6 JUNE 1968 

HANDLING 

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STRUCTURAL CRITERIA FOR LABORATORY 

VEHICLE FOR THE MOL PROGRAM 

SAFSL EXHIBIT 30044 

r72., SPECIAL 3e1 - • tc, 

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L - 6003 

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Systezts Pro&ram Office Ci 

B. A. Knight 

-■-dt•bite'r"tfl LLIUiL IiiillULliiU 

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• 

REVIEW OF 

SAFSL EXHIBIT 30044 

STRUCTURAL CRITERIA FOR LABORATORY ti 

VEHICLE FOR THE MOL PROGRAM 

May 22, 1968 

The undersigned has reviewed the document and understands 

the contents to the extent necessary to scope subsequent 

proposals. 

General. Electric Comp:tny 

. C. Abbate 

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As not.cd 

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E 

—4 astr.-.4-1,1k 

• S1,4 \r",e, c:4■11* 

NOTE: Signature acknowledges agreement 

vi.th-this:dOcument, but such 

agreement does not extend to the 

documents referenced herein which 

axe not yet agreed upon. 

4 w 

Aercispace Corporation 

R. H. Herndon • 

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Pale 3oft ist,„ SPECIAL 

--tretrr sy MAL 

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30044 

ACTION ITEMS 

DAC, OE, EK to provide for all pressurized systems the following: item, 

location, internal volume, operating pressure, proof and ultimate design 

factors of safety and associated justification, Which are not in compliance , 

with WRT range documentation.. (AFWTRM 127-1 and 1 STRADM 127-200) due • 

23 July 1968. 
Nomr.rrriPir 1.11 i.vhilL lislisL)1.111U 

- ;•• 

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SAFSL EXHIBIT 30044 

MANNED ORBITING LABORATORY (MOL) 

STRUCTURAL CRITERIA FOR THE LABORATORY VEHICLE 

• 

. I. INTRODUCTION 

(M) A. Scope 

This document presents the basic requirements and information governing 

the structural design for the Orbiting Vehicle system less Gemini B of 

the 1. armed Orbiting Laboratory System (MOL). 

Included herein are the following: 

1. Basic facts and references pertinent to the structural design. 

2. Basic objectives for the philosophy of structural design. 

3. Conditions and environments for which the vehicle must be investigated 

and designed. 

4. Requirements for establishing loads and other environmental factors for 

the design conditions. 

5. Definition of terms. 

(R) B. Authority 

This document shall govern the design of all vehicle structural 

. components. Any deviation from these requirements shall be noted by 

formal request to the SPO with proper justification included. 

(R)- C. Intent 

The intent of these criteria is to provide a set of design conditions, 

requirements, and objectives which, when implemented, will ensure that 

the structural components achieve acceptable and compatible structural 

integrity. 

All deliverable data and/or documentation specified in this exhibit shall 

be in accordance with the respective contractor's CDRL (DD 1423 or 

equivalent) as detailed by Forms 9. . 

SECRET SPEC! 11A;1111.13 
L -6003 

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LVI111. 1111,1WL.13111.7 

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II. DEFINITIONS, NC:ENCLATURE, AND REFERENCES 

(M) A. Definitions 

1. Limit Load--The maximum anticipated load, or combination of loads, 

which a structure may be expected to experience during the 

performance of specified missions in specified environments. 

2. Ultimate Load--Obtained by multiplying the limit load by the 

ultimate factor of safety. 

• 

3. Factor of Safety--An arbitrary value to account for uncertainties 

and variations from item to item in material properties, 

fabrication quality and details, and internal and external load 

distributions. 

4.. .Ap3p_jad'I'elLmeratures--Maximum.calculated temperatures to which the 

structure will be subjected during the performance of specified 

missions in specified environments. 

5. Critical Condition--A loading or temperature condition, or 

combination thereof, which dictates the design of a portion of the 

structure. 

6. Failure - -A structure is considered to have failed when it can no 

-.longer perform its intended function. FailureNof a. structure may 

result in loss of the vehicle, or any part thereof, and may 

present a hazard to operating personnel. 

Excessive Deformations--Deformatiors, elastic or inelastic, 

-resulting from application of loads and temperatures are 

excessive when any portion of the vehicle structure can no longer 

perform its intended function. 

8. Pressure Vessels and Components--Containers that must sustain an 

internal pressure; e.g., inhabited areas, propellant tanks, solid 

motor cases, nozzles, thrust chambers, liquid or gas storage 

bottles, plumbing, tubing, piping, etc., but not adapters, 

interstages, skirts, or fins, even though these are acted on by 

internal pressure. 

9. Nominal Pressure--The rated operating pressure of the system. 

10. Maximum Expected Operatinq Pressure (MEOP)--The maximum anticipated 

operating pressure including the effects of temperature, transient 

peaks, and variations in pressure and-vebicre acceleration. 

11. Limit Pressure--Same as MEOP above: 

12. Ultimate Pressure--The limit pressure multiplied by the appropriate 

safety factor. 

.SECHT SPECInt EIANDIM 

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13. Proof Pressure--That pressure which is applied,to a pressure vessel 

for the purpose of an acceptance test. The proof pressure is 

derived by multiplying the limit pressure (MEOP) by the proof 

pressure factor of safety.. (An acceptance proof pressure test 

is a test conducted under the appropriate environmental condition*, 

including temperature, for each class of pressure vessels.) 

14. Proof Pressure Factor--The proof pressure factor shall be defined 

for each class of pressure vessel utilized in the, system. The 

proof pressure factor shall be selected to demonstrate a 

predetermined minimum margin of safety with respect to the MEOP 

and shall include the effects on material properties resulting 

from differences in the test temperature and the design temperature. 

The nominal stress at proof pressure shall be less than the 

minimum guaranteed yield strength of the material. 

15. Burst Pressure--Burst pressure is the pressure which an article 

must sustain without rupture. Burst pressure is the ultimate 

pressure adjusted for the effects on material properties 

resulting from differences in the test temperature and the design 

temperature. (A burst test is a test conducted under the 

appropriate environmental conditions*, including temperature, 

for each class of pressure vessels.) 

16. Erection Phase--That time period from erection of the launch 

- vehicle to removal of the gantry or other external support. 

1T. Prelaunch Phase--That time period from removal sof gantry or other 

support until vehicle liftoff. 

18. Launch Phase--That time period from vehicle liftoff until the 

launch transients damp out. 

19. Ascent Phase--The ascent phase covers.the time period from launch 

transients dampout to ascent vehicle burnout. . 

20. Orbit Phase--That time period from ascent vehicle burnout to 

deorbit. 

21. Descructive flutter is considered to be flutter of a catastrophic 

nature (rapid breakup of structure) and limit-amplitude flutter 

which will cause functional failure of equipment or structure. 

22. Thrust Termination Condition--This condition is composed of axial 

loads due to oscillating longitudinal thrust forces caused by 

"blowing" the Stage "0" forward thrust ports in combination with 

lateral loads (shear and bending moment) from time compatible air 

loads conditions. This condition ig-aeged.by-am,abort event and 

can occur at any time during Stage,"0"-flight. ,The ultimate factor 

of.safety to be used for this condition is 1. 10. 

* Appropriate environmental condition, i.e., an especially 

suitable substitute conditon or a direct simulation of the design 

condition. f. 

L-6 0 0 3 

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!SECRET SPECIAL lifialLING 1 Page,G ofd, 

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• SECRET SPECIAL 

(14) 

(R) 

B. Nomenclature 

32 feet per second squared 

feet per second 

miles per hour 

pounds per square foot 

diameter of meteoroid, inches 

.density of meteoroid, gms/cc 

weight density of the wall material, lb/in.3 

meteoroid velocity, fpsVelocity of an elastic wave along the axis of a slender 

prismatic bar of the target materials, fps 

grams 

cubic centimeter 

million electron volts 

steradian, unit of solid angular measure 

kilometers per second 

C. Imlicable Documents 

The following documents, of the exact issue indicated, are applicable 

to the extent specified. Documents called out are applicable as 

specified herein. 

MIL-RDBK-5 Strength of Metal Aircraft Elements, 

Nov 1964 

MIL-RM.-17 Plastics for Flight Vehicles 

g 

fps 

mph 

. 

= 

= 

psf = 

d = 

Pi 

V = 

gins = 

cc = 

MeV 

STER = 

kmps = 

SAFM 30033 

SAFSL 10011 

SAFSL 30012 

Environmental Design Criteria for MOL 

System Lab Module and Mission Module 

and Associated AGE. 

Crew Systems-Design Comnibility 

Criteria for the MOL. Program, 

1 November 1967, Preliminary 

Design Loads Criteria for the MOL 

Orbiting Vehicle 

--grafft SPECIAL MIRING 

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- SECRET SPECriL R18*,1°I n O 

-17M7Trers- vs i.visit. iscssius.assu 

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E.- 

NIL-M-8555A Missiles, 'alided: Design and 

Construction General Specification for, 

6 October 1960 

SS-MOL-1B System Performance andTesign Requirements General Specification 

Where .a conflict occurs between the .applicable documents and SAFSL. 

Exhibit 30044, the latter shall govern. 
-Hitt SPECIAL 11111111111IG 

-Ortiltrr 111-11111LIOU 

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III. DESIGN CRITERIA 

(R) A. General 

(R) 

The structure shall possess sufficient strength, rigidity, and other 

necessary characteristics required to survive the critical loading 

conditions and environments that exist within the envelope of mission 

requirements. It shall survive those conditions and environments in' 

a manner that does not reduce the probability of successful completion 

of the Mission below the prescribed limit. 

Consistent with the structural design principles and assumptions listed 

herein and in NIL-M-8555A, the structure shall be designed to achieve 

minimum weight wherever practicable. Proper consideration shall be 

given to the affect on system cost and development schedule. 

The structure shall be designed by the critical flight conditions 

wherever possible. It shall be an objective that the nonflight 

conditions and environments shall not increase the flight weight over 

that required for the flight conditions. 

1. Design Conditions and Environments 

The environmental phenomena corresponding to each design condition 

shall include all factors that can influence the structural 

design and typically include heating, vibration, shock and 

acoustics, in addition to quasi-static and dynamic loads. Consideration shall be given to the deteriorating effect of prolonged 

exposure to the space environment. Where possible all such 

phenomena shall be determined statistically. 

a. External and Internal Load Distribution 

(R,T) 

(R,T) 

(BT) 

External loads shall be determined by conservative analyses 

of the design environment. The aerodynamic loads may be 

determined from appropriate wind tunnel tests or calculated 

by conservative methods considered to be sound engineering 

practice. The effects of aeroelasticity on the distribution 

and intensity of loads shall be considered. 

The internal structural load distribution shall be determined 

by rational analyses. Effects of deformations, nonlinearities, 

and temperature on internal load distribution shall be included 

in analyzing the load distribution. 

b. Combined Loads 

• 

and Internal Pressure 

When internal pressure effects in combined load conditions 

are stabilizing or otherwise beneficial to structural load 

Capability, the nominal internal operating pressure for that 

condition shall be used instead of the ultimate design internal 

pressure in the loads analysis. 

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(ET) 

(R,T) 

(R,T) 

Malfunctions 

The vehicle structure shall not be designed to withstand loads 

produced by any subsystem nalfunction that would otherwise 

result in failure to accomplish the mission. Malfunctions 

shall not result in structural failures which jeopardize the 

probability of successful crew abort. 

d. Nisaliement and Dimensional Tolerances 

The effects of allowable structural misalignments, control' 

misalignments, and other permissible and expected dimensional 

tolerances shall be considered in the analysis of all limit 

loads, loads distributions, and structural adequacy. 

e. Dynamic Loads 

Dynamic loads shall be determined for all quasi-static and 

transient phenomena expected in each design environment. The 

calculation of all dynamic loads shall consider the effects of 

vehicle structural flexibilities and damping and coupling of 

structural dynamics with the control system and the external 

environment. A final set of dynamic loads shall be determined 

utilizing experimental values of structural flexibilities and 

• dynamic charcateristics as obtained from appropriate tests and 

assembly modal surveys. 

f. Load and Thermal Fatigue 

The effects of repeated loads and elevated and/or cryogenic 

temperature will considered in the structural design. The 

design structural adequacy of the 'vehicle in flight shall not 

be impaired by fatigue damage resulting from exposure to 

nonflight and launch environments.' 

(R,T) g. Vibrational and Acoustical Loadings 

The effects of the vibrational and acoustical environment shall 

be accounted for in design wherever possible by rational 

analysis and/or test of the response of the dynamic system to 

..the environment. 

(R,T) h. Creep Deformation 

The effects of permanent creep deformation shall be considered. 

by rational methods of analyses; Where not otherwise critical, 

e.g., alignment, apermanent deformation of 1 percent shall 

be considered. as the maximum permissible. value . • • . 

(R,T) i. Thermal Stresses 

Thermal stresses shall be combined with the appropriate load 

stresses when calculating requited strength. -Thermal stresses 

shall be based on the applied temperature, and shall be 

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. considered limit values. . 

SECRET SPECIAL tILIID1I3 
These values are to be consistent with overall reliability 

.requirements. 

3. Strength Reouirements 

",Lblitt 1)10.tlitL 

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(B) 

(R,T) 

2. Material Properties and Allowables 

a. Material strengths and other mechancial and physical properties 

shall be selected from sources of reference, such as 

NIL,HDBK-5 and MIL-HDBK-l7, and contractor allowables when 

appropriate. Strength allowables and other mechanical 

properties used shall be appropriate to the loading conditions, 

design environments, and stress states for each structural 

member. 

b. Values 

Allowable material strengths used in the design shall reflect 

the effects of load, temperature, and time associated with 

the design environment, either individually or in combination, 

as applicable. Allowable yield and ultimate properties are as 

follows: 

1) For single load path structures, the minimum guaranteed 

values are to be used. 

2) For multiple load path structures, the 90 percent 

probability values are to be used. 

a. At Limit Load 

The structure shall be designed to have sufficient strength to 

withstand the limit loads resulting from aerodynamic pressures, 

inertia accelerations, applied temperature, etc., which 

combine at any one time to result in the highest induced 

stresses and minimum allowable without experiencing plastic 

deformation or excessive elastic deformations. 

b. At Ultimate Load 

The structure shall sustain the ultimate loads (plastic deformation permissible) resulting from aerodynamic pressures, inertia, 

acceleration, applied temperatures, etc., which combine at any 

one time to result in the highest induced stresses and minimum 

allowables. 

t 

c. Margin of Safety 

• 

Margin of safety is defined as MS = 1/R 1, where R is the 

- ratio of applied load (or stress, as applicable) to the 

allowable load (or stress). In determining the factor R, the 

effects of combined loads or. stresses (interaction) shall be 

included. 

L - 6 0 03 

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(R,T) 

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For minimum weight, the structural design shall strive for 

the smallest permissible margins of safety, which shall be 

zero, except in certain specific instances where specified 

finite values may be.reauired. 

(R) 

(R,T) 

4. Stiffness Requirements 

Under Limit Loads 

The structure shall not experience permanent deformation at 

limit load and in the appropriate design environment. 

b. Under Ultimate Loads 

Structural deformations shall not precipitate structural failure 

during any design conditions and environment at loads equal 

to or less than ultimate loads. 

c. Aeroelastic Requirements 

Destructive flutter or related dynamic instability or divergence 

phenomena shall not occur on the vehicle, or its components, 

at any condition along the design trajectories. To ensure 

safety, it shall be shown by analytical or experimental data, 

or both, that at any altitude along the trajectory, an increase 

of 30 percent in the dynamic pressure Will not result in 

destructive flutter or divergence. 

Internal Support Structure 

The basic chassis of the components (Ref. Para 3.10 SAFSL 

Exhibit 30012) and the immediate support structures shall have 

fundamental resonant frequencies greater than 30 cps. 

Vibration isolator techniques and/or associated analyses which 

evaluate the design adequacy must be provided for SPO approval. 

5. Thermal Requirements 

The effects of temperature shall be considered in design of the 

vehicle. Thermal analysis shall be based on rational transient 

analysis of heat fluxes from aerodynamic heating, engine exhaust 

-gas radiations, engine system and electronic equipment heat sources, 

including consideration of the heat sink effect of the mass of 

structure, fuel, and equipment. 

Aerodynamic heating shall be based on the design trajectories 

(Para. III-B). Aerodynamic heating rates shall be calculated by 

use of techniques considered to be cznalid-vnginiering practice. 

, - 

Thermal effects on the structure, including heating rates, temperatore, thermal stresses, and deform ations, and mechanical and 

physical property changes will be based on critical design heating 

environments. 
ii.b111L 

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6. Factors of Safety 

(B) a. Plight Loads 

Air Loads, Dynamic Loads, 

Pressure Loads (Venting, 

Buffeting, etc.) 

KA Mode* 

KB Mode* 

Thrust Loads 

Thrust Termination Loads 

(other than normal staging 

conditions) 

b. Nonflight Loads (Other than 

pressure) 

Limit., 

• Ultimate 

1.00 1.40 

1.00 1.25 

1.00 1.25 

N/A 1.10 

Dangerous to personnel 1.00 1.50 

Non-dangerous to personnel 1.00 1.25 

• *.Reference SS-MOL-1B 

Pressure Loads 

Limit 

Propellant Storage Tanks 1.00 • 

Cryogenic Storage Tanks 1.00 

Rocket Motor Cases 1.00 

Thrusters 

Pressurized Cabins (On-Orbit) -4.00 

'Minimum 

Proof Ultimate 

• 

1.50 2.00 

1.50 2.00 

1.50 2.00 

1.33. 2.00 

1.50 2.00 

2.00 4.00 

Pneumatic Systems Components 

a. Heat exchangers, accumulators, 1.00 

fans, blowers, valves, 

filters, regulators, pressure 

switches, pressurant tanks, 

quick disconnects. 

b. Lines (tubing), fittings, 1.00 

hoses 

Hydraulic Systems Components 

a. Heat exchan

• 

gers, (including." 1.50: 2.00 

cold plates & cold panels), 

• accumulators, pumps, valves, 

filters, regulators, pressure 

switches, pressurant tanks, 

quick disconnects. 

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b. Lines (tubing, including 

radiator tubes), fittings, 

hoses \ 

Propulsion System Components 

Lines (tubing), hoses (flexible), valves, filters, 

regulators, switches, 

fittings (connectors) 

Reactants Supply System Components 

Lines (tubing), valves, 

_ fittings (connectors) 

Fuel Cell System Components 

Valves, regulators, heat 

exchangers, gas pressure 

vessels 

Pressurized Electronic System 

Components 

*Minimum 

Limit Proof Ultimate 

1.00 2.00 4.00 

1.00 2.00 4.00 

1.00 2.00 4.00 

1.00 1.50 2.00 

1.00 1.10 1.50 

Containers (black boxes) 

and battery boxes. 

(11) d. Thermal Loads 

. Thermal Loads/stresses 1.00 Not 1.00 

Applicable 

(T) e. When substantiated by rational analysis that factors of safety 

lower than those listed above are consistent with attainment of 

specified probabilities of mission success/crew safety, such 

factors shall be substituted. This does not apply to 

minimum proof safety factors. 

B. Design Phases 

(R) 1. Ground Phase 

Structtral design considerations skill include consideration of 

all environaents to which structure and its component parts are 

exposed during manufacturing, handling, transportation, erection, 

• 

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and storage. Except for local attachments and structure such as 

ground bearing structure, the ground loads shall not govern design 

of the structure,,if practicable. 

Minimum value to be used at equivalent operating environment or 

paragraph II, A, 14 Definitions, vhichever higher. 
6003- 

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SEMI SPECUI 1111111MG 

fimIelf111. SSSSSS 1411.11%•4 

• A • 

• 

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(R) 

(R,T) 

(R,T) 

(R,T) 

2. Prelaunch and Erection Phases 

The vehicle shall be capable of sustaining all prelaunch and erection 

design.loads as specified in SAFSL Exhibit 30012. 

3. Launch Phase 

The vehicle shall be capable of sustaining all design load conditions 

as may be experienced during launch operations as - specified in 

SAFSL Exhibit 30012, Consideration shall be given to the loading 

and environment induced by abort during this phase. • 

Ascent Phase 

The vehicle structure shall be designed for the entire power 

flight environment as specified in SAFSL Exhibits 30003 and 

30012. Consideration shall be given to the loading and 

environment induced by abort during this phase. 

5. Orbit Phase • 

The vehicle shall be designed for geophysical environments and 

loading conditions associated with orbital flight. 

• The design of the vehicle and 

not limited to, consideration 

its parts shall be based on, but 

of the following conditionS; 

a. Maneuvering Loads 

(R) Loads resulting from maneuvers for changing orbits, orbit 

adjust, attitude control, etc., as well as any other 

'maneuver necessary for the completion of the mission shall be 

determined and shall include the interaction of the propulsion 

system and the guidance and/or control system With the 

flexible vehicle. 

Meteoroid Environment 

(R) The MOL vehicle will encounter a flux of meteoroids as it orbits 

the Earth. The magnitude and characteristics of this flux 

shall be taken as specified in Section 3.2.5.e of SAFSL 

Exhibit 30003. The vehicle structure, pressurized volumes, 

space radiators (tubes and also fins, if used as part of the 

meteoroid protection structure), solar panels, etc., shall be 

designed to achieve the required probability of no destructive 

penetrations by neteoro5ds for the duration of the mission. 

A destructive penetration is one which impairs the function 

of the punctured element. The;following- criteria shall be 

utilized: 

_ 

1) Meteoroid Penetration - The minimum thickness of structure 

necessary to resist penetration by a. meteoroid mass less 

than a given mass, m, shall be determined from the formulas 

given in this paragraph. 
a)iinsie Plate Wall 

The thickness-mass relationship for a single plate 

wall shall be taken as 

t = 148 K ( m ) 1/3 

1 Et 

p

t 

SECP,ET SPECIAL EILIDLING 

NRO APPROVED FOR 

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where 

t is the thickhess of the wail, in. 

is the meteoroid mass, gm 

is Young's modulus of the wall material, 

psi 

p

t is the weight density of the wall material, 

K1 is the single plate effectiveness factor. 

To prevent perforation only, Kishall be taken as 

1.5. To prevent spalling of the inner face as veil 

as perforation, i.e., space radiator tube application, 

K1 shall be taken as 2.25. 

b) Double Plate Wall 

The thickness-mass relationship for a double plate 

wall shall be taken as 

= 222 K ( ).l/3 

2 

m 

 t pt 

where 

t is the total thickness required to prevent 

perforation, in. 

K

2 is the double plate wall effectiveness factor 

boa, Et, and pt are defined above] 

The effectiveness factor, K ' depends on wall spacing 

and on whether or not an..ene2

zzgy absorbing filler is 

used. The values of Ko giyen in Table 1 'shall be 

used as appropriate: The values of'K2 for use with 

an energy absorber apply to flexible, open cell 

polyurethane foam of density 1.5 to 2.0 lb/cu ft. 

Other materials may be used, provided an equivalent 

effectiveness can be demonstrated. 

lb/cu inch 

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the thickness of the cuter plate or shield must be 

from 15 to 25 percent of the total thickness required 

in order that optimum shield effectiveness and the 

values of K2 

listed in Table 1 can be applicable. 

c) The penetration equations given in Paragraphs III.B. 

5.b.1.(a) and (b) are primarily for aluminum 

alloy but are considered adequate for most conven-. 

tional structural materials. 

(R,T) 

. Radiation Environment 

The effect of both natural and artificial radiation environment 

shall be considered in designing the structure, radiators, solar 

panels, etc., including not only the deterioration and induced 

radiation effects on the materials, but also the shielding that 

may be required for human occupants and sensitive equipment. 

The radiation environment is specified in SAFSL Exhibit 30003. 

d. Other Environments 

Other environments, both natural. nd induced, to be used in the 

structural design of the vehicle are given in SAFSL Exhibits 

30003 and 10011. All items and components shall be designed 

for the most severe environmental conditions with consideration 

of both operational and nonoperational states. 
..,,,-CASE I 

Two plates spaced h inches apart. 

No filler between plates. 

2 

1.0 0.50 

1.5 0.35 

2.0 0.27 

CASE II 

Two plates spaced h inches apart. 

Low-density foam energy absorbing medium between plates. 

K

2 

1.0 0.33 

1.5 0.25 

2.0 0.20 

CASE III 

Two plates spaced h inches apart. 

Honeycomb with axis of cells normal to plates. No filler 

in cells. 

h < 1.0 K2 = 1.0 

b > 2.0 K2 = 0.7 . 

- 

Use a straight line interpolation of K2 between'h = l and 

h = 2. 

414'1MT arEtau HiUiLMMU 

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TABLE 1 

-EFFECTIVENESS FACTOR FOR DOUBLE PLATE 

WALL CONSTRUCTION, K2 

SECRET SPECIAL IIANDLIiIPJ 

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APPENDIX I 

-III-A.1.a. External and Internal Load Distribution - Second 

paragraph (internal loads). 

b. III-A.l.e. Dynamic Loads 

c. III-A.5 Thermal Requirements 

SECRET SPEChlt 11.`MLial 

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EK DEVIATIONS TO SAFSL EXHIBIT 30044 STRUCTURAL CRITERIA 

FOR LABORATORY VEHICLE FOR THE MOL PROGRAM 

1. Under paragraph II-C, Applicable Documents and also paragtraph II-A-2-a, 

MIL-HDBK-17, Plastics for Flight Vehicles shall not apply to tg until 

this document has been reviewed and agreed upon by EK. 

2.- Under paragraph II-C, Applicable Documents and also paragraph III-A, 

maL41-8555A, Missiles, Guided: Design and Construction General Specification for, 6 Oct. 1960 shall not apply to EK until this document 

has been reviewed and agreed upon by EK. 

3. The following paragraphs are not directly applicable to EK: 

a. III-A.l.a. External and Internal Load Distribution, first paragraph 

(External loads). 

b. III-A.4.c. Aeroelastic Requirements - Does not apply by virtue of 

non-exposure of EK equipment to this environment. 

III-B.5.b. Meteoroid Environment - )tot applicable by virtue of., 

nOn-exposure. 

/// h. The EK effort to accomplish the requirement or task shall be confined to 

EK equipment only. All information or other data necessary to accomplish 

said effort or task will be furnished by the customer or associate 

contractors as applicable.