Microfiche (MFI A

PhEUMATIC NUTATOR ACTUATOR MOTOR BY

G. R. Howland

Prepared For

N A T I O N A L AERONAUTICS & SPACE A D M I N S T R A T I O N

CONTRACT N A S 3 - 5 2 1 4

I

BENDIX PRODUCTS AEROSPACE DIVISION

SOUTH BEND, INDIANA 46620

https://ntrs.nasa.gov/search.jsp?R=19650013373 2018-08-25T21:23:59+00:00Z

NOT ICE

This report was prepared as an account o f Government sponsored work. Neither t he United S ta tes , nor t h e National Aeronautics and Space Administration (NASA), nor any person ac t ing on behalf of NASA:

A.) Makes any warranty o r representat ion, expressed o r implied, wi th respect t o the accuracy, completeness, o r usefulness of the information contained i n t h i s repor t , o r t h a t t he use of any information, apparatus, method, o r process disclosed i n t h i s repor t may not in f r inge pr iva te ly owned r i g h t s ; o r

B.) Assumes any l i a b i l i t i e s with respect t o t h e use of , o r f o r damages r e su l t i ng from t h e use of any infor - mation, apparatus, method o r process disclosed i n t h i s report .

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Requests f o r copies of t h i s repor t should be r e fe r r ed t o

National Aeronautics and Space Administration Office of Sc ien t i f i c and Technical Information Attention: AFSS-A Washington, D.C. 20546

c

*

NASA No. C R - 5 4 3 8 2 B e n d i x No. BPAD-864-15664R

,

THIRD QUARTERLY REPORT

PNEUMATIC NUTATOR ACTUATOR MOTOR

G. R. H o w l a n d

Prepared For

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

March 31, 1965

CONTRACT NAS3-5214

TECHNICAL MANAGEMENT NASA LEWIS RESEARCH CENTER

CLEVELAND, OHIO ADVANCED DEVELOPMENT AND EVALUATION D I V I S I O N

VERNON D. GEBBEN

THE BENDIX CORPORATION BENDIX PRODUCTS AEROSPACE D I V I S I O N

SOUTH BEND, INDIANA

TABLE OF CONTENTS

SECTION 1 - SECTION 2 -

2.1 2.2 2.3

SECTION 3 - 3.1 3.2 3.3

SECTION 4 -

INTRODUCTION

MECHANICAL COMPONENTS

I n i t i a l Assembly Break-In Running Performance Measurements

COMMUTATION CIRCUIT

Logic Circuit Tests Pressure Error Valve Bistable Directional Amplifier

FOURTH OUARTER GOALS

Page 1-1 - 2-1

2-1 2-1 2-1

3-1

3-1 3-6 3-6

4-1

APPENDIX A - DISTRIBUTION LIST FOR CONTRACT NAS3-5214 QUARTERLY

APPENDIX B - DISTRIBUTION LIST FOR ABSTRACTS OF CONTRACT NAS3-5214 REPORTS A- 1

QUARTERLY REPORTS B- 1

i

, , -.

LIST OF ILLUSTRATIONS

Figure

2-1

2-2

2-3

2-4

3-1

3-2 (a)

3-2 (b)

3-3

3-4

3-5

Title

Pressure Profile - Bellows It1 and #5 Mechanical -

Commutator

Output Torque Versus Input Speed

Corrected Output Torque Versus Input Speed

Reversed Stall Torque

Commutation Plate Test Setup

Logic Circuit Output Pressure Differential

Logic Circuit Output Pressure Level

Test Setup for Model Directional Amplifier

Low Pressure Pressure Recovery

High Pressure Pressure Recovery

Page - 2-3

2-4

2-5

2-6

3-2

3-4

3-5

3-7

3-9

3-10

ii

4

PNEUMATIC NUTATOR ACTUATOR MOTOR

BY

G. R. Howland

ABSTRACT

This is t h e t h i r d quar te r repor t of a twelve-month program t o design, f a b r i c a t e and t e s t a prototype pneumatic nuta tor actuator motor f o r drum control of a nuclear reac tor .

During the th i rd quar te r , both t h e mechanical components and t h e f l u i d log ic c i r c u i t were assembled and tes ted . Performance of the motor, operated by a mechanical commuta- t i o n system, is described. The r e s u l t s of t he log ic c i r c u i t optimization program is a l s o given.

c

PNEUMATIC NUTATOR ACTUATOR MOTOR

G . R. Howland

SUMMARY

This repor t descr ibes t h e t h i r d qua r t e r accomplishments o f a twelve-month program t o develop a pneumatic ac tua tor motor of a new concept. produces a high torque, low speed mechanical output proport ional t o a pneumatic input pressure d i f f e r e n t i a l s igna l . t h e motor is accomplished by closed loop f l u i d in t e rac t ion (vortex type) devices ,

The ac tua to r motor operates from a pneumatic power supply and

The commutation log ic of

The mechanical components of t he motor were assembled and t e s t ed . Commutation was accomplished by a mechanical valving assembly which was ex te rna l ly driven. var ious input speeds, improving t h e motor performance .

The maximum obtainable torque was measured f o r A discussion is given of poss ib le methods of

I n i t i a l t e s t i n g and adjustment of t h e complete commutation log ic c i r c u i t is described. t h a t the c i r c u i t w i l l be capable of operat ing and con t ro l l i ng t h e motor.

Measurements o f t h e log ic c i rcui t output i nd ica t e s

The an t ic ipa ted goals f o r t h e fou r th and f i n a l qua r t e r are l is ted.

SECTION 1

INTRODUCTION

The Pneumatic Nutator Actuator Motor i s being developed by Bendix Products Aerospace Division under Contract NAS3-5214 f o r NASA-Lewis Research Center. and evaluate a pneumatic actuator motor f o r control of a nuclear reactor . Contract NAS3-5214. conventional gear, vane o r pis ton type ac tua tors , required t o operate the motor have no moving p a r t s and are composed of f l u i d in te rac t ion (vortex type) devices.

The purpose of the contract is t o bui ld

The required performance is given i n the spec i f ica t ions of The motor i s of a d i f f e r e n t concept from t h e

The log ic c i r c u i t s

During t h e t h i r d quarter , t he mechanical components of t he ac tua tor hardware were assembled and t e s t ed . by means of a mechanical commutation valving driven external ly .

The motor was operated

The pure f l u i d commutation p l a t e s were assembled and tes ted . Optimization of t he bleed o r i f i c e s i z e s was obtained.

Section 2 ou t l ines the present s t a t u s of t he mechanical Section 3 describes the s t a t u s of t he commutation components,

c i r cu i t ry . The fourth quar te r goals are given i n Section 4.

1-1

.

SECTION 2

MECHANICAL COMPONENTS

2.1 INITIAL ASSEMBLY

The actuator motor mechanical components were initially assembled to verify the assembly procedure. The only problem encountered during assembly (except for a minor bearing relief requirement) was the scram spring. friction was developed by the coils rubbing together. with the vendor, a more stringent specification was written and new springs are being manufactured.

This spring is a torsional clock type. It was found that excess After discussion

Delivery is expected about the middle of April.

For initial evaluation of the motor performance, the unit was assembled without the scram spring, torsion shaft, drum brake and dynamic seal . 2.2 BREAK-IN RUNNING

After initial assembly and adjustment, the motor was run continuously at an input commutation speed of 1000 rpm (5.6 rpm output speed) for fifteen minutes in each direction. On dis- assembly some flaking of the molybdenum disulphide lubricant on the gear teeth was noted. After approximately ten hours of running, mostly under high load condition, no further flaking of the lubricant was evident and the gear teeth appear in excellent condition.

No output load was applied.

2.3 PERFORMANCE MEASUREMENTS

After run-in, the pressures supplied to the bellows were monitored by gages on the mechanical commutator. It was found that the commutator was "breaking before making1', causing the number of pressurized bellows to vary between three and four, depending on the angular position of the commutator. The distribution slot in the commutator was modified to provide a more even pressure distribution. Figure 2-1 shows the pressure

2-1

variations in bellows #1 and # 5 . It can be seen that the reduction in one bellows pressure is accompanied by a corresponding increase in the other bellows pressure. and vent ports of the commutator are "short circuited" during portions of the commutation cycle. This short circuit causes an increase in the supply flow and a consequent reduction in the bellows pressure. reduction can be seen in Figure 2-1 each time a bellows is pressurized, Unsuccessful attempts were made to add capacitance to the inlet and bellows supply lines to minimize this pressure variation.

In order to obtain this symmetry, the supply

This

Maximum output torque for a given commutator speed was determined by loading the output shaft until the gear teeth disengaged. A plot of maximum output torque against input commutator speed is shown in Figure 2-2. Output shaft speed can be obtained by dividing the input speed by 180 .

This method of shaft loading will indicate the torque obtained when the pressurized bellows pressure is at a minimum. transient bellows pressure and measuring the minimum obtained, the output torque can be corrected to determine the actuator performance assuming a uniform bellows pressure. shown in Figure 2-3. which could be obtained with the self-commutation circuit.

By monitoring the

This corrected torque versus speed curve is The corrected curve indicates the maximum torque

The torque required to back drive the motor was found by holding the mechanical commutator stationary and applying sufficient torque to the output shaft to cause tooth disengagement. Figure 2-4 for various combinations of pressurized bellows.

This torque is shown in

Previous experience with nutator gear concepts has shown that the mechanical efficiency (n) is independent of the direction of drive. efficiency can be calculated from the output torque (To) and the back driving torque (Tr) as follows:

The

2-2

.

0

, i

. ._ . . - , - > ...., . . ::: ,.. !.

I

. ~ . , . ~, ,

..: -16- - ' - _

2-3

n Q) k 3 VI VI

E x d

m F VI

g d d a m

d N br 9 M CJ

0 4 snresSoig aaaeur “0. . 0 d d d 6 I I I

cpunod t p u ~ 2 : : d d 9 d N

OI 9 d

N 0 00 0 0 0 0

0 0 N d

0 ’0 d d

0 0 0 4

0 .O Q,

0 0 00

0 0 b

0 .O 9

0 .O v)

0 .O d

0 ’0 M

0 0 N

0 0 4

0

n

U E a Q, 0) a v)

w 3 a E U

P w w a m

s 5 a

w

3 s E O

CJ I N

LL

anbsoj andang

. 0 0 00 4

0 0 f- 4

0 0 \o 4

0 0 v1 rl

0 0 f 0 0 M

t d

0 0 cy rl

0

d n 2 0 k 0 - 0 - 3

53,

a3 a o w 0 m + r

G o u 0 00

0 z 0 0 \o

0 0 v1

0 0 d

0 0 M

0 0 cy

0 2

3

rr) 1

(Y

2-5

x - Clockwise Rotation o - Counterclockwise Rotation

-

-

-

-

Bellows Sup ly Pressure - 70 psig (48 x 10-8 newtons/meted)

6.38

489 in.lb. average

5.80

5-22

4.64

550

0

500

I I 1 1 1 1 1 1

450 al 3 ’ 400

350 4 4.06

FIGURE 2-4 REVERSED STALL TORQUE

2-6

c

or , from Figures 2-3 and 2-4,

This e f f i c i ency agrees c lose ly with t h e o r ig ina l design estimate (68%).

versus supply pressure cha rac t e r i s t i c s , but was terminated when a rapid de t e r io ra t ion i n output torque was noted. t h a t a l l four f lexure p ivo t s were e i t h e r broken o r badly d i s to r t ed . I t is f e l t t h a t a f a i l u r e of t he pivots resu l ted from t h e shock loading employed by t h e method of tes t and is not i nd ica t ive of t h e performance under normal operation. The pivot holes were rebored t o take l a rge r flexure pivots.

Further t e s t i n g of the motor was s t a r t e d t o determine t h e torque

Disassembly of t h e u n i t showed

This w i l l increase the torque capac i ty by 50%.

The maximum corrected output torque obtained was 2.89 meter-kilograms (250 in . lbs.) (see Figure 2-3). With a measured e f f i c i ency of 71.5%, t h e i n t e r n a l torque developed is 4.05 meter-kilograms (350 in. lbs.). The design in t e rna l torque is 7.05 meter-kilograms (610 in. lbs.) . I t appears t h a t t h e motor is producing only 57% of t h e design value. This torque reduction can be caused by one or more of t h e following fac tors .

(a) Bellows pressure is measured upstream o f a 1.015 x 10-3 meter (,040 inch) diameter o r i f i c e , would reduce t h e actual bellows pressure below the measured value .

Any appreciable bellows leakage

(b) Bellows e f f e c t i v e area is less than t h e design requirements.

(c) The nuta t ion angle i s incor rec t ly set.

(d) Inaccuracies i n gear p ro f i l i ng has r e su l t ed i n a reduced angle of force centroid.

2-7

To inves t iga te these poss ib le causes, t h e following ac t ion was taken:

(a) A bellows tes t f i x t u r e was fabr ica ted t o allow p res su r i za t ion of an individual bellows assembly. showed t h a t only two of t h e s ix t een on hand (e ight spare) had appreciable leakage. had neg l ig ib l e leakage.

A check of a l l the bellows

The e igh t bellows taken from t h e motor

(b) Two bellows were se lec ted a t random and t h e force f o r a given applied pressure was measured. The fo rce measurement gave an e f f ec t ive bellows area of 2.67 x 10-4 meters2 (.414 in.2) and 2,65 x 10-4 meters2 (.411 in ,2) . These areas are within t h e allowable l i m i t of 2,80 x 10-4 meters2 35% (,435 in.2 3 5 % ) .

(c) G (d) The nuta t ion angle and t h e gear p r o f i l e cannot be measured

d i r e c t l y and any ind i r ec t measurement is open t o question. After r e p a i r o f t he f lexure p ivots , it is expected t h a t t h e motor w i l l be operated with t h e pure f l u i d commutation c i r c u i t . Shims w i l l be added a t t h e ou te r casing junct ion and under t h e pivot po in t s t o vary t h e nuta t ion angle, The optimum nu ta t ion w i l l then be determined by t h e angle which r e s u l t s i n maximum output torque.

The repaired actuator motor is p resen t ly being assembled. The commutation pressure pick-offs w i l l be ad jus ted f o r operat ion with t h e pure f l u i d c i r cu i t ry .

2-8

.

SECTION 3

COMMUTATION C I RCUIT

3.1 LQGIC CIRCUIT TESTS

The commutation c i r c u i t p l a t e s shown i n Figure 3-7 of t h e Second Quarterly Report (reference NASA CR-54282) were assembled with the appropriate test p l a t e s and funct ional ly checked. leakage occurred both r a d i a l l y between t h e p l a t e s and a x i a l l y along the b o l t holes. The leakage also changed after disassembly, making it d i f f i c u l t t o size t h e f ixed o r i f i c e s f o r t h e s e l ec to r and power valve supply pressures.

A l a rge amount of

The bellows pressures could, however, be sequenced i n t h e proper order and t h e operation of t h e logic c i r c u i t was ve r i f i ed , and grease were used f o r sea l ing purposes, but it was found t h a t Krylon prevented easy separat ion of t he p l a t e s and grease contaminated t h e flow channels. being used, is t o lap and s i l v e r p l a t e a l l p l a t e s before assembly. photograph of t he p l a t e assembly i s shown i n Figure 3-1,

"Krylon"

The method found most successful, and present ly A

The bleeds were re-manifolded so t h a t the supply pressures are i n series rather than i n pa ra l l e l , from a common plenum. model commutation c i r c u i t had indicated t h a t a s e r i e s o r i f i c e arrange- ment provided the most optimum bellows pressures ,

Test on the

Many attempts were made t o optimize the bleed sizes used t o obtain these pressures. below:

The e f f ec t s of various changes are summarized

CAUSE

(1) Decrease i n se l ec to r valve bleed size.

EFFECT - Improves m i n i m but reduces maximum bellows pressure,

3-1

i

b cn w

w s a

CAUSE

(2) Increase i n size of power valve bleeds.

- EFFECT

Improves maximum but increases minimum bellows pressure . -

(3) Increase i n size of pick-off bleeds.

Improves bellows pressure d i f f e r e n t i a l

Reversing t h e bleed sizes has t h e opposite effect. I t was extremely d i f f i c u l t t o find an optimum combination of t h e bleeds. Consequently, two new t e s t p la tes were fabr ica ted making it poss ib le t o simulate a l l bleeds externally by hand valves. These valves made it much eas i e r t o set up the optimum point, and i n t h e f i n a l ana lys i s , t h e pressure-flow cha rac t e r i s t i c s can be measured t o determine equivalent bleed sizes. The t e s t p l a t e s were lapped and assembled with t h e commuta- t i o n p la tes . By spot checking several po in ts i n t h e commutation c i r c u i t , ad jus t ing t h e hand valves, and rechecking the points, an optimum s e t t i n g of t h e valves was obtained and data were recorded f o r each s t e p of t h e commutation c i r c u i t . The performance of t h i s c i r c u i t i s shown i n Figures 3-2(a) and 3-2(b) .

Figure 3-2(a) ind ica tes the average pressure d i f f e r e n t i a l obtained between t h e four pressurized outputs and t h e four non-pressurized outputs f o r each sequence of pick-off pressure. pressure levels of t h e pressurized and non-pressurized outputs.

Figure 3-2(b) shows t h e average

I t can be seen t h a t t h e pressure d i f f e r e n t i a l was a maximum when t h e four pressure pick-offs were covered, and a minimum when t h e pick- o f f s were open. d i r ec t iona l s igna l was applied (PDR Hi). va r i a t ion i n t o t a l flow applied t o each of t h e s e l e c t o r valves. flow va r i a t ion caused a change i n t h e s e l e c t o r supply pressure, which i n t u r n a f fec ted the a b i l i t y of t h e s e l e c t o r output t o control t h e power valve .

This was p a r t i c u l a r l y noticeable when t h e r i g h t This va r i a t ion was due t o t h e

The

3-3

\

o x x x

o o x x

0 0 0 %

0 0 0 0

x o o o

X X O O

X X X O

X X X % /

x x o o

% O O O

o o o o [ g

0 o o x p

O O K X ...-' X W K X

3-4

1 0 cy m I

\ o x x x

O O X X

0 0 0 %

0 0 0 0 ,

3 4 0 0 0

x x o o

X X X O

x x x o

1::: 0 0 0 0

0 0 0 %

X X K X J

I I

K O

3-5

Considerable improvement i n t h e pressure d i f f e r e n t i a l va r i a t ion can be obtained by employing a vortex pressure regula tor across the se l ec to r supply. performance of t h e complete actuator motor has been determined, commutation c i r c u i t , adjusted t o give the performance shown i n Figure 3-2, w i l l be used t o operate the ac tua tor motor.

I t is not proposed t o attempt t h i s modification u n t i l The

3.2 PRESSURE ERROR VALVE

No fur ther work beyond t h a t reported i n t h e Second Quarterly Report was performed on t h e pressure e r r o r valve. valve w i l l be done when the t o t a l system performance has been evaluated.

The s i z ing of t h i s

3.3 BISTABLE DIRECTIONAL AMPLIFIER

A b i s tab le f l i p - f lop was obtained from t h e Bendix Research Laboratories Division f o r evaluation. t o determine t h e performance of a typ ica l f l i p - f lop under conditions of high supply and high vent pressures. 10.3 x 104 newtons/meter2 (15 psig) and 131 x 104 newtons/meter2 (190 psig) sup l y pressures.

pressure. valves .

The purpose of t h e tests was

Tests were conducted with

In both cases, the re i s approximately a 10.3 x 10 i newtons/meter2 (15 ps i ) drop from supply pressure t o rece iver

The control po r t s were pressurized slowly by manually operated

Figure 3-3 is a flow diagram of the test setup, S t r a in gage-type

Points 3 and 6

pressure transducers were used. and control pressures of t h e amplifier a t s i x d i f f e r e n t operating points . Supply pressure remained constant throughout t e s t ing . involve control flow continuing i n t o the amplif ier after t h e main stream has changed posit ions, The control flow occurring at t h i s point was determined by maintaining t h e control port hand valve a t exac t ly the same posi t ion as it was when the b i s t ab le valve was at t h e threshold of switching.

Figure 3-4 i l l u s t r a t e s t he rece iver

3-6

Atmos , Atmos ,

Rec ,

I I I I I Left Rinht 1 Receiver Receiver

/

Ret ,

I Left RiQht I

GN2 -# , dhfrnt Contro 1 Right

Rec, Rec t ,

Rec. - Recorder P,T, - Pressure Transducer

Atmos. - Atmosphere

FIGURE 3-3 TEST SETUP FOR MODEL DIRECTIONAL AMPLIFIER

3-7

It can be seen from Figure 3-4 that the receiver recovery pressures are 40% ofthe quantity, supply pressure minus vent pressure. recovery was determined by slowly increasing both the receiver impedances at the same time until the amplifier began to oscillate. At this point, both impedances were reduced slightly until the amplifier stabilized. The pressures that appear in Figure 3-4 are the maximum stable pressures obtainable .

Pressure

During the high pressure test, the vents were connected to each other and shut off from the atmosphere so that better pressure recovery could be maintained. Figure 3-5 illustrates the results of this test.

A test run with 138 x 104 newtons/meter2 (200 psig) supply pressure, 121 x 104 newtons/meter2 (175 psig) maximum and 113 x 104 newtons/rneterZ (165 psig) minimum receiver pressures was made to check the weight flow rate through the amplifier. The supply flow rate was .00042S kilograms/ second (.00094 lb./sec.) GN2. The high side receiver flow was ,000226 kilograms/second (.0005 lb./sec.) . The commutation circuit requires a high side flow of approximately ,00454 kilograms/second (-01 lb./sec.) GN2, a weight flow rate twenty times greater than transmitted by the tested amplifier.

It is believed the amplifier can be scaled to meet the higher flow requirements and yet maintain the 121 x lo4 newtons/meter2 (175 psig) high side, 113 x 104 newtons/meter2 (165 psi ) low side pressures with a supply pressure of 138 x 104 newtons/meterg (200 psig).

The pressure-flow characteristics of the directional signal in the actual commutation will be measured to determine more precisely the requirements before a bistable unit is fabricated.

3-8

PCL-PCR

PRR-PRL x lo3 Newtons/

meter2 ._ - 1 psi

Psupply 10e3~104 Meter2 (I

Pvmt - 0

-48.3' -7 a Pu = 41,4 x 103 newtons/meterZ (6,O psig)

PCR - 2.76 x 103 nswtons/meterZ (-0.4 psig) @ PRR = 41.4 x 103 newtons/meter2 (6.0 psig)

PCL - -2,76 x 103 newtons/meter2(-0,4 psig)

FIGURE 3-4 LOW PRESSURE PRESSURE RECOVERY

newtons/ ter2

3-9

\

meter2

-4 1 -

p s i

*S

1.4 x

.,.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ,._. .... _... . ._. . . . . . . . . . . . . . . . . . . . . . . . . ..-. I 1 L ' . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

p s i

131 x 104 newtons/ meter2 (190 psig) vents connected

x lo4 newtons/meter2 (176 psig) 2 x 104 newtons/meter2 (164.8 ps ig ) x 104 newtons/meter2 (176 psig) 9 x 104 newtons/meter2 (164 ps ig )

103 newtons/meter 2

F I G U R E 3-5

3-10

H I G H PRESSURE PRESSURE RECOVERY

SECTION 4

FOURTH QUARTER GOALS

The in tegra t ion of t h e commutation c i rcui t and t h e ac tua tor motor w i l l be made e a r l y i n t h e four th quarter. pick-off pos i t ions w i l l then be adjusted t o obta in optimum performance. Once the completed system is optimized, flow measurements w i l l be made t o determine t h e requirements of the pressure e r r o r valve and t h e d i r ec t iona l f l i p - f lop , These u n i t s w i l l then be fabr ica ted , t e s t e d and incorporated with t h e ac tua tor motor system.

The nuta t ion angle and t h e

An electromechanical torque motor of t h e NERVA drum actuator design w i l l be used t o provide the input signal. t i o n c i r c u i t r y , dynamic response measurements w i l l be made.

Upon completion of t h e commuta-

The complete ac tua to r motor w i l l be connected t o t h e NERVA drum f i x t u r e and operated on hydrogen gas a t a gas and environmental temperature down t o -280°F. t h e cryogenic temperatures.

Operation of the scram mechanism w i l l be demonstrated a t

Due t o t h e f ab r i ca t ion lead time, it i s not an t i c ipa t ed t h a t t h e d i r ec t iona l ampl i f ie r o r pressure e r r o r valve w i l l be evaluated at cryogenic conditions. commutation log ic should, however, i nd ica t e t h e f e a s i b i l i t y of t h e e n t i r e system .

The operation of t h e remaining components of t h e

An ana ly t i ca l study of t h e comparison between t h i s ac tua tor motor and more conventional concepts has been s t a r t ed . The performance d a t a obtained during t h e four th quarter w i l l be incorporated i n t h i s study.

4-1

APPENDIX A

DISTRIBUTION L I S T FOR

CONTRACT N A S 3 - 5 2 1 4 QUARTERLY REPORTS

NASA-Lewis Research Center (3) 21000 Brookpark Road Cleveland, Ohio 44135 Attention: Vernon D. Gebben

NASA-Lewis Research Center (2) 21000 Brookpark Road Cleveland, Ohio 44135 Attention: Lewis Library

NASA-Lewis Research Center (1) 21000 Brookpark Road Cleveland, Ohio 44135 Attention: James E. Burnett, Technology

Ut i l i za t ion O f f ice

NASA-Ames Research Center (1) Moffett Field, Cal i fornia 94035 Attention: Library

NASA-Goddard Space F l ight Center (1) Greenbelt, Maryland 20771 Attention: Library

NASA-Marshall Space F l ight Center (2) Huntsvi l le , Alabama 35812 Attention: Library

NASA-Marshall Space Fl ight Center (1) Huntsville, Alabama 35812 Attention: Michael A, Kalange,

R- ASTR-NF

NASA-Western Operations (1) 150 Pic0 Boulevard Santa Monica, Cal i forn ia 90406

NASA S c i e n t i f i c 6 Technical Information

Box 5700 Bethesda, Maryland Attention: NASA Representative

Facil i ty (6 & Reproducible)

NASA-Lewis Research Center (1) 21000 Brookpark Road Cleveland, Ohio 44135 Attention: C. J. Shannon

NASA-Lewis Research Center (1) 21000 Brookpark Road Cleveland, Ohio 44135 Attention: Lewis Technical

Information Division

NASA Headquarters (1) Washington, D.C. 20546 Attention: F. C. Schwenk, NPO

NASA-Flight Research Center (1) P.O. Box 273 Edwards, Cal i forn ia 93523 Attention: Library

NASA-Langley Research Center (1) Langley S ta t ion Hampton, Virginia 23365 Attention: Library

NASA-Marshall Space F l ight Center (3) Huntsvil le, Alabama 35812 Attention: Roy E. Currie, Jr.

R-ASTR-TN

NASA-Manned Spacecraft Center (1) Houston, Texas 77001 Attention: Library

Jet Propulsion Laboratory (1) 4800 Oak Grove Drive Pasadena, Cal i forn ia 91103 Attention: Library

Harry Diamond Laboratories (3) Washington 25, D.C. Attention: Joseph M. Kirshner

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Harry Diamond Laboratories (2) Washington 25, D.C. Attention: Library

Wright-Patterson Air Force Base (2) Ohio Attention: Library

U. S. Atomic Energy Commission (3) Technical Information Service Extension P.O. Box 62 Oak Ridge, Tennessee

NASA-Lewis Research Center (2) 21000 Brookpark Road Cleveland, Ohio 44135 Attention: Nuclear Rocket Technology

Off ice

NASA Headquarters (1) Washington, D.C. 20546 Attention: John E. Morrissey, NPO

Army Missile Command (2) Redstone Arsenal, Alabama Attention: Library

U. S. Atomic Energy Commission (3) Technical Reports Library Washington, D.C.

Los Alamos S c i e n t i f i c Laboratory (1) Los Alamos, New Mexico Attention: Joseph Perry, N-4

NASA Lewis Research Center (1) 21000 Brookpark Road Cleveland, Ohio 44135 Attention: Alan S. Hintze, SNPO

Case I n s t i t u t e of Technology (1) Mechanical Engineering Department Cleveland, Ohio Attention: Prof. Charles Taft

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APPENDIX B

DISTRIBUTION LIST FOR ABSTRACTS OF

CONTRACT NAS3-5214 QUARTERLY REPORTS

NASA-Lewis Research Center (10) 21000 Brookpark Road Cleveland, Ohio 44135 Attention: Vernon D. Gebben

NASA Headquarters (1) Washington, D.C. 20546 Attention: Iierman H. Lowell, R E I

NASA-Marshall Space Fl ight Center (10) Huntsvil le, Alabama 35812 Attention: Roy E. Currie, Jr.; R-ASTR-TN

NASA-Marshall Space F l ight Center (1) Huntsvil le, Alabama 35812 Attention: Je ro ld Peoples, R-ASTR-NFM

Harry Diamond Laboratories (20) Washington 25, D.C. Attention: Joseph M. Kirshner

Army Missile Command (5) Redstone Arsenal, Alabama Attention: William A. G r i f f i t h

Army Missile Command (1) Redstone Arsenal, Alabama Attention: B. J. Clayton

Army Transportation & Research Command (1) F t . Eust is , Virginia Attention: George W. Fosdick

Bolling Air Force Base (1) Washington, D.C. 20332 Attention: Major C. R. Wheaton

Wright-Patterson A i r Force Base (1) Ohio Attention: James F. Hall

NASA Headquarters (1) Washington, D.C. 20546 Attention: John E. Morrissey, NPO

NASA-Langley Research Center (1) Langley S ta t ion Hampton, Virginia 23365 Attention: Harvey V. Fu l l e r

NASA-Marshall Space F l ight Center (1) Huntsvil le, Alabama 35812 Attention: William White, R-ASTR-TN

NASA-Marshall Space F l ight Center (1) Huntsvil le, Alabama 35812 Attention: Russel Alcott , R-ASTR-NFM

Army Material Command (1) Research Division Washington 25, D.C. Attention: Major W. T. Kerttula

Army Missile Command (1) Redstone Arsenal, Alabama Attention: T. G. Wetheral

Army Munitions Command (1) Picatinny Arsenal Dover, New Je r sey Attention: S i l v i o J. Odierno

Army Transportation & Research

F t . Eust is , Virginia Attention: Robert R. Piper

Command (1)

Kirt land A i r Force Base (1) New Mexico Attention: Capt. Charles V. Fada

Wright-Patterson Air Force Base (1) Ohio Attention: Seth A Young

B-1

Wright-Patterson A i r Force Base (1) Ohio Attention: Ronald Ringo

Office of Naval Research (1) Dept. of Navy Washington, D.C. 20360 Attention: Stanley Doroff

Bureau of Weapons (1) Munitions Building Washington 25, D.C. Attention: Richard A.Retta

Massachusetts I n s t i t u t e of Technology (1) Department of Mechanical Engineering Cambridge 39, Massachusetts Attention: Forbes T. Brown

Wright-Patterson A i r Force Base (1) Ohio Attention: Charles Bentz

Office of Naval Research (1) Washington, D.C. 20360 Attention: Ancel E. Cook

U. S. Atomic Energy Commission (1) Division o f Reactor Development Washington 25, D.C. Attention: Frank C. Legler

NASA-Lewis Research Center (2) 21000 Brookpark Road Cleveland, Ohio 44135 Attention: Nuclear Rocket Technology

Office

.

B-2