NASA Contractor Report 3328 

NASA-CR-3328 

\ q ~ (; ~ C' .~ ~ C{ C~ ''----------~ 

Environmental Protection Requirements 

for Scout/Shuttle Auxiliary Stages 

G. L. Qualls, S. S. Kress, 

W. W. Storey, and P. N. Ransdell 

CONTRACT NASl·12500 

SEPTEMBER 1980 

NI\SJ\ 

IIBR/~RY GDPY 

SE? 4 9 1'J(50 

LANGLEY RESEARCH CENTER 

LIBRARY. Nll,SA 

HA.\IPTON, VIRGINIA 

-- --

1111111111111 1111 11111 11111 11111 11111 11111111 

NF02121 
NASA Contractor Report 3328 

Environmental Protection Requirements 

for Scout/Shuttle Auxiliary Stages 

G. L. Qualls, S. S. Kress, 

W. W. Storey, and P. N. Ransdell 

Vought Corporatioll 

Dallas, Texas 

Prepared for 

Langley Research Center 

under Contract NASl-12500 

NI\S/\ 

National Aeronautics 

and Space Administration 

Scientific and Technical 

Information Branch 

1980 
FOREWORD 

This study provides recommendations for enabling the Scout upper stages to endure the expected 

temperature, mechanical shock, acoustical and mechanical vibration environments during a specified 

shuttle mission. 

The study effort consisted of the following five tasks: 

(I) Determination of Shuttle-Launched Mission Trajectory 

for a 545 kilogram (1200 pound) payload· 

(II) Compilation of Environmental Conditions in the Shuttle 

(III) Determination of Scout Upper Stages Environments in Space 

Shuttle Launched Missions 

(IV) Compilation of Scout Upper Stages Environmental 

Qualification Criteria and Comparison to Shuttle Mission 

Expected Environments 

(V) Recommendations for Enabling Scout Upper Stages to 

Endure the Expected Shuttle Mission Environments. 

iii 
TABLE OF CONTENTS 

Page 

FOREWORD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . iii 

TABLE OF CONTENTS... .. .. .. .... .. .... .. .. .. .. .... .. .... .. .... .... .. .. .. .. v 

LIST OF FIGURES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. vii 

LIST OF TABLES.... ...............................................•........ ix 

GLOSSARY OF TERMS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . . . . . x 

1.0 SUMMARy............................................................. 1 

2.0 INTRODUCTION........................................................ 5 

3.0 SPACE SHUTTLE PAYLOAD BAY ENVIRONMENTAL CONDITIONS............. 6 

3.1 Pressure Altitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 

3.2 Solar Radiation Earth Albedo. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 

3.3 Meteoroid ....................................................... ··. 8 

3.4 Vibration ................................................... ········ 8 

3.5 Acoustic ..................................................... ·····. 8 

3.6 Mechanical Shock. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 

3.7 Acceleration ...................................................... ·. 10 

3.8 Temperature........................................................ 10 

4.0 MISSION TRAJECTORY DETERMINATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 

5.0 ENVIRONMENTAL PROFILE FOR A SHUTTLE LAUNCHED SCOUT ORBITAL 

MISSION ................ ; ............................................ " 18 

6.0 COMPILATION OF SCOUT UPPER STAGES ENVIRONMENTAL QUALIFICATION CRITERIA AND COMPARISON TO SPACE SHUTTLE MISSION 

EXPECTED ENVI RONMENTS ........................................... " 20 

6.1 Vibration........................................................... 20 

6.2 Mechanical Shock .................................................. " 20 

6.3 Acceleration........................................................ 24 

v 
TABLE OF CONTENTS (Continued) 

Page 

6.4 Acoustic........................................................... 24 

6.5 Meteoroid.......................................................... 25 

6.6 Thermal............................................................ 25 

7.0 RESULTS OF ANALYSES FOR ENABLING SCOUT UPPER STAGES TO ENDURE 

THE EXPECTED SHUTTLE MISSION ENViRONMENTS........................ 29 

7.1 Dynamic Analyses. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ... . . . . . . . . . . . . . . . . .. 30 

7.2 Thermal Analysis. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 35 

8.0 CONCLUSIONS AND RECOMMENDATIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 52 

APPENDIX A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 

REFERENCES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 56 

vi 
LIST OF FIGURES 

Figure No. Title 

1-1 SCOUT UPPER STAGES.... . .. .. .. .. .. .. .. .. .. .. .. .... ........ .... .... . 1 

1-2 SCOUT UPPER STAGES AND PAYLOAD SUPPORT PALLET.................. 3 

3-1 SHUTTLE PAYLOAD BAY RANDOM VIBRATION CHARACTERiSTiCS.......... 8 

3-2 SHUTTLE PAYLOAD BAY ACOUSTIC (LAUNCH) ENVIRONMENT 

CHARACTERISTICS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 

4-1 SHUTTLE LAUNCHED SCOUT MISSION TRAJECTORY PROFILE.............. 16 

6-1 RANDOM VIBRATIONS OF SCOUT QUALIFICATION TESTS AND SPACE 

SHUTTLE PAYLOAD BAy................. .. .... .............. ...... ... 22 

6-2 SCOUT MECHANICAL SHOCK LEVELS (MAXIMUM SHOCK LEVELANTARES MOTOR)..................................... ............... 23 

6-3 ACOUSTICAL ENVIRONMENT CHARACTERISTICS OF SPACE SHUTTLE 

AND PRESENT SCOUT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 24 

6-4 MAXIMUM TEMPERATURE DURING SHUTTLE LAUNCH. . . . . . . . . . . . . . . . . . .. 26 

6-5 MINIMUM TEMPERATURE DURING SPACE SHUTTLE ORBIT. .. .. .. .. .. . .. .. 27 

6-6 MINIMUM TEMPERATURE DURING SCOUT ORBIT. . . . . . . . . . . . . . . . . . . . . . . .. 28 

7-1 SCOUT/SHUTTLE PALLET RESTRAINT SYSTEM.. .. .. .. .. . . .. .. .. .. .. .. ... 32 

7-2 ACCELERATION SPECTRAL DENSITY DUE TO RANDOM VIBRATION INPUT 

SPECTRA ............................................................ 34 

7-3 SUN-TO-VEHICLE ORIENTATION FOR MINIMUM AND MAXIMUM HEATING. .. 35 

7-4 ANTARES AND ALTAIR MOTOR THERMAL MODELS....................... 37 

7-5 UPPER "C" SECTION THERMAL MODEL. .. .. .. .. . . .. .. .. .. .. .. .. .. .. .. . .. 38 

7-6 "0" AND "E" SECTION THERMAL MODELS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 39 

7-7 2·STAGE SCOUT MOTOR CASE TEMPERATURE VS SHUTTLE LAUNCH TIME... 41 

7-8 ANTARES MOTOR NODAL TEMPERATURE VS SHUTTLE ORBIT TIME. . . . . . .. 42 

7-9 ALTAIR BONDLINE (NODE 2) TEMPERATURE VS SHUTTLE ORBIT TIME. .. ... 43 

7-10 ALTAI R PROPELLANT AND BONDLINE TEMPERATURE VS SCOUT ORBIT TIME 44 

7-11 UPPER "c" TEMPERATURE VS SHUTTLE ORBIT TIME.. .. . . .. .. .. .. .. .. ... 45 

7-12 ANTARES NOZZLE AND SHROUD TEMPERATURE VS SCOUT ORBIT TIME.. .. 46 

vii 
LIST OF FIGURES (Continued) 

Figure No. Title 

7-13 UPPER "c" TEMPERATURE VS SCOUT ORBIT TIME-MAXIMUM 

HEATING ORBIT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 47 

7-14 UPPER "c" TEMPERATURE VS SCOUT ORBIT TIME-MINIMUM 

HEATING ORBIT. . . . . . . . . . . . . . . . . . • . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . . . .. 48 

7-15 "0" AND "E" SECTION TEMPERATURE VS SCOUT ORBIT TIMEMAXIMUM HEATING ORBIT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 49 

7-16 "0" AND "E" SECTION TEMPERATURE VS SCOUT ORBIT TIMEMINIMUM HEATING ORBIT.. .... .... . ... .. ...• .... .. .. .. .. .. .. .... ..... 50 

8-1 SPECTRUM TO BE USED IN SCOUT ACOUSTICAL TESTS. . . . . . . . . . . . . . . . . . .. 53 

viii 
LIST OF TABLES 

Table No. Title 

1-1 EQUIPMENT EVALUATED IN THE ENVIRONMENTAL PROTECTIONSCOUT/SHUTTLE AUXILIARY STAGES STUDY. . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 

2-1 STUDY TASKS. . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . 5 

3-1 ENVIRONMENTAL PROFILE FOR SHUTTLE PAYLOAD (CARGO) BAY... .. .. . 7 

3-11 PAYLOAD BAY WALL THERMAL ENViRONMENT.......................... 10 

4-1 SCOUT UPPER STAGES WEIGHT SUMMARY.. .............. ............... 12 

4-11 DEPLOYMENT TRAJECTORY STATE.. .. .... .. .. .. .. .. .. .... .. .. .. .. .. ... 15 

4-111 TRAJECTORY PARAMETERS AT EVENT TIMES.. .. .. .. .. .. .. .. .. .. ... . .•• 17 

5-1 SEQUENCE OF EVENTS-NOMINAL TRAJECTORY. . . . . . . . . . . . . . . . . . . . . . . .. 18 

5-11 ENVIRONMENTAL PROFILE FOR A SHUTTLE LAUNCHED SCOUT MISSION... 19 

6-1 LIST OF SCOUT EQUIPMENT FOR ENVIRONMENT COMPARISON AND SUMMARY 

OF ENVIRONMENTAL TESTING PERFORMED............................. 21 

6-11 TEMPERATURE RAN(3ES FOR PRESENT SCOUT COMPONENTS AND ROCKET 

MOTORS ............................................................ 29 

7-1 SCOUT/SHUTTLE PALLET COORDINATES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 31 

7-11 SCOUT/SHUTTLE PALLET CANTILEVERED MODAL FREQUENCIES. .. ... .... 32 

7-111 SCOUT/SHUTTLE PALLET DYNAMICS RESPONSE LOADS.... .. .. .. ... ... ... 33 

7-IV SCOUT UPPER STATES MATERIALS AND PROPERTIES. . . . . . . . . . . . . . . . . . . .. 40 

7-V SUMMARY OF THERMAL ANALYSES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 51 

ix 
GLOSSARY OF TERMS 

ABBREVIATIONS 

PSD Power spectral density (expressed in g2 per Hertz) 

CrH Thermal capacity 

Cp Specific heat 

t Thickness 

RMS Root mean square 

dB Decibel 

BTU British thermal unit 

V Velocity 

fps feet per second 

m meter 

kg kilogram 

°c degrees Celsius 

of degrees Fahrenheit 

TIM telemetry 

K Conductivity 

RCS Reaction control system 

N2 Nitrogen gas 

EMI Electromagnetic interference 

N/m2 Newtons per square meter 

SYMBOLS 

as Solar absorptance 

€ Emittance 

p Material density 

~ V Small change in velocity 

'Y Path angle 

ifJ Inclination angle 

NOMENCLATURE 

Scout upper stages - The Scout third and fourth stage motors and associated interstages. 

x 
1.0 SUMMARY 

This study used a typical trajectory whose derivation was based upon the Scout upper stages, 

Figure 1-1, launching a 545 kilogram (1200 pound) payload from the Space Shuttle. Deployment of 

the Scout upper stages and the payload occurred from a typical 296 kilometer (160 nautical mile) 

circular orbit for the Space Shuttle. For the Scout upper stages trajectory, a maximum altitude, 

Hohmann transfer type mission was used. The environmental conditions encountered during this 

mission and the conditions resulting from an abort situation, i.e., re-entry and landing, were 

identified. These conditions and their effects upon the equipment listed in Table 1-1 were evaluated. 

Thermal and dynamic analyses were conducted to determine the effects on the Scout upper 

stages during Shuttle buildup, launch and orbit conditions. Similar analyses were conducted for the 

periods of upper stage deployment, burn and coast phases of operation. 

The thermal analysis defines the thermal protection requirements for the Scout auxiliary stages 

for the total mission duration, including the twenty-four hour on-station orbit with the Space Shuttle 

payload bay doors open. This analysis resulted in two recommendations; (1) add thermal protective 

coatings and (2) maintain the pre-launch temperature of the Space Shuttle payload bay between 100 

to 320 C (500 to 900 F) to assure that the temperature of the Antares motor is within its specified 

ignition temperature limits. 

Upper C 

section 

3rd stage 

Antares motor 

(30" dia) Lower D 

section 

4th stage 

FIGURE 1-1.- SCOUT UPPER STAGES 

Payload 
TABLE 1-1.- EQUIPMENT EVALUATED IN THE ENVIRONMENTAL PROTECTION -

SCOUT/SHUTTLE AUXILIARY STAGES STUDY 

Vehicle transition sections: 

C section 

D section 

E section 

Rocket motors: 

* Altair IliA 

* Antares liB 

Components: 

Guidance & Control 

Instrumentation 

Reaction control 

Poppet valve electronics 

Rate gyro unit 

Inertial reference unit 

Yardney battery pack 

Fourth stage T/M transmitter 

Thruster valves [267 newtons and 8.9 

newtons (60 pound and 2 pound motors)] 

Relief valve (H202) 

Quick disconnects (regulated N2) 

Hydrogen peroxide tanks 

Pressure regulator 

* Referred to as Altair or Antares in the text for brevity. 

The dynamic analysis used the baseline pallet design described in Reference 1 and shown in 

Figure 1-2. The analysis was performed taking into account mechanical shock, mechanical vibration 

and acoustical vibration. The mechanical shock and vibration analysis resulted in determination of 

vibrational modes of the Scout/pallet system and the maximum vibrational and shock loads on the 

Scout induced by the Space Shuttle. F rom these, the recommendations that (1) the E Section be 

redesigned to withstand the Space Shuttle induced loads, (2) no vibration isolators be used between 

the Space Shuttle sill supports and the pallet or between the pallet and the Scout, and (3) the Scout 

Standard Environmental Test vibration spectrum be extended to include the 10 to 20 Hertz region, 

were made. The Scout environmental qualification criteria do not include an acoustical vibration test. 

Consequently, it is recommended that the Shuttle payload bay acoustical levels, modified by an 

appropriate safety factor, be established as a qualification test for Scout upper stages to be launched 

from the Shuttle. 

2 
w 

- - --- --

_____ 

-

--

-------- -:::::-::::: "-

u • --

- -- -

"II' ".-" I / / / """" , 

,Ii r l : __ ' -I - (1l 

t1fl::::: --- ---T-- - 'L _ ,jl I I I I I \ __ ,/' 'I : I ,", _ L ' I · "J -p-- " --I 

___ ' I' 

___ 

" -c-: _ J ,,'--- / 

; I --' --- ,," _ _ 'I' / / Jl ,- 1- I / // '/ / .. " --.j' / - -.:..-.:.- -',,' --= -

---

----

Spacecraft 

Hold down clamp 

Two stage scout 

launch vehicle 

J; ,----- ----I tl:" ------ I J; A / Longeron p

_-{v;o=410 

U"tJU- 400 

If= 

\ -.....-- g 

Support pallet 

FIGURE 1-2.- SCOUT UPPER STAGES AND PAYLOAD SUPPORT PALLET 
J:o. 

eyo,I// 94/ 7 

/ ('-0' Ie.. 305 

Support pallet 

SECT. A-A 

---, 

Ajustable spacecraft 

hold down arm 

Electro/mechanical 

or pneumatic actuator 

Hold down clamp 

15 Ft (4.S7M) dia· 

payload envelope 

Typical hold down clamp & bulkhead arrangement 

I 

,..,..--.. down 

/

,. '. In open 

, , pOSi

SECT. B-B 

Typical spacecraft 

cradle & hold down 

Support pallet 

( 

<r 

Spacec

Yo 

(94) T Zo 

(414) 

Crossbea

FIGURE '·2.-SCOUT UPPER STAGES AND PAYLOAD SUPPORT PALLET (Continued) 
2.0 INTRODUCTION 

The potential utilization of the Scout third and fourth stage motors and associated interstage 

sections as auxiliary stages for Space Shuttle applications will expose the Scout to environmental 

conditions not previously encountered. Thermal conditions in space will be more severe because of 

(1) potentially longer coast times between stage burns and (2) space orientation of the Shuttle with 

the payload bay doors opened and closed, and with the payload bay oriented toward or away from the 

sun. New mechanical dynamic and thermal environments will also be encountered by the Scout 

stages during launch of the Shuttle and, in the event of a mission abort, when the Shuttle may return 

to Earth with the Scout stages still in the payload bay. 

At the start of this study, the Scout F-l, with the Antares liB motor as the third stage, was one 

of the Scout standard configurations. Subsequently, the Antares liB motor was deleted, resulting in a 

slight decrease in vehicle performance. The effect of this reduction on the environmental conditions 

determined in the study, is negligible and the recommendations are valid for Scout upper stages using 

the Antares IIA motor. 

This study was accomplished under a series of five tasks, Table 2-1. The study guidelines are 

described in the following paragraphs. 

Task I 

Task" 

Task "I 

Task IV 

Task V 

TABLE 2-1.- STUDY TASKS 

Determination of Shuttle-Launched Mission Trajectory 

Compilation of Environmental Conditions in the Shuttle 

Determination of Scout Environments in Shuttle Launched 

Missions 

Compilation of Scout Upper Stages Environmental Qualification 

Criteria and Comparison to Shuttle Mission Expected Environments 

Recommendations for Enabling Scout Upper Stages to Endure 

the Expected Shuttle Mission Environments 

The two upper stages (less the heatshield) of Scout were used as configured by the Scout Phase 

VII procurement. The interface between the Scout upper stages and the Shuttle payload bay was taken 

as the baseline pallet design, Figure 1-2. 

The Shuttle payload bay worst case environmental characteristics were summarized from the 

Shuttle payload accomodations document, Reference 2. The conditions of normal launch along with 

abort conditions of re-entry, landing and crash were taken into consideration. 

A trajectory analysis was performed to develop a mission timeline as the basis for predicting the 

environmental conditions encountered by the Scout after launch from the Shuttle. The developed 

trajectory produces an orbit with an apogee of 15,726 kilometers (8,492 nautical miles), a perigee of 

10,522 kilometers (5,682 nautical miles), and an inclination of 28.5 degrees with a 545 kilogram 

(1200 pound) payload based on operating from the Shuttle in a circular orbit of 296 kilometers 

(160 nautical miles) at 28.5 degrees inclination. This trajectory provides approximately 2.4 hours 

coast time between Antares burnout and Altair ignition. 

5 
Subsequent to the identification of the Shuttle environmentally induced characteristics upon 

the Scout upper stages, and the establishment of a nominal trajectory, an environmental profile was 

developed for the Scout upper stages. This profile began with the Shuttle payload bay doors open 

and the Shuttle starting an on-orbit phase of twenty-four hours. The on-orbit phase was followed by 

Scout/Spacecraft check-out and countdown. The nominal mission trajectory began at this point with 

Scout deployment and separation from the Shuttle. The environmental conditions associated with the 

total mission timeline, the twenty-four hour on-orbit phase with the Scout exposed in the Shuttle, and 

the Scout mission from deployment through the spacecraft separation are presented in Section 5. All 

pertinent environmental conditions were reviewed and those considered significant were identified 

and evaluated with the exception of EMI which is awaiting definition in Reference 2, paragraph 

4.2.2.8. A preliminary analysis of potential micrometeoroid damage was performed. The analysis 

used the meteoroid environment model given in Reference 3 and was performed only upon the two 

rocket motor cases. This damage probability to the two-motor subsystem was assessed at .0036 

(99.64% probability of no damage). 

After the significant environments were established for the Shuttle launched mission, the land 

launched Scout mission environments were compiled and a comparison made between the two missions. 

Incompatibilities exist in the thermal, mechanical shock, vibration and acoustic environments and are 

discussed in Section 6. Results of the analyses concerning pre-launch restrictions, thermal insulation, 

"E" section redesign and design verification testing to overcome the incompatibilities are presented 

in Section 7. Section 8 presents the conclusions derived from the analyses and recommendations for 

enabling the Scout upper stages to endure the environment of a Shuttle launched mission. Appendix A 

defines changes in the predicted Shuttle environmental conditions, compiled from Reference 2, which 

have occurred since completion of the effort associated with Section 3. 

3.0 PREDICTED SPACE SHUTTLE PAYLOAD BAY ENVIRONMENTAL CONDITIONS 

Reference 2 was reviewed and analyzed to determine the most severe environmental conditions 

in the Shuttle payload bay. A profile of these conditions, Table 3-1, is provided for the Shuttle launch, 

on-orbit, Scout deployment, and re-entry and landing (abort) mission phases. A twenty-four hour 

Shuttle on-orbit time with the payload doors open was assumed to provide deep-space soak conditions 

and is covered in a subsequent profile, Table 5-11. The applicable environmental levels are described in 

the following paragraphs. 

3.1 Pressure/Altitude 

(Reference 2, para. 4.2.2.1) 

The pressure/altitude environment affects the mission flight phases of launch, on-orbit, Scout 

deployment, and re-entry and landing (abort). The launch pressure will be local ambient. The payload bay is vented during boost to the desired 296 kilometer (160 nautical mile) orbit and depressurizes in 120 seconds to 0.02 millimeters of mercury. The pressure remains at space vacuum unless 

an abort situation is encountered. When this occurs, the pressure during re-entry and landing increases 

from space vacuum to local ambient in 350 seconds. These pressures and variations are within the 

ranges encountered in a typical Scout land launched mission and present no problem for the Scout 

upper stages in a Shuttle launched mission. 

6 
TABLE 3-1_- ENVIRONMENTAL PROFILE FOR SHUTTLE PAYLOAD (CARGO) BAY 

Space shuttle mission phase 

Environment Shuttle On-orbit station Scout deployment 

launch (doors closed) (doors open) 

Natural: 

• Pressure (vacuum) X X X 

• Solar radiation 0 0 X 

• Earth albedo 0 0 X 

• Earth radiation 0 0 X 

• Space sink temperature 0 0 X 

• Meteoroids 0 0 X 

Induced: 

• Vibration X <P <P 

• Acoustic X 0 0 

• Mechanical shock <P 0 <P 

• Acceleration X X <P 

• EMI X X X 

• Temperature X X X 

• Zero "g" 0 X X 

Legend: 

X - Applicable environment 

<P - Applicable environment - negligible effect 

o - Not applicable 

3.2 Solar Radiation, Earth Albedo 

(Reference 2, para. 4.1.2.2) 

Re-entry and 

landing (abort) 

X 

0 

0 

0 

0 

0 

X 

<P 

X 

X 

X 

X 

0 

Solar radiation, Earth albedo, Earth radiation, and space sink temperatures are applicable during 

the Scout deployment phase. The effects of these were evaluated starting with initial conditions 

created by prelaunch ground environmental controls. The ambient payload bay temperature will be 

between 4 and 490 C (40 and 1200 F) as determined by the setting of the Shuttle cargo bay environmental control system. During boost the temperature will rise to between 4 and 650 C (40 and 1500 F). 

Upon opening of the payload bay doors and starting with this temperature range as the initial temperature, the heat load will be affected by: 

Solar radiation @ 1399 watts per square meter (444 BTU/ft2hr) 

Earth albedo of 30% 

Earth radiation @ 243 watts per square meter (77 BTU/ft2hr) 

Space sink temperature of O· Kelvin (00 Rankine) 

This heat load will be incident upon the Scout upper stages depending upon Shuttle (orientation) 

attitude. 

7 
3.3 Meteoroid 

(Reference 2, para. 4.1.2.4) 

The meteoroid environment becomes significant after the Scout upper stages are deployed from 

the Shuttle and is discussed in Section 6.5. 

3.4 Vibration 

(Reference 2, para. 4.2.2.2) 

The vibration environment affects the mission phases of launch, re-entry and landing, (abort), 

and aborted mode handling. The re-entry and landing vibration levels will be less than for the launch 

phase. Duration of the launch random vibration, Figure 3-1, is expected to be approximately 28 

seconds per mission and exists at the Shuttle sill attach points. . 

After the landing (normal or abort), the Space Shuttle must be towed to the refurbishment area. 

Towing presents different loads than other phases of operation which is to be simulated by four 

sinusoidal sweeps at one half octave per minute a~ the levels and frequencies of: 

2-5Hz, 2.54 em (1 inch) double amplitude 

5-26 Hz, 1.3 g peak 

26-50 Hz, .09 em (.036 inch) double amplitude 

50-100 Hz, 5 g peak 

.1 Ascent 

8.4 sec/mission 

\--

Liftoff 

20 sec/mission 

/ 

.01~--~--~~~~~~----~--~~~~~LL __ ~ 

10 20 50 100 200 500 1,000 

Frequency, Hz 

FIGURE 3-1 .. -SPACE SHUTTLE PAYLOAD BAY RANDOM VIBRATION CHARACTERISTICS 

3.5 Acoustic 

(Reference 2, para. 4.2.2.3) 

An acoustic environment occurs in the payload bay during the launch and re-entry (abort) 

mission phases, Figure 3-2. The re-entry levels are considered negligible in comparison to the launch 

phase levels. The 1/3 octave band sound pressure level peaks at an approximate amplitude of 135 dB 

8 
at 300 Hz over a broad band spectrum of 20 to 10,000 Hz. A transient maximum of approximately 

145 dB occurs during the thrust build·up and lift-off for about 15 seconds. Another maximum of 

approximately 140 dB occurs at about 50 seconds. 

3.6 Mechanical Shock 

(Reference 2, para. 4.2.1.3) 

The mechanical shock environment is most severe in the aborted mode handling. The requirement is for a 20 g terminal sawtooth pulse of 11 millisecond duration. One shock is required in 

each direction of each of the three orthogonal axes. 

N 150 ~-------------------------------------------- E 145 dB Overall 

-

z 

-g c3- 140 

::sN 

~ 1!:! 

"C ' 

~!g 130 

..c _' 

~ ~ >~ 

~ 1!:! 120 u ::s O~ _ (YlQ) .... 

..- 0. 1 00 r..-........ Ioo.L.o .............. ...u._~ ........ -'-,&...L.....&....II....I..lL..L.L_-'--.&......JL...L.."-'-...I....I~u.I 

Q) 

5C" 

~ E 

Q)-

.... z 

0.::1-

"CO 

.c N 

::s 1!:! 

o , 

cnm 

= "C E _' Q) Q) 

> > 

O~ 

2 3 4 6 8 1 02 2 3 4 6 8 103 2 3 4 6 8 104 

Frequency, Hertz 

150~---------------------------------------

140 

130 

120 

110 

100 ~~~ __ ~ __ ~ __ ~ ____ ~ __ ~ __ ~ __ -L_~ __ ~ 

-10 o 10 20 30 40 50 60 70 80 90 

Time, seconds 

FIGURE 3-2.- SHUTTLE PAYLOAD BAY ACOUSTIC (LAUNCH) 

ENVIRONMENT CHARACTERISTICS 

9 
3.7 Acceleration 

(Reference 2, para. 7.6) 

The environment of zero "g" exists during the on-orbit Scout deployment mission phase with 

the only on-orbit accelerations being those induced by the Space Shuttle reaction control system. 

The aborted mode crash acceleration environment provides steady state levels of + 9.0 g and - 3.3 g 

in the (X) longitudinal axis, ± 1.5 g in the (V) lateral axis, and + 4.5 g and - 2.0 g in the (Z) vertical 

axis. The X, V, and Z coordinate system and sign convention follows that of the Shuttle. These are 

short duration accelerations; in the order of less than a second. 

3.8 Temperature 

(Reference 2, para. 4.2.2.7.1) 

The maximum and minimum temperatures and heat fluxes are presented in Table 3-11 for the 

various mission segments. 

TABLE 3-11.- PAYLOAD BAY WALL THERMAL ENVIRONMENT 

Mission flight phase Payload bay wall thermal environment 

Parameter Design minimum Design maximum 

Prelaunch Temperature, 0c (OF) +4 (+40) +49 (+120) 

Launch Temperature,oC (OF) +4 (+40) +65 (+150) 

On-orbit Total bay heat flux, ~ 9.45 (Loss) ~ 0 (Gain) 

(door closed) Average watts per meter2 (~3 (Loss) 

(BTU/tt2 hr) 

Heat flux, local area, ~ 12.51 (Loss) ~ 9.45 (Gain) 

watts per meter2 (~ 4 (Loss) (~3 (Gain) ) 

(BTU/tt2 hr) 

On-orbit (doors Temperature,oC (OF) -182 (-296) +98 (+209) 

open, empty payload bay) 

Absorbed heat flux, 0 232 (+74) 

watts per meter2 (Tail to sun) (Top to sun) 

(BTU/tt2 hr) 

Abort: 

Entry and post Temperature, °c (OF) -73 (-100) 93 (+200) 

landing 

10 
4.0 MISSION TRAJECTORY DETERMINATION 

The design trajectory selected for this study was based on the following: 

(a) Stages used were the Antares and Altair. 

(b) Payload weight of 545 kilograms (1200 pounds) 

(c) Shuttle parking orbit of 296 kilometers (160 nautical miles) circular, inclination of 28.5 

degrees 

(d) Spacecraft final orbit to be the maximum average apogee-perigee achievable consistent with 

items (a) through (c). 

The weights break-down for the Scout upper stages, modified for the Shuttle launched mission, is 

presented in Table 4-1. The Scout F-1 weights, shown for comparison purposes, are from Vought 

Corporation Report No. 2-53492/4R-23000, "Scout Vehicle S-193 and Sub. Weight Report" dated 

31 January 1974~ 

After orbital injection, the Shuttle will be orbiting the Earth in any of several modes, i.e., 

rotisserie mode, fixed orientation to Earth, fixed orientation to Sun, etc., while it is performing its 

routine functions. However, when preparing to deploy a launch vehicle, the Shuttle must be reoriented so that the vehicle will be in the proper orientation to enter its mission. For the Scout upper 

stages, the required orientation would be such that it will be deployed at an angle of 135 degrees 

relative to the Shuttle velocity vector as shown in Table 4-11 and the inset of Figure 4-1. None of 

the published information for the Shuttle defines the required separation distance to ensure Shuttle 

safety at rocket motor ignition of the launch vehicle. The required separation will be a function of 

rocket motor size and was beyond the scope of this study. However, in a previous study, Reference 1, 

a nominal separation of 1.85 kilometers (1 nautical mile) was established as a safe separation and was 

used in this study. Using the above deployment angle and separation distance, and a deployment 

velocity of 1.5 meters per second (5 feet per second), the deployment trajectory, Table 4-11, will 

place the Scout upper stages approximately 1.85 kilometers (1 nautical mile) below (toward Earth) 

and 0.74 kilometer (0.4 nautical mile) ahead of the Shuttle in 950 seconds and the Antares motor 

can be fired to boost the upper stages into the transfer orbit, Figure 4-1. The upper stages are then 

reoriented through 180 degrees for Altair firing. Following a coast of 2.37 hours, the upper stages 

will be at apogee of the transfer orbit and the Altair is fired to place the payload in the final orbit. 

Trajectory parameters and separation distances are presented in Table 4-111. 

11 
TABLE 4-1.- SCOUT UPPER STAGES WEIGHT SUMMARY 

Baseline 

Scout study 

F-l stages 

Item description 

Altair stage burnout [92.84] [119.34] 

Motor and hardware (79.57) (79.57) 

Pressure transducer .36 .36 

Motor inert 55.42 55.42 

Ignition harness .88 .88 

Tape - installation ignition harness .52 .52 

TM ring module (TIM & IGN) 20.39 20.39 

Dynamic balance weight 2.00 2.00 

Upper D (13.27) (13.27) 

Hardware upper D to motor .18 .18 

Upper D structural and harness 13.09 13.09 

Change to basic Scout (26.50) 

Altair ring mod. - component insul. .60 

Ring mod TIM package 5.65 

Spacecraft adapter 20.00 

Attach hardware - PIL to motor .25 

Antares stage burnout [763.14] [804.33] 

Lower D spin items (39.36) (39.36) 

Spin table struc. & compo 24.79 24.79 

Explosive bolts .53 .53 

Spin motors (4-1 KS 75) 4.50 4.50 

Inner bearing race 9.54 9.54 

Lower D (21~.24) (219.24) 

Ring & hdw. - spin to lower D 6.20 6.20 

Outer bearing race 11.97 11.97 

Lower D & components 179.39 179.39 

I RP installation & hardware 20.79 20.79 

Tunnel covers and hardware 0.54 0.54 

Hardware (lower D to motor) 0.35 0.35 

12 
TABLE 4-1.- SCOUT UPPER STAGES WEIGHT SUMMARY (Continued) 

Baseline 

Scout study 

F-l stages 

Change to basic Scout - lower D (2.95) (35.9B) 

Guidance battery (28V) 15.18 

Guidance battery (37V) 7.71 

TM battery 1.18 

Radar beacon battery 4.51 

TIM package & encoder 1.50 

Brackets & instal. Irge. batt. 5.90 

Electrolyte 2.95 

Motor section (259.51 ) (259.51 ) 

Antares motor inert 223.10 223.10 

Fillet .35 .35 

Headcap transducer .48 .48 

Nozzie tape .70 .70 

Dome tape .32 .32 

Motor tunnel and hdw. - TM 4.06 4.06 

Motor tunnel & hdw. - guid. 4.07 4.07 

Tunnel harness & hdw. - TM 6.07- 6.07 

Tunnel harness & hdw. - guid. 10.76 10.76 

Nozzle shroud & hdw. 9.60 9.60 

Changes to basic Scout motor sect. ( 1.12) (13.87) 

Reflective tape 2.98 

Cork (0.25") 10.89 

Destruct charge and hdw. 1.12 

Upper C (208.80) (208.80) 

Hardware upper C to motor .86 .86 

Upper C and components 192.73 192.73 

Balance weight - 00 3.65 3.65 

Balance weight - 3150 2.90 2,90 

N2 remaining 1.00 1,00 

Tunnel covers & hdw. 7.66 7.66 

13 
TABLE 4-1.- SCOUT UPPER STAGES WEIGHT SUMMARY (Concluded) 

Baseline 

Scout study 

F-l stages 

Changes to basic Scout upper C (32.16) (27.57) 

Destruct system 17.96 

H20 2 tank bladder material change .80 

H20 2 tank 3.80 

H20 2 brackets & tubes 3.00 

Relay box & brackets 3.00 

H20 2 tank and nozzle insulation .50 

H20 2 remaining 14.20 16.47 

Weight Summary 

Altair burnout 92.84 119.34 

Altair consumed 608.26 608.26 

Altair ignition 701.10 727.60 

Spin-up weight 740.46 766.96 

Antares burnout 1,464.24 1,531.93 

Antares consu med 2,581.24 2,581.24 

H202 consumed 4.30 5.53 

Antares ignition 4,049.78 4,118.70 

14 
TABLE 4-11.- DEPLOYMENT TRAJECTORY STATE 

Space Shuttle 

Orbit: Altitude = 296 km (160 n.mi.) circular 

Inclination = 28.5 degrees; Period = 90.445 min 

Altitude 

296 km 

(160 n.mi.) 

Auxiliary stages 

Deployment maneuver 

I:l.V = 1.52 m/sec (5 fps) 

Orbit after deployment 

Velocity (V 0) 

7.73 km/sec 

(25354.04 fps) 

I/J = -135 degrees 

Path angle h g) 

o degrees 

Perigee = 292 km (157.9 n.mi.) 

Inclination = 28.5 degrees 

Apogee = 296 km (160 n.mi.) 

Period = 90.445 min 

Trajectory state 

Altitude Velocity (V 11 Path angle hl1 

196 km 7.73 km/sec -0.008 degrees 

(160 n.mi.) (25350.5 fps) 

Vehicle attitude 

Latitude Longitude Roll Pitch 

26.00 degrees 80.77 degrees o degrees -62.4 degrees 

Azimuth 

102.103 degrees 

Yaw 

101.5 degrees 

Note: (1) All altitudes based on equatorial earth radius of 6378.17 km (3443.934 n.mi.) 

(2) Latitude and longitude assumed, azimuth calculated based on latitude and 

inclination. 

15 
16 

°0 c 

\ 

Shuttle orientation 

during 24-hour orbit 

Shuttle orbit (::JeD 160 n.mi. 28.50 incl. -...... ',1 ~ 90 \ \ II 

Shuttle 9' Qc.1;// orientation c:::' I 

\ for deployment 0 

~ / 

CD 

<D 

o 

~ Altair Antares ,/' 

~-.......I / ~/ [-B---

°0 

Predeployment checkout, T - 7260 sec 

Orient Shuttle to deployment attitude 

Deploy upper stages, T -60 sec 

Antares burn 

293 x 15,792 km (158 x 8,527 n.mi.) orbit, T + 950 sec 

Reorientation maneuver, T + 979 sec 

Antares separation/Altair burn 

10,522 x 15,726 km (5,682 x 8,492 n.mi.) orbit, T + 9,525 sec 

CD Spacecraft/Altair in orbit, T + 9,824 sec 

Altair separation 

Coast time = 2.37 hr 

between CD and CD 

FIGURE 4-1.- SHUTTLE LAUNCHED SCOUT MISSION TRAJECTORY PROFI LE 
TABLE 4-111.- TRAJECTORY PARAMETERS AT EVENT TIMES 

, 

Time Altitude* Velocity Path angle Azimuth Apogee/perigee 

sec Event km n.mi. km/sec (fsp) degree degree km n.mi. 

0 Deploy 296 ( 160) 7.73 (25350.5) -0.008 121.500 296/292 (160/158) 

950 Antares ignition 289 ( 156) 7.74 (25375.01 -0.059 118.482 307/289 (116;156) 

978 Antares burnout 292 ( 158) 9.59 (31446.9) 0.370 118.601 15,790/292 (8527/158) 

5220 Coast midpoint 11,467 (6,192) 4.12 (13515.4) 29.598 67.288 15,726/293 (8492/159) 

9525 Altair ignition 15,726 (8,492) 2.89 (9488.1) 0.252 61.427 15,725/296 (8491/160) 

9559 Altair burnout 15,726 (8,492) 3.95 (12969.3) 0 61.330 15,725/10,522 (8492/5682) 

*Altitude based on equatorial radius of 6377.65 km (3443.934 n.mi.l 

Separation 

Time Horizontal Vertical Total 

sec Event km n.mi. km n.mi. km n.mi. 

0 Start deployment 0 (0) 0 0 0 

0 Clear shuttle bay 0 (0) .002 (-0.001) .002 (0.001) 

950.0 Antares ignition +.78 (+0.419) -1.849 (-0.998) 2.000 (1.0811 

978.9 Antares burnout +28.95 (+15.634) -1.367 (-0.738) 28.985 (15.652) 

17 
5.0 ENVIRONMENTAL PROFILE FOR A SHUTTLE LAUNCHED 

SCOUT ORBITAL MISSION 

The trajectory analysis mission times of Section 3.0 and typical Scout event times were combined 

to form a detail mission timeline for the Shuttle launch"ed mission, Table 5-1. A profile of environmental levels, expected durations, and mission phases for this mission is presented in Table 5-2. 

TABLE 5-1.- SEQUENCE OF EVENTS-NOMINAL TRAJECTORY 

Relative time ~t 

(seconds) (sec) Mission event 

(Assume a Shuttle on-orbit time of 24 

hours before initiation of Scout mission.) 

-7260 6300 Start Scout/spacecraft checkout and countdown. 

- 960 900 Scout terminal countdown 

- 60 60 I nitiate Scout deployment and separation. 

00 10 Separation from Orbiter 

10 Activate RCS 

940 Coast 

950 29 Antares ignition and burn 

979 8540 Close dead band and coast 

9519 1 Spin motor ignition 

9520 2 Altair/spacecraft separation from Antares 

9522 3 Retro Antares 

9525 34 Altair ignition and burn 

9559 265 Minimum time to P/L separation 

9824 Separate P/L 

18 
.... 

<0 

TABLE 5-11.- ENVIRONMENTAL PROFILE FOR A SHUTTLE LAUNCHED SCOUT MISSION 

Time line 

Shuttle on-orbit 

phase for T - 24 hours 

doors open 

Environment 

Pressure 

... (vacuum) .... 

Solar radiation .... 

... 

Earth albedo .... 

Earth radiation 

.... 

P/L Bay 

.... temperature .... 

Zero "9" 

... 

Meteoroid 

Vibration .... 

Mechanical .... .... 

shock 

Acceleration ... 

Scout/spacecraf 

deployment and 

separation 

IJ 

..$'!. q- ...,'I)./! Jl 

'Ii:iS 'Ii cia' # 

/ I 

Scout/spacecraft 

deployment and 

separation from Coast 

orbiter T - 1 min. 

.f:c-

/ 

Antares Burn 

Jl 

tf;- ... 

/ 

Coast 

Q .. 

;: ",'" '" 

o '" 

.... e:$' ",Q.$i' .:Jt$ 

..,-Slo 

q ... 

/ / /" / 

U 

Coast Altair Burn 

Deep space vacuum; use 13 x 10-9 newtons/meter2 (1 x 10-10 torr) for design considerations 

Exposed to 1399 watt/meter2 (444 btu/ft2/hr) on the side facing the sun 

Use 30% for spectrum areas of concern 

I 

Exposed to 243 watt/meter2 (77 btu/ft2/hr) on the side facing the earth 

-lS20C design mlnlmuL, 9SoC for design 

Gravitational field Is negligible; use zero "g" for design consideration 

An analysis was performed using the meteoroid environment model of Reference 3. 

Results of the analysis yielded a probability of survival of 0.9964. The analysis was 

performed on only the two un Insulated rocket motors (Antares and Altair) • 

None Negligible Less than 0.3 Negligible None Less than 0.3 

control grms random - control grms random - motor no discrete motor no discrete 

firings firings 

None ... Less than None Less than -. ±60 g. ±60 g. 

",01 

q 

/ 

N

N

Negligible .. Thrust aceel. None S.S rad/mln (1.40) rpm Impart

vehicle above" 0" section spin 

of 6.9 g Ing (4th stage and payload), 0 

<159 

Thrust accel. of 4.5 II 

EMI To be provided as stated by JSC 07700 Vol. IV Rev. 0 .... Negligible I J 

Temperature 

Notes: (1) 

(2) (3) 

Thermal considerations, In addition to environment temperature, account for (1) electrical power dissipa

(2) RCS valve temperature dissipation, and (3) rocket motor nozzle heat radiation. These occur In local

areas and will be treated at the Individual transition section and/or component level. 

I 

Vibration and mechanical shock levels are enveloped 

for the aft and forward motor shoulders. 

Temperatures given are for the surface of the vehicle. 

Unless otherwise noted time Is In seconds. 

I 
6.0 COMPILATION OF SCOUT UPPER STAGES ENVIRONMENTAL 

QUALIFICATION CRITERIA AND COMPARISON TO SPACE 

SHUTTLE MISSION EXPECTED ENVIRONMENTS 

A comparison of the Shuttle launched Scout upper stages mission environment to the present 

Scout mission environmental qualification requirements was performed to identify their incompatibilities. Recommendations for resolving these incompatibilities are presented in Section 8.0. 

The environments were grouped into the three categories of dynamics, meteoroid, and thermal 

and are discussed in the following paragraphs. These data also include the environmental testing that 

has been performed on the Scout components and is included in summary formin Table 6-1. 

A comparison of the differences between Scout qualification test levels and Scout/Shuttle 

expected levels is contained in the following sub-sections. 

6.1 Vibration 

The Scout upper stages, during transportation in the Shuttle, will encounter different random 

vibration spectra than are used in the Scout qualification tests, Figure 6-1. The Shuttle spectra, with 

a total duration of 28.4 seconds, exist at the payload bay sill support points and are transmitted to 

the Scout upper stages through the support pallet, Figure 1-2. 

Sinusoidal vibration tests were made early in the Scout program. However, analysis of flight data 

indicated that all vibration data was random. Consequently, sinusoidal testing was stopped. 

6.2 Mechanical Shock 

Mechanical shock qualification levels for the Scout upper stages are: 

C Section: 68 g. terminal sawtooth, 6 milliseconds duration 

D Section: 60 g. terminal sawtooth, 6 milliseconds duration 

E Section: 75 g. terminal sawtooth, 6 milliseconds duration 

The most severe mechanical shock during flight of the Scout upper stages occurs at Antares 

ignition and is shown in Figure 6-2. 

The Shuttle mechanical shock environment is 20 g. terminal sawtooth, 11 milliseconds duration, 

plus several rectangular pulses of 0.23 g. to 1.5 g. with durations ranging between 170 to 350 milliseconds. The differences between these spectra are negligible; consequently, no further qualification 

of Scout upper stages in mechanical shock is considered necessary. 

20 
I\,) 

..... 

TABLE 6-1.- LIST OF SCOUT EQUIPMENT FOR ENVIRONMENT COMPARISON AND 

SUMMARY OF ENVIRONMENTAL TESTING PERFORMED 

Tested to Scout Environmental 

Scout environment flight acceptan

qual levels evaluation tests 

Vehicle sections: 

"C" section (upper) T-A 

"0" section 

Contractor supplied separation system V V 

("E" section) 

Rocket motors: 

Antares V,T Altair T 

Guidance and control components: 

Poppet valve electronics T-S, V, MS V, T-A 

Rate gyro unit T-A V, T-A 

Inertial reference platform V, T-A 

Yardney battery pack 

Instrumentation: 

4th Stage TIM transmitter MS,V T-A, V, MS 

Reaction control components: 

Thruster valves (60#, & 2# motors) T-A 

Relief valves (H20 2) T-A, T, V 

Quick disconnect (unregulated N2) MS,A T-A 

Hydrogen peroxide tanks T-A 

Pressure regulator, N2 T-A 

Legend: 

T Temperature MS Mechanical shock 

V Vibration T-A Temperature-altitude 

A Acceleration 

__ T-S _____ 
22 

.005 

Shuttle 

ascent 

8.4 sec/mission 

""~---,. 

.OOl~----------------------------------------------------~ 

FIGURE 6-1.- RANDOM VIBRATIONS OF SCOUT QUALIFICATION TESTS AND SPACE 

SHUTTLE PAYLOAD BAY 
60 

50 

40 

30 

b, 20 

c: 10 o 

',tj Transverse 

\ 

"E" section 

"0" section 

"c" section 

E Q) O~--------------------------------------------------~ 

~ -10 (.) 

« -20 

"c" section 

-30 "E" section 

-40 

-50 

-60~~====*=*==============C=C====~======~ 

en 

60 

50 

40 

30 

20 

C, 10 

c: 

o 

',tj 0 

E 

~ -10 (.) 

~ -20 

-30 

-40 

-50 

-60 

a 

, 

V 

r 

~ , 

-I 

I 

a 

100 200 300 400 500 600 700 800 900 1,000 

Frequency, Hertz 

Longitudinal 

I I I I I I I I I 

100. 200 300 400 500 600 

Frequency, Hertz 

i 

\ 1 "C" section 

"E" section 

"0" section 

"0" section 

/ "E" section LT" section 

, I I I I I 

700 800 900 1,000 

FIGURE 6·2.- SCOUT MECHANICAL SHOCK LEVELS 

(MAXIMUM SHOCK ENVELOPE - ANTARES MOTOR) 

23 
6.3 Acceleration 

The expected mission acceleration levels are lower than the Scout environmental test levels; 

therefore, no incompatibility exists. However, the Scout support pallet must be capable of withstanding 15 g's in the shuttle Z axis and 10 g's in the X and Y axes. 

6.4 Acoustic 

For the acoustic environment, no Scout test levels are required. However, the Scout vibration 

test levels include the effects of vibrations induced by sound. The reverberant sound field within 

the Shuttle will be different in character from the sound field generated during flight of a Scout 

through the atmosphere. The overall sound pressure levelsfor the Shuttle payload bay and the 

flight of a Scout through the atmosphere are comparable; however, at portions of the frequency 

range the Shuttle levels will exceed the Scout flight levels and are so noted in Figure 6-3. 

It has to be assumed that during the period that acoustics are encountered, they are applied 

uniformly over the entire Scout upper stages and support pallet. The design of the pallet to the 

levels presented in Figure 6-3 is required. 

N 

~ 150~------------------------------------------~ 

z 145 dB Overall "Oa 3N 

~ ~ 

-g CD~ 

1'0"0 .0 _ 

I Q) 

Q) > >~ 

J9 ~ o ::::I 

o~ _ MQ) ... .... 0. 

24 

140 

130 

"c" section 1 ~::~~;i~;$~~~~~~'D" section Scout ~ "E" section 

120 

110~~~~~~~~~~--.. -.~--~~~--~~~ 

234 2 3 4 2 3 4 

Frequency, Hertz 

FIGURE 6-3.- ACOUSTICAL ENVIRONMENT CHARACTERISTICS OF 

SPACE SHUTTLE AND PRESENT SCOUT 
6.5 Meteoroid 

The land launched Scout mission, because of its relatively short duration, has not been concerned 

with meteoroid damage. In the Shuttle launched mission, the Scout upper stages will be exposed to 

the deep space environment for approximately three hours after deployment from the Shuttle. Using 

the method of Reference 3, the probability of meteoroid damage was assessed as 0.00364, or a 99.64% 

probability of no damage. This is considered an acceptable probability for purposes of this study. 

6.6 Thermal 

During Shuttle prelaunch operations, temperatures in the payload bay can be set between 40 and 

490 C (400 and 1200F), Reference 2, Table 4-1. The Antares motor ignition temperature minimum 

and maximum limits are 100 and 320C (500 and 900 F), respectively. For the Altair- the limits are 40 

and 380C (400 and 1000F). Consequently, during prelaunch operations with the Scout upper stages 

in the Shuttle, the payload bay temperature must be held within the motor ignition temperature 

limits, with the Antares being the more critical. 

For the post launch conditions, a layer of white paint on the outside of all motors and vehicle 

sections was assumed as a starting point for all thermal analyses. Under that condition, the maximum 

allowable temperatures were never approached in space and all further analyses were restricted to the 

minimum temperature condition. 

For analysis, the Scout vehicle was considered as 5 major sections. The thermal capacities for 

these sections is listed below: 

Upper "c" Skin CTH = PCpt = 5104 joule/meter2 °c 

(.2495 BTU/ft2 OF) 

Antares Motor Case CTH = 9328 jou le/meter2 °c 

(.4560 BTU/ft2 OF) 

Lower "0" Skin CTH = 6683 joule/meter2 °c 

(.3267 BTU/ft2 OF) 

Upper "0" Skin CTH = 3717 joule/meter2 bC 

(.1817 BTU/ft2 OF) 

Altair Motor Case CTH = 3964 joule/meter2 °c 

(.1938 BTU/ft2 OF) 

CTH = Thermal Capacity P = Material Density 

Cp = Specific Heat t = Thickness 

Since the thermal eapacity is a direct indication of the speed at which a section will change temperature, only the minimum thermal change (Antares motor case) and maximum thermal change (Upper 

"0" section skin) conditions were considered. All other sections listed above will have temperature 

variations which will lie between these two extremes. 

The results of these analyses are seen in Figures 6-4 through 6-6. Figure 6-4 shows the maximum 

Scout temperatures reached during the Shuttle launch-to-orbit segment of the mission, for an initial 

payload bay temperature of 490 C (1200F), to be 540C (1280 F) for the Upper "0" skin and 51 0C 

(1240 F) for the Antares motor case. Temperatures for the Antares motor case further indicate that 

insulation or pre-launch bay temperature limitations will be required to keep motor temperatures 

within acceptable limits. Figure 6-5 shows the minimum steady-state temperature distribution 

throughout the Shuttie earth orbit phase of the mission. With the white paint coating on the outer 

skin surfaces, minimum temperatures of -1000C (-1480 F) and -760 C (-1050F) will exist for upper 

25 
"0" section skin and Antares motor case, respectively. These temperatures are unacceptable and new 

thermal protection will have to be defined to protect motors and section components. Figure 6-6 

illustrates minimum temperatures during the Scout orbit segment of the mission after Antares ignition. 

An unacceptable Upper "0" skin minimum temperature of -108oC (-1630 F) will exist while other 

Scout sections will have minimum temperatures below this value and are also unacceptable. Again, 

thermal protection of vehicle sections will be required to bring temperatures up to specified motor 

and component minimums. The acceptable temperature ranges for the present Scout components 

and rocket motors are given in Table 6-11. 

65 150 

60 140 

u u. 

0 0 

(OUTSIDE SURFACES OF SCOUT COATED WITH WHITE PAINT) 

Note 1: Upper "0" represents maximum temperature rise, Antares motor 

represents minimum temperature rise, all other sections will 

have temperature rises which lie between these two extremes. 

Shuttle payload bay 

temperature at 

lift-off 

Scout upper "0" skin, CTH = .1817 OJ' OJ' .... .... [ ::J ::J 

~54 .... ~130 .... OJ OJ a. a. E E OJ OJ 

l- I49 120 I 

Antares Motor case, CTH = .4560 

38 100~~----~----~----~----~----~----~----~----~ 

o 60 120 180 240 300 360 420 480 

Launch orbit flight time, sec 

FIGURE 6-4.- MAXIMUM TEMPERATURE DURING SHUTTLE LAUNCH 

26 
-107 -160r-----------------------------------------------~ 

-96 -140 

-84 -120 

u 0-62 

e' 

:::l 

.... 

E 

~-51 

E 

Q) 

I-

-40 

-100 

u. 

o -80 

e' 

:::l 

.... 

E 

~-60 

E 

Q) 

I-

-40 

-29 -20 

• Outside surfaces coated with white paint 

• Note 1- on Figure 6-3 applies 

• Cargo bay doors open for 24 hrs - temperatures stabnized 

• One shuttle orbit = 90 min 

Scout upper "0" skin CTH = .1817 

Antares motor case, 

CTH =.4560 

Initial temperatures for scout orbit 

for CTH = .1817 & CTH = .4560 

Antares liB 

ignition t 

Sun 0 - EarthG 

Based on above Sun-earth 

OL-~----~----~----~----~--~~--~----~----~----~ o 10 20 30 40 50 60 70 80 90 

Shuttle orbit time, min 

FIGURE 6-5.- MINIMUM TEMPERATURE DURING SPACE SHUTTLE ORBIT 

27 
• Outside surfaces coated with white paint 

• Note 1- on Figure 6-3 applies 

• Antares ignition @ tScout orbit = 0 

-118 -180r--------------------------, 

-107 -160 

-96 -140 

0 u. 

0 0 

a) a) ... ... Z-84 Z-120 co co ... ... OJ OJ 

a. a. 

E E OJ OJ 

I--73 1-_100 

-62 -80 

~-- Maximum temperature 

variation 

_-- Minimum temperature 

variation 

u----~-Initial temperatures from 

Figure 6-4 

Scout upper "0" skin, 

CTH = .1817 Section 

-51 -60L-~-----L-----L----~----~----~----~----~-----

o 20 40 60 80 100 120 140 160 

Scout orbit time, minutes 

FIGURE 6-6.- MINIMUM TEMPERATURE DURING SCOUT ORBIT 

28 
TABLE 6-11.- TEMPERATURE RANGES FOR PRESENT SCOUT COMPONENTS AND 

ROCKET MOTORS 

Temperature range 

COMPONENTS: Min °c (OF) Max 0c (OF) 

Reaction control system 

Operating: 4 (40) 49 (120) 

Non-operating: - 7 (20) 71 (160) 

Guidance electronics -40 (-40) 66 (150) 

TIM Transmitter -18 (0). 80 (176) 

Batteries -18(0) 49 (120) 

MOTORS: 

Antares Case bond temperature limits have 

been established at 40C (400 F) 

minimum and 380C (1000 F) maximum. 

Altair Case bond temperature limits have 

been established at 20C (350 F) 

minimum and 41 0C (1050 F)·maximum. 

7.0 RESULTS OF ANALYSES FOR ENABLING SCOUT UPPER STAGES TO ENDURE 

THE EXPECTED SHUTTLE MISSION ENVIRONMENTS 

Analyses were performed on the dynamic, meteoroid and thermal conditions identified in 

Section 6.0, with the results presented in this Section. Section 8.0 presents recommendations, 

based on the analytical results, to enable the Scout upper stages to endure the Shuttle launched 

mission environments. 

Differences were found between the Scout vibration test levels and the predicted dynamic 

environment during all phases of Shuttle operation. Also, a thermal incompatibility exists from 

the time the Space Shuttle payload bay doors are open until separation of the Scout upper stages 

from its payload. 

29 
7.1 Dynamic Analyses 

Analyses were performed to determine the compatibility of the Shuttle launched Scout upper 

stages in the dynamic environment imposed by the Shuttle mission as defined in Section 6.0. The 

following items were determined in support of these analyses: 

(1) Modes of vibration in· the axial, lateral, and vertical directions of the Scout/pallet 

dynamic system. . 

(2) Maximum RMS flight loads and acceleration spectral densities imposed on the Scout 

by the Shuttle random vibration environment. 

(3) Maximum loads imposed on the Scout by the Shuttle mechanical shock environment. 

(4) Maximum loads imposed on the Scout by the Shuttle sinusoidal vibration environment. 

The Scout upper stages and the Shuttle pallet were mathematically modeled using finite element 

techniques. A typical spacecraft envelope was used as the payload configuration. The physical properties of the Scout vehicle were taken from Vought Corporation Report No. 23.392 "Scout Structural 

Dynamics Design Data Report" Revision B dated 14 February 1976 and those of the spacecraft and 

pallet from Reference 1. The nodal locations of the Scout/pallet finite element model are presented in 

Scout station coordinates in Table 7-1. For the analysis the model was cantilevered at the appropriate 

support points as shown in Figure 7-1. 

The first 12 cantilevered modes of the S'cout/pallet system with rigid attachment members are 

presented in Table 7-11 for the axial (X direction), lateral (Y direction), and vertical (Z direction) 

models. As noted in Table 7-11, the nature of the mounting system and the relatively large mass 

and moment of the Scout/pallet system result in very low frequency fundamental modes in all three 

axes. 

The random vibration spectra representative of the Shuttle lift-off and ascent environment are 

shown in Figure 3-1. These spectra were analytically imposed on the Scout/pallet model and the 

RMS loads and acceleration spectral densities determined at various Scout stations. The maximum 

axial loads, and lateral and vertical bending moments are presented in RMS values in Table 7-111. 

Acceleration spectral densities for locations in the Scout "0" and "E" sections are plotted in Figure 

7-2 and compared with current Scout 95% confidence limits at these locations. Figure 7-2 shows 

that a lateral acceleration spike at 19 Hz exceeds the current Scout limit for both the "0" and "E" 

sections but is not considered a problem to the structural integrity of the Sections or of any component. 

The limit was not exceeded at any other location in any other axis over the frequency range of interest. 

The most severe mechanical shock condition of the Shuttle environment is the aborted-mode 

handling requirement of a 20g terminal sawtooth pulse of 11 milliseconds duration. This shock forcing function was applied to the Scout/pallet model and maximum axial loads, lateral bending 

moments, and vertical bending moments determined at various Scout stations. These maximum loads 

and moments are presented in Table 7-111. It appears that the magnitude of these loads would not be 

appreciably reduced by the installation of isolators. All loads shown in Table 7-111 are within the 

current structural capability of the Scout vehicle except those at Station 47.8 for the "E" Transition 

Section. 

30 
TABLE 7-1.- SCOUT/SHUTTLE PALLET COORDINATES 

Axial (X direction) cantilevered at (X = 182.7, Y = 88, Z = 414) and (X = 182.7, 

Y = 88, Z = 414) 

Lateral (Y direction) cantilevered at (X = 182.7, Y = 0, Z = 305) 

Vertical (Z direction) cantilevered at (X = 171.3, Y = 88, Z = 414 

X= 171.3, Y=·88,Z=414 

X= 182.7, Y=88,Z=414 

X = 182.7, Y = -88, Z = 414) 

Scout station Coord. no. 

- 31.3 1 

37.27 2 

47.77 3 

65.9 4 

72.7 5 

84.5 6 

99.8 7 

102.7 8 

103.7 9 

124.1 10 

131.1 11 

137.7 12 

161.5 13 

182.7 14 

191.9 15 

218.6 16 

238.18 17 

31 
32 

Axial restraints A 

8 

Lateral restraint C 

Vertical restraints A 

8 

o 

E 

z 

.... .-x 

Scout coordinates 

(X= 182.7, Y=88,Z=414) 

(X = 182.7, Y = -88, Z = 414) 

(X = 182.7, Y = 0, Z = 305) 

(X= 182.7, Y=88,Z=414) 

(X= 182.7, Y=-88,Z=414) 

(X = -171.3, Y = 88, Z = 414) 

(X = -171.3, Y = -88, Z = 414) 

y 

FIGURE 7-1.-SCOUT/SHUTTLE PALLET RESTRAINT SYSTEM 

TABLE 7·11.- SCOUT/SHUTTLE PALLET CANTILEVERED MODAL FREQUENCIES 

Mode no. Axial (X direction) Lateral (Y direction) Vertical (Z dire~tion) 

1 2.1 0.7 2.0 

2 39.4 10.6 3.4 

3 88.5 13.7 7.4 

4 115.3 19.3 23.3 

5 136.4 33.0 42.4 

6 179.9 44.3 66.4 

7 258.3 67.9 80.9 

8 349.6 115.8 108.1 

9 381.6 137.2 144.6 

10 411.6 152.9 150.6 

11 609.9 215.2 214.8 

12 635.9 224.4 239.3 
The most severe sinusoidal vibration environment imposed by the Shuttle is that for the 

aborted-mode handling. The input vibration spectrum for this condition is given in Section 3.4. 

This spectrum was analytically applied to the Scout/pallet model and resulting maximum loads and 

moments are presented in Table 7-111. The loads resulting from this sinusoidal input are excessive. 

The sinusoidal test spectrum defined for this condition is unrealistic when applied to heavy structural 

elements and should not be considered as a part of the dynamic environment imposed by the Shuttle 

mission. 

TABLE 7-111.- SCOUT/SHUTTLE PALLET DYNAMIC RESPONSE LOADS 

47.8 84.5 

Scout 

payload 

envelope 

V 

/ 

/ 

Max. axial rms load 

(X direction) 371.9 (83.6) 399.0 (89.7) 

newtons (lbs) 

Max. lateral rms 

bending moment 904 (8000) 370 (3274) 

(Y direction) 

joules (in.·lbs.) 

Max. vertical rms 

bending moment 8.61 (76.2) 7.21 (63.8) 

(Z direction) 

joules On.-Ibs.) 

Max. axial load 

(X direction) 23,237 (5,224) 18,771 (4,220) 

newtons (lbs.) 

Max. lateral 

bending moment 15,634 (138,370) 4,420 (39,120) 

(y direction 

joules (in.·lbs.) 

Max. vertical 

bending moment 12,777 (113,090) 2,626 (23,240) 

(Z direction) 

joules On.-Ibs.) 

Max. axial load 

(X direction) 62,053 (13,950) 66,545 (14,960) 

newtons (Ibs.) 

Max. lateral 

bending moment 116,826 125,187 

(Y direction) (1,034,000) (1,108,000) 

joules On.-Ibs.) 

Max. vertical 

bending moment 182,922 234.217 

(Z direction) 

joules (in.·lbs.) 

(1,619,000) (~,073,OOO) 

131.1 

- J 

\ 

358.0 (80.5) 

138 (1221) 

21.47(190) 

15,035 (3,380) 

14,972 (132,510) 

6,601 (58,420) 

79.979 (17,980) 

140,101 

(1,240,000) 

308,675 

(2,732,000) 

192.0 

Scout 

stations 

)0 

\ 

96.0 (21.6) 

491 (4342) 

18.98 (168) 

1,121(252) 

11,175 (98,910) 

1,456 (12,890) 

155,287 (34,910) 

190,718 

(1,688,000) 

534,644 

(4,732,000) 

Response loads 

from random 

vibration 

Response loads 

from mechanical 

shock 

Response loads 

from sinusoidal 

vibration 

33 
.10r-------------------------, 

N 

I 

NO) -.01 

> +oJ 

·en 

c: 

Q) 

"C 

e 

+oJ 

tJ 

Q) 

a. 

en 

c: 

o 

.~ 

e 

Q) 

Qi 

tJ 

tJ 

<{ 

. 001 

.0002 

34 

I 

n 

" , , 

I , 

I , 

I , 

, , I , 

I , 

, 

, 

, 

, 

, 

, "c" section 

"0" section 

\ , 

, 

20 

, "E" section 

\\ ~ 

~ 1\ 

\./. \ 

\\Jf\ \ " r , 

I " I 

, I '\ ' I \ " , " " 

Note: Upper 95% confidence limits . 

----- "E" section response (sta.47.8) 

--- "0" section response (sta. 103.7) 

100 Frequency, Hz 1,000 

FIGURE 7-2.- ACCELERATION SPECTRAL DENSITY DUE TO RANDOM 

VIBRATION INPUT SPECTRA 

10,000 
Spectral levels of acoustic noise within Shuttle cargo bay during launch of Shuttle are expected 

to be over ten decibels higher than spectral levels of acoustic noise at the surface of an air-launched 

Scout as shown in Figure 6-2. Therefore, Scout is underqualified to Shuttle noise levels, regardless 

of any modifications of Scout attachment to Shuttle. Acoustical testing will be required to qualify 

the Scout vehicle for Shuttle launches. 

7.2 Thermal Analysis 

Thermal analyses were performed on the Scout upper stages vehicle for the Shuttle launched 

mission environment. The analyses were done following the thermal study discussed in Section 6.6 

which indicated that components of the Scout upper stages vehicle, with its outside surface painted 

white, would be subjected to temperatures below their minimum limits, Table 6-11. These analyses 

were done to define the thermal protection requirements for the Scout upper stages for this mission, 

and to recommend coatings and/or insulation necessary to insure proper Scout operation. 

The phases of the Scout mission and their corresponding thermal environments are seen in Figures 

4-1 and 7-3.· Figure 4-1 illustrates the Scout mission phases and timeline. For this investigation, a 

24-hour Shuttle Earth Orbit, with bay doors continuously open, was assumed. The assumed ShuttleEarth orientation is also shown in Figure 4-1. Other Shuttle-Earth orientations were considered; 

however, the orientation used was felt to be the extreme case. Based on the mission trajectory 

Sun position for 

maximum heating orbit 

o · 

Altair 

ignition 

o 

Sun position for I 

minimum heating orbit 

~---.lL 

Scout upper 

stages orbit 

Scout upper 

stages 

Antares ignition 

FIGURE 7-3.- SUN-TO-VEHIClE ORIENTATION FOR MINIMUM AND MAXIMUM HEATING 

35 
described in Section 3.0, orbital characteristics for the Scout vehicle after Antares ignition were calculated using methods described in References 4 and 5. Figure 7-3 indicates the vehicle orientation 

for maximum and minimum solar th~nnal environments seenhy the Scout upper stages vehicle during 

this orbit. Other Sun-Earth positions were considered;however, the two cases presented in Figure 7-3 

will be the extremes seen by the vehicle. Earth radiation and albedo heating inputs were also estimated. 

The methods and charts used are found in Reference 8. 

The thermal models used in these analyses are described in the following paragraphs and are 

pictorially displayed in Figures 7-4 through 7-6. The skin and component materials and properties 

are given in Table IV. 

Figure 7:-5 shows a cross-section sketch of the Upper "c" Section without a component attached 

to the skin and with the Scout rate gyro attached to the skin. "0" and "E" section final models with 

superinsulation are seen in Figure 7-6. 

Throughout these analyses, all transient nodal temperatures were calculated using methods 

described in Reference 6. Antares nozzle outer wall temperature decay was estimated by assuming 

heat loss through radiation to the aluminum radiation shields which make the double wall shroud 

around the nozzle. Initialtemperatures were found in Vought Corporation Report 23.124 "Scout "c" 

Section Thermal Control Study" dated 15 June 1964. The results of these analyses follow in the order 

of rocket motors, Upper "c" section, and "0" and "E" sections. 

Temperatures at nodes 1,2, and 3, Figure 7-4, for the Antares.and Altair were computed for all 

mission phases assuming an outside motor case thermal coating consisti.ng of aluminum tape to white 

paint in a ratio of ten parts aluminum tape to one part whit~ paint. Figure 7-7 illustrates the 

temperature rise experienced by both motors at the specified minimum and maximum temperature 

limits of the Shuttle bay environmental control system. The temperature rise incurred is a result of 

aerodynamic heating on the Space Shuttle bay door outside ~rfaces, Reference 2. Heat is then 

transferred to the Scout upp.er stages through thenn.al radiation and free convection. Figure 7-8 

shows the stabilized Antares nodal temperatures achieved after the Shuttle has been in orbit for 24 

hours with the cargo bay doors open continuously. It is apparent that, at an initial prelaunch cargo bay 

temperature of 490C (1200F), the Antares motor will not be suffi<;iently cooled to meet the specified 

upper firing limit of 320C (9OOF). However, for an initial te.mper:ature of 21 0C (700F), the motor will 

have stabilized at a temperature well within the allowable ignition range of 100 to 320C (500 to 900F). 

Figure 7-9 shows the Altair temperature variation in the Shuttle orbit for cargo bay pre-launch 

temperatures of SoC (400F) and 21 0C (700Ft Figure 7-10 illustrates Altair temperature distributions 

for maximum and minimum Scout heating orbits as defined in Figure 7-3. These results indicate that 

the Altair motor temperatures will lie well within the 40 to 430C (400 to 1100F) ignition temperature 

limits ~f the motor using recommended thermal protection. 

The results of the Upper "c" section thermal analysis, where Upper "c" outside skin is covered 

with .13 cm (.05 inch) cork coated with six to one ratio of aluminum tape to white paint are presented 

in Figures 7-11 through 7-14 .. Figure 7-11 shows the Upper "C" inside skin and rate gyro temperature variations while in the last Shuttle orbit prior to Antares ignition. Figure 7-12 illustrates 

the estimated Antares nozzle outer wall and corresponding radiation shield temperatures after motor 

ignition. Figure 7-13 shows the inside skin and rate gyro temperatures achieved during the maximum 

Scout heating orbit. Figure 7-14 shows the same for the minimum Scout heating orbit. Both Figures 

7-13 and 7-14 include the Antares nozzle and solar heating inputs. These figures indicate that the 

thermal protection presently utilized for the rate gyro will be adequate for this mission. The other 

components in Upper "Ct

, section are influenced less by temperature change than the gyro and are, 

therefore, also adequately protected. 

36 
W 

"-J 

1.27 f3\ 

3.68 - (.05) 

(.145)-.-5.1 pi AZ (.20) It 

260 

(10.24) 

A. Antares thermal model 

mm (in.) 

Note: 

CD} CD 

CD 

10.2 

1.27 (.08) --

(.05) .51 == 

(.02) 

143.4 

(5.646) 

\ CD.. . ... =t=

\ ... ." · . {CD 

CD 

B. Altair thermal model 

Nodes for thermal analysis 

FIGURE 74.- ANTARES AND ALTAIR IliA MOTOR THERMAL MODELS 
Cork 

\,. Upper "C" skin - 1.27 _______ ~II ________ "'" 

(.05) \ -h 

3276 ............... - Fiberglass 

(.1·29) 

Rate ~~ 8 i _~ 6.35 

gyro· Aluminum heat shield (.25) 

Aluminum radiation shroud ,e : ,~< 

Nozzle 

Upper "C" section thermal model with rate gyro 

Cork Upper "C" section 1.27 :> (.05)~ .. , ___________ --------.. , 

32.76 ~.- :;;> (.129) Fiberglass 

Double wall 

shroud 

O.762~ (.03) 

2.28 

(.09) 

~~~~ 

:;p 

2.92 

(.115) 

--<t nozzle - - --------

mm (in.) Upper "C" section sketch 

FIGURE 7·5.- UPPER "c" SECTION THERMAL MODEL 

38 
w 

CD 

T 

2.08 

(.082) 

_ Magnesium 

Upper "0" skin 

mm (in.) 

T 

2.59 

(.100) 

Steel 

Lower "0" skin 

-t2.08 

(.082) --L Magn

"E" sec

FIGURE 7·6.- "0" AND "E" SECTION THERMAL MODELS 
TABLE 7-IV_-SCOUT UPPER STAGES MATERIALS AND PROPERTIES 

Upper "C" Section Skin and Components 

I t Density Cp 

I Material 

Kg/m3 (lb/ft3) Joules/KgOC Joules/hroC m 

I mm (ft) BTU/lboF 

Skin Fiberglass 3.3 (.0108) 1762 (110) 880 (.21 ) 603 

{ Flb,,,,I ... .8 (.0025) 1842 (115) 1592 (.38) 1497 

Nozzle Asbestos phenolic 3 (.010) 1473 (92) 1843 (.44) 1347 

Silica phenolic 4.9 (.0162) 1473 (92) 880 (.21 ) 898 

Radiation Aluminum .3 (.0010) 2659 (166) 896 (.214) 729,547 

shield 6.4 (.021 ) 

Rate gyro Aluminum 2659 (166) 896 (.214) 729,547 

Antares Motor 

t C.,k 1.28 (.0042) 480 (30) 1969 (.47) 156 

Skin Spiralloy 3.9 (.0128) 1986 (124) 1047 (.25) 1247 

Insulation 4.4 (.0146) 1794 (112) 1437 (.343) 823 

Propellant (Rubber base) 264.4 (.8675) 1794 (112) 1248 (.298) 1640 

Lower "D" Section 

Skin Cork 1.3 (.0042) 480 (30) 1969 (.47) 156 

Steel 1.3 (.0042) 7849 (490) 544 (.13) 46,142 

Altair Motor 

t Spl"II.y 2.0 (.0067) 1986 (124) 1047 (.25) 1247 

Skin Insulation 1.3 (.0042) 1794 (112) 1437 (.343) 823 

Liner .5 (.00167) 961 (60) 1437 (.343) 823 

Propellant (Rubber base) 135.6 (.445) 1794 (112) 1248 (.298) 1640 

"E" and Upper "0" Section 

Skin Magnesium 2.0 I (.0067) I 1810 (113) 1005 (.24) 236,947 

-
10: 1 Aluminum tape-white paint on outside skin of motor case 

53.4 - 128 

Altair 

52.3 126 \ Note: 1-Temperature rise caused 

51.2 124 by aerodynamic heating to 

shuttle. This heat is then 

transferred to Scout through 

radiation and free convection 

50.1 122 Antares 

(J u. 

o 48.8 0 1201--==~-- Initial temperature = 490 C (1200 F) 

Pi 

a 

E 

Q) 

e' 

:l 

..... 

E 

Q) 

Co E 7.8 Co 46 E 

2 - Actual motor temperatures 

will be lower due to more 

thermal capacity 

Q) 

I- ~ 

6.7 

Initial temperature = 4.40 C 

~(:4~OO~F~) __ ~=====:~_----- Antares 

4.4 40 

3.3 38 

2.2 

3 - Initial temperatures are shuttle bay prelaunch 

minimum and maximum 

60 120 180 240 300 

Shuttle launch time, seconds 

360 

FIGURE 7-7.- 2-STAGE SCOUT MOTOR CASE TEMPERATURES VS 

SHUTTLE LAUNCH TIME 

420 480 

41 
N Shuttle orbit 24 hr 

last orbit before motor ignition 

10: 1 Aluminum tape-white paint on outside skin of motor case 

120. 

Tinitial = 49°C (120°F) Node CD 

CD 

43.51- 110 

---

0) 

-

fs' 38 u. 0 100 

Node .. Propellant ... ... ::J ::J 

+-' (See Figure 7-4A) +-' ctI ctI .. Bondline 

... ... 

Q) Q) 

a. a. .. Outside skin 

32 E Q) 90 

l- I26.5..... 80 

CD Tinitial = 21°C (700F) 

21 70 CD 

o 10 20 30 40 50 60 70 8

Shuttle orbit time, min 

FIGURE 7-8.- ANTARES MOTOR NODAL TEMPERATURES VS SHUTTLE ORBIT TIME 
24.4 76.------------------------...... 

23.9 75 

23.3 74 

22.8' 73 

22.2 72 

(J u.. 

o 0 

~' 

::::I 

..... 

~ 21.7 

a. 

E 

Q) 

I11.1 

10.5 

Tinitial = 21 0C 

(700 F)* 

Last orbit before Antares ignition 

10: 1 Aluminum tape-white paint on 

outside skin of motor case 

Shuttle in orbit for 24 hr 

Note: Propellant temperature variation 

will be less and these temperatures 

will always be well within specified 

ignition limits 

10.0 Tinitial = 4.4°C (400 F)* 

9.5 49' 

8.9 48 *Temperature at beginning of 

24 hr orbital period in shuttle. 

Cargo bay doors open. 

8.3 

47~ _____ ~ _____ ~ _____ ~ _____ -J 

o 25 50 75 100 

Shuttle orbit time, min 

FIGURE 7·9.- ALTAIR BONDLINE (NODE 2) TEMPERATURE VS SHUTTLE ORBIT TIME 

43 
u 

0 

QJ. 

... 

::J 

+18.9 66-----------------------------, 

+16.7 62 

+14.4 58 

+12.2 54 

u. 

0 

QJ •

... 

::J 

..... 

10: 1 Aluminum tape-white paint on outside skin of motor case 

Tinitial = 4.4oC (400 F) 

............... Maximum heating Scout orbit 

..... 

E +10.0 E 50 QJ 

Co 

E 

QJ 

l44 

QJ 

Co 

E 

QJ 

I-

+7.8 46 

+5.5 42 

+3.3 

+1.1 34 

-1.1 

Node 0---- Bondline 

Node CD --Propellant 

(see Figure 7-4B) 

-

Initial from Figure 7-9 -CMax heating => t = 45 min in Shuttle orbit 

for node CD Min heating => t = 67.5 min in Shuttle orbit 

20 40 60 80 100 120 140 

Scout orbit time, min 

FIGURE 7-10.- ALTAIR PROPELLANT AND BONDLINE TEMPERATURE VS SCOUT 

ORBIT TIME 
.:>. 

01 

Temperatures stabilized 

last orbit before Antares ignition 

(CTH) rate = 3 CpV = .342 gyro 

+37.8 r , 100 I 6: 1 Aluminum tape white pa

+26.71- 80 

u 

0, +15.5 

e 

::J 

10 

'-

Ql 

0. 

E 

+4.4 

-17.8 

LL 

o 

e 60 

::J 

+" 

E 

Ql 

C. 

E 

Ql 

I- 40 

20 

0 0 

I. 

& J'I-. 

"I/) 

l'&/J) 

\0&1": 

....... ql'lt. 

- - - - - ",,,.,, •• :.,/ .. & *' -

*This inside skin temperature 

was calculated w/o component 

attached to skin. With rate gyro 

attached,· inside skin temperature 

rate gyro temperature 

10 20 30 40 50 

Shuttle orbit time, min 

on outside skin 

Rate gyro temperatu

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

60 70 8

FIGURE 7-11.- UPPER "c" TEMPERATURE VS SHUTTLE ORBIT TIME 
(.) 

0 

lU-

.... 

:l 

..... 

248.9 

Maximum heating orbit 480~~~--------~~--~~~~--------------------~ 

226.7 440 

204.4 400 

182.2 360 

160.0 320 

LL 

0 

lU-

.... 

:l 

..... 

Antares nozzle outerwall 

Inner AQ radiation shield 

Outer AQ radiation shield 

Antares ignition @ tScout = 0 

tburn = 28.9 sec 

e 137.8 e 280 Q) Q) 

c. c. 

E E 

IU IU l- I115.5 240 

46 

93.3 200 

71.1 160 

48.9 120 

26.7 80~-----L------~-----L------~----~------~----~ 

o 20 40 60 80 100 120 140 

Scout orbit time, min 

FIGURE 7-12.- ANTARES NOZZLE & SHROUD TEMPERATURES VS 

SCOUT ORBIT TIME 
Maximum heating orbit 

(CTH) rate = .3424 

gyro 

6: 1 Aluminum tape-white paint coating 

104.4 220r---------:::::::=:::::::---------, 

u 

o 

~' 

93.3 

82.2' 

71.1 

::J 

.... 

~ 60.0 Ql 

a. 

E 

Ql 

I48.9 

200 

180 

LL 

o 

~' 

::J 

160 

~ 140 .... 

Ql 

a. 

E 

Ql 

I120 -

Inside skin temperature * 

Rate gyro temperature 

37.8 100 

26.7 80 

60 

*Inside skin temperature w/o component 

attached, with rate gyro attached. 

Inside skin temperature ~ rate gyro 

temperature 

40'~----~------~----~----~------~----~----~ 

o 20 40 60 80 100 120 140 

Scout orbit time, min 

FIGURE 7-13.- UPPER lie" TEMPERATURE VS SCOUT ORBIT TIMEMAXIMUM HEATING ORBIT 

47 
Minimum heating orbit 

(CTH) rate = .3424 

gyro 

4S.9 120---------------------------. 

37.S 100 

(J 

o 

~-

::s 

E26.7 

Ql 

a. 

E 

Ql 

~ 

15.5 

4.4 

u. 

o 

~­

aso 

E 

Ql 

a. 

E 

Ql 

~ 

60 

6: 1 Aluminum tape-white paint coating 

*This inside skin temperature 

was calculated wlo component 

attached to skin. With rate gyro 

attached, inside skin temperature ~ rate gyro temperature 

Inside skin temperature* 

o 20 40 60 so 100 120 140 

48 

Scout orbit time, min 

FIGURE 7-14.- UPPER "e" TEMPERATURE VS SCOUT ORBIT TIMEMINIMUM HEATING ORBIT 
The "0" and "E" Section outside skins wrapped with 7-layer superinsulation were analyzed to 

determine their thermal characteristics. Superinsulation was used for these sections rather than tape 

and paint because of the section material's rapid response to temperature change. The rocket motors 

and the Upper "c" Section with the motor nozzle did not require this type of insulation because of 

their much slower response to change in solar environments. Figures 7-15 and 7-16 show the 

results of the "O"and "E" Section thermal analyses. Figure 7-15 indicates the inside skin temperature variation as a function of orbit time for the maximum heating Scout orbit while Figure 7-16 

illustrates the same for the minimum heating orbit. It should be noted that the skin coating called 

out for Upper "0" section may be conservative. Superinsulation was used to protect the Altair 

nozzle because of the long (2.4 hour) exposure to deep space environment during the coast phase 

between Antares burn-out and Altair ignition. 

82.2 180 

Maximum heating orbit 

wl7-layer superinsulation 

71.1 160 

60.0 140 Upper "0" and "E" section 

inside skin temperature 

u u.. \ 0 48.9 

0 

120 Q)~ Q)~ 

... ... ::l ::l .... .... co co 

... ... Q) Q) 

a. 37.8 a. 100 

E E Q) Q) 

l- I26.7 80 

15.5 60 t-~---

4.4 40 

o 20 40 60 80 100 120 140 

Scout orbit time, min 

FIGURE 7-15.- "0" AND "E" SECTION TEMPERATURES VS SCOUT ORBIT TIME -

MAXIMUM HEATING ORBIT 

49 
Minimum heating orbit with 7-layer superinsulation 

+37.8 100.-------------------------, 

+26.7 80 

LL Upper "D" and "E" section inside skin temperature 

0 U 

o +15.5 1-. 

0,; (IJ •

... ... ::J ::J +-' +-' co co ... ... (IJ (IJ 

0. 

E +4.4 ~ 40 (IJ (IJ 

l- I-

-6.7 20 

-17.8 o~----~----~----~------~----~----~----~ 

o 20 40 60 80 100 120 140 

Scout orbit time, min 

FIGURE 7-16.- "0" AND "E" SECTION TEMPERATURES VS SCOUT ORBIT TIME -

MINIMUM HEATING ORBIT 

The predicted temperatures of each vehicle section,jnsulated as recommended in this study, are 

compared with allowable temperature limits of the components within that section, Table 7-V. The 

component temperature .limits are Qualification levels except for the two motors which are restricted 

by the allowable propellant temperatures for proper ignition. This comparison shows that the allowable temperature limits are exce~ed only in Upper "C" Section skin, without an attached component, 

in the maximum heating mission. The Upper "e" Section, condition can be corrected by (1) flying the 

minimum heating orbit or (2) reducing the 6: 1 ratio of aluminum tape to white paint to reduce the heat 

absorption of the section. Consequently, it is concluded that the Scout upper stages can endure the 

thermal environment of a Shuttle launched mission. 

50 
U1 

-4 

TABLE 7-V.- SUMMARY OF THERMAL ANALYSES 

Component Predicted Temperatures in Vehicle Sections oC (OF) 

Temperature Shuttle orbit 

Vehicle Section Limits 0C (OF) (24 hr after launch) Scout orbit 

Component Minimum heating orbit Maximum he

Minimum Maximum Minimum Maximum Minimum Maximum Minimum 

Upper "C" section 

Rate gyro -17.7 ( 0) 71.1 (160) Skin only Skin only Skin o

Thruster valves - 6.7 (20) 71.1 (160) - 4.4 (24) 1 23.3 (74) 6.7 (44) 146.1 (115) 9.4 (49) 

Relief valves -17.7 ( 0) 71.1 (160) 

Quick disconnects -17.7 ( 0) 135.0 (275) With component With component With comp

H202 tanks - 6.7 (20) 71.1 (160) Attached to skin Attached to skin Attached 

H20 2 4.4 (40) 71.1 (160) 6.1 (43) 13.3 (56) 10.0 (50) 21.7 ( 71) 9.4 (49) 

Pressure regulator -12.2 (10) 80.0 (176) 

Lower "D" section 

Poppet valve elect. -17.7 ( 0) 71.1 (160) 13.9 (57) 16.1 (61) - 2.8 (27) 13.9 ( 57) 15.0 (59) 

Inertial ref. unit -17.7 ( 0) 62.8 (145) 

Guidance battery -17.7 ( 0) 73.8 (165) 

Altair skin 

4th stage TIM xmtr -17.7 ( 0) 80.0 (176) 8.3 (47) 11.1 (52) 3.9 (39) 8.9 ( 48) 9.4 (49) 

Motor propellant 

Antares 10.0 (50) 32.2 ( 90) 22.2 (72) 22.2 (72) N/A N/A N/A 

Altair 4.4 (40) 37.8 (100) 6.1 (43) 6.1 (43) 6.1 (43) 6.1 ( 43) 6.1 t43) 

Note: Predicted temperatures are based on pre-launch temperature of 4.4oC (400F) in payload bay except for Antares propellant w

assumed to have initial temperature of 21.10C (700F) because of ignition temperature restriction. 
8.0 CONCLUSIONS AND RECOMMENDATIONS 

From the results of the structural dynamic, meteoroid damage, and thermal analyses discussed in 

the previous sections the following conclusions and recommendations are made. 

(1) The low frequency response characteristics of the pallet to the Space Shuttle mounting 

system provide significant attenuation of vibration and shock inputs from the Space Shuttle. Vibration isolators will not be effective in further reducing the loads imposed on the Scout vehicle. Therefore, it is recommended that the Scout upper stages and payload be retained in a support pallet of 

tubular construction with rigid bulkheads at each clamping point. The clamping points are required to 

be at the aft end of the Upper "c" Section, each end of the Antares motor chamber, the aft end of the 

Altair motor chamber, and the aft end of the payload or the forward end of the Altair motor chamber. 

The payload requires at least one clamp. Recommended clamping points are shown in Figure 1-2. 

The pallet requires retention in the payload bay of the Space Shuttle by a five point attach. At 

the aft end of the Antares motor chamber, the pallet is fixed to the Space Shuttle payload bay longerons to react up and down loads as well as fore and aft loads. Also at the same station, the pallet is 

attached to the Space Shuttle payload bay keel to react side loads. The forward end of the pallet is 

fixed to the longerons to react the up and down loads. 

(2) Lateral spectral density response at 19 Hz of the Scout "0" and "E" sections to the Shuttle 

random vibration spectrum was higher than the current Scout 95% confidence limits at that frequency. 

Based on previous experience with similar structures, it is concluded that addition of vibration isolators would not be effective in reducing this acceleration level. At all other locations the response levels 

were well below the Scout limits, It is concluded that the response at 19 Hz does not present a 

problem to the structural integrity or reliability of any component. However, to ensure the validity 

of this conclusion, it is recommended that the random vibration test spectrum defined for the Scout 

Standard Environmental Test be expanded to include the frequency range 10-20 Hz when applied to 

components of the Space Shuttle launched Scout upper stages. 

(3) All response loads imposed on the Scout stages are within the present design limits except in 

the E Section (Station 47.8). A redesign of the section will be necessary. 

(4) The sinusoidal test spectrum defined for the Shuttle aborted-mode handling condition is considered unrealistic when applied to heavy structural elements. The sinusoidal vibration should not be 

considered as part of the dynamic environment imposed by the Shuttle mission. 

(5) The acoustical noise level of the Space Shuttle bay is higher than the present land launched 

Scout. However, the difference: in level offers a minimal risk to the Scout upper stages vehicle. It is 

recommended that the risk be eliminated by performing acoustical qualification test on the Scout 

upper stages assembled. vehicle to the spectrum given in Figure 8-1 with an appropriate safety factor 

to establish the test levels. 

52 
Or---------------------------------------------------------~ 

e -5 

::J-

~Qj 

Q) > c.~ -10 -Ce 

C ::J 

::J II) 

~ ~ -15 

-co. 

C-c 

10 C -.20 

.c ::J 

Q) 0 

> II) 

lO- t) Cii -25 

o lii "E~ :c ciI -30 ....... 

~ r:c' 

O-c -35~~~~~~~~~ __ ~L_~~~~~~~~~~~~~~~~~~ 

- 20 31.5 50 80 125 200 315 500 800 1250 2000 3150 5000 8000 

25 40 63 100 160 250 400 630 1000 1600 2500 400 6300 1QOOO 

One-third octave-band center frequency, Hertz 

145 dB(re20J,LN/m2) for 1 min 

FIGURE 8-1.- SPECTRUM TO BE USED IN SCOUT ACOUSTICAL TESTS 

(6) The micrometeoroid analysis yielded an assessed damage probability of .00364 (99.64% 

probability of no damage). This is on the rocket motor cases only and without any thermal protection. It is concluded that this probability is sufficiently small that it is of no consequence. It is 

recommended that this environment be neglected since the addition of thermal protection will 

further enhance the Scout upper stages survivability. 

(7) For the Antares motor with an outside motor case coating of a ten to one ratio of aluminum 

tape to white paint, the bondline and propellant temperatures, for a prelaunch temperature of 490 C 

(1200 F) will not be cooled to meet the upper firing limit temperature of 320 C (900 F). Therefore, 

it is recommended that ground controls maintain the prelaunch Shuttle bay temperature between 

1QoC and 320 C (500 to 900 F) to assure an Antares motor will remain within specified ignition 

temperature limits. 

(8) For the Altair, with an outside motor case coating of a ten to one ratio of aluminum tape to 

white paint, the bondline and propellant temperatures will lie well within'the firing limits of the 

motor for all mission conditions. 

(9) It is concluded that the present thermal protection used on the rate gyro unit is adequate. 

No further thermal insulation is required. 

(10) Upper "c" Section covered with .13 cm (.05 inch) cork coated with a six to one ratio of 

aluminum tape to white paint will maintain temperatures within operating ranges of the components. 

It is therefore recommended that this method of thermal protection be used. 

53 
(11) "0" and "E" Section outside skins wrapped with seven layer superinsulation will maintain 

temperatures within operating ranges of the components. It is recommended that this method of 

thermal protection be utilized. 

With the completion of the design to incorporate these recommendations, the Scout upper 

stages will endure the environments imposed by the Space Shuttle mission. 

54 
Appendix A 

UPDATING OF SHUTTLE PAYLOAD BAY ENVIRONMENTAL CONDITIONS 

At the completion of Task II, Compilation of Environmental Conditions in the Shuttle, Change 13 

was the latest revision to Reference 2. Subsquently,six more changes have been issued, with the most 

recent, Change 19, being released on 2 December 1976. This appendix will update the results of 

Task II.to include the data through Change 19. These datacould not be included in the study; however, in most cases, the revised data are less severe than used in the study so that the conclusions and 

recommendations are still valid. The referenced paragraph numbers are from Reference 2. 

1. Electromagnetic Interference (EMI), paragraph 4.2.2.8. 

In Change 13, EMI was TBD and was subsequently defined in Change 18, released on 

14 October 1976. A cursory review indicates no problems are anticipated. 

2. Pressure Altitude, paragraph 4.2.2.1 

Figure 4-2, 4-3, and 4-4 were revised by Change 16 but the revisions have no effect on 

the results of this study. 

3. Acceleration crash loads, paragraph 7.6.1 

Table 7-13 was added by Change 19 and revised the emergency landing design load factors 

in the + X direction from 9 g (Change 13) to 4.5 g (Change 19). The results of the study are 

still valid. 

4. G round Purge, paragraph 4.2.1.2. 

Change 13 stated that the ground air purge temperature is selectable over a range of 7.20 -

48.80C(45 - 1200F). Change 18 revised the limits to 7.2 - 37.80C (45 - 1000F). The 

results of the study are still valid. 

55 
REFERENCES 

1. Scout/Shuttle Integration Study Final Report, NASA CR-121173, April 1973. 

2. Space Shuttle Systems Payload Accommodations, JSC Report .07700, Volume XIV, Revision 0, 

Change 13,22 December 1975. 

3. Micrometeoroid Environment Model (Near Earth to Lunar Surface), NASA SP-8013, March 1969. 

4. Orbital Mechanics of Satellites, Article from Proceedings of the American Astronautical Society 

Western Region Meeting by G. S. Gedeon, 1958. 

5. An Introduction to Celestial Mechanics, F. R. Moulton, MacMillan Company, N. Y., 2nd Edition, 

1914. 

6. Customer Utilization Instructions - Program Heat II, Computer Technology, Inc., April 1963. 
1. Report No. I 2. Government Accession No. 3. Recipient's Catalog No. 

NASA CR-3328 

4. Title and Subtitle 5. Report Date 

Environmental Protection Requirements for Scout/Shuttle September 1980 

Auxiliary Stages 6. Performing Organization Code 

7. Author(s) 8. Performing OrganIzation Report No. 

G. L. Qualls, s. S. Kress, W. W. Storey, and 

P. N. Ransdell 

10. Work Unit No. 

9. Performing Organization Name and Address 

Vought Corporation 11. Contract or Grant No. 

Dallas, Texas 75265 NASl-12500 Task R-153 

13. Type of Report and Period Covered 

12. Sponsoring Agency Name and Address Contractor Report 

National Aeronautics and Space Administration 14. Sponsoring Agency Code 

Washington, DC 20546 

15. Supplementary Notes 

Langley Technical Monitor: Thomas L. Owens 

Final Report 

16. Abstract 

A study was conducted to determine the requirements for enabling the Scout upper 

stages to endure the expected temperature, mechanical shock, acoustical and mechanical 

vibration environments during a specified Shuttle mission. The study consisted of: 

determining a Shuttle mission trajectory for a 545 kilogram (1200 pound) Scout payload; compilation of Shuttle environmental conditions; determining of Scout upper 

stages environments in Shuttle missions; compilation of Scout upper stages environmental qualification criteria and comparison to Shuttle mission expected environments; 

and recommendations for enabling Scout upper stages to endure the expected Shuttle 

mission environments. 

17. Key Words (Suggested by Author(s)) 18. Distribution Statement 

Scout Unclassified - Unlimited Shuttle 

Upper stages 

Environment Subject Category 15 Requirements 

19. Security Oassif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price 

Unclassified Unclassified 64 A04 

For sale by the National Technical Information Service, Springfield, Virginia 22161 

NASA-Lang1 ey. 1980 
End of Document