lspe qualification and flight acceptance t/v test summary ... · t/v test summary and thermal...

LSPE Qualification and Flight Acceptance T /V Test Su.m..mary and Thermal Design Final Report

NO.

ATM 1110

This ATM Summarizes the analytical and test results of the Lunar Seismic Profiling Experiment Thermal Control Systems. The report is divided into three sections. The first section introduces the hardware and develops the mathematical thermal model of the explosive package. The second section summarizes the Qualification and Flight Acceptance thermal vacuum testing programs and the third section presents the lunar surface predictions of the hardware.

Prepared by:~~ D. Toelle

Checked by: G. Psaros

Approved by: E. Granholm

REV. NO.

MO. RIV. MO.

ATM 1110 LSPE Qualification and Flight Acceptance T/V Test Summary and Thermal Design Final Report PAGI OF

SUMMARY

The LSPE high explosive package maintains thermal control, within the +40 °F to 180 OF operating limits, passively, by means of insulated surfaces and thermal coatings.

A 35 node thermal math model was developed utilizing the Bendix thermal analyzer computer program which accounts for all modes of heat transfer including radiation and conduction. This model was used to optimize the thermal design during the initial design phases by considering selective insulation surfaces and package shape, and determining effects of soil conductivity on lunar surface to package heat leak.

Qualification and Flight Acceptance thermal vacuum tests are summarized including test setups and pertinent results. Detailed correlation studies are summarized and compared with the analytical model demonstrating the validity of the model in predicting thermal response.

Lunar predictions are presented which are based on the teat correlated thermal math model. These predictions include both a nominally clean and dust cove red model deployed equatorially and at a 20° latitude landing site. Peak temperature of a clean explosive package will be +167°F; whereas, a dust covered package with antenna handle exposed to the sun could attain +177°F.

I:.SPE Qualificatoon and Flight Acceptance T/V Test Summary and Thermal Design Final Report

TABLE OF CONTENTS

NQ, REV. NO.

ATM-1110

I • • PAGI 1 OF V\.

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DATE 20 Sept. l

Paragraph Contents Page

1.0

2. 0

3. 0

4.0

s.o

6. 0

7.0

Scope ----- _, __

SECTION I

EXPERIMENT OBJECTIVES AND THERMAL ANALYSES

Background and Purpose ----------- ------Design Specification Requirements

3. 1 Temperature Requirements

3. 2 Power Requirement

Thermal De sign and Analyses Goals

---- ---------- ---

4. 1 De sign Goals ---------------- -----

4. 2 Thermal Analyses Goals

Analytical Thermal Model

5. 1

5. 2

5. 3

5.4

5.5

5. 6

5.7

Nodal Description

Thermal Resistances

Solar Heating

Lunar Surface Temperature

Baseplate Handle Extension and Edge Protrusions

Multilayer Bag

Lunar Surface to High Explosive Conductivity

5. 8 Antenna Heat Leak ------------------------

5. 9 External Coatings-Optical Properties

5.10 Heat Leak Summary

SECTION II

QUAL AND FLIGHT THERMAL VACUUM TESTS

Background

Test Objectives

1

2

2

2

3

4

4

4

5

5

5

5

5

5

9

9

12

12

12

16

17

LSPE Qualification and Flight Acceptance T/V Test Summary and Thermal Design Final Report

TABLE OF CONTENTS (CONT.)

NO. RIV. NO.

ATM-1110 t [ .·

PAGI ii OP vi

DATI2 0 Sept. 1 97 2

Paragraph Contents Page

8. 0

9. 0

Description of Test Conditions and Test Installation

8. I Thermal Test Conditions

8. 1. I 8. 1. 2

Qual Model Conditions Flight Model Conditions

8. 2 Vacuum Chamber ------------

8. 3 Lunar Surface Simulator

8. 4 Solar Simulation

8. 4. I 8. 3. 2

High Explosive Package Solar Simulation Geophone Infrared Heaters

8. 5 Experiment Location --------------

8. 5. I 8. 5. 2

High Explosive Package (Qual Test) Geophone Array (Qual and Flight Tests)

8.5.2.1 8.5.2.2

Geophones Qual Test -----------Geophones Flight Test

8. 6 Thermocouple Locations

8. 6. 1 8. 6. 2

Qualification Model Flight Model ---------------------------

Results and Discussion

9. 1 Graphical Summary of Results

9. I. 1 9. 1. 2

Qual Test Results Flight Test Results

9. 2 Factors Affecting Correlation of the Analytical Model

18

18

18

18

18 18

20

20 20

20

20 24

24 24

24

24 24

30

30

30 30

with Test Data ____________ _________ 37

9. 2. 1 9. 2. 2

View Factor Effects of Solar Simulation

9. 2. 2. 1 Errors in Lamp Adjustments (Qualification Test) ------------------

9. 3 Comparison of Data and Correlated Temperatures

9. 4 Geophone Infrared Heater-Flight Test

37 37

37

37

41

A••~•PIIO& Ystama DMelon

Paragraph


TABLE OF CONTENTS (CONT.)

Contents

SECTION III

LUNAR PREDICTIONS

10. 0 Lunar Predictions ---------·-·

10. 1 Nominal Clean Experiment

MO. RIV. MO.

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DATE 20 Sept. 197 2

Page

44

44

44 10. 1. 1 Nominal Operation of LSPE

(Equitorial Deployment) ---------··-10. 1. 2 Off-Latitude Operation (20° latitude)

10. 2 100% Dust Degraded Experiment

10. 2. 1 Nominal Operation of LSPE (Equitorial Deployment)

10. 2. 2 Off- Latitude Operation (20° Latitude)

11. 0 Lunar Predictions Summary

1!.0 References

Appendix A Thermal Math Model Nodes

;Appendix B Thermal Model Node to Node Resistances

44

44

44

44

46

47

Table

3. 1

3. 2

3.3

5. 1

5. 2

8. 1

9. 1

9. 2

9. 3

11. 1


TABLES

Title

Thermal Plate Specification Temperature (High Explosive Package)

Thermal Plate Specification Temperature (Central Electronics)

Geophone Specification Temperature

LSPE Thermal Coating Properties

LSPE High Explosive Package Heat Balance

LSPE Qualification Thermal Vacuum Test Conditions - Explosive Package

LSPE Qualification Thermal Vacuum Test Data and Correlation for a 1/8# Explosive Package

LSPE Qualification Thermal Vacuum Test Data (Geophone and Antenna Socket)

LSPE Flight Acceptance Thermal Vacuum Test Data (Geophones}

Lunar Deployed High Explosive Baseplate Operating Temperatures

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DATE 20 Sept. 1972

3

3

3

13

14

19

39

41

LSPE Qualification and Flight Acceptance TIV Test Summary and Thermal Design Final Report

~pace \~Division

Figures

5. 1

5. 2

s. 3

5.4

8. 1

8. 2

8. 3

8. 4

ILLUSTRATIONS

De scription

Lunar Deployed Nodal Model of the H. E. Package

Lunar Surface Temperature vs. Sun Angle and Latitude

Lunar Soil Transient Model Nodel Diagram

Effects of Soil Conductivities on LSPE High Explosive Baseplate Temperatures

LSP Lunar Surface Thermocouple Locations

Lunar Surface Temperature Profile (Qual T IV Test)

Lunar Surface Temperature Profile (Flight TIV Test)

Qual Model T IV Test Setup (H. E. Package and

ATM-1110

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DATE 20 Sept. 197 2

Page

7

8

10

11

21

22

23

Transmitting Antenna) ------ -- -- ---- · - -· ·· · ---- 25

8. 5

8. 6

8.7

8. 8

9. 1

9. 2

9. 3-9.6

Qual Model TIV Test Setup (Geophone Array)

Flight Model T IV Test Setup (Geophone Array)

LSPE Qual Model Thermocouple Locations (H. E. Baseplate)

LSPE Qual Model Thermocouple Locations (Geophone and Antenna Mount)

Qual TIV Test Events Summary (H. E. Baseplate) --····

Qual T IV Test Thermocouple Temperature Profile

Flight Acceptance Test Thermocouple Temperature Profiles (Geophones)

26

2.7

28

29

31

32

33-36

Figures

9.7

1 o. 1


ILLUSTRATIONS (CONT.)

Description

Qual T/V Test Radiometer Response

LSPE High Explosive Package Operation Temperature Profile ·---------- --- ----- -· -·

NO. REV. MO.

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DATE 20 Sept. 1972

Page

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45

1. 0 SCOPE


ATM-1110

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DATE 20 Sept. 1 97 2

The purpose of this report is to document the development of the Lunar Seismic Profiling Experiment thermal analysis and the results and conclusions resulting from the thermal vacuum testing of the.LSPE Qualification and Flight Models in the Bx.A thermal vacuum test chamber. This report is in three parts; experiment objectives and thermal analysis, Qual and Flight thermal vacuum testing, and lunar predictions.


ATM-1110

PAGE 2 OF 41

DATE 20 Sept. 1972

SECTION I

EXPERIMENT OBJECTIVES AND THERMAL ANALYSES

This section summarizes the objectives of the LSPE experiment and the development of the thermal model and analysis.

2. 0 BACKGROUND AND PURFOSE

The Lunar Seismic Profiling Experiment (LSPE) consists of eight packages, each containing an explosive charge and detonation mechanism, and a central electronics package which is housed within the ALSEP Cen-tral Station. The explosive charges weight from 1/8 pound to 6 pounds and are approximately equivalent to TNT in energy per pound. They will be deployed from the Lunar Roving Vehicle (LRV) by the astronauts at distances from 160 meters to 2. 4 kilometers from an array of four geophones deployed on the lunar surface. The charges will be detonated after the astronauts leave the lunar surface by a r. f. command from the ALSEP Central Station.

The explosive package (EP) temperature range between 40°F and 180°F will be maintained for the EP components over the period from lunar morning to lunar noon during which the package is to be exposed to the lunar environment. Absorbed solar heat at high sun angles will be minimized by means of a 20 layer multilayer insulation bag inside the fiberglass top cover and by a coating of white thermal coating on the exterior of the upper portion of the package. The remaining exterior surfaces of the EP are coated black to permit rapid initial warm-up of the packages which will be deployed at low sun angles when temperatures are near the mini-mum operating limit. ! ~ ··

3. 0 DESIGN SPECIFICATION REQUIREMENTS

3. 1 Temperature Requirements

NO. REV. NO.

ATM-1110 LSPE Qualification and Flight Acceptance T/V Test Summary and Thermal Design Final Report PAGE 3 OF 47

DATE 20 Sept. 1972

TABLE 3.1 3. I. 1 High Explosive Package THERMAL PLATE TEMPERATURE

Minimun1 Maximum

Operational Limits +40°F +180°F

Non-Operational Limits -80°F +185 OF

TABLE 3. 2 3. 1. 2 Central Electronics THERMAL PLATE TEMPERATURE

\ i

Ope rating and Non-operating Limits Minimum Maximum

Qual -22oF +158°F

Acceptance -l0°F +146° F --TABLE 3. 3

3. I. 3 Geophones and Cables GEOPHONE TEMPERATURE

Minimum Maximum

Operating Limits -1 00°F +261 oF

Non-operating Limits -279° F +261 oF

3. 2 Power Requirement

The design limit power required of the experiment shall be 9. 0 watts of operating power.

LSPE Qualification and Flight Acceptance T IV Test Summary and Thermal De sign Final Report

4. 0 THERMAL DESIGN AND ANALYSIS GOALS

4. 1 Design Goals

ATM-1110 ,---

PAGE 4 OF

DATI 20 Sept. 197 2

4. 1. 1 Maintain the high explosive package electronics and mechanical components within the specified temperature limits.

Minimize the effects of solar radiation

Provide good component heat paths to the temperature controlled baseplate.

Minimize the effects of heat leaks

4. 1. 2 Design to a ::1::25 a off-equator deployment.

4. 2 Thermal Analyses Goals

4. 2. 1 Determine heat leak or gain through

Experiment cover

Multilayer bag.

Baseplate extensions and protrusions

Receiving antenna

High explosive

4. 2. 2 Determination of thermal performance in a lunar environment.

4. 2. 3 Recommend thermal coatings.

4. 2. 4 Design and supervise fabrication oi thermal simulator

4. 2. 5 Develop a thermal math model.

4. 2. 6 Correlate analytical data with test results obtained from thermal Simulator, Prototype, Qual, and Flight model tests.

NO. REV. NO.


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DATE2Q Sept. 1972

4. 2. 7 Utilize data obtained from the performance of DVT to design Qual and Flight models.

4. 2. 8 Utilize data from the DVT and ALSEP system Qualification and Flight tests to verify the performance of lunar hardware.

(


""' ATM-1110

P'AGE 6

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DATEzO Sept. 197 2

5. 0 ANALYTICAL THERMAL MODEL

5. I Nodal Description

The thermal model of LSPE (Figure 5,1) was developed utilizing the Bendix Thermal Analyzer Computer Program. The model consists of 35 nodes representing various components of the LSPE in addition to the lunar surface and space. These nodes and their physical significance are listed in Appendix A.

5. 2 Thermal Resistances

There are 101 resistances in the LSPE thermal model. These resistances represent all heat exchange, both through conduction and radiation, between all nodal surface of the experiment and the environment. These resistances, their interconnecting nodes, configuration factors, and surface areas are listed in Appendix A.

5. 3 Solar Heating

The absorbed solar flux is produced in model by applying equivalent heat to the surface node of the irradiated surface.

The surfaces receiving solar irradiation are, the electronic's cover, the high explosive cover, the baseplate extensions, and the receiving antenna.

5. 4 Lunar Surface Temperature

Variation of the lunar surface temperature as a function of deployment angle and solar angle was considered in the analysis. Temperatures of the surface as a function of these variables are indicated in Figure 5. 2. During lunar night the lunar surface was taken as -300 oF.

5. 5 Baseplate Handle Extension and Edge Protrusions

Mounting of the receiving antenna and fixing of the package to the transport frame during transit require portions of the baseplate to be exposed to solar radiation. Maximum exposure occurs when the sun is

FigUre 5~i

/; . . RECEIVING ANTENNA

-ELECTRONICS COVER

ATM-1110 Page 7 eli 4]7 20 Sept. 197 2

MU~TILAYER BAG --~,

. .) .. '~ \ .. t~' { \ .... ~ . \_ ... '

LUNAR DEPLOYED MODEL HI': PACKAGE ' I 4 ·~

THERMAL CONTROl STRIPE

-~

-200

---;.-.----·-· tOO 0

~-- t --• ~-.....

. - l:iS ~ (/)" -·--w· CD

8

CD 0

,:! ----g Cl)

~

--. ·-:-a-

------100

( . - : .. I.( .. '_E 10 ~ 10 -:;.THE CENTIM&.lt:l:!

~ £~ t"--!; ;_ 0 !"!t'o{P I""';

46 1!5t2 ~ t '

ATM-1110 Page 8 of 47 20 Sept. 197 2

(

r:---- 1 T--,-:- ·:·.~--.~:·. -------·-· .. --··------- ----

·'

~----~--------

f-. ~---'--- ~

. i -I

-------- -----~_L- ----~-~-=-~~: ------·-.... ~ ... ~ti~~*~~t~(f~ : :

_ . n j _. __ T _ _ _____ ~ _ __ _ _ . ~'; {{X~~- rrcz ..

·-· 1 • :. - _ .. __ - l

-=---L_ +-~- ~~ ~----·- ~=- ----: ---,

~_:== ~CL:=::l =s~1::.Y · -· ;~~ ~~~: ~--~_:--:~ ~;~·.:~-~: T:

t ::-::·:. i ::::::: .::.r:..:::. ., - ·- . ~- --- ----. ---. --------

-- .... -:\:. :.-:J'-~---=-=:__:.. __ --- ----- . ---- -----· ---------"1-: . ----- ---·----·-- -.

-.. L · -1-... :~_.-:..:L ----------·-:-~~~ ·-----f~~~_:-~--~=--

-----------~-·· ... ~ \ . .JF~tc~J·-_-------_-------- ----------------- ___ j_

- --:; •

- . - z.:lAO~

.-.• c~ ··r;;:: ' -··".";;~ . ·-~c~tu.u·-~F ~C ~ •.. · .. . ..

-~I:-:~7::-~-l:-.-- -- -=~~~-=~-_:-~-~-:_:_--~~- ____ :-__ :...:_=. ---i~:--- __ ::·J_ i~~~~t~----;( t· -.: -:... . . .. ::

-------------~-

----!

j

. ; ..:s\mr-1&8- ; . _j

> r ! ' I nl .. - ..• - t· I ..... , I I I .... "j• I- l- r f .. , i . I - i ' I '--------

! ---~--,

··--JQ--, 0

= <§un~~~ton_l•~l~· ~~-~&~=--:·~~~T~=~1J~:=_:\L~~=t ~~-· -:

__ J..:: __ :.:..:_ __ _:__ ...:..--------~---··--·.:.·--------!..... ·- • ~- •• I . ' •••· !• • -~------------- ·-· --------..

Figure 5. 2 ; . . ; . : :· . ; - - ! ·.:- I . , - :. . tunar S\lrface 'l'EfiZlPSrature -vs -Sun Aiigler m :Latitude : .. - -~· ... - :

..• - . ---. :. ---~ _____ l._..:_ -- . __ J...:..~J~---_____ -------. -· --- --


ATM-1110

PAGI! Q

DATI! 20 Sept. 197 2

45 degrees to the handle extension eenter-line and dust coverage is 100%. As indicated in a subsequent section the direct solar impingement on the baseplate increases from 0. 287 watts to 1. 05 watts when covered with dust.

5. 6 Multilayer Bag

A multilayer bag was produced from 20 layers of double sided aluminized mylar and spacers. This bag encloses the top and top one half of the electronics cover and is bonded to the inside of the electronics cover. This bag serves to protect baseplate components from high sun angle temperatures and also distributed the electronics temperatures evenly throughout the top of the enclosure. The bag thermal conductivity was taken as K/L = 0. 010 Btu/Hr- oF- Ft2.

5. 7 Lunar Surface to High Explosive Conductivity

A study was undertaken to determine the effect of the local lunar soil thermal conductivity on the high explosive baseplate temperature. The six pound explosive was used as the model since the entire explosive (k ';; 0. 20 BTU/ oF- HR - Ft) making the lunar surface to baseplate thermal coupling the highest for all packages. Figure 5. 3 indicated a sketch of the soil model used.

The model was developed from concentric soil nodes with the outer node forming the boundary of previously determined temperature data.

The boundary node temperatures were obtained in accordance with values presented in reference ~77 which gives values of lunar soil temperature gradients with respect to time at depths to the adiabatic soil temperature depth. Figure 5. 4 indicates the results of the baseplate temperature analyses for three different soil conductivities, K = 0. 60 (lunar rock), K = 0. 0011 (Apollo 11) and K = 0. 01. Note that LED520 indicates K = 0. 00242 BTU/oF - Hr - ft.

It was determined that soil conductivities between K = 0. 001 and K = 0. 01 remained adiabatic, however, lunar rock would cause substantial heating. This study prompted the requirement that packages must be deployed on lunar soil and not rock or crust.

of 47 20 Sept. 197 2

LUNAR SOIL TRANSIENT MODEL NODAL DIAGRAM

Figur-e 5. 3

Adi.abat,i.c Soil.

Depth

t.

High Explosive Cover

/

/ /

Surface Node.,

-~-

~age 11 of 47 20 Sept. 1 97 2

EFFECTS OF SOIL CONDUCTIVITIES ON LSPE HIGH EXPLOSIVE BASEPLATE TEMPERATURES

-...-----r----o-y

zoo-,__ __ _

l&o ~-------4P------~-4--------~--------~--------+------~

l

120

ROck BTU/HR- F-FT

Ll111'ar Sot . K = o:; o 1 "

~~~------~~-------4---------+--------~--------4-------~ A .J-.1.1n.a.:r .Soi · .. ~ - 0. 00 ',"

', ' "-' . .,,

sol--------~---------4---------+--------~--------~------~

60 ~----..4.---0 20 40 80 100 llO

Aaroapace rP~,,"Vt8ms Dlvlalon

LSPE Qualification and Flight Acceptance T IV Test Summary and Thermal Design Final Report

5. 8 Antenna Heat Leak

ATM-1110

PAGE 12.

DATE 20 Sept. 1972

The high explosive package design requires the 6 foot antenna be mounted directly to the aluminum baseplate via an extension which protrudes from the package. Thermal isolation is provided to prevent transmission of the absorbed solar heat to the baseplate components, This isolation is provided by means of the fiberglass sleeve forming the handle, and by means of fiber spacers and washers isolating the antenna clip from the baseplate,

5. 9 External Coatings - Optical Properties

Three coatings are significant in the analysis, The high explosive cover is 0. 030 inch fiberglass coated with 3M-401-Cl0 flat black, the electronics cover is also 0. 030 inch fiberglass with the bottom half coated with 3M-401-Al0 white velvet coat. The receiving antenna is thin walled brass with a bright chrome plate finish. Optical properties of these and other internal coatings are indicated in Table 5. 1.

5, 10 Heat Leak Summary

Table 5, 2 summarizes the significant package to environment heat leaks during the maximum temperature. This table includes heat exchange for the nominal and 100% dust degraded conditions.

Component

Baseplate/ Covers

Baseplate/ Covers

Baseplate

Antenna (1)

Fiberglass Covers

NUo KRY, teO.

f\.TM-1110 LSPE Qualification and Flight Acceptance T/V Test Summary and Thermal Design Final Report

JIAGI 13 OP 47

DATE20 Sept. 1972

TABLE 5. 1 t·'

LSPE THERMAL·COATING PROPERTIES

c oatinsz Propertv

3M-401-Cl0 at! f. = o. 96/0. 92

3M-401-A10 at/f.= 0.25/.92 ---Bright Tin Plate at! f. = o. 25/0.05

Bright Chrome at! f. = o. 48/ o. 16 Plate

Electroless Nickel f. = o. 33 Plate

-----

(1) Surface temperature 300°- 400°F.

J

TABLE 5. 2

ATM-1110 Page 14 of 47 20 Sept. 1972

LSPE HIGH EXPLOSIVE PACKAGE HEAT BALANCE

BASEPLATE HEAT LEAKS (WATTS)

Path Nominal

Thermal Bag -0.0307

Black Thermal Control Stripe {sun side) +0. 934

Black Thermal Control Stripe (shade side) -0.911

Direct Exchange with Space -1.04

Direct Exchange with Lunar Surface +0.44

Direct Solar to Handle Extension +0. 287

Antenna to Handle Extension +0.240

1 OOo/o Degraded

+0. 0866

+0.684

-1.212

-1. 15

+0.375

+1. 05

+0. 172


"'"

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PAGI 15 47 Of

DATI20 Sept. 1 97 2

SECTION II

QUAL AND FLIGHT THERMAL VACUUM TESTS

This section swn.ma.rizes the Qual and Flight thermal vacuum test results and correlations.

MO. RIV. MO.

lA. TM-111 0 LSPE Qualification and Flight Acceptance T/V Test Summary and Thermal Design Final Report

PAGI 1 6 OF 47 Aaroa...,•oe

~~-""'4&telne Dhrialan

6. 0 BACKGROUND


The Lunar Seismic Profiling Experiment Qualification Thermal Vacuum Tests were performed during the period of 20 May 1972 thru 7 June 1972. The Flight Acceptance Tests were performed during the period 01 July 1972 thru 11 July 1972, both at the Bendix Aerospace Systems Division in Ann Arbor, Michigan. This report presents the thermal data obtained during those tests together with a correlation of the thermal mathematical model with experimental data. Also included is a brief description of the test installation.

.Aera1pace

LSPE Qualification and Flight Acceptance T/V TestSummary and Thermal Design Final Report

ATM-1110

PAGI! 1 7

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.· ~~~S'terntl Division DATEzo Sept. 1972

7. 0 TEST OBJECTIVES

The objectives of the LSPE Qualification and Flight Acceptance Tests were to subject the LSPE and integrated ALSEP to the Lunar thermal/ vacuum environment demonstrating the ability of the LSPE design to withstand these extremes without loss of function.

~' ' "

' ~ >1i >-'

' " ' ,, '


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PAGI 18 Of 47.'

o•nzo Sept. 1 q7 2

8. 0 DESCRIPTION OF TEST CONDITIONS AND TEST INSTALLATION

8. 1 Thermal Test Cbnditions

8. 1. 1 Qual Model Conditions

The LSP high explosive package temperatures were correlated for four test conditions. These conditions simulate various phases of the operating and non-operating mission. (See Table 8. 1). The first two conditions were designed to simulate the minimum operating temperature and solar simulation at the 60° critical solar angle. Conditions 3 and 4, which occurred subsequent to the battery firing and operation mode, were designed to simulate a non- operating temperature limit soak.

The geophones, located on the 14' x 14' lunar surface with the ALSEP central station, were allowed to follow the local lunar surface temperature through its phases.

8. 1. 2 Flight Model Conditions

There was no solar simulation of the flight hardware during Flight Acceptance Thermal Vacuum.

Four geophones were placed on the 14' x 14' lunar surface and cycled through lunar morning, noon, and night with the ALSEP hardware.

8. 2 Vacuum Chamber

Space was simulated by the Bendix 20' x 27' thermal vacuum chamber. A vacuum was maintained at greater than 1 x 1 o- 5 torr. throughout the test. The chamber walls will be painted black to simulate the emissivity of deep space. Liquid nitrogen at -300°F was circulated throughout the cold wall to simulate the temperature of space.

8. 3 Lunar Surface Simulator

The lunar surface was simulated by a 5' x 5' black metal plate with 8 inch vertical lips located in the northeast area of the 20' x 27' chamber. The surface was mounted horizontally in the chamber and separated from other surfaces by means of vertical liquid nitrogen cold

1.

2.

3.

4.

1

NO. RIV, NO.

lA TM-111 0 LSPE Qualification and Flight Acceptance T/V Test Summary and Thermal Design Final Report ,_AGI ] 9 Of 47

DATE 20 Sept. 197 2

TABLE 8. 1

LUNAR SEISMIC PROFILING EXPERIMENT QUALIFICATION THERMAL VACUUM TEST CONDITION- EXPLOSIVE PACKAGE

Lunar Surface Cold Wall Solar Intensity (oF) (oF) (Suns)

'

Minimum Ope rating +135 -300 -Limit Condition

Critical Solar +224 -300 1. 25 1

Angle Condition

Minimum Non- +52 -300 -operating Condition

Maximum Specifica- +235 -300 1. 25 1

tion Condition

Lamps are 60 degrees from horizontal

r·····


IATM-1110

PAGE 20 Of 47

DATE 20 Sept. 197 2

panels. The original surface was heated by means of a heat exchanger, however chamber verification proved this inadequate so an additional cover plate was added including resistance heaters. Figure B. 1 indicated the location of thermocouple on this surface.

This surface was used in the Qual test only since Flight packages were not simulated.

8. 4 Solar Simulation (Infrared)

8. 4. 1 High Explosive Package Solar Simulation

Solar simulation was achieved by using an array of two infrared quartz electric heaters. These heaters directed through the center of the electronics package at an angle of 60° from the lunar surface simulator and approximately 18 inches above it. The lamps were oriented such that two sides of the experiment were equally illuminated. Solar intensity was determined by monitoring the output of a radiometer coated with 3M-401- Cl 0 balck thermal coating. This radiometer was oriented normal to the IR array directed energy. This array existed on Qual test only.

8. 4. 2 Geophone Infrared Heaters

During Flight Acceptance Test the geophone array was irradiated via an array of infrared heaters to maintain the geophones at +250oF during the lunar noon condition.

8. 5 Experiment Location

8. 5. 1 High Explosive Package (Qual Test)

The high explosive package was placed in the center of the 5' x 5' lunar surface simulator. The package was placed on a 5 inch high aluminum standoff to provide an accurate view factor to the lunar surface simulator. The receiving antenna was extended partially in order that it remain within the high intensity field of the infrared solar array.

L 13

s

Figure 8. 1

fi .L !V!- l l l U

Page Zl of47 ZO Sept. 1972

LSP LUNAR SURFACE THERMOCOUPLE LOCATIONS

'Upper Lunar Surface

i.s3 ':

s

!Lbwer Lunaf'.oS'uriacev

LSlO) s

LS-..2'

s

' .. LSl6S

L811 S

'LS6

s

LS8 s

L5 18

G

350

300

250

1!..

I 200 w a: ;::)

1-a: a: ::::: 150 :2: w !-

10

sa

0 0

Figure 8. 2

BENDIX AEROSPACE SYSTEMS DIVISION

--- .. " .. - ... .1. ... v

Page 22 of 47 20 Sept •. 1 97 2

ALSEP ARRAY 'E' THERMAL VACUUM QUALIFICATION TEST ZERO TIME = 000001 OF 05/20/72

~ 155 LSPE UPPER LUNAR SURFACE TEMPERATURE AT LOCATION 2 ~ 157 LSPE UPPER LUNAR SURFACE TEMPERATURE AT LOCATION ~ A 159 LSPE UPPER LUNAR SURFACE TEMPERATURE AT LOCATION 6 ~ 161 LSPE UPPER LUNAR SURFACE TEMPERATURE AT LOCATION 8

tfl " :!

r-" L I~ r v v----1V' )JIJ~ ~ ...,,..t'vr

,....., ("'\ J1.,_ ~ lf ~ "" ~ -- ....... _ ~

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~~ {'--'

~

~ ~

!

..rJ ~ l~~~ ~~ • .,.... ~ .--.-. _,~

l -~--!--"' ~ ·~ ~-~

- ' ~ ------ ------- '----- -· ---

30 60 so 120 150 180 210 240 270 300 330 360 390 420 1450 ELAPSED TIME - HOUMS

350

300

250

... -' 200

IAJ a: ;;;, ,_. ~ ~ 150 ::t: w ,_.

100

50

0 0

Figure 8. 3

.t\. .l lVl- 1 1 1 u

Page 23 of 47 20 Sept •. 1972

BENDIX AEROSPACE SYSTEMS DIVISION ALSEP ARRAY 'E' THERMAL VACUUM CUALIFICATION TEST

ZERO TIME = 000001 OF 05/20/72

~ 162 LSPE LUNAR SURFACE TEMPERATURE AT LOCATION 01 m 16q LSPE LUNAR SURFACE TEMPERATURE AT LOCATION 03 A 169 LSPE LUNAR SURFACE TEMPERATURE RT LOCATION 08 ~ 170 LSPE LUNAR SURFACE TEMPE~ATURE AT LOCATION 09 X 177 LSPE LUNAR SURfACE TEMPERATURE AT LOCATION 16

-

11

ni!J,...,-. -- ~ ~~ ' :X.

(j

... ;._, ,_.J - _ .. ~

, J.

,..-~

' .

-lit' ~.

'

I --------- --~~--L___

30 - 60 90 120 150 180. 210 240 270 300 330 360 - 390 ELAPSED TIME - HOURS

I I I

~

~---

420 450


~~M- 111 0 ,--- - - -

PAGI 24 OF '47

o•n2o Sept. 1 97 2

8. 5. 2 Geophone Array (Qual and Flight Tests)

8. 5. 2. 1 Geophones Qual Test

The Qual geophones were each set horizontally in a V groove of a machined finish aluminum block. This block contained an adjusting screw to tilt the geophones simulating lunar gravity. All geophones were located on the 14' x 14' lunar surface simulator on the outer zone in the northeast corner of the surface. This entire array was covered with a multilayer insulation blanket.

8. 5. 2. 2 Geophones Flight Test

Location of the Flight geophones was similar to Qual except that the aluminum blocks were coated with high emissivity paint to provide a more rapid temperature response. The geophones were irradiated by infrared heaters in lieu of the multilayer blanket in order to attain lunar noon temperatures of +250°F.

8. 6 Thermocouple Locations

8. 6. 1 Qualification Model

Six thermocouples were designated to measure the experiment temperatures. Four100f these were located within the high explosive package, one was on the transmitting antenna mounting socket, and one was mounted on a geophone outer shield. (See Figures 8. 7 and 8. 8)

8. 6. 2 Flight Model

Four thermocouples were located on the outer shields of each of the four geophones.

Figure 8. 4

ATM-1110 Page 25 of 47 20 Sept. 1972

QUAL MODEL T /V TEST SETUP (H. E. PACKAGE AND TRANSMITTING ANTENNA)

Fig

ure

8. 5

QU

AL

MO

DE

L T

/V T

ES

T S

ET

UP

(G

EO

PH

ON

E A

RR

AY

)

AT

M-1

11

0

Pag

e 2

6 o

f 47

2

0 S

ep

t. 1

97

2

Figure 8. 6

FLIGHT MODEL T /V TEST SETUP (GEOPHONE ARRAY)

ATM-1110 27 of 47 20 Sept. 1972

L'SP- l T~E.~M/>.L BI\TTE.R"(

Figure 8. 7

.n. .J. lV.L- .1 .1 l V

Page 28 of 47 20 Sept. 1 97 2

LSPE QUAL MODEL THERMOCOUPLE LOCATIONS

I

~ _jA

-L<;:-,?-3 BASEPLATE

BASE. PLf:\1E ASS'( (REF D\.l,lG 2.'?>48552.)

H\5\-\ EX?LOS\\IE PACKAGE

SECT\ON A- A

/YLSP-3 REF

lr-LSP-4 REF

REF

I Figure 8. 8

ATM-1110 Page 29 of 47 20 Sept. 1 97 2

LSPE QUAL MODEL THERMOCOUPLE LOCATIONS

L5P-S &EOPHONE •a

GEOP~ONE

L SP TRAN::.M ITTER ANTENNA ON f-IFE SUBPALLET

NO. lilY. NO.


ATM-1110

PAGI 0, 47

DATr20 Sept. 1 97 2

9. 0 RESULTS AND DISCUSSION

9. 1 Graphical Summary of Results

9. I. 1 Qual Test Results

9. 1. 1. 1 Baseplate and Summary of Events Figure 9. 1 • ..._ -'·

Figure 9. 1 indicates a summary of the high explosive base-plate temperatures indicating the thermal test conditions. The high explosive baseplate temperature during the critical solar angle simulation exhibited a uniform distribution. Three baseplate thermocouples indicated 166 o, 168 o and 169 oF.

9. 1. 1. 2 LSPE Thermocouple Summary (Figure 9. 2)

Figure 9. 2 _includes all baseplate th~rrn.ocpuple_s including the thermal battery TIC LSP 01, the geophone TIC LSP05 and the antenna socket TIC LSP06.

The thermal battery and baseplate T/C's peak sharply at 136 hours of elapsed time. This peak is the result of the thermal battery firing. The baseplate and components all peak at 205 oF some 30 minutes after the firing of the thermal battery. The thermal battery thermocouple T/C LSP 01 was damaged subsequent to the firing and read low for the remainder of the test.

The geophone thermocouple LSP 05 indicated +137 o /295 o /-202° F for design limit/ acceptance noon/lunar night conditions respectively.

The antenna socket thermocouple LSP 06 indicated +157 o /145 o /-12 oF respectively for the three test conditions. Table 9. 2 summarizes these temperatures.

9.1. 2 Flight Test Results (Figure 9. 3, 9. 4, 9. 5 and 9. 6.)

Each of the four Flight model geophones was thermocoupled. The results are summarized in Figures 9. 3 through 9. 6 and in Table 9. 3. The lunar noon temperature distribution over the geophones was 184° I 225°/244°/2l9°F. The night distribution was -228°/-216°/-216°/-228°F,

..... 1.0 ..... 0

0' . 00

Q)

J.l

So •rot

~

Pot ::> E-l J:il tl.l

E-l tl.l J:il E-l

> -E-l ...:I J:il Cl 0 ~

...:I <

::> 0

Figure 8.10 Page 32 of 51

FLIGHT MODEL T /V TEST SETUP

4.00

300

I 200

1.1..

I 100 UJ a: :::J 1-a: a: w 0 a. X: w I-

-10

-20

I

I

l -30-0

l!l 093 LSP 2 A 095 LSP II

Figure 9. 1


ATM-111 0 ·' Page ·31 of 47 20 Sept. l 97 2

ALSEP ARRAY 'E' THERMAL VACUUM QUALIFICATION TEST ZERO TIME = 000001 OF 05/20/72

BASEPLATE !RECEIVER SlOE) TEHPERATURE (!) 0911 LSP 3 BASEPLATE ICENTERl TEHPERRTURE BASEPLATE ITJHER SlOE) TEHPERATURE

Critical Solar Angle (60°)

I I Maximum Specification Condition_ Condition - Lunar Surface Lunar Surface +235 - Solar

\ t<2<°F -\•• Simol•tloo Simulation

Thermal Battery Firing ' / \

\ / Minimu1;n Non-Operating \ Minimum Specification Condition - Specification Condition -Lunar Surface + 135°F - No ./ s Lunar Surface +SZ°F - No Solar Simul;~.tion. _, Solar Simulation

\ l\ 1\a

~ \ - \

('( ,.... -- ..,

~

ll. .)

- ~_}II l\ J \ ) ~ -·

( \ -- \ ....... \ \... __ /

~

'

30 60 90 120 150 180 210 240 270 300 330 360 390 1120 ELAPSED TIME - H~UAS

1150

400

300

200

.... I 100

...., a: :::; 1-a: a: ...., 0 0.. ~ ...., 1-

-100

-20

-30

[!) 092 LSP 1 A 0911 LSP 3 X 096 LSP 5

.

0 30

Figu:re 9. 2


ATM-1110 Page 32 of 41 20 Sept. 1972

ALSEP ARRAY 'E' THERMAL VACUUM QUALIFICATION TEST ZERO TIME = DOOOOl OF 05/20/72

THERMAL BATTERY TEMPERATURE (!) 093 LSP 2 BASEPLATE !RECEIVER SJOEJ TEMPERATURE BASEPLATE ICENTERJ TEMPERATURE ~ 095 LSP I& BASEPLATE ITJHER SJOEl TEMPERATURE GEOPHONE TEMPERATURE )( 097 LSP 6 ANTENNA TEMPERATURE

~

I ~ T ~

!\.... .... ....

l~ ~ __.r ~ --! -e.

~ 'IlL ~ \ JB --, 1 ~ \ r ,...

\ ~

-,. ( \l.

\ - \ / ~ ~

·~ " N ~ 1/ '

. 60 90 120 150 lBO 210 240 270 300 330 360 390

ELAPSED TIME - HOURS

';-.J I(

·1.120 1&50

I 1!00

300

200

-I£.

J I 100 w a: :::l 1--a: a: w 0 Q_

X: w ,_

-lC

-20

-30

~Oql GEOPHONE NUMBER 1 TEMPERATURE

It ......

\ =

I

' '

) 0 20 40 60 80

Figure 9. 3

BENDIX AEROSPACE SYSTEMS DIVISION ALSEP ARRAY 'E' THERMAL VACUUM ACCEPTANCE TEST

ZERO TIME = DD0001 OF 07/01/72

• )~ -.... -,..

r I \

'J...,. ~

100 120 1~0 160 180 200 ELAPSED TIME - HOURS

ATM-111 0 P~ge 33 of ~7 20 Sept. 1972

(l

/ IJf

~

220 21!0

I

AI 'J \}

260 280 300

400

300

200

IL.

) I 100 w a: :::> t-o: a: w 0 a.. :r: w t-

-100

-20 J

-30 I

m0~2 GEOPHONE NUMBER 2 TEMPERATURE

1'\" ......

\ f

0 20 l!O 60 80

Figure 9. 4

BENDIX AEROSPACE SYSTEMS OIVISI~N

..n. .1. ~VJ.- .l .l .1 V

, Pag~ 34 of 47 20 Sept. 1 97 2

ALSEP ARRAY 'E' THERMAL VACUUM ACCEPTANCE TEST ZEA~ TIME = 000001 OF 07/01/72

'

M I

.

f J \ ~

< '

I

(l ~I \ )' J ~

l ""-.e- ~

~

100 120 1l!O 160 180 200 220 2110 260 280 ELAPSED TIME - HOURS

I

300

!tOO

300

200

-I.!.. l l 100

w a: :::> ;--a: a: w c a.. X: w 1-

-10

-20

-30

~0~3 GEOPHONE NUMBER 3 TEMPERATURE

It _...._

\ ~

I

}

'

J 0 20 40 ~p 80

Figure 9. 5


ATM-1110 Page 35 of 47 20 Sept. 197 2

ALSEP ARRAY 'E' THERMAL VACUUM ACCEPTANCE TEST ZERO TIME = 000001 OF 07/01/72

M ....

I I \

l ~ l:l =

I

(1, ~I )' u \1

100 120 140 160 180 200 220 240 260 280 ELAPSED TIME - H~UAS

I

300

400

300

200

~

t 100 l.&.J a: ::> ,_ cr; a: l.&.J 0 a.. X: l.&.J ,_

-l'J

-2C

-30

~ 04q GEOPHONE NUMBER q TEMPERATURE

I j .

I

II ........

I \

I :

)

I

J I I 0 20 L!O 60 80

Figure 9. 6


ATM-1110 Page.36 of 47 -:::o

20 Sept. 1972

ALSEP ARRAY 'E' THERMAL VACUUM ACCEPTANCE TEST ZERO TIME = 000001 OF 07/01/72

~

! I \

"/

~

(1 AI \ l' J \1

~ l.Jil ~ ....

100 120 1~0 160 180 200 220 2L10 260 280 ELAPSED TIME - HOURS

I

300

MO. RIV. NO.

ATM-1110 LSPE Qualification and Flight Acceptance T/V Test Summary and Thermal Design Final Report PAGE 37 OF . 47


9. 2 Factors Affecting Correlation of the Analytical Model with Test Data

9. 2. 1 View Factor

The high explosive package view factor of the lunar surface simulator during the Qualification test was 0. 475 instead of 0. 50, which is the actual lunar view factor. This reduced view of the lunar surface reduces the baseplate operating temperature by 6 oF, during the critical 60° solar angle conditions.

9. 2. 2 Effects of Solar Simulation

9. 2. 2. 1 Errors in Lamp Adjustments Qualification Test

The incident energy impingement upon the LSP radiometers during the two conditions requiring solar simulation was 1. 25 suns or 162. 5 watts/ sq. ft. Of this 162. 5 watts/ sq. ft, 11. 25 watts was a result of radiation from the lunar surface which was +224 oF. This occurs because of the radiator tilt of 60° to the horizontal. The actual contribution of the total heat load attributable to the infrared lamps is 1. 16 suns or 151 watts/ sq. ft. This factor results in a 4°F decrease in the baseplate temperature during the critical solar angle condition.

9. 2. 2. 2 Absorptance of 3M-401-Al0 White Coating - Qualification Test

Heat absorbed on the white coated surfaces including the top of the electronics cover and the baseplate handle extension are higher than under actual solar irradiation. The white coating tend to absorb a greater percent of incident energy in the long wavelength spectrum (infrared). Since the quartz lamps emit both visible and infrared, the effective absorptance tance S.ncreases from 0. 25 to 0. 42.

This phenomonon has little effect on the insulated electronics cover, however, increased absorption on the handle increases the baseplate temperature 1. 5o F during the critical solar angle condition.

9. 3 Comparison of Data and Correlated Temperatures

Table 9. 1 includes the test temperatures of the critical nodes for the Qualification test. The.- baseplate was correlated to within 3 oF for all conditions tested. The only exception was the thermal battery subsequent to firing which ran consistently low after the firing.

Figure 9. 7

ATM-111 0 Page 3$ of 47 2Q Sept. 1 97 2

1 ' ·Bendix Aerospace Systems DiVision l · ~ J ' ~ 1\ '-: • • ALSEP Array.' E' Thermal Vacuum Qualificatiort Test' r \ ' · " 1

--- ' 1

'Zero Time = 000001 of 05 /?.0 !7Z

I . ,. I ' I ·. J t:l 01-5: LSPE .Radiometer Response

\ l i l 751\1 !

! \ I i50! i I ~ ~~lr" ~r~~~~;

l I I II I I I I I I I . I I Ill ! ! I II I I I I

,.,, I • 11 I I I I I I I 111 I I II I I : : : -: I

0<1 ' I I I . '

\ I i i

75 I 1

I I so 1 ( I

!

T l

I I

I

) ,~1 I : . II I I ~, I ·- --

' 0 1--~30 __ __._60 ___ 90 120 150 180 2}0 z .. v ~OV C>V\J .>JU C>OV -'7V •4U ... ::OU

Elapsed Time - Hours

2~

Location

Thermal Battery

Baseplate Receiver Side

Baseplate Timer Side

Baseplate Center

-·--

'

Table 9. 1

LUNAR SEISMIC PROFILING EXPERIMENT QUALIFICATION THERMAL VACUUM TEST DATA AND CORRELATION FOR 1/8 I EXPLOSIVE PACKAGE

TEST CONDITIONS

Minimum Specification Critical Solar Angle Minimum Non-Operating Condition Condition Specification Condition

Test Data Analytical Test Analytical Test Analytical Data Data Data Data Data Data

34°F 33°F 161°F 169°F 0 * -40 F -33°F

36° 33° 166° 169° -34° -33°

35° 33° 168° 169° -340 -33°

0 33° 169° 169° -340 -33° 35

.. .. * Subsequent to Battery Firing t!'e T /C Indicated a. Lower. Reading than considered normal

...

•'

ATM-1110 Page 39 of 47 20 Sept. 1972

Maximum Specification Condition

Test Analytical Data Data

151°F* 174°F

174° 174°

176° 174°

176° 174°

--·--

Location

Geophone

Table 9. 2

ATM-1110 Page 40 of 47 20 Sept. 1972

LUNAR SEISMIC PROFILING EXPERIMENT QUALIFICATION THERMAL VACUUM TEST DATA

TEST CONDITION

' Acceptance Design Limit Qual

Noon Noon Night

295oF 3l7°F -202 °F

Transmitting -Antenna 145° 157 ° -12 ° Socket

/•

NO. REV. NO.

~TM-111 0 LSPE Qualification and Flight Acceptance T/V Test Summary and Thermal Design Final Report

fiAGI 41 OF 47

DATE 20 Sept. 197 2

9. 4 Geophone Infrared Heater - Flight Test

The four Flight geophones were irradiated via quartz infrared lamps to attain temperatures comparable to luna:r; surface temperatures. Examining the temperatures of the four geophones, Table 9. 3, during lunar noon indicates the center geophones to be warmer than the outer ones. This is attributed to the higher intensity at the center.

Location

Geophone #I

Geophone #2

Geophone #3

Geophone #4

Table 9. 3

ATM-111 0 Page42 of 47 20 Sept. 1 97 2

LUNAR SEISMIC PROFILING EXPERIMENT FLIGHT ACCEPTANCE THERMAL VACUUM TEST DATA*

TEST CONDITION

I Acceptance Noon Acceptance Night .•

I

184°F -228°F

225° -216°

244° -216°

219° -228° ---- -----------~---~ -~-----~-

* No High Explosive Package was Tested During Flight Acceptance T /V

4l81"G Ill aoe

LSPE Qualification and FlightAcceptance T IV Test Summary and Thermal Design Final R~port

NO.

ATM-1110

PAGE 43

REV. HO.

OF

. stama Dlvlalon OATI20 Sept. 197 2

SECTION Ill

LUNAR PREDICTIONS

This section summarizes the lunar surface analysis of the correlated thermal model.

LSPE Qualification and Flight Acceptance T IV Test Summary and Thermal Design Final Report

NO.

~TM-1110

PAGE 44 -~

REV. NO.

OF 47

DATE 20 Sept. 1 Q7 2

10. 0 LUNAR PREDICTIONS

10. 1 Nominal Clean Experiment

10. 1. 1 Nominal Operation of LSPE (Equatorial Deployment)

Figure 10. 1 depicts baseplate operating temperatures of a clean high explosive package with maximum projected area exposed to solar radiation. This occurs where two sides of the package are equally irradiated and the antenna is exposed. A maximum temperature of +167 oF occurs at a 60° solar angle.


Figure 10. 1 depicts the baseplate operating temperatures of a clean high explosive package baseplate deployed off-latitude at a zoo angle with the equator. Two solar conditions are considered; one with maximum exposed area as above, and one with minimum exposed area or only one surface irradiated.

The package baseplate with two surfaces irradiated will peak at 167oF just as the equatorial deployment, however, it will peak at a higher solar angle, namely 68 degrees.

The package with only one surface irradiated, naturally follows a lower temperature curve. It's equilibrium temperature at the LM touchdown solar angle is +58°F. This package baseplate would peak at 145°F.

10. 2 1 OOo/o Dust Degraded Experiment

10. 2. 1 Nominal Operation of LSPE (Equatorial Deployment)

Figure 10. 1 depicts the baseplate operating t~mperature of an explosive package which is 1 OOo/o degraded with dust t Y = 1. 0). The maximum baseplate temperature of this degraded package would be +177 oF at a solar angle of 60 degrees.


Figure 10. 1 depicts the baseplate operating temperature of an explosive package 100% dust degraded which is deployed at the 20 degree latitude. This package baseplate temperature will peak at +177•F at a 68 degree solar angle.

f

~--,

r;; o_

t, Cl k ::1 .. "' : k Cl 13. e

j - Cl E-o Cl ..

-· i Cl ,a

"' ~lEI ~~ ..

u ' ·-a

-- 0 k ... , __ .- ~ ....

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:~ •.' I

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.

150

, .. 140

\3o-

lZO r-

' llO I

~I I 'l •', I ·'._I' i'· I I 1 ~~ i ·.,t\ • \I""',

'. r .. ' • : ' ' '"'FiguJ'e, 10• 1 " ' '

Lunar Seiamic Profiling Experiment High Exploaive Package Operation Temperature Profile

'':M aximum 0 L Jperatimr i mit -- --- -·- -· ... ..

...--:

ATM-1110 Page 45 Of" 41 20 Sept. 197 2

r.:J-~ v "' / v :..._ " ~- ~ ~-, I

;} ! ~

I v - I

~ / v ) l,f' I ~ X

./ I

7 I / v

/ -- _ ___! -

I II

/ '

I _,

v I [7

· Nominal J1ean .aur!a.c 0 a (Equatoril..l) .. i I I

A IOOo/o Dus De~rraded ur!aces IEQ\.atoriall

lOO .v / fes (Z0° LatiLde) · I j 7 'Nominal C lean Surfac

I . - JOO'fu!.\!.1!! ~f····· .... <!,e"rued_~ .

1/ "" v

I X I Nominal• lean surfac e (Z0° Lati. ude)

• ·Minimu In al;>aorbed !solar load '

9G ---- 1--------

j I 80 ., I .

LM-. i.~ . • E etonation I---·

II ' Operation j=tange

!/ .

' f

t----

~ \

~ ~ ~

I

--

__ .;__,

--

--L------

f*

p.

~

~

1.>

-0 10 zo 30 40 50 60 70 80 90


11.0 LUNAR PREDICTIONS SUMMARY

Table 11. 1 summarizes the lunar surface predictions.

TABLE 11.1

LUNAR DEPLOYED HIGH EXPLOSIVE BASEPLATE OPERATING TEMPERATURES

Maximum (Clean) +167 oF

Maximum (1 OOo/o Degraded) +177 OF

Minimum (Clean) + 58°F

NO. REV. NO.

iATM-1110

46 47 IIAGI Of


12. 0

NO. REV. NO.

ATM-111 0 LSPE Qualification and Flight Acceptance T/V Test Summary and Thermal Design Fmal Report

PAGE 4 7 OF _.i1_

DATE 20 Sept. 1 972

REFERENCES

1) AL 900131 "Lunar Seismic Profiling Experiment Specifications", Bendix Aerospace Systems Division.

2) AL 900431 "Specification for Seismic Detection System for Lunar Seismic Profiling Experiment", Bendix Aerospace Systems Division.

3) TP 2365582 "ALSEP Array E Deployed System Design Limit Thermal Vacuum Test Procedure", Bendix Aerospace Systems Division.

4) TP 2365575 "ALSEP Array E Flight System Deployed Thermal Vacuum Test Procedure", Bendix Aerospace Systems Division.

5) Internal Memo 9712-551 "LSPE Structural/Mechanical/Thermal/ Simulator T/V Test", Bendix Aerospace Systems Division.

6) ATM-1109 "Lunar Seismic Profiling Experiment Design Verification Thermal Vacuum Test, " Bendix Aerospace Systems Division.

7) Internal Memo 70-210-143 "PSE, One-dimensional Thermal Analysis of Various Lunar Soils at Off Equatorial Latitudes" Bendix Aerospace Systems Division. '

8) LED-520-lF "Design Criteria and Environments for the LM", Grumman Aircraft Engineering Corp.

LSPE Qualification and Flight Acceptance T /V Test Summary and Thermal Design Final Report

/~raapace ly8tams Dlvlalon

APPENDIX A

THERMAL MATH MODEL NODES

10 Lunar Surface 14 High Explosive 15 High Explosive 16 Electronics Cover Black Stripe 17 Electronics Cover Black Stripe 18 Baseplate 19 Space 20 High Explosive Cover 21 High Explosive Cover 22 High Explosive Cover 23 High Explosive Cover 24 High Explosive Cover 28 Electronics Cover White Top 29 Multilayer Blanket 30 Electronics Cover White Stripe 31 Multilayer Blanket 32 Electronics Cover White Stripe 33 Multilayer Blanket 34 Antenna 35 Antenna 36 Antenna 37 Antenna Handle 38- Silicone Rubber Corner 39 Silicone Rubber Corner 40 Antenna Handle 41 High Explosive 42 High Explosive 43 High Explosive 44 High Explosive 45 Antenna 46 Antenna 47 Antenna 48 Antenna 49 Antenna 50 Antenna

NO. RI!V. NO.

ATM 1110

PAGE 1 Of l

DATE 20 Sept. 1972

•

------------------------- -~- ----- --- ----- --------

.Appendix B

Thermal Initial

Table Number (Heat Input)

Product of (Absor~tance 8. Abl\orbing Area) Node Capacitance Temperature

o 1 -o -o · -o 10 0 0 -,IOOOE+01 14 l 0 ,IOOOE-01 15 ----~---0 ,1000£-01

------- ---16 1 --- 0 .1000E-01 17--1 --0 ,IOOOE-01

-~---lA ~---. 0--- ,2540E+OO ------ 19 ---~-----0 -- -,lOOOE+Ol

20 ----.--0 --- .<'OOOE-01 --------21 ---~--- 0--- ,?OOOE-01

22_1 ____ 0 _____ ,lOOOE-01 ---------2j--l---O --- ,lOOOE-01

24--1--0 --- ,1000E-01 ----------- 2A -- 0 -- 0 - ,l200E-01

29 ----o- 0-- .IOOOE-01 ------30 -- o-·-o --- ,lOOOE-01

---· ----~---~ 31 - 0 ---0 ~ ,1000E-01 32--- o--o. -- ,1000£-01

------33 --0- 0 ,1000£-01 --- 34 - o --o -- .11'lOE-OI

35 0 --- 0 .23AOE-01 36 ____ o·-o ~- ,3300E-ot

------37---- 0 0 --- .1000E-01 - 3A --- 0---- 0 - ,2540[+00

-------39-- cr~---o-- · ,2S40E•oo 40 ___ o·- 0 --- ,IOOOE-01

----- --~----41 ---- 0 ---0 ,5'520E+OO ----~--42 0- 0-- ,IOSOE•OO

4 3 --- 0 -- - 0 , 12 4 0 E- 0 1 --44 -- 0 -- 0 -~ • 3500E-O 1

------ 4<; 0 - 0 ,1 OOOE-0 1 ------~-46 -----o--0 --- ,1000£-01

----------47 0 0 -~ ,1000E-01 -------4A o-- 0--,1000£-01

49 0 o--.1000E-01 50 0 0-~-- ,lOOOE-01

NODE OATA ___ _ --~- . ----~-----------

,4oooE•02 1 -o-o. ,4000£•02 0 0 o. --------------------,4000(+02 -----~------ 0 - 0 o. ,4oooE•02 -- ---------~---- 3 -o .6oooE-ol ,4000[+02 ---~-------- ---~ 0 0 o. ,4000E•02 --------~-- ---- 4 -o-o.

-,4S<:IOE•03 ------~--- ----- --- 0 0 O, ----------------- ·------------,4000E•02 ________ ------ - 3 -0 ,9600E-Ol ---- ---- -------- ------,4000E•02 --~---- -- ·o o o. ~---

,4oooE•o?-- ------------------ o o o. --,4000E•02 -------------- 0 - 0 0, ,4000[•02 -- -------------- 0 0 o. ---~- -~--- ------------------------.4000E+02 --------------- 2 -0 .4SOOE·OI-----------~-------------

,4000E+02 - -------------- 0 0 O. -------------- --------~-------,4000£+02 ------------ - 3 -0 ,1720E•Ol _________ _ ,4000[+02 -------~-------- 0 0 o. ,4oooE•02- · ··o - o o. ,4000(+02 ------~--~---- --- - 0 0 o. ,4000E•02 --- 3 -o ,19BOE-ot ___ -------

---------------

,4000E•O? --------------------- 1 •0 ,3960E·Ol ,4000E•02 --- ----- -- 1 -o .s2oor-o1 ,4000E•O? ----------~-------- 1 -0 ,1'l'50E•Ol ·------·-- -----~-------- ---~---

,4000E•02 _______________ - 3 •0 ,3180E-Ol _____ _

,4000E•02- ---o o o. -----------------------------,4ooor•o2 - o o o. ,4000E•02 ------------- 0 0 0, --------------.4000(+02 --------------;-- --- 0 0 o. ,4000[+02 -------------- 0 0 o. ,4000[•02 ----------~-- ---- - 0 0 o. -- --~----------~---~-,4ooor•o2 ----- ------ ---~ --- 3 -o ,6ooor-oJ--------~----------

.4000E•02 -- ----------- 3 -0 ,6000E-03 _________ ~--~-------------

.4000E+02·-----~------------ -3 -0 .1200E-02 __________ ~-------~----

.4000E+02 ------ --- ---~ ----- 3 -0 ,2400E-OZ -----------,4000[+02 ------------ --- 3 -0 ,4'lOOE•02 ------,4000E+02 --------------- -----3 -0 ,9<lOOE-02-

1 of 4

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Resistor Connecting -Number Nodes

Radiation ---- -- _ Configuration _______ _ --------

0 22 23 24

0 14 IS 16

Area Factor

-o -o -o --RESISTOR DATA 15 ,1BOOE+03 O, 18 -- ,62SOE-Ol. ~6424E.;.11

18 ---- .9600E-Ol- ,1332E-09

o. o. ·o oo. ,6000E-Ol 0~ -----o -- 0 O, ,8100[+00 o. --- 0 ·0 o.

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·-------------------· ---- -----------------------

--- -------zs--Ir- 18- --- .9&aor-or ~ 1332E•u9···;enror-•oo·-o;·--- ---o--·o-v;·-------------------------- -----·26- ·14·- 20 -- .• 7lOOE.;.or-··.3649r-lO-~liiOOE+OO 0~-----o--o--..------- ----------------- ----- ·27 --14 21 ---.7100£-01 -.3649£-10 ..• 3000E•OO o.--------··o··--- 0 O.

-----·za··--15--20 -----.7Joor-o1-- .3649E-10--~3oooE•oo o.------- o-·-·o o. -------29 ___ 15 -21 ---- • 11oor-o1 · .3649£-10- ·.3ooor•oo o.------o- o o.

------------30 ... 11 ----10 ------ .'1560E-01 .• 7369£-10 .• 4500E•OO O.- -----~~- 0 O. -- - ----- · 31 16 ··· 10 .9s6oE-Ol • 7369£-10 ·· .4soor•oo o.-------·o- o o. ---------------------- ~-- 32--11-- 1'1 ---- .'1560E-01 .73t>9E-l0 o4500E•OO 0.---------o 0 O. --------------------------

33 16 19 .9'560£-01 • 7369£-10 .4500[•00 o. ---------- 0. 0 o •. 34 20 10 .1410E•oo .11o2r-o9 · .4500E•OO o.-------·-·o o o.------~-------35 21 10 .1430£+00 .1102£-09 .4500£•00 o. ------ .. - 0 0 o. ----------------- ------------

----------36. 20 19 .1430[+00 .1102[-09 .4500[•00 o. ------- 0 0 o. ------------------------------------------- .... ----- 37 21 19 .1430[ •00 .11 02[-09 .4500[ •00 0. -- ---- . 0 0 o. -------· --- --- 46 22 23 .6700[•03 o. o. o. ---- -0 0 o. -------------- 47- 23 24 .1li0E+03 O. O. O. ----- --- 0 0 Oo . -----------------------------48 ... 22 42 .2500[+03 o. o. o. ---------- 0 0 o. ---------------49-- 23· 41 -- .1110E•oo .S134E-to .2700E•oo o. ------ ·o o o. ---------------- so - 24 14 -· .9000[•02 o. o. o. -------- 0 0 o. ---------

----51 - 15 18 ---- .9000[•02 o. o.. o. ----- 0 0 o. -----"52- 39·-·14 ---- .2469E•02 o. ----o. ------ --- o.-------- o · o o. · -------------------------

------- 53-- 38 14 ---- .2469£•02 o. --_--- o. o.------·o · o o. ----------------54-· 39-- 15 --- .2469E•02 o. ------ o. -------- · o.------ o· - o o. ----

-55 - 38 ... 15 .2469[•02 o. ·------ o. ··········· o. ------·-·· 0 0 o. ----- 56----34----35 --- .so70E•o3 o. ---- o. -------- -o. -------- o - o o.-

--------·s7· 35 -- 36 ---- .2700E•03 o. ------- o. ------ o. -------- o o o. --60 - 4o · 1a-· .3920E•02 o. ------ o. ---- ---- o.----------- o o o.

------------ 61 37 20 .3920E•02 o: ------ o. ----- 0.-------. 0 0 O. --------64 39 20 .1230[+04 o. ---· o. ·-- --- o. ------ 0 0 o. -----------------------65-- 38 21 - .1230[+04 o. ------ o. - ---- o. 0 0 o.

--------66 - 34 19 - .10'50£+00 .1529£'""'10 -- .BSOOL-01 o.------ 0 0 Oo --- ------------67 34 ··1o .losoE•oo .1529E..;lo- .esooE-ot o. --------- o o o. --- --------------------------

-----68 - 35 ---19. --- .2090E•OO .3043[•10- .BSOOE-Ol·o.--------- 0 0 O.------- ---· ------ 69 35-- 10 .2090[•00 .3043£-10 .BSOOE-01 O. --- ··- -- 0-- 0 O • .,.-----------

10 36 19 --- .2130£•00 .3975£-10 .8500E-Ol O. 0 0 O. - ----- .. -----71 36 - 10 .2730£+00 .397Sf-10 .8'500E-01 O. ---- 0 .. 0 O.

,--- 37·-·19 ------ .6800£-0l .3564£-10- o3060E•OO Oo ----------- 0 0 O. -------------- ----- -----73 37-- 10 .6BOOE-Ol .• 351i4f-10 .31)60[+00 O. --------- 0 0 O. --------------

---- 74 37 20 .6BOOE-Ol .33'>5f-10 .2F!AOE•OO O. ------- 0 0 O. ------- 75 2A -··z9-- .5400E•03 o. o. o. ·------- o o o. -- -----------76 · 29--- 18 --- .1560E•oo .1336E-IO · .5oooE-01 o. ------- o o o. --------------

-----77 30 31 -- .8660[+03 o. o. o. -----------· 0 0 o. 7B 31 18 .9600E-o1 .8222f-ll- .5ooor-o1 o. ------------ o o o.

---------79 32 33 -- .8660[•03 o. o. o. ----- ------0 - 0 o.-80 33 18 .9600£-01 .8?22E-ll .SOOOE-01 O. 0 0 O. --- -------

···------ 81 28 -19 .1740[+00 .2683[-09 .9000[+00 o. ----- 0 0 o • 82 30 - 19. --- .9600£-01 • 7400E-10- .4500E+OO O. --- --- 0 0 O.

--------- 83 - 30 10 .9600E-01 • 7400E-10 .4500£•00 o. - --- 0 0 o. ---- . 84-- 32 .. 19 -- .9600£-01 • 7400£-10 .• 4500£•00 o. --- 0 0 o. ------

as-· 32 --lo -- .9600E-o1 • 74oor-1o- -.45ooE•oo o; o ··· o o. --------------------------------89- 37 ___ 40 ---.1soor•o2 o. --·-o. o~---- o--·o 0~-------------------------------- 91-- 41 - ·43·--.• 1270E•03 o. ·-o. o.----o- o o.-

----

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..... ---------------------

---------------------------- ------------------

-~--------"92- -,_,2 44 .2500£+03--IJ.--- • . If. 0 Olr. ~3--l,.--~;r--.623SE•02-o-.-- o.------o-;-------o-o·:~------- ----------------------

94 ---- 4t ---42 --- ·.n2oE•03 ·o·.------o-. ·o. ------- o- o· ---------95 ---38--10- --·.zoooE-01- ;lS42E:;;Io--~4500E+"oO-o. ---- ---- 0---0

9t> ---39 --·-io ---- ·.2000E-Ol .lS42E;l"lf -~4500E+OO o; --------- 0 0 --------- ----- 97 38 19 .?OOOE-01 .1S42E-10 .4SOOE•OO o. 0 0

------- 9A 39 19 ----- .zoooE-01 .l542E-10 .4500E•OO 0.------- o·· 0 --------- 99 15 43 .6215£•02 o. o. o. ----- 0 0

100 43 44 .6480[+02 o. o. o. -------- 0--. 0 -------101 43 18 .1110E•OO .ll41E-10 .• 6000E-01 O. ----- -- o·- 0

------- 102 18. 44 .1660[•02 o. o. o. ----------- 0 0 -- ------ 103 18 30 .65SOE-02 .62A3E-12 .5~00E-Ol O. -------- o·- 0

---~-- -------·104 18 16 --- .6SSOE-02 .2087E-ll .1Rf>OE•OO Oo ----- -----· 0- 0 ------------105 18 20 ---- .65SOE-02 .27?6E-11 .2430[•00 O. ------ 0 0

lOf, 18 10 .6SSOE-02 .6362£-11 .5670£+00 Oo - ---- 0 0 107 18 -19 --- .65SOE-02 .70f,9£-11 .6300[+00 Oo ------ 0 0

---------101! 18 -20 .1780E-Ol .4330£-11 e1420E•OO O. --------- o·· 0 ---------109 18 16 -- .1780E-01 .4330£-Il .1420E•OO 0. ------- 0 0

llO 18 19 ---- .l7ROE-01 .8903£-Il .2920E+OO O. -------- 0 0

o.-o. o.-o.-o. o. o •. o. o. o. o. o. o.- --------------

-------------

0. ----------------0. o.

, 3 of. 4-.

111 ---18--10- .1780E-01-.80l9E-Il -.2o<,30E•OO O. -------- o··-o 112-""18 ""19 --- .9700[-02 .7477£-11 .4500[•00 o. -- --···--· 0 0 113--- 18 - 10 .9700£-02 .6730[-11 .40SOE•OO O. ----- 0- 0 114---18 ···2o -- .6900E-03 .4787E-12 .4o50E•OO o. --------· o- o

0.--------------------------------

·ns--1s --16 ____ .6900E-o3- .47B7E-12- .4o50E•OO o. ------- o -- o "116 -- 18 -- 17 .?340E-02 .16?3E-11 .4050E•OO o. 0 0

---------117""""18 21 - .2340£-02 .16?3£-11 .4050[+00 o. 0 0 118·- "18 --19 - .3030E-02 .2316E-11 .4t;OOE+OO Oo- -------- 0- 0 119-- 18 --10 -- .3030£-02 .2102E-11 .4050E+OO O. -- 0 0 120 40 45 .21180[+01 o. o. o. 0 0 121 -- 45 --46 .?880[+01 o. o. o. ----- ------ 0 0 122 45 19 .3230E-02 .4703£-12 .esooE-01 o. o o 123- 45 - 10 -- .3230£-oz-· .4703E-12 .8SOOE-01 o. --------- o -- o 124 46 47 - .43?0[+01 o. o. o. - --- - 0 0

---125 47 10 .6470E-02 .9421E-12 .ASOOE-01 0. 0 0 126 47 19 .647oE-o2 .9421E-12 .8soor-o1 o. ------- o o 12 7 4 7 - 4 8 • 8 64 0 E + 0 1 0 • 0 • 0 • --- --- . 0 0 1211 48 10 .1290£-01 .1878E-ll .8500E-01 O. - ·---- 0 0

----------129 411 19 .1290E-01 .1878£-11 .esooE-01 o. -------- o o 130 48 49 .l1?~E•02 O. O. O. ------- 0 - 0

---------131 49 1o .zsGoE-01 .3771£-ll .8c;oo£-01 o. o o 13? 4'l 19 .?5'lOf-01 .3771£"-11 .ac;ooE-01 o. o o

-- 133 46 10 .J230f-02 .4703f-12 .ao:;ooE-01 o. o o ------- 134 46 19 .3230E-02 .<+703f-12 .11<;00E-01 O. -------- 0 0

----------~135 49 50 .THOE+O?O. Oo O. 0 0 ·. - ---- --.---136 '50 10 .51BOE-01 • 754?f-ll .BSOOE-01 D. 0 0 ·• 137 50 19 - .SlAOE-01 • 7542f-11 .A500E-01 O. - 0 0

13A 50 36 .'l'lROf•02 O. O. 0. 0 0

0 0

9 0

------- -1 - -o ------- · -1 -o

-o

1 · ·---;;o. -o.

-o -o. -o -o.

-o -o

FUNCTJON--9 DATA .?OOOE•Ol .1000£•01 .2990£•03-0.

0. o. o. o. o. -o. o. o. o. o. o. 0 ~-o. o. o. o. o. o. o. o. o. o. o. o. o. o. o.

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- --------u--v~----1 oz-~ ~ •-o--lr---o---o---~-----~-

--- ~--

---r- o-----z--o.-- ------o.;--------- -- ~---- -- ------ -----------·---~

~----- ------ 0. ---- -.3000E•O:r··-;J?.OOE•02 -.6DOOF.+02 ;2400E+02- .2500E•02- .4800E+02 --~HOOE+Or ------~-----. 7200EHI2 .l620E+O:J-~9600E•02 - .ZOOOE+OJ - .1200[+03 ---.z270E+03 -.1440E+OJ--~Z420E+ll3----------

------- --- - .1680£+03 .2500£+03 --.1920£+03 - .2490£+03 -;2160£+03 - .2410E+03 -~2400£+03 - .Z230F.+OJ _________ _ .2640[+03 .19~0[•03 .?AA0£+01 .1560f.+03 .3120E+Ol .9800£+02 .3360E+03 .3BOOE•Ol -.3600£+03 -.1900£+03 .3A40E+03 -.2320£+03

-- - ---~- ------ ~ ...;1----··.;.o --~---o o.

z o--~.------o. -o. o. o. - .2950[•02 .1140£•03

---- --- .1180£+03 .3830£•03. ei475E+03 .4270f+03 ---------- -- ~ , - -- .2360[+03 .3830[+03 .2650£+03 .3120E+03

---------------- .3530£+03 o. -.3531£+03 o. ----------;;~-~---o··- ·.;.o - o.

.5900[+02 .2210[+03 - .8850[+02 - .3120[+03

.1770£•03 .4420£+03 ~ .2060£+03 .4270£+03

.2950£+03 .2210[+03 .3240[+03 - .1140£•03

.JA40E+03 O.

--------..--·-u----.----o ~ · -o. -- ------~- ~- - - - ---- -- ~- -- ----;442or+o:r-.2950E•02 -- .4270E•03 ~--.s9oOE•oz- ~ .3830E•o3 - .8850E+02 ---~-:n2or•oJ ------ o.

-- - ~- .ll80E+03 .2210£+03 -- .1475£•03 .ll40F.+03 .1770£+03 o. - .2060[+03·--~~1140[+03 __________ _ .2360£+03 .2210[+03 ---.2650£+03- -- .3120£+03 .2950£+03~ .3830[+03 -- .3240[+03-- .4270£+03 ----------

-r---cr--.a--- o:JSJ0£•03 .4420£+03- .3'531£+03 o. - .3840[+03 o.

r--.----~-o.

------------ ~~---'-- ~a.

---- ------ .2360[+03 --------~----o----o --- o.

-----------~-- ·-o"---.-o ~---o. ~~ -~-----

-o. .9000£-01 --.5900[+02 ~ .1170£+01 .1180£+03 .9800E•00-.2960E+03~- .1180£+01- .3540£+03

---- -- -·----- ~-----~---~- -----------

- ---- -·- ------------------------------------

---- -----· -------------------

-- -- ------ --- --·- - ----- - ------ --- ----

.9800£+00 --.1770£+03 ---~1060E+Ot-·--------

.8950E+OO-

-- ---- -------

------ ~~-- -----------

--- ---- - -------

- ----·----

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lspe qualification and flight acceptance t/v test summary ... · t/v test summary and thermal...

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