main landing gear drop test report - dtic
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REPORT DUMBER 147
MARCH 1964
MAIN LANDING GEAR DROP TEST REPORT
/
M LIFT FAN FlieNT'RESEARCH AIRCRAFT PROGRAM
CONTRACT NUMBER DA44-177-TC-7?5
GENERAL^) ELECTRIC
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DDC AVAILABIIITY NOTICES
Distribution of this document is unlimited.
2 This document is subject to special export controls and each trans- mi ttal to foreigr governments or foreign nationals may be made only with prior approval of US Army Aviation Materiel Laboratories^ Fort Eustis, Virginia 23604
3. In addition to security requirements which must be met, this docu- ment is subject to special export controls and each transmittal to foreign gcvernmems or f c re i E" .nationals may be made only with prior approval of USAAVLABS, Fort Eustis, Virginia 23604
4. Each transmittal of this document outside the agencies of the US Govcrnmenr must have prior approval of US Army Aviation Materiel Laboratories, Fort Eustis, Virginia 23604.
5. In additicn to security requirements which apply to this document and must be met. each transmittal o^*side the agencies of the US Government most have prior apprcval of US Army Aviation Materiel Laboratories. Fort Eustis, Virginia 2 36C4„
6. Each transmittal ot this document outside the Department of Defense mast have prior approval of US Army Aviation Materiel Laboratories, Fort Eusfis. Virgiria 2 3604.
7. In additio" to security requirements which apply to this document a-d must be met, each transmittal outside the Department of Defense must have prior approval of US Army Aviation Materiel Laboratories, Fort Eustis, Virgin: a 23604.
8. Ibis document may be further distributed by any holder only with specific prior approval of US Army Aviation Materiel Laboratories, Fort Eustis Virginia 23604,
9. yr addition to security requirements which apply to this document and must be met,, it may be further distributed by the holder only with, specific prior approval of US Army Aviation Materiel Laboratories, Fort Eustis, Virginia 236C4
DISCLAIMER
10,, The findings in this report are not to be construed as an official Department cf the Army position unless so designated by other authorized documents.
/ 11 „ When Government, drawings, specifications, or other data are used for any purpose other than in connection with a definitely related Ccvernment procurement operation , the United States Government thereby incurs no responsi- bility ncr a-.y obligation whatsoever; and the fact that the Gcvernir.ert may have formulated, furnished; or in any way supplied the said drawings, speci ficaticns or other data is not to be regarded by implication or otherwise as
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in any manner licensing the holder or any other person or corporation, or ronveying any rights or permission, to manufacture, use, or sell any patented invention that may in any way be related thereto«
12. Trade names cited in this report do not constitute an official endorsement or approval of the use of such commercial hardware or software.
DISPOSITION INSTRUCTIONS
^ I'Sy) Destroy this report when no longer needed. Do not return it to origtrtator.
1^+. When this report is no longer needed. Department of the Army organi- zations will destroy it in accordance with the procedures given in AR 380-5.
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REPORT NUMBER 147 MARCH, 1964
MAIN LANDING GEAR
DISTü: .J DROP TEST REPORT
7i
XV-5A LIFT FAN
FLIGHT RESEARCH AIRCRAFT PROGRAM
ADVANCED ENGINE AND TECHNOLOGY DEPARTMENT
GENERAL ELECTRIC COMPANY
CINCINNATI, OHIO 45215
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r r r
1S10LTR-1 DROP TEST REPORT
K W. LOUD MACHINE WORKS. Inc POMONA CAUFORN1A
Pag« 1
r REVISIONS
DaU
11-6.63
Chang« L«tt«r D««crlyClon
Pag« 2: Addcid App«adlx "A" Drop T««t R«quir«m«ntf Add«d App«ndix "B" Basic Strut Air Pr«isar« Carv«
Pag« 5: Corr«ct«d Mats Trav«! Valuss Addad: Aircraft Configuration Aircraft Sign Convention Not«s 167 Psig Drop T«st Inflation Prassur«. "8«« also Appondix "B" Added: 167 Psig Inflation Prassur«
: Addod: 167 Psig Inflation Prassur« : Add«d: 167 Psig Inflation Pr«ssur< : Add«d: 167 Psig Inflation Prsssun 3. U, 15, k 16: Added Calibration
Paga 9: Pag« 10 Pag« 11 Pag« 12 Pag«s 1
Approval«
/.; /
7
Values. 167 Psig Inflation Pressur«
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1510LTR-1 DROP TEST REPORT
H. W LOUD MACHFNE WORKS. Inc POMONA. CALIFORNIA
Page 2
TABLE OF CONTENTS
Paragrapn
1.0
2. Ü
3.0
4.0
5.0
Figure I
Figure II
Figure III
Figure IV
Figure V
Figure VI
Figure VII
Appendix A
Appendix B
General
Applicable Documents
Summary
Discussion
Results
Table I
Drop Tost Tower
Reaction Platform
Orifice and Metering Pin Configuration.
Record #9770, Strut Stroke or Mass Travel-Inches
Record ^9772, Strut Stroke or Mass Travel-Inches
Record #9785, Strut Stroke or Mass Travel-Inches
Record #97d7, Strut Stroke or Mass Travel-Inches
Oscillograph Records #9770. #9772. #978S. #9787
Drop Test Requirements
Basic Strut Air Pressure Curve
Pag<
3
3
3
4
4
5
b
7
8
9
10
11
12
13 thru 16
17
19
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1510LTR-1 DROP TEST REPORT
H. W. LOUD MACHINE WORKS. Inc POMONA. CALIFORNIA
Page 3
1.0 GENERAL:
The shock absorber portion of the HlOLlOO Main Landing Gear, but
using a dummy cylinder was tested on 2 August 1963, in accordance
with the H. W. Loud Test Procedure 1S10LTP-4. Revision "A". This
report presents the successful completion of the established test
requirement».
The tests were witnessed by H. W. Loud Quality Control and Mr.
Heinz J. Kowaczek of Federal Aviation Agency.
2.0
2. 1
2.2
APPLICABLE DOCUMENTS:
1510LTP-4, Revision "A . H. W. Loud Drop Test Procedure.
SCDLÜ001, Ryan Main Gear Specification.
3.0 SUMMARY:
The results of the tests demonstrate satiafactory energy absorption
characteristics of the shock absorber. (See Table I)
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1510LTR-1 DROP TEST REPORT
H. W. LOUD MACHINE WORKS. Inc POMONA, CALIFORNIA
Page 4
4. 0 DISCUSSION:
The shock absorber was mounted in the drop tower (See Figure I).
The ground roactions were meaaured with a reaction platform (See
Figure II). 'x he strut was serviced with hydraulic fluid «und extended
\v ith 167 pbig air pressure. The tire waa inflated to 180 paig.
5.0
The teats were performed in accordance w th the 1510LTP-4, Rev-
ision "A" Test Procedure. See Appendix "A" for a copy of the test
requirameata taken from the procedure.
Figure III shows the configuration of the metering pin and oriiice.
RESULTS:
The test results are given in Table I. The curves of vertical load vs
stroke and vertical load vs mass travel after contact are given in
Figures IV, V, VI, and VII. The actual tost oscillograph traces are
fcld out pages
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1510LTR-1 DROP TEST REPORT
H. W. LOUD MACHINE WORKS Inc POMONA. CALIFORNIA
Page 5
TABLE I
Drop Serie« Record No.
Aircraft Configuration
Drop Height (Inches)
Actual Jig Wt. (lbs)
Energy Abeorbad (Ft. Ibi)
Wheel Speed (rpm)
3 9770
1 9772
2 9785
^
4 9787
2 PT Level 2 PT Level Tail Down 2PTVTOL! Gear Fwd. Gear Fwd. Gear Fwd. Gear Aft I 12500 lb. 9200 lb. 9200 lb. 9200 lb. !
6.80
6238
2983
2292
18.70
4638
5985
1971
18.70
4638
6210
1971
18.70
4638
6363
Sinking Velocity (Ft/sec)
6 10 10 10
Mats Travel (Inches) 6.89 8.61 8. 37 9.35
Tire Deflection (Inches) 1.52 1.64 1.65 1.66
Oleo Stroke (Inches)
5.54 7.02 6.78 7. 50
Platform Vert. Reaction (lbs)
7050 11370 12100 10840
Plat. Drag Fore 1450 2820 2000 o Reaction (lbs)Ait 3270 4090 4640
Strul Efficiency (%)
81.4 82.4 81.3 8x6
(a) 167 psig drop test inflation pressure
(b) See aUo Appendix "B"
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1-ilOLTR- 1 DROP TEST REPORT P a g e 6
H. W. LOUD MACHINE WORKS. Inc POMONA. CALIFORNIA
F I G U R E I
D R O P T E S T T O W E R
XVSA MAIN LANDING G E A R
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1 5 1 0 L T R - 1 D R O P T E S T R E P O R T P a g e 7
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1510LTR-1 DROP TEST REPORT Page 8
) K W. LOUD MACHINE WORKS. Inc. POMONA. CAIJP0KN1A
FIGURE III
- r~ .320/ . 310
< rk — ( } \ V
120R Typ. i •i '. 300 301 DU.
1310L113 ORIFICE CONFIGURATION (HALF SIZE)
10. 34
9. 360
1.915 —
9. #40
8.800
— M i 5 -STRAIGHT TAPER
) f \ -T -» -4
It Ff Vrj r J I T
.445
.443
.481
.479
DU.
DU.
J /
.451
.449
.376
.374
12°
DU.
DU.
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-I
1510L112 METERING PIN CONFIGURATION (HALF SIZE)
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DROP TEST REPORT M10LTR-1 P*I« *
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f510L.TR-1 DROP TEST REPORT Page 10
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1510LTR-1 DROP TEST REPORT
H. W LOUD MACHINE WORKS. Inc POMONA. CMJFORNIA
Appendix A
Ptiiiv 17
APPENDIX A
DROP TEST REQUIREMENT
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ISlOLTR-l DROP TEST REPORT Appendix A
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