROTECTION FORSHIPBOARD EQUIPMENTS .......................................... 233

C. M. Salerno, Barry Controls, Watertowrt, Massachusetts

*PORTABLE INSTRUMENTS FOR USE IN CONNECTION WITH SHIPBOARD

VIBRATION CODES ................................................ 243R. K. Brown and A. Hagen, Naval Ship Research and Development Center,Washington, D. C.

SUPPLEMENT

RIGID AND RESILIENT SHIPx3OARD PIPING SYSTEMS: WHAT CONSTITUTESACCEPTABLE SHOCK PERFORMANCE/QUALIFICATION.? ... ...........

D. M. C. Hurt, Naval Ship Engineering Center, Hyattsville, Maryland

DAMPING VALUES OF NAVAL SHIPS OBTAINED FROM IMPULSE LOADINGS ......W. P. Foster and H. F. Alma, Naval Ship Research and Development Center,Washington, D. C.

CATAPULT-EXCITED MAST-ISLAND VIBRATION ON AN AIRCRAFT CARRIER ... •...•.•.•.13A. Hagen and K. McConnell, Naval Ship Research and Development Center,Washington, D. C.

COMPRESSED-AIR LAUNCHERS ....... 21H. M. Cole, Naval Ordnance Laboratory, Silver Spring, Maryland

EQUIPMENT CABINET MOUNTING FOR SHIPBOARD SHOCK ................ 29P. V. Roberts, Raytheon Company, Bedford, Massachusetts, and A. Smith,Canadian Naval Engineering Test Establishment, Montreal, Canada

RESPONSE OF THE LOW SPEED FAE AND HELICOPTER TRAP WEAPONS(HTW) TO CAPTIVE-FLIGHT VIBRATION . .......................... 47

W. W. Parmenter, Naval Weapons Center, China Lake, California

RESPONSE OF TIAS MECHANICAL MODEL DURING LABORATORY SINE ANDRANDOM VIBRATION COMPARED TO INFLIGHT AND VIBROACOUSTICRESPONSES....... . .... ........ •........... 63

P. Bouclin and L. G. Janetzko, Naval Weapons Center, China Lake, Cpl~ifornia

PANEL DISCUSSION ON CAPTIVE FLIGHT DESIGN AND TEST CRITERIA .......... 83

Bulletin 41Part I

CASC (CAPTIVE AIR SPACE CRAFT) - A POSSIBLE CONCEPT FOR RIVERINEBOAT DESIGN. . .. ., .............................................. . ...

V., H, Van BL,2er, Naval Ship Research and D .velopment Laboratory, Panarni City,Florida, and N. Elmore. Naval Ship Research and Development Center. Portsmouth, Va.

PROBLEMS OF DAMPING THE WINDOW AREAS OF SONAR DOMES., ................ 13Howard N., Phelps. Jr., Naval Underwater Systems Center., New London, Connecticut

OThis pAper not presented at Symposium.

115

APPLICATION OF THE FINITE ELEMENT METHOD TO THE SHOCK AF" _FSONAR TRANSDUCERS ............................... .... 21

Vincent D. Godino and George A. Ziegra, General Dynamics/Electric P vision,Grotois, Connecticut

DYNAMIC RESPONSE OF ABOVE-GROUFID TARGETS TO A BLAST WAVE . . . . . . . .. 35P. N. Mathur, D. M., Rogers, R. H. Lee, and J. W, Murdock, The Aerospace Corporation,San Bernardino, California

Bulletin 41

Part II

Kpniote Talk

THE DYNAMIC CENTURY ...................... ...D. Zonars, Air Force Dynamics Laboratory, Wright-Patterson Air Force Base, Ohio

Physiological Effects

TESTING AND MODELING STANDING MAN'S RESPONSE TO IMPACT .5..........Joseph Gesswein and Paul Corrao, Naval Ship Research and Development Center,Washington, D.C.

EQUAL ANNOYANCE CONTOURS FOR THE EFFECT OF SINUSOIDALVIBRATION ON MAN............................ ........ .. ......... 13

C., Ashley, Mechanical Engineering Department, University of Birmingham, England

Isolation

ISOLATION FROM MECHANICAL SHOCK WITH A MOUNTING SYSTEM HAVINGNONLINEAR DUAL-PHASE DAMPING.................... ........... ... ...

J. C. Snowdon, Ordnance Research Laboratory, The Pennsylvania State University.University Park, Pennsylvania

INTERACTIVE OPTIMAL D1ESIGN OF SHOCK ISOLATION SYSTEMS .... 47W., D., Pilkey, University of Virginia, Charlottesville, Virginia

DESIGN OF HIGH-PERFORMANCE SHOCK ISOLATION SYSTEMS..................• ., 53Ronald L. Eshleman, IIT Research Institute., Chicago, fIlinois

ELASTIC WAVE PROPAGATION IN A HELICAL COIL WITH VARYING CURVATUREAND ITS APPLICATION AS AN IMPACT LOAD DISPERSER . .. , ; ............... 77

Nam P. Suh., Department of Mechanical Engineering, Massachusetts Institute ofTechnology,. Cambridge., Massachusetts

ANALYSIS OF THE INVERTING TUBE ENERGY ABSORBER............. . . .. . 89,J. M. Alcone, Sandia Laboratories, Livermore, California

THE EFFECTS OF PAYLOAD PENETRATION AND VARIOUS ANALYTICAL, MODELSON THE DESIGN OF .A 3PPHERICAL CRUSHABL E CASING FOR LANDINGENERGY ABSORPTION ................ .................................. 95

Robert W. Warnex and Margaret Covert., NASA Ames Research Center

I 16

rS. .. . .•.f - • ,-- -~-• •••

EFFECT OF FREE LAYER DA1MPING ON RESPONSE OF StiFFENED PLATESTRUCTURES .............................. .......... 105

David I. G. Jones, Air Force Matc-ials Laboratory, Wright-Patterson AFB, Ohio

"*TJRATION CONTROL BY A MULTIPLE -LAYERED DAMPING TREATMENT .......... 121A. D. Nashif, Uni-,ersity of Dayton Research Institute, Dayton, Ohio and. T. Nicholas,Air Force Materials Laberatory, Wright-Patterson Air Force Base, Ohio

DETERMKNAT'7CN OF DAMPING PROPERTIES OF SOFT VISCOELASTIC MATERIALS ..... 133Fakhruddln Abdulhzii, IBM General Systems Division, Rochester, Minnesota

IMPROVING RELIABILITY AND FLIMINATING MAINTENANCE WITH ELASTOMERICDAMPERS FOR ROTOR "-ST'ZMS ................................... 141

J. L. Potter, Lord Manufact-'wing Company, Erie, Pennsylvanip

EFFECT OF HIGH POLYMER ADDITIVES ON DIFFUSER FLOW NOISE ...... ......... 151B. M. Ishino, California State College, Fullerton, California and R. C. Binder,University of Southern Caifornia, Los Angeles, California

HAWK SUSPENSION S•'STEM PERFORMANCE ON M754 TRACKED VEHICLE........... 159Paul V. Roberts, haytheon Company, Missile Systems Division, Bedford, Massachusetts

Bulletin 41Part III

Instrumentation

A PRACTICAL APPLICATION OF ACCELEROMETER CALIBRA 'iONS . .. . ....R. R. Bouche, Endevco, Dynamic Instrument Division, Pasad -na, California

DESIGNING AN INSTRUMENTED TEST EGG FOR DETECTING IMPK%"T BREAKAGE...... 11William L, Shupe, USDA, Agricultural Research Service, Transportation and FacilitiesResearch Div., University of California, Davis. California and Robert M., Lake, MayoClinic, Rochester, Minnesota

AN ACCELEROMETER DESIGN USING FERROFLUID ULTRASONIC INTERFEROMET'RY...., 17Jack G. Parks, U.S.. Army Tank-Automotive Command, Warren, Michigan

HYBRID TECHNIQUES FOR MODAL SURVEY CONTROL AND DATA APPRAISAL. 25Robert A. Salyer, TRW Systems, !nc., Redondo Beach, California

OBJECTIVE CRITERIA FOR COMPARISON OF RANDOM VIBRATION ENVIRONMENTS. .. . 43F. F. Kazmierczak, Lockheed Missiles and Space Company, Sunnyvale, California

THE APPLICATION OF ANALOG TECHNIQUES TO RT .AL TIME ANALYSIS ANDSCREENING OF DYNAMIC DATA ................................. ..... 55

Roger C. Crites, McDonnell Aircr dt Co., St., Louis,, Mo.

SHOCK LOADING AND HOLOGRAPHIC INTERFEROMETRY IN NDT ...... .......... 63R, L. Johnson, R. Aprahamian and P. G. Bhuta, TRW Systems Group.Redondo Beach; Califo-nia

117

U

Data Analysis

A NEW qYvNTHESIS TECAdNIQUE FOR SHOCK SPECTRUM ANALYSIS............. ,... 75Willam G. Pollard, Spectral Dynamics Corporation of San Diego. San Diego, Californji

THE ROLE OF LATENT INFORMATICt4 IN INFORMATION PROCESSING INMEASURING SYSTEMS ..................... . ................. ......... 81

Peter K. Stein, Arizona State University, Tempe. Arizona

Test Facilities

USBR VIBRATION TEST SYSTEM........................................ . 109R, M. McCafferty, U.S. Bureau of Reclamation, Denver, Colorado

MULTI-DEGREE OF FREEDOM MOTION SIMULATOR SYSTEMS FOR TR!.1,4SPORTATIONENVIRONMENTS. . .. . .. . .. . . ................... ........... .. .. 119

T. K., DeClue. R. A. Arone and C. E. Deckard, Wy.e Laboratories, Huntsville, Alabama

DESIGN AND FABRICATION OF AN AIRCRAFT SPAT CRASH SIMULATOR ........... 133Nelson M, Isada, State University of New York at Buffalo, Buffalo. New York

DESCRIPTION OF A SHOCK AND VIBRATION DISPLACEMENT AMPLIFIER ... 149D,. Cerasuolo and J,- Chin, Raytheon Company. Sudbury, Massachusetts

ARTILLERY SIMULATOR FOR FUZE EVALUATION... . .. 155H. D. Curchack, Harry Diamond Laboratories. Washington, D.C.

GAS SPRING FIRING AND THE SOFT RECOVERY O1 A HARD-WIRE INSTRUMENTED155 MM PROJECTILE . . - ,. . .. ., .- ......... , .'' ........ 175

S. L. Fluent, Heat, Plasma, Climatic, Towers Division. Sandia Laboratories,Albuquerque, New Mexico

FULL-SCALE RECOIL MECHANISM SIMULATOR (FORCED FLUID FLOW THPOUGH ACONCENh;hC ORIFICE). . ....... ................... 87

W., J. Courtney, lIT Research Institute, Chicago, Illinois and R, Rossm!ller andR. Reade, U.S. Army Weapons Commr d, Rock Island, Illinois

!SOTOPE FUEL IMPACT FACILITY ......................... . .. . 195Larry 0. Seamons, Sandia Labordtories, Albuquere,-e,. New Mexico

A REVERBERATION CHAMBER FOR USE AT REDUCED PRESSURES ............... 207M. H. Hieken, J. N. Olson, and G. W. Olmsted, McDonnell Aircraft Company,St. Louis, Misaouri

DESIGN OF AN OFF X,.)AAD VEHICLE MOTION SIMULATOR ................... 215.,elson M. Isa an, Cornell Aeronautical Laboratory, Inc., and State University ofIlew York at Aufialo,. Buffalo, New York and Robert C., Sugarman, and E. Donald Sussman,*..ornell Ae' onautic,.l Laboxratory, Inc., Buffalo, New York

AN AERIAL CABLE T1:ST 'FACILITY USING RCCKET P0!ER *.......... . .. 223C. G. Cotbuon, Sandia l.aboratorleq Aibtquý,rque. N .w Mexico

I i IS

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Bulletin 41

Part IV

"Vibration

SURVEY OF SPACE VEHICLE VIBRATION ANALYSIP AND TEST TECHNIQUES .......W. Henricks, R. J. Herzberg, B. G. Wrenn, Lockheed Missiles -,d Space Company,Surnyvale, California

METHODS USED TO REALISTICALLY SIMULATE VIBRATION ENVIRONMENTS ......... 29J. V. Otts, Centrifuge, Vibration, and Acoustics Division, Sandia Laboratories,Albuquerque, l4ew Mexico

SIMULATION OF COMPLEX-WAVE PERIODKc VIBRATION ....................... 37A. J. Curtis, H. T. Abstein, 3:., and N. G. Tinlin',, Hughes Aircraft Company,Calver Cit,, Ca!ifornia

RATIONALES APPLYING TO VIBRATION FOR MAINTENAN ZE.................. 51A. H. Griuniy, Canadian tr,'es Headquarters, Ottawa, Canada

SPECIFICATION OF SINE VIBRATION TEST LEVELS USING A FORCE-ACCELERATIONPRODUCT TECHNIQUE ......................... ......... ..... 69

A. F. Witte, Vibration ani Acoustics Test Division ,Sandia Laboratories,Albuquerque, New Mexico

SOME EF"-ECTS OF EQUALIZATION WITH A SINGLE MASS VS AN ELASTICSYSTEM ON ACCELERATIONS AND STRESSES ,,,.... ...... ....... 79

R. M. Mains, Wasington University

A METHOD FOR PREDICTING STRUCTURAL RESPONSES FROM LOWEFk LEVELACOUSTIC TESTS . . . * ... . . . . .. .. , ... .. . .. . .... ....... .. .. .. . . . . 87

D. 0. Smalwood, Centrifuge, Vibration, Acoustics Division, Sandia Laboratories,Albuquerque,, New Mexico

SWEEP SPEED EFFECTS IN RESONANT SYSTEMS ..................... 95

Ronald V. Trull, USAF, 4750th Test Squadron, Tyndall AFB, Florida

THE DYNAMIC RESPONSE OF A STEEL EYEBAR CHAIN SUSPENSION BRIDGEOVER THE OHIO RIVER TO VARIOUS EXCITATIONS ...... .. . . ... .... 99

R. F. Varney, J., G. Viner, Federal Highway Administration, Department ofTransportation, Washington, D.C.

DUAL SPECIFICATIONS IN RANDOM VIBRATION TESTING, AN APPLICATIONOF MECHANICAL IMPEDANCE. .ý . ........... ..... 109

A. F. Witte, Vibration and Acoustics Test Division, Sandia Laboratories, kl.iuquerque,New Mexico and R. Rodeman, Applied Mechanics Division, Sandia Laboratories,Albuquerque, New Mexico

VIBRATION - A DIAGNOSTIC TOOL FOR SHOCK DESIGN . . .. .... 119Culver J. Floyd, Raytheon Company, Submrine Signal Division, Portsmouth,Rhode Island

THE RESONANT RESPONSE OF A MECHANICAL SYSTEM SUBJECTED TOLOG kRITHMICALLY SWEPT AND OOTCHED BASE EXCITATION. USINGASYMPTOTIC EXPANSION ..... e, ........ ., , ......................... . , I 7

B., N. Agrawal, COMSAT Laboratories. Carksburg, Maryland

11

|

EFFECTS OF FLIGHT CONDITIONS UPON GUNFIRE INDUCED VIBRATIONENVIRONMENT ................................................. 133

J. A. Hutchinson and B. G. Musson, LTV Aerosp-mce Corporation, Vought AeronaL'icsDivision, Dallas, Texas

THE BOX CAR DYNAMIC ENVIRONMENT .... ............................. 141Robert W. Iuebke, C and O/B and 0 Railroad Companies, Baltimore, M.ryland

THE NOISE ENVIRONMENT OF A DEFLECTED-JET VTOL AIRCRAFT ................. 161S. L., McFarland and D. L. Smith, Air Force Flight Dynamics Laboratory, Wright-Patterson Air Force Base, Ohio

VIBRATION SIGNATURE ANALYSIS OF BEARINGS AND ELECTRONIC PACKAGES... ....... 173Charles H. Roos, General Electric Company, Aerospace Electronic Systems,Utica, New York

OUTER LOOP CONTROL FOR VIBRATION TESTING ................ ....... 183Gordon Lester, Perkin-Elmer Corpor'tion, Danbury, Connecticut and James Gay Helmuth.Chadwick-Helmuth Company, Inc., Monrovia, California

EMPIRICAL PREDICTION OF MISSILE FLIGHT RANDOM VIBRATION,.... * ..... . .. 189A. E. Kartman, The Bendix Corporation, Mishawaka, Indiana

STRUCTURAL VIBRATIONS IN THE BELL AH-IG HELICOPTER DURINGWEAPON FIRING. . . .. .......... ................................... ... 195

R. Holland, Kinetic Systems, Inc., Boston, Massachusetts and D. Marcus and J. Wiland,U.S. Army Frankford Arsenal, Philadelphia, Pennsylvania

CHARACTERISTICS OF GUNFIRE INDUCED VIBRATION IN HELICOPTERS .......... ... 209C. E. Thomas and V. C. McIntosh, Air Force Flight Dynamics I aboratory,Wright-Patterson Air Force Base, Ohio

INFLIGHT VIBRATION AND NOISE STUL 'OF THREE HELICOPTERS... . ..... 221Phyllis G. Bolds and John T. Ach, Air Porce Flight Dynamics Laboratory.Wright-Patterson Air Force Base, Ohio

Bulletin 41

Part V

Shock

A t,09CUWSIC• OF PYROTECHNIC SHOCK CRITERIA...........................M. B., MeGrath, Martin Marietta Corporation, Denver, Colorado

A SUMMARY OF PYROTECHNIC SHOCK IN THE AEROSPACE INDUSTRY . . .. .. 9W, P. Rader, Martin Marietta Corporation, Denver, Colorado and William F., Bangs.Goddard Space Flight Center, Greenbelt, Maryland

MEASURES OF BLAST WAVE DAMAGE POTENTIAL . ....... ...... 17C. T. Morrow, LTV Research Center, Western Division, Anaheim. California

SilOtK RESPONSE OF A BILINEAR, HYSTERETIC BEAM AND SUPPORT SYSTEM ........ 27Bruce E. Burton, Ohio Northern University and Robert S. Ayre, University ofColorado, Boulder, Colorado

120

r

DIGITAL FOURIER ANALYSIS OF MECHANICAL SHOCK DATA. 39H. A. Gaberson, and D. Pal, Naval Civil Engineering Laboratory,Port Hueneme, California

THE COMPUTER DETERMINATION OF MECHANICAL IMPEDANCE FOR SMALLARMS FROM THE RESPONSE TO RECOL. . . .. .. ............... .• 53

L. B. Gardner, R. K. Young. and D. E. Frericks, U.S. Army Weapons Command.Rock Island, Illinris

SHOCK PULSE SHAPING USING DROP TEST TECHNIQUES ............................ 59R. E. Keeffe and E. A. Bathke, Kaman Sciences Corporation, Colorado Springs,Colorado

ANALYSIS OF PROJECTILE IMPACT ON COMPOSITE ARMOR...................... 69Richard A. Fine, IBM Corporation, Rochester, Minnesota and -dymond R. Haggknd,Worcester Polytechnic Institute, Worcester, Massachusetts

A SYSTEMATIC APPROACH TO SHOCK HARDENING ........... 77J. L. Lipeles, Littleton Research and Engineering Corporation, Littleton,Massachusetts and D. Hoffman, Naval Ammunition Depot, Crane. Indiana

THE DEVELOPMENT OF SHOCK TEST CRITERIA FOR AIRCRAFT DISPENSERWEAPON EJECTION MECHANISMS . ., .......... ........ . I........ 89

K. D. Denton, K, A. Herzing, and S. N., Schwantes, Honeywell. Inc., OrdnanceDivision, Hopkins, Minnesota

SHOCK LOAD RESPONSE OF AN ELASTIC ANNULAR PLATE ON ADISTRIBUTEL) FOUNDATION .......................... 101

John R. Mays, Department of Civil and Environmental Engineering, University ofColorado, Denver, Colorado and James E. Nelson, Space Systems Dynamics, MartinMarietta Corporation, Denver, Colorado

Fragility

METHODOLOG" AND STANDARDIZATION FOR FRAGILITY EVALUATION 111R. C. Rountree, Logicon, San Pedro, California and F, B. Safford, TRW Systems Group,Redondo Beach, California

CONTROLLING PARAMETERS FOk THE STRUCTURAL FRAGILITY OF LARGESHOCK ISOLATION SYSTEMS .: ., ................. . ............ 129

!.7obert J, Port, Air Force Weapons Laboratory, Kirtland Air Force Base. New Mecico

HARDNESS EVALUATION . ............ 135W. H. Rowan, TRW Systems Group, Redondo Beach, California

FRAGILITY TESTING FCR HYDRAULIC SURGE EFFECTS ... ........ 143D., M. Eckblad, The Boeing Company, Seattle, Washington and W. L., Hedrick, TRWSystems Group, Redondo Beach, California

INITIAL DESIGN CONSIDERING STATISTICAL FRAGILITY ASSESSMENT.............. 155R. L., Grant, the Boeing Company, Seattle, Washington

TRANSIENT PULSE DEVELOPMENT .......................... 167J. Crum and R. L. Grant, The Boeing Company, Seattlc ashingion

121!

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Bulletin 41

Part V1

Lvy-amIcs

PARAMETRIC RESPONSE OF MONOSYMMETRI2 IMPERFECT THIN-WALLEDCOLUMNS UNDER SW1USUiDAL LOADING ...................................

Stanley G. Ebner, USAF I demy, Colorado and Martin L. Moody,Univey ijity of Colorad-, r&.,.. ,Colorado

PREDICTION OF UPSTAGE RANDOM VIBRATION ENVIRONMENT U'NG APTATISTICAL ENERGY APPROACH ................................ 9

D. E. dines, G. R. T ulker, and R. D. Hellweg, McDonnell Douglas Astronautics Company-West, Santa Monica, Califorma

ON THE REDUCTION AND PREVENTION OF THE FLUID-INDUCED VIBRATIONSOF CIRCULAR CYLINDERS OF FINITE LENGTH ................... . 31

D~rse W. Sallet, Department of Mechanical Engineering, Universit:, of MarylandCollege ."ark, Maryland and U.S. Naval Ordnance Laborat._.';, Whit Oak,Sil-- •.':ing, Maryland

EFFECTS OF LOOSENESS ON DYNAMIC BEHAVIOR ............................ 39R. E. Beckett, K. C. Pan, U.S. Army Weapons Command, Rock Ialqnd. Illinois andD. D. Penrod, The University of Iowa, IoWa City, Iowa

DYNAMIC DEFLECTIONS OF MULTIPLE-SPAN GUIDEWAYS UM'DERHIGH SPEED, AIR CUSHION VEHICLES.......................... ,:. 47

James F. Wilson, Duke Un;vrsity, Durham, North Cnroiina

ANALYSIS OF THE MOTION OF A LONG WIRE TOWED FROM ANORBITING AIRCRAFT ".' . ., • • . . - - ... ...... ." . e '., . ,. ... V. ' ... .: 61

3. A. Crist. Department of Engineering Mechanics, USAF Academy, Colorado

A POSTSHOT STUD'I OF THE DYNAdIC RESPONSE OF THE LASL MOBILETOWER DURING THE PLIERS EVENT . :., , ,.... ..................... . . I.P . . 75

R.. E. Bachman, E. F.; Smith, Holmes and Farver, Inc.. Las Vegas. Nevadn andR. P, Kennedy, Holmes and Narver, Inc.. Los Angeles. California

BOUNDS FOR ThE RESPONSE OF A CONSERVATIVE SYSTEMUNDER LYNAAMIC LOADING . ...... ...... , ,. , . , ,., . .: ............... , .7

H.e BrauchUi, Tfe University of Alabama in Huntsville. Huntsville, Alabama

THREE DEGREE OF FREEDOM SPRING MASS E. ECTION SYSTEM . .. . . . . . 93R. Muskat, Aerospace Corporation. San Bernardino California

STRuCTURAL DYNAMICS OF A PARABOLOIDAL ANTENNA .................... 103Myron L.: Gossard and William B. I'aile, Jr., Lockhet' Missiles a.:d Space Company,Sunnyvc, , California

AN APPLI:ATiON OF COMPONENT MODS SYNTHESIS TO ROCKE-iMOTOR VIBRATION AI0 ALYSIS 1 .. . ,. ...... 115

:F, R, Jensen, Hercules Inc., and He., N., Christiansen, Brigham k' ung Uni,'ersity

COMPARISON OF CONSISTENT AND LUMPED MASS MATRIX SOLUTIO.'WIT4 THE EXACT SOLUTION FOR A SIMPLY-SUPPORTED TIMOSHENKO BEAM ...... 123

C., Oaum, J, T. Higney, Gibbs and Cox Inc., New York,, New I orK and A. Jenks,"3so international Inc.. New York., Nf w York

122

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"APPLICATION OF APPROXIMATE TRANSMISSION MATRICES TO DESCRIBETRANSVERSE BEAM VIBRATION'S .... .......................... 133

R. D. Rocke a-d Ranjit Roy, University of Missou.'i-Rolla, Rolla, Missouri

MEASUREMENT OF MOMENT-CURVAT'iRE RELATIONSHIP FOR STEEL BEAMS ....... 141V. H. Neube:t and W. Vogel, The Penns3 Ivania State University,University Park, Pennsylvania

SELF-SYNCHRONIZATION OF TWO PCCZN.TRIC ROTORS ON A BODY INPLANE MOTIOI4 ......................................... 159

M'rio Paz, Associate Professor, University of Louisville, Louisville, Kentucky

PROPAGAT1C." OF THF ERROR IN COMPUTED FREQUENCIES AND MODE SHAPESRESUJT-rC FROM A D!9CRETE MASS REPRESENTATION OF UNIFORM,SLENDLA BEAMS WITH \ ARYING HEIGHT-TO-LENGTH RATIOS ............ 163

Fran,".* tq. Henderson, Naval Ship Research and Development Center,Waaington, D. C.

Dynamic Stress Analysis

A DISCUSSION ON THE ANALYTICAL DYNAMICS, STRESS,AND DESIGN INTERFACES ....................................... 179

Irvin P. Vatz, Teledyne Brown Engineering, Huntsville, Alabama

DYNAMIC STRESS ANALYSIS IN A STRATIFIED MEDIUM .................. 187Jackson C.S. Yang, Ames Research Cent'er, NASA. Moffett Field, California

COMPARISON OF STRUCTURAL LOADS: STATIC VERSUS DYNAMIC .............. 197Paul J. Jones and William J. Kacena, III, Martin Marietta Corpoi ation,Denver, Colorado

EGGSHELLING AND VIBIRATIONS OF A HIGH SPEED SHAFT WITHNASTRAN ANALYSIS ...... ..... ......... ........ ......... 203

Dennis J. Martin and William C. Walton. Jr., NASA Langley Research Center.Hampton, Virginia

PARAMETRIC STUb, OF A BEAM WITH A COMPOUND SIDE-BRANCH RESONATORAS A DEVICE TO EVALUATE PRELIMIF"ARY DESIGN LOADS ................. 211

J., Roger Ravenscraft, Teledyne Brown Engineering, Huntsville, Alabama

RAIL LAUNCHING DYNAMICS OF THE SAIA-D SURFACE-TO-AIR MISSILE ........ 219Martin Wohltmann, Leonard A. Van Gulick. H, Carlton Sutphin, Martin MariettaCorporation, Orlando. Florida

Bulletin 41

Part Vi1

Mathematical _A"ysis

ROCKET-SLED MODEL ITUDY OF PREDICTION TECHNIQUES FOR FLUCTUATE GPRESSURES AND PANA'L RESPONSE, .: ...... I.................

Eric E. Ungar, Roh E.,ranek and Newman Inc., Cambridge, Mas,:,chusetts

DETEI.N.MINATION OF S'RUCTURAL PROPERTIES FROM TEST DATA . *........9

A. F. Galef and D. L. Cronin, TRW Systems Group., Redondo Beach, Cslifornila

123

VALIDITY OF MATHEMATICAL MODELS OF DYNAMIC RES•PONSE OF STRUCTURESTO TRANSIENT LOADS ...................................... 19

Wilfred E. Baker, Southwest Research Institute, San Antonio, Texas

DYNAMIC RESPONSE OF PLATES WITH CUT-OUTS ...................... 29Nicholas L. Basdekas, Office of Naval Research, Arlington, Virginia andMichael Chi, Catholic University of America, Washington, D. C.

NATURAL FREQUENCIES AND MODE SHAPES OF PLATES WITHINTERIOR CUT-OUTS ............ 37

Jon Monahan, P. J. Nemergut, USAF Air Force Institute of Technology,G.E. Maddux, Air Force Flight Dynamics Laboratory Wright-Patterson AFB, Ohio

FINITE BEAM ELEMENTS FOR DYNAMIC ANALYSIS ..................... 51V. H. Neubert, The Pennsylvania State University, State College, Pennsylvania andH. Lee, Westinghouse Research Labor atory, Pittsburgh, Pennsylvania

EVALUATION OF MODELS FOR ONE-DIMENSIONAL VIBRATION SYSTEMS ............ 61R. D. Rocke, University of Missouri-Rolla, Rolla, Missouri

DYNAMIC ELASTOPLASTIC RESPONSE OF GEOMETRICALLY NONLINEARARBITRARY SHELLS OF REVOLUTION UNDER IMPULSIVE ANDTHERMAL LOADINGS ..... ............. 81

T. . Chung, J. T. Oden, R. ". Eidson, J. F. Jenkins, and A. E. Masters,Research Institute, The Un•versity of Alabama in Huntsville, Huntsville, Alabama

RIGID BODY MOTIONS OF 2LASTICALLY RESTRAINED UNDERWATER STRUCTURESFROM DETONATION-INDUCED SHOCK ............. 89

H. S0 Zwibel and J. G. Hammer, Naval Civil Engineering Laboratory,Iort Hueneme, California

EXTENSION OF CLASSICAL BINARY FLUTTER MODEL USING ROOT LOCUS ....... 109J. C. Hornbuckle, and R. L. Sierakowski, University of Florida, Gainesville Florida

STIFFNESS AND MASS MAfRICES FOR A TRIANGULAR ELEMENT ................. 123Mario Paz, Associate Profes'or, Civil Engineering Department. University ofLouisville, Louisville, Kentuck) and Earl Berry, Jr., Graduate Student,University of Louisville, Louisville, Kentucky

HELICOPTER FUSELAGE VIBRATION RESPONSE ANALYSIS USING THEhYBRID COMPUTER ...... ............. ........................... 131

James D. Cronkhite, Bell Helicooter Company, Fort Worth. Texas

VIBRATION OF A CLASS OF NONCONSERVATIVE SYSTEMS WITH TIME-DEPENDENTBOUNDARY CONDITIONS ..... ........ ... ........... 141

Shoei-sheng Chen, Argonne National Laboratory, Argonne. Illinois

Fluid-Structure Interactions

A VARIATIONAL APPROACH TO THE FLUID-SHELL DYNAMICINTERACTION PROBLEM . ., ,, ... - .. ..... • . .,. ... ....... 151

A. S. Benson. Lockheed Missiles and Space Company. Sunnyunle, CaliforniaI EQUIVALENT MECHANICAL MODEL OF PROPELLANT FREE-SURFACEVIRRA7IONS IN THE SATURN S-IVB WORKSHiOP CONFIGURATION 1..... . 169

Frankiln T.. Dodge .ind Luis R., Gnrza, Southwest Research Institute,

3,n &Altofnio,. Texas

024

THE EFFECT OF LIQUID OSCILLATIONS ON THE LM PROPELLANT QUANTITYGAUGE SYSTEM ......................................... 181

M. Rimer, Grumman Aerospace Corporation, Bethpage, New York andD. G. Stephens, NASA Langley Research Center, Hampton Virginia

DERIVATION OF SKYLAB PROPELLANT STORAGE MODULE RANDOM VIBRATIONENVIRONMENT ........................................ 195

A. E. Chirby, R. A. Stevens, H.C. Allen and W.R. Wood, Jr., North AmericanRockwell Corporition, Space Division, Downey, California

THE FLUTTER OF A HYDROFOIL ......... . ...................... 205Thomas M. Wnrd, California institute of Technology, Pasadena, California andRaymond C. Binder, University of Southern California, Los Angeles, California

SUPPLEMENT

AN AIR PULSER FOR VIBRATION TESTING ............................ IJ. R. Peoples, Naval Ship Research and Development Center, Washington, D.C.and J. G. Viner, Federal Highway Administration, Washington, D. C.,

STATISTICAL APPROACH TO OPTIMIZE RANDOM VIBRATION TEST SPECTRA ........ 25David L. Earls and John F. Dreher, Air Force Flight Dynamics Laboratory,Wright-Patterson Afb, Ohio

THE EFFECT OF TAILFINS ON "HE VIBRACOUSTIC ENIRONMENT OFEXTERNALLY CARRIED AIRCRAFT STORES ........................... 33

John F. Dreher, Air Force Flight Dynamics Laboratory, Wright-PattersonAir Force Base, Ohio

THE EFFECTS OF VISCOUS DAMPING ON DYNAIvaC LOAD FACTORS FORSINGLE DEGREE-OF-FREEDOM SYSTEMS ........................... 45

Harry Price Gray, Naval Ship Research and Development Center, Washington, D.C.

THE EFFECT OF CAVITATION ON THE FLAT PLATE HULL UNDERWATERSHOCK MODEL .. ........................................ 49

R. J. Scavuzzo, Rensselaer Polytechnic Institute, Hartford Graduate Center,East Windsor Hill, Connecticut, and D. 1). Raftopoulos, The University of Toledo,Toledo, Ohio

125

Appendix A

~i~i pig. �1 127

APPENDIX A

Shock and Vibration Bulletins36 through 41

Bulletin No. Part No. Date DDC

36 1 Mar. 1967 AD 381 3042 Feb. 1967 AD 647 6443 Jan. 1967 AD 646 9624 Jan. 1967 AD 647 6455 Jan. 1967 AD 646 9836 Feb. 1967 AD 651 4037 Feb. 1967 AD 651 404

37 1 Apr. 1968 AD 390 496L2 Jan. 1968 AD 667 2273 Jan. 1968 AD 667 2284 Jan. 1968 AD 667 2295 Jan. 1968 AD 668 2466 Jan. 1968 AD 688 3287 Jan. 1968 AD 608 230

Supplement Jan. 1968 AD 831 154

38 1 Aug. 1968 AD 682 2012 Aug. 1968 AD 683 3133 Nov. 1968 AD 683 314

Supplement Aug. 1968 AD 847 594

39 1 Apr. 1969 AD 502 850L2 Feb. 1969 AD 688 4453 Jan. 1969 AD 684 0654 Apr. 1969 AD 688 7885 Dec. 1968 AD 684 0666 Mar. 1969 AD 688 789

Supplement Apr. 1969 AD 853 161

40 1 Dec. 19691-R Dec. 19692 Dec: 19693 Dec. 19694 Dec. 19695 Dec. 19696 Dec. 1969

Si-pplement Dec. 1969

41 1 Dec. 1970 "2 Dec. 1970 *3 Dec. 19704 Dec. 19705 Dec. 19706 Dec. 1970 *

"Dec. 1970Supplement Dec. 1970 •

*Not available through either DD)' or NTIS see availability statement.Availability

Bulletins 36 Pan 1, 37, Part 1 and Supp Pment, 38 Supplement, and 39 Part 1 and Supplement should be ordered from the DefenseDocumentation Center (DD('), Canweror Station, Alexandria, 'irginia 22314.Bulletins 36 Parts 2.7. 37 Parts 2-7. 38 P, rts 1-3. and 39 Parts 2.6. should ibe ordered from the National Technical Information Ser.vite (NTIS). U.S. Department of Commere, Springfield, V'irgini 22151.Bulletins 40 and 41 should be ordered from the Navv Publcvation and Printing service Office, Naval Distinvt Wsslhmgton, Bldg 157-2.Washington Navy Yard, Washington, D.C. 20390. The price for vither the 40th or the 41st Bulletin is $15 00 for the complete getA c'i•ek or money order lpayable to the Treasurer of tlh U'nited Sitaes mult tivonilluJay the order

129

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