ALSEP fuel cask mount design review meeting #247...BENDIX SYSTEMS DIVISION ANN ARBOR~ MICH.'~ndi/ CORPORAliC~ MINUTES 9712-864 Pg. 2 Fuel Cask Mount Design Review Date of Meeting 5

:'; -- ~

ALSEP FUEL CASK MOUNT DESIGN REVIEW MEETING

NO.

ATM-760

PAGE 1

REV. NO.

OF 3

Aerospace Systems Division DATE 5-27-68

The MSC design review team visited BxA Monday, 20 May, to review the design of the cask, the fuel capsule, and the integrated cask mount assembly, with particular emphasis being placed on safety.

Prepared By

I

Approved By t 1. r:. {': --~M~o~Ka~t-z~-t:)-+-------

NO. REV. NO.

ATM-760

3 ALSEP FUEL CASK MOUNT DESIGN REVIEW MEETING P.AGE

2 OF

~Division DATE 27 May 1968

The subjects presented by cognizant BxA engineers are noted in the following Meeting Agenda:

• Introduction

W. Durrant

• Review analyses and tests pertaining to potential vacuum welding problems.

W. Durrant

• Review of integrated cask testing performed on prototype hardware.

L. Wagman & J. McNaughton

• Verification of on-pad installation and removal techniques for the cask capsule and associated G. E. furnished hardware.

C. Ahlstrom

• Review of integrated structural /thermal cask qualification test plans, including cask, capsule and support structure.

C. Ahlstrom

• Review of verification of crew compatibility with the integrated cask system. This review should include the functional and safety aspects.

H. Grubbs

The minutes of the meeting are covered in the attached ALSEP 9712-864. These minutes document the subject material covered by each cognizant engineer, along with subsequent questions and answers.

Copies of the "viewgraphs" used to form the basis for presentation are also attached. The figure numbers corresponding to the Agenda subject are listed below:

Aerospace Systems Division

Introduction

ALSEP FUEL CASK MOUNT DESIGN REVIEW MEETING

Analyses and test pertinent to potential vacuum welding problems

Prototype hardware integrated cask testing

Verification of on-pad installation and removal techniques

Integ rated structural/thermal cask qualification test plans

Verification of crew compatibility with integrated cask system

NO.

ATM-760

PAGE 3

REV. NO.

OF 3

DATE 27 May 1968

Figures 1 & 2

Figures 3 thru 7

Figures 8 thru 57

(Film)

Figure 58

Figures 59 thru 6 3

,,~ncfY CORPORATION

ATTENDEES

Bendix

M. Katz L. Wagman E. VanValkenburg J. Maszatics J. McNaughton c. Ahlstrom H. Grubbs R. Redick K. Wright E. Rutz D. Dewhirst R. Hostettler w. Durrant

BENDIX SYSTEMS DIVISION ANN ARBOR., MICH.

Fuel Cask Mount Design Review

NASAIMSC

D. Medlock D. Gr eenshields R. Miller R. Ferguson T. Kerr D. Lind T. Herrington J. Grayson

MINUTES 9712-864

Date of Meeting 5 I 20 I 68

l. 0 The meeting was opened and a welcome given to our visitors by E. VanValkenburg.

2. 0 W. Durrant reviewed the present mechanical design of the Cask Assembly and discussed in detail the analyses and test pertaining to possible vacuum welding phenomenon.

2. 1 Question

Answer

2. 2 Question

Answer

2. 3 Question

Answer

2. 4 Question

Answer

Review of materials making up gearbox in particular the bearings.

All self aligning steel bearings. W. Durrant will check on specific material and respond to T. Herrington and J. Grayson.

Temp and pressure at which gear box was tested?

Have we run lab tests on cold welding of titanium to steel?

No, our component level tests did not indicate a need for such tests.

What prevents pin and lever of upper trunnion release from coming loose as occurred at MSC?

Model at MSC is not representative of final design.

Pg. 1

BENDIX SYSTEMS DIVISION ANN ARBOR~ MICH.

'~ndi/ CORPORAliC~

MINUTES 9712-864 Pg. 2

Fuel Cask Mount Design Review Date of Meeting 5 I 2 O I 6 8

2.5 Question What materials make up trunnion release pin? Interior Rod?

Answer Rod should be microsealed. The balls are definitely microsealed.

2. 6 Question On-pad temp. of release pin?

Answer

2. 7 Explanation given of new dome removal mechanism.

2. 8 Question

Answer

2. 9 Question

Answer

2. 10 Question

Answer

Material from which springs are fabricated?

Inconel X

Can direction of pin in dome release mechanism be changed to allow release of nut in one direction and dome removal in opposite direction.

Have new release in house and will demonstrate it.

What are effects of radiation on cold welding?

Are not aware of any but BxA tests have not been made.

3. 0 Vibration Test Program

Test item w I electric capsule subjected to sine sweep 1 g magnitude

1. at 280°F 2. at 600°F.

Details of accelerometers - see handout.

Details of strain gages - see handout

2 element rosette type - temp compensate~ ..

Band location of strain gages - see handout.

Slides of test shown u

High temF accelerometers used - o. k. up to 700 F.

Film of Vibration run - full level.

Discussion of Data From Tests

See Handout Pictures.

BENDIX SYSTEMS DIVISION ANN ARBORI MICH. MINUTES 9712-864 Pg. 3

·~ncf~, CORPDAAliQN Fuel Cask Mount Design Review Date of Meeting _ _.5;..:.l.-2 ... o._/..;.6.;;..8 __

Launch & Boost Sine Max Transmissibility Max Transmissibility Max Transmissibility

Y -Axis Z-Axis X-Axis

7. 6 max 1. 6 max 3. 8 max

Launch & Boost Random: Z-Axis input Launch & Boost Random: Cross Axis (Y /Z}

Fuel Cask sine input Cask & Support Random - X response Cask & Support Random - Y response Cask & Support Random - Z response

Sine response X input/ output Sine response Y input/ output Sine response Z input/output

1 g sweep launch & boost (X axis} II II

Discussion Grayson/ Maszatics on differences in transmissibilities predicted and those actually experienced in test. System is non-linear and transmiss. therefore varies v,;.ith input level.

J. Grayson asked if information from test has been included in rewritten ICS - answer is not yet.

4. 0 J. McNaughton- Discussion of On-pad cooling and Thermal/Vacuum Testing.

Question

Answer -

Dimensions and A P of nozzle.

The design of the Qual cask coolin~nozzle has been completed and copies transmitted to MSFC. he nozzle has a 5 inch diameter inlet, a 2 1 I 4 inch dia. exit and an overall length of 8 inches. The predicted performance of the nozzle is shown in the enclosed viewgraph for nozzle inlet pressure versus I. U. tapoff flowrate. The data is derived from the engineering tests conducted at MSFC combined with the results from the BxA Prototype cask cooling test program.

The preliminary interface layout for the Bendix/ MSC/ MSFC cask cooling configuration is described in the viewgraphs. The interface locates the exit plane of the nozzle 2 ft below the cask. For this configuration,nozzle pressures are pre-dicted to range from 0. 3 to O. 6 psig with corresponding nozzle

flow rates from 15 to 30 lb/min. Maximum cask surface temperatures for these conditions with a 130°F SIVB I. U. inlet temperature range from 230°F to 275°F.

MINUTES 9712-864 Page 4

5. 0 C. Ahlstrom - On-pad Operations

Film shown on installation of cask assembly on LM.

6. 0 C. Ahlstrom - Cask Qual Test

1.

2.

3.

Question

Answer

4.

5.

6.

Distributed TM-157. Exhibit B - Qual Test Plan and described Qual Plan

QTRR will be after Acceptance according to Ahlstrom. Grayson stated that the rest of the ALSEP Program has been run such that the QTRR precedes acceptance. Timing of QTRR will be resolved by BxA - L. Wagman.

Qual Test start on 6/14/68 with D-2 Qual on 6/17/68.

When will ICS be can pleted?

Will be completed before Qual according to M. Katz. At Grayson's request a date on which spec will be completed for NASA review. Date given by M. Katz is 31 May 1968. The ICD and ICS will be mailed on this date.

Concern was expressed over fact that T/V Test does not cover entire mission time. Time allocated according to McNaughton is for nominal mission and was dictated by economics.

Question raised on use of live capsules throughout Qual Program. Answer was that the capsule, cask, and BxA cask assembly will all be qualified. Qual is a system level test with no upper dome modification allowable on Qual or Flight hardware.

Data was requested on band strain. Copies of the ATM by Dr. D. Dewhirst on this subject will be obtained by C. Ahlstrom.

7. 0 H. Grubbs - Mission & Crew Safety Features of Cask

1. Discussion of cask safety features.

2. Film on ALSEP unloading and cask unloading w/RTG fueling.

3. Protective device will withstand at least 30 lbs.

4.

5.

8. 0 General

l.

2.

3.

Question, D. Lind - Storage provisions for lanyard?

Answer - 2 strips of Velcro tape.


BxA will deliver the 2 GFE casks as a part of the E-2 model. Hardware will be representative of the Qual/ Ft design and delivered approximately 24 July 1968.

The following drawings were transmitted to J. Grayson of NASA/ MSC. 2337960, 2338140, 2338141, 2338142, 2338143, 2338218, 2338219, 2338220, 2338221, 2338348, 2338375, 2338138, 2337980, 2337979, 2337981, 2337982, 2337983, 2337984, 2337985, BSX 7658 {Preliminary}, Lanyard Hook {Preliminary), Astronaut Guard/ Gearbox {Preliminary), and Center Plunger Dome {Preliminary). These drawings relate to the redesign of the cap removal lock and the one-piece lanyard.

Differences between Proto and Qual:

{a) Change in dome release to center plunger.

(b) Gear box swivel change. ·

(c) Adjustment on axial band.

(d) 1 piece lanyard. '1

(e) Increase in axial band thickness, from • 017 to • 030.

(f} Cut-off thermal shield - analysis indicates that input to LM is within spec.

(g) Addition of astronaut guard.

{h) Increase in surface area of trunnion pads.

Question on T / C instrumentation of LM skin. New Grumman blankets were used on Proto T /V. How representative is this blanket? LM Panel is now made of 4 mil? Inconel. Behind this is aluminized Kapton and Mylar.

•

4.


TIC on rear face of shield is not included in final design. Will be mounted upon final approval. According to Grayson TIC is still shown on BxAI GAEC ICD.

Grayson asked for look at ICD location ofT I C. Interface problem should be resolved by MSC. Signal conditioning components for this TIC have already been included in the LM.

TIC instrumentation on LM Panel was bonded to Inconel foil and used for steady state conditions only.

Approved by: (original signed by) T. Herrington, MSC

Recorded by: . ~----L. Wag[;6a:'n, BxA

Distribution All Attendees R. Long C. W eatherred

Approved by: ~~~~--~~~-----------M. Katz, BxA

-

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Figure 2

FUEL CASK SUPPORT ASSEMBLY ~

HEAT SHIELD ASSY

SUPPORT STRUCTURE ASSY

4422-1

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........ .......

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Figure 3

CASK ROTATION DETAILS

~ TRUNNION RELEASE

,.......-TRUNNION RELEASE. CORD

GEARBOX

GEARBOX OPERATING CORD ' I \\ \ ...... , / ........ __

~iii~'

4422-4

B I I I

SPROCKET HOUSING

Figure 4

TILT GEARBOX ASSEMBLY

A

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UPPER TRUNNION

4422-5

Figure 6

DOME RELEASE DETAILS

\

' AXIAL BAND UPPER SECTION

LEVER /

RELEASE

LOCKING PLUNGER

DOME ATTACHMENT BOLT

~

4422-7 I

SPLINE REMOVAL CLAW i

I

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\

\ JO.) .ll!S'!'~ CJIA TIIRU FROM PLOT Hal.£

9) .094~:88~ OJA THRU FROM PILOT HOL£

Figure 7 ~ DOME REMOVAL TOOL

tE'==---==tl

--r .75

4

4422-8

Figure 8

PROTOTYPE FUEL CASK VIBRATION TEST

l g SINUSOIDAL SURVEY- 280° F (LAUNCH AND BOOST)

-- 600° F (LUNAR DESCENT)

3g SINUSOIDAL- 280°F(LAUNCH AND BOOST)

FULL LEVEL RANDOM - 280° F (LAUNCH AND BOOST)

~iii~'

6607-1

i

4

5 6

Response Accelerometer in direction of vibration Response Accelerometer in direction of vibration Triaxial Response Accelerometer Triaxial Response Accelerometer

NOTE: Location Z and 3 will be used if the accelerometer blocks at locations 5 and 6 come off during vibration,

Figure 9 liiiii' ACCELEROMETER LOCATIONS

Input Accelerometer - Fixture/ Teat Item Interface

6

-Z

r +X

+Y

+Y

r +X

Fixture/ Test Item Interface (opposite)

VIBRATION TEST SETUP 5607-21

12

Figure 10

STRAIN GAGE LOCATIONS ON SUPPORT STRUCTURE

·JO.S INDICATE STRAIN GAGE IDENTIFICATION

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Figure ll

STRAIN GAGE LOCATIONS ON BAND ASSEMBLY g

24

* FULL-BRIDGE STRAIN GAGES: (ALL OTHERS, HALF-BRIDGE STRAIN GAGES)

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FREQUENCY - cps

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VIBRATION SPECTRUM- CROSS AXIS RESPONSE

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FREQUENCY - cps 5607-6

Figure 17

FUEL CASK SINUSOIDAL 11iiiii111 LAUNCH AND BOOST INPUT SPECIFICATION

x- axis : 5-23 cps 0. 5 in. d. a.

23-100 cps 13 g- peak

y- axis : 5-30 cps 0. 5 in. d. a.

30-100 cps 23 g -peak

z- axis : 5-18 cps 0. 3 in. d. a.

18-100 cps 5. 0 g - peak

5607-2

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Figure 18

CASK AND SUPPORT LAUNCH AND BOOST ~

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PURPOSE:

TESTS:

Figure 30

VERIFY THE THERMAL INTEGRATION OF THE ALSEP/GLFC/LM CONFIGURATION FOR THE PRELAUNCH AND FLIGHT ENVIRONMENT

TEST SERIES INCLUDED THE FOLLOWING SIMULATED FLIGHT ENVIRONMENTS:

1. PRELAUNCH AMBIENT ENVIRONMENT( FREE CONVECTION CASE}

2. PRELAUNCH CASK COOLING WITH FORCED CONVECTION(35 RUNS}

3. LAUNCH AND BOOST TRANSIENT TESTS

. 4. EARTH ORBIT WITH AND WITHOUT SOLAR HEATING

5. TRANSLUNAR WITH AND WITHOUT SOLAR HEATING

Figure 31

INTERFACE AND DESIGN REQUIREMENTS USED FOR INPUT CRITERIA FOR Bx.A THERMAL MODEL OF ALSEP/CASK/LM INTERFACE CONFIGURATION

•

•

•

•

Bendix

G. E .

GAEC

MSC

l) Prototype structural design configuration 2) Prototype thermal shield design

A. Circumferencial angle of shield with cask is 135° B. Total hemispherical emittance ~ . 10

3) 800°F maximum temperature with l50°F circumferencial gradient around cask

l) 2) 3) 4) 5)

l)

2)

3) 4)

l)

2)

3)

4)

5)

-l9D cask design configuration Material properties per CCP #29 Graphite coatings for total emittance~ 0. 80 per -19D and CCP #29 1530 watts maximum power Fuel Capsule design per ICS 314119

100 Btu/hr maximum heat leak into LM due to direct cask radiation and conduction 2 70°F maximum temperature on LM (not including new astronaut thermal door) Mechanical interface per LID 360-22809 Environmental interface per ICS LIS 36"0-22402 and LED 520-IF

NAA SLA internal and external thermal coatings per MSC transmittal dated June 1966 LM vehicle thermal coatingrper LM-3 and on report by J. Smith, of MSC, dated January 1967 LM vehicle mission profile per MSC June 1966 transmittal and LD-520 -F Apollo Program environment specification per M-DE 8020. 008B dated April 1965 Bx.A /MSC eontract 9-5829, Exhibit B

Input Structure Coordinates

Surface Em is sivities

Aero Heating Property Boundary Conditions

Figure 32

Confac I & II Programs

Thermal Radiant Interchange Program

Bendix Thermal Analyzer Program

Output

Output Configuration fSLA/LM/cask · Factors A LSEP/SIVB

Surfaces

{ Diffuse Multiple Reflection Gebhart Method

f Output Matrix 13 x 13 for 75 f & Resistors

{ 30 Nodes, 115 Resistors

{Nodal Temperature vs Time Nodal Heat Balance

Computer Programs Used in Thermal Model of ALSEP /Cask/LM Interface

•

•

Figure 33

DESCRIPTION OF BxA DIGITAL COMPUTER PROGRAMS UTILIZED FOR THERMAL ANALYSIS OF ALSEP /CASK/LM INTERFACE

15 node, 3 dimensional thermal model for ALSEP / cask/LM configuration defined by CCP #29, reference Figure 1

25 node, 3 dimensional thermal model of ALSEP /LM vehicle interface to evaluated GAEC temperatures on thermal door and landing gear, reference Figure 2

22 node, 3 dimensional thermal model of BxA /GAEC support structure interface for conduction heat leak evaluation

20 node, 3 dimensional thermal model of ALSEP/cask interface to evaluate axial and circumferencial gradients for on pad cooling temperature and thermal stresses

• 35 node, 2 dimensional model of Saturn SIVB Instrumentation Unit (I. U.) manifold to determine flow distribution and pressure gradients in I. U. manifold for on pad cooling requirements

Figure 34

BENDIX THERMAL MODEL NODES

FUEL CASK SUPPORT ASSEMBLY

II

Note: Node 13 is • Saturn Vehicle & I. U.

'~&.

liiiiW

) ... ~ HEAT SHIELD ASSY

r SUPPORT STRUCTURE ASSY

LM PANEL----'

0

Shadow Earth Oriented

Figure 35

---- <:J::J \

Begin Translunar Injection T = 6000 sec s

= 600 sees.

\ (\

Earth shadow

\"/ I

I Leave Earth Shadow T = 2820 sees.

ALSEP/cask/LM/SLA Earth Orbit Cas~ With and Without Solar Heating

Sun Oriented

Figure 36 ~iii~' TABLE 3-1

ALSEP/ CASK/ LM INTERFACE SPECIFICATION REQUIREMENTS VERSUS PROTOTYPE TEST RESULTS AND

PRETEST PREDICTED VALUES

Interface Specification Test Pretest ~ecification Requirement Results Predicted Values

MAXIMUM FUEL CASK SURFACE TEMPERATURE BxA/GE 800°F 615°-798°F 672° -785°F

MAXIMUM FUEL CASK CIRCUM-FERENTIAL TEMP GRADIENT BxA/GE 150°F 130°F 140°F

MAXIMUM FUEL CAPSULE SUR-FACE TEMPERATURE BxA/GE 1400°F 1210°-1320°F 1220° -1302°F

MAXIMUM HEAT LEAK TO LM BxA/GAEC 100 BTU/HR .60 BTU/HR 75 BTU/HR

MAXIMUM LM SKIN SURFACE TEMPERATURE (EXCEPT ASTRO-

270°F 238°F 240°F NAUT THERMAL DOOR) BxA/ GAEC

ASTRONAUT THERMAL DOOR BxA/GAEC 400°F 3 88°?"-- 400°F

.. MAXIMUM CASK THERMAL SHIELD TEMPERATURE BxA 600°F 588°F 558°F

5607-30

Figure 38

SLA/ LM Canister Used for Proto Cask Cooling and T / V Test

~ ()'Q j:: li (D

VJ

"'

Prototype Conical Nozzle Configuration Inside SLA/ LM Canister

150 lb/ min

PHYSICAL CONFIGURATION OF

CS11/LEM/SLA - BLOCK II

-------VENT SLOT (Typ. 8)

.,_ _____ s-1 va

RTG COOLING DUCT ASSY

:,··,., /' ',,,~) ~__,·

ACCESS DOOR~ ~

··~ :22.: .......... r~

~-

GAS BEARING SUPPLY

Figure 41

,.-·.

:21 ~ .... _.,1'

·15· -........ -·

I.LI.~8et:ut;T 5.00 OtA

-Y ,..,. "Toi1i'"

Figure 42

PROPOSED RTG CASK COOLING INTERFACE CONFIGURATION

/

j A ......... SHEE~ 2

I

/ .,

:.!!!:!:!.

~

LEM

~

5607-43

Figure 43

RTG CASK COOLING NOZZLE LOCATIONS FOR BxA PROTOTYPE TESl PROGRAM

)--~____/ LIN I ==---+-- ' ...... -

~--------"'--------~

~iii~'

,........ --d ..... DIWt.-~ ~·Ill --

~ ~ r ~~~t==--==n-- I I -- - k\_t -

lil.<.lll!l'l-;!: .... -....... .. --.... .,.,.

'5607-42

s:: .... E -. ,D -rz:l f-4

~ ~ ...:1 fz. fz. fz. 0 ~ < f-4

Figure 44

50

40 -l I I I

30 ~ ! I

Total Flow zzsf/~in

ZOO#IV~i~ \ \

\ \ . \ zso0 \X\

175f/min \' \ \ \~ .. .

Z75°

\ \

~00° zo 1 10 J

I

I l

Surface Temperat~re

0 -,+

0 oz

•' .. Z.75"

\, '\. .,

~iii~~'

Nozzle Diameter

Z.ZS"

---

Nozzle Pressure and Flow Rate for Maximum Cask Surface Temperature Versus Predicted I. U. Flow Conditions (From MSFC) Nozzle Z ft. Below Cask

1. 75"

-, \

\

' ' ' \ '\ '',, \

',,·\ '\ \

1. 51 psig ',

\ " 1. 91 psig Supply Pressure

-r·----·-06

·-· --,--- .... , 1.0 l.Z

TAPOFF PRESSURE - psig 5607-32

117+ 1

Figure 45

FUEL CAPSULE AND CASK SURFACE TEMPERATURE RESULTS ON PAD FORCED COOLING WITH 17.5 LB/MIN OF AMBIENT AIR TEMPERATURES FOR IN-LINE NOZZLE VARIATIONS SHOWN FOR NOZZLE OFFSET 2 INCHES

+I2 192_65 218 +24

-14 194~~0 +12

157 -4

~~,,, , , , \ - - - - - - -- - - - - - - - - - - - - T -,.-l II~ ---- ...

1220:1 I23~~2 ~:-- ... ',,

ILL. <\--------------------~~~- \; '\ 11 : : \ I \ II 1 1 1 I 1

------1.;1_1!..._-f I I 1

I I I I I I 11 I 1 J I

II : I I I

----,-- --T------ -+l,...- -~- : \ I I ; I

1257+ I 1221+1 ",-- / / - - [I : ' .. -'

! I,' :, I~ , ... __ _, ----

''7*>>?77~---- -- - ·------- --- ___ _ L_r-

\

\~Zzt b \,~

i +35 201_20

\ I \

I79+I8 I67+2I -30 -I2

\ (~

liiiiii'

142~~

\ I44~~

Surface Description Test Results, °F Pre-Test Predictions, °F

I. Capsule Surface 2. Cask Exterior Surface

a. Center b. Ends

3. Cask Domes 4. The rrnal Shield 5. LM Panel 6. SLA

1094-1257

I79-222 I57-206 115 -I44 75-92 72-109 70

Ill0-I245

I75-230 I53-I94 I2I-166 70-85 70-100 70 5607-39

~ 0

Q) 1-< ::s .. (1j 1-< Q) p..

E Q)

E-< Q) u ~ Jot

~ u Po. ~ 0

450

400

350

300

250

zoo

150

0 1 2

Figure 46

3 4 5

GLFC Surface Transient Warmup Forced Convection Off at Time -= 0

6 7 8

Time After Removal of Cooling Air - Minutes

9 10

5607-35

Figure 47

Prototype Cask and Support Structure Attached to Simulated LM

Figure 48

Fuel Cask and Support Assembly for Prototype Thermal Tests

385

Figure 49

FUEL CAPStn...E AND CASK SURFACE TEMPERATURE RESULTS ON PAD WITH FREE CONVECTION

545 609 587 536

- - - - - - - -- - - - - - - - - - - - - T -,.-l !\"'""" ---........

5 i~·~9 ~:--, ',,

I l~ ' ' ' I r • , ' ' l_____.£; "' ~- ---- - -- - -- -- -- ______ I~ . ' _} l \ II -,-, I I

tl I I I I I

11 1 : 1 I \ -------1-;-1..!.1-+ I I I I

I I I I i 11 I I I I

II : I I I

-----r----\------~-;-.-=r! \ \ II ~-· / I

1309 1284 ::.: ~~--/ , ~I ., .,' !J.-..J -__ ..,,

---- -- - ------------- _l_l-

541 527 506

liiii1'

,./397

387


1. Capsule Surface 1182-1309 1146-1232 2. Cask External Surface

a. Center 527-609 548-580 b. Ends 506-545 461-519

3. Cask Domes 385-397 364-437 4. Thermal Shield 93-135 90-121 5. LM Panel 75-91 77-85 6. Astronaut Door 91-154 85-170

5607-34 7. SLA 71-77 70

Figure 50

FUEL CAPSULE AND CASK SURFACE TEMPERATURE RESULTS EARTH ORBIT WITH SLA ON - MAXIMUM AND MINIMUM SOLAR HEATING

692/717 772/793 784/798 692/718

498/519 - - - - - - - -- - - - - - - - - - - - - T -, l l\ ...... "'\ --- ..........

/1315 1:\ ~'--, ', 124:~·~- z,s l\ \

LL I ' ' I I \~ - - - - - - - - -- -- - - - - - - - - +-' -= -1- I II I I I I I, I I I I

liiiia-

II: I \ I -------'lh-',----1 : I I i I

482/510

11 I I I I 1 I : I I I

-----\·-----·T ----~T.-~'! _ .\ Jl ~-" ,' I

1298/1307 1263/1269 ,, ; ,'.;/ , l t,. '// ,/ ~,. __ ....., ----"

-- - -------- _l_J-

\ 635/661 665/692 630/660

'-.~)

Surface Description Test Results, oF Pre-Test Predictions, °F

1. Capsule Surface 1210-1315 1293-1302 2. Cask External Surface

a. Center 635-798 643-775 b. Ends 627-718 617-687

3. Cask Domes 482-519 447-559 4. Thermal Shield 310-588 350-550 5. LM Panel 0-240 28-215

- 6. Astronaut Door 118-383 219-400 7. SLA 210- 261 250 5607-38

471/502-

453/493·-····-·

Figure 51

FUEL CAPSULE AND CASK SURFACE TEMPERATURE RESULTS TRANSLUNAR (SLA OFF) - MAXIMUM AND MINIMUM SOLAR HEATING

657/688 764/787 777/795 689/712 739/773 \ I I I

liiiiil'

-- ----------------------r'-- -""' 496/521 ~r·~ ----, ,, ' ' I ~ '' '

12471Hz ·f'\ \ 11 r-~, ·. 1 '

L,L...- )e \·-- - - - - - - - - -- - - -· - - - - - - -- 14--4 .l -= ,... ; \ II I 1 I 1 1 I I I I I 11 I I I I I

-------h-1 .!.1-4 I I I I I I

I I I I ---- -~---- -r---- ~-

1299/1301 1266/1267 ~--'

?)? >:h »,, ~- - -- - - - - - - - - - - - ·- - - - - _l_J-

658/692 621/657


I. Capsule Surface 1212-1311 1281-1290 2. Cask External Surface

a. Center 640-795 634-770 b. Ends 612-712 590-690

3. Cask Domes 453-521 435-541 . 4. The rma1 Shield 283-604 270-494 5. LM Panel -214-+217 -131-+273 6. Astronaut Door -12-+337 1-380 7. SLA -300 -300 5607-33

490/523/

Figure 52

DOME RELEASE LUNAR SURFACE TEMPERATURES

)23/563

."._ 545/578

AXIAL BA0iD UPPER SECTION

LEVER ,...43/584_/

BODY, RELEASE

' "536/577 366/403 ' LOCKING PLUNGER

DOME ATTACHMENT BOLT

~

L I 543/584

545/578 . 5607-40

Figure 53

STRUCTURE ASSY. FUEL CASK ~iii~' MAXIMUM AND MINIMUM THERMAL VACUUM TEMPERATURES

·liii.AaS

S«T/011 A:A

233U07 33Z/43Z /

' .

402/4"99---- .. ·-····

381/4 7 7 -----u__jll

325/431· I I •

530/604

" 490/566

""'-

I'

403/493

@IIU:£5

493/573

'0'" .U.It

.25alf 11(1:

-.

-.6st.o, £

~91/;;·-

198/33;'·0.

L- !14JO _j_

5607-31

Figure 54

PREDICTED CASK STRUCTURE AND ASTRONAUT THERMAL GUARD TEMPERATURES OUR lNG LUNAR SURFACE DEPLOYMENT

I

I j I

J rtr··=:·: -- .

6000 7>

, ; I . ,~ I I I ' I

L II I

I I . I .... I I I ..

-->-1. _..t__--i

t----r;· \ ; :~\.-__ --\ I ! ' I l ~_LJ

~-----· c=:::--- --

700°

L_ ___ _

: .. "l><i~ l.....J

650°

550°

iiiiiii'

. 240°

I

225°

Figure 55

GAEC STRUT TEMPERATURE RESULTS TEMPERATURES SHOVvN IN FOLLOVVING ORDER:

SLA On 'lV /Sun SLA On W /0 Sun SLA Off W /Sun SLA Off W /0 Sun

146 97

12.0 73

"~~i ~\ ~~ !li~ /

/ /

'"~~/ ""' .. /

236y 2.56

146 2.01

148 80 67 151 93 88 67

33 \\ 86 2.~~\ /

' flO~ ' /

/ /

/

42.

iiiiili'

5607-25

Figure 56

~

19/183

70/215 \ 63/214 ~ 54/207

T -----..

8926 27/187

\

43/203

' 42/205 ?

82/217

T 1211/2y r ~203 / >nn/J ""'lJ / -ym 160/274

306 i7/213

~ I y \f/0

LEM THERMAL BLANKET TEMPERATURE RESULTS EARTH ORBIT 'NITH SLA ON, WITH AND WITHOUT SOLAR HEATING

5607-36

Figure 57

LEM THERMAL BLANKET TEMPERATURE RESULTS TRANSLUNAR WITH SLA OFF, WITH AND WITHOUT SOLAR HEATING

-205~

-85/45 -17VJ76 I -214/158 -116/6

~ ~ -42/149

I , n...., I • ~ ..

~~~ v -114~3

-162/-24 7/227 7 \1

! I

-10/81 71/140 . r

-2/201 -167/-5

~;/36 ~!Z8 7

/. -171/1ZO

r~ -ZZ/\0 ,- \ 1~18

~

5607-37

Figure 58

ACCEPTANCE AND QUALIFICATION TEST PROGRAM OUTLINE AND TASK NUMBERS

z z 0 0 -1-1- a.. <( <( u u :::l -- I u.. u.. ~ -

u ....J ....J <( <( <(

:::l co :::l 0' 0' - - N CV'\

""'" Ll'\ I..A.J 1- 1- 1- 1- s: I

:iE :I: :I: :I: :I: :iE - (.!) (.!) (.!) (.!) (.!) -0::: - - N

ACCEPTANCE ....J ....J ....J ....J ....J I a.. u.. u.. u.. u.. u.. a

0 ASSEMBLY & INSTRUMENTATION AO co DO EO FO GO HO 1 WEIGHT AND CG MEASUREMENT A1 C1 D1 El F1 G1 H1 2 LAUNCH VIBRATION A2 C2 D2 E2 F2 G2 H2 3 FUNCTIONAL TILT TEST A3 C3 D3 E3 F3 G3 4 INSPECTION A4 C4 D4 E4 F4 G4 H4

QUALIFICATION

0 INSTRUMENTATION INSTALLATION BO 1 AIR SOAK 81 2 THERMAL VACUUM 82 3 INSPECTION 83 4 LAUNCH VIBRATION }

SHOCK B4 H5* LUNAR DESCENT VIBRATION

7 FUNCTIONAL TtLT TEST 87 8 INSPECTION 88 H8 9 TEST REPORTS 89 H9

----- -·-

• TASK H-5 INCLUDES ONLY LAUNCH VIBRATION

1-::::c (.!) -....J u.. Ll'\

I

:iE -N I

a

KO K1 K2

K4

5807-22

ALSEP fuel cask mount design review meeting #247...BENDIX SYSTEMS DIVISION ANN ARBOR~ MICH.'~ndi/ CORPORAliC~ MINUTES 9712-864 Pg. 2 Fuel Cask Mount Design Review Date of Meeting 5

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