NRO A PROVED, 

RELEA E 1 JUL* YW.k 

DO'cumenk'No. 

'',ZAft' -Cop 

REPORT NO. 

TOR-469(5527-39)-1 

Pressure Suit and Extravehicular 

Performance Data for MOL 

FEBRUARY 1965 

Prepared by 

SPECIAL STUDIES DIRECTORATE 

Manned Orbiting Laboratory System 

Manned Systems Division 

Prepared for COMMANDER SPACE SYSTEMS DIVISION 

AIR FORCE SYSTEMS COMMAND 

LOS ANGELES AIR FORCE STATION 

Los Angeles, California 

EL SEGUNDO TECHNICAL OPERATIONS• AEROSPACE CORPORATION 

CONTRACT NO. AF 04(695)-469 

PROPERTY OF 

AEROSPACE C2::PORATION 

RETURN TO LIBRARY 
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Report No. 

TOR-469(5527-39)-1 

PRESSURE SUIT AND EXTRAVEHICULAR 

PERFORMANCE DATA FOR MOL 

Prepared by 

Special Studies Directorate 

Manned Orbiting Laboratory System 

Manned Systems Division 

El Segundo Technical Operations 

AEROSPACE CORPORATION 

El Segundo, California 

Contract No. AF 04(695)-469 

February 1965 

Prepared for 

• 

COMMANDER SPACE SYSTEMS DIVISION 

AIR FORCE SYSTEMS COMMAND 

LOS ANGELES AIR FORCE STATION 

Los Angeles, California 
R. 

Bioastronautics 

Special Studies Directorate 

Manned Systems Division 

. E. Rober 

utics 

-BSI5 i°ecaial Studies Directorate 

Manned Systems Division 

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Report No. 

TOR-469(5527-39)-1 

PRESSURE SUIT AND EXTRAVEHICULAR 

PERFORMANCE DATA FOR. MOL 

Prepared by 

W. C. Hayden 

Experiment Liaison 

MOL Experiments Development 

Special Studies Directorate 

Manned Systems Division 

Approved by 

H. W. Nordyke, Director 

MOL Experiments Development 

Special Studies Directorate 

Manned Systems Division 

S. M. Te 

Assoc. Group Director 

Special Studies Directorate 

Manned Systems Division 

The information in a Technical Operation Report is developed for a particular 

program and is therefore not necessarily of broader technical applicability. 

El Segundo Technical Operations 

AEROSPACE CORPORATION 

El Segundo, California 
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PART I CONTENTS 

Page 

1. 0 INTRODUCTION I - 1 

1. 1 Purpose I- 1 

1. 2 Scope I- 1 

1. 3 Criteria I- 2 • 

2. 0 PERFORMANCE AND DESIGN DATA 1-3 

2. 1 Motion Limitations 1-3 

2. 1. 1 Neutral Position 1-3 

2. 1. 2 Motion Limits 1-3 

2. 1. 3 Mobility 1-3 

2. 1.4 Arm Mobility I-5 

2. 1. 5 Egress Motion 1-9 2. 1. 6 Hand Dexterity I-12 2. 1. 7 Ballooning Measurements 1-12 

2. 2 

2. 3 

Visor Data 

2. 2. 1 Clear Visor Properties 

2. 2. 2 Antiglare Visor 

2. 2. 3 Visor Quality Assurance 

2. 2.4 Helmet Angular Visibility 

Suit Dimensions 

I-14 

IL14 

1-18 

1-18 

I-19 

I- 20 

2.4 Environmental Data 1-20 

2. 5 Life Support Provisions 1-23 

2. 6 Instrumentation Provisions 1-25 

2. 7 Damage Resistance 1-26 

2. 8 Waste Disposal Provision 1-26 

2. 9 Food Handling Provisions 1-26 

2. 10 Interface Provisions I-26 

2. 11 Bioinstrumentation and Communication 1-29 

- 
I-1. 

PART I FIGURES 

Total Number of Contacts for Each Body Segment for 

Suit: (A) Body Clearance; (B) Egress Configuration; 

Page 

and (C) Conditions 1-4 

1-2. Spatial Configuration of Console Array Distances 

with Average Performance Scores for Each Location I-6 

1-3. Total Performance Time for the Push Button 

(% Decrement in Performance vs Control Location) 1-7 

1-4. AP-22s-2 Arm Reach Envelope 1-8 

1-5. Egress Motion 1-10 

1-6. Visor Critical and Non-Critical Optical Areas I-15 

1-7. Portable Life Support System Schematic 1-24 

1-8. MOL Extravehicular Space Suit I-27 

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PART I TABLES 

Page 

Reach Capability Wearing G-3C Full Pressure 

Suit (One Subject) 1-5 

1-2. Functional Arm-Reach Test - X-20 Full Pressure 

Suit (Three Subjects) 1-9 

1-3. Dexterity Test Summary and Percentage 

(n = 17) - AP-22s-2 Suit I-12 

1-4. Hand Dexterity - X-20A Suit - Mean Percentile 

Totals I-12 

1-5. Gemini Full Pressure Suit - Pressure Growth 

Increments - Standing 1.-13 

1-6. Gemini Full Pressure Suit - Pressure Growth 

Increments - Seated 1-13 

1-7. Example for Calculation of Spectral 

Transmittance Deviations I-17 

1-8. X-20 Full Pressure. Suit Field of Vision Test 1-19 

1-9. MOL Extravehicular Space Suit Environmental 

Design Requirements 1-21 

-v- 
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PART II CONTENTS ' 

Page 

1 . 0 INTRODUCTION II-1 

2. 0 ELAPSED TIME 

3. 0 ALLOWABLE DUTY TIME 11-4 

4. 0 WEIGHT FACTORS 11-8 
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PART II FIGURES 

II-1. Maximum Crew Duty Cycles, 

Station (Three Cases) 

11-2. Maximum Crew Duty Cycles, 

Station (One Case) 

Two-Man 

Four -Man 

Page, 

II-5 

II -6 
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PART II TABLES 

Page 

II-1. Weight Factors, Life Support 11-9 

11-2. Weight Factors, AMU II-10 

11-3. Weight Factors, Unmanned Maneuvering Unit II-11 
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• 

S 
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PART I 

PRESSURE SUIT DATA 

• 
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1. 0 INTRODUCTION 

1.1 Purpose 

The characteristics and performance information, derived from a number of 

pressure suit tests and specifications, are presented herein to assist in the 

design of extravehicular operations. Assembly, alignment, and servicing of 

large structures is a primary objective of the MOL program, and MOL suit • 

development should support this objective to a maximum extent. 

1. 2 Scope 

Since extended duration operations with minimum restraint during extravehicular assembly are desired, the requirements for the MOL extravehicular 

suit are similar in many respects to the requirements of the Apollo suit. 

Therefore, the Apollo suit technology (viz, that represented by the A-5H 

prototype garment) embodies many characteristics desirable in the MOL 

extravehicular suit. Water cooling may be required to reduce body water 

losses from perspiration during high metabolic energy expenditures. Performance data on the A-5H type suit was not available for inclusion in this document; 

thus, design and performance data from numerous pressure suit tests, including 

G-4C suit specification data, is presented. This data is intended for use as a 

guide and, in general, it can be expected that the-MOL suit will provide improved 

mobility and dexterity. 

The MOL mission profile imposes two extremes on suit design and development: 

(1) The first requirement is for a flight suit to be worn in the Gemini B capsule 

during launch and re-entry. This suit must be compatible with the flight operations and ejection seat, and with the MOL tunnels and hatches; the environment 

and lower torso mobility is less stringent than for the extravehicular mission. 

(2) The second requirement is for EVA, where environmental and task design 

constraints challenge the current suit state-of-the-art. 

I-1 
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• 

Two suits may be necessary to provide maximum crew performance for the 

flight (G-4C type) and extravehicular modes (A-5H type); however, every effort 

will be made to integrate both requirements into a one-suit concept without 

degradation of suited-operator performance. 

1.3 Criteria 

The MOL space suit (or suits) will be designed to withstand launch, on-orbit, 

and re-entry environments as defined in the MOL General System Specification 

and associated Work Statement. 

1-2 
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2.0 PERFORMANCE AND DESIGN DATA 

2.1 Motion Limitations 

2.1.1 Neutral Position 

The suit neutral positions cannot be determined until the suit has been 

fabricated; however, the NASA G-2C suit neutral position may be used as 

an approximation. Details may be obtained from David Clark Company 

Drawing No. S-964. 

2.1.2 Motion Limits 

The gross motions necessary for transfer, locomotion, and soaring tasks 

require 30 to 60 percent more time for the suited condition than for the 

unsuited condition. Normally, however, most non-emergency extravehicular 

tasks will be performed slowly to reduce overcontrol, overheating, tumbling, 

and entanglement problems. Except for emergency retrieval functions, 

better indices of adequate performance will be force, contact, displacement, 

and kinetic criteria. 

Suited motions can be performed by the in-orbit crewman that cannot be 

performed in the suited condition on earth (e. g. , the crewman can transfer 

from the Gemini B to the laboratory vehicle with arm motions only). 

2.1.3 Mobility 

Figure I-1 depicts body contacts for the egress motion; typically, upper torso 

contacts are more frequent and positive, and lower contacts are generally 

the result of aimless, flailing limbs. 

Previous evaluations of the X-20, AP-22s-2, Gemini, and Apollo suits have 

included single measures of arm reach, arm grasp, manipulation times, 

and finger dexterity tests of the seated operator. A series of time, kinetic, 

and kinematic tests to systematically assess the operator's total motion 

capability will be conducted on the MOL suit when available. 

• 

1-3 
• 

126 

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-5 IN. HATCH CLEARANCE 

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• Figure I-1. Total Number of Contacts for Each Body Segment for Suit: (A) Body Clearance; (B) Egress Configuration; 

and (C) Conditions 

I-4 
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• 

2.1.4 Arm Mobility 

Figures 1-2 and 1-3 relate the effect of control location on response time of tne 

left hand for the unsuited subject. Such baseline data is available tor comparative studies of suited subjects. The 6570th AMRL has conducted such 

analyses of the Gemini and Apollo suits and presented the data as suited 

decrements by zone area. For example, the 5 percent line in Figure 1-3 

indicates the locations in space wherein the unsuited subject suffers a 5 percent reduction decrement in performance (reaction + reach + manipulation 

time) with the left hand pushing push-buttons. 

Figure 1-4 illustrates that reach tests have yielded total decrements of up to 

62.6 percent for the X-20 suit (1st figure) and 6 percent between inflation 

levels of the AP-22s-2 suit (2nd figure); however, such measurements must 

be carefully related to the test situation. 

A crewman's reach capability while wearing the Gemini 3C suit is shown in 

Table I-I. The X-20 suit functional arm-reach test results are shown in 

Table 1-2. 

Table 1-1. Reach Capability. Wearing G-3C Full Pressure Suit 

(One Subject) 

Volumes of Reach Envelope 

Shirtsleeve 

Gemini suit - vented 

Gemini suit - pressurized 

(3. 5 psi) 

Subject's Stature 

Subject's Weight 

23.4 cu ft 

(approximately 15th percentile) 

18.0 cu ft 

(reduction of 23 percent) 

7.2 cu ft 

(reduction of 69 percent) 

5th percentile 

50th percentile 
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SHIRTSLEEVE 

2 1/2 P e i AP-22S-2 FULL 

3 1/2 psi PRESSURE SUIT 

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VERTICAL SAGITTAL PLANE THROUGH THE ARM 

REACH ENVELOPES AT A POINT CORRESPONDING 

TO THE RIGHT SHOULDER 

HORIZONTAL PLANE THROUGH THE ARM REACH 

ENVELOPES AT 35 INCHES ABOVE THE SEAT 

REFERENCE POINT 

Figure I-4. AP-22s-2 Arm Reach Envelope 

I-8 
Suited - 

Pressurized 

(5 psi) 

Suited - 

Shirtsleeves Unpressurized 

Volume 

Percent Decrement 

from Shirtsleeves 

Percent Decrement 

from Shirtsleeves 62. 6 percent 

11.95 cu ft 

17. 05 in. 

27.8 percent 

Grasping Reach 

Envelope 

Radius of Sphere of 

Equal Volume 

31.94 cu ft 23. 59 cu ft 

26.2 percent 

23.61 in. 21.32 in. 

9. 7 percent 

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• 

Table I -2. Functional Arm-Reach Test - X-20 Full Pressure Suit 

(Three Subjects) 

2. 1. 5 Egress Motion 

During zero-gravity, egress time is inversely related to hatch size. One 

inch of shoulder clearance requires 55 percent more time for egress than 

10 inches of shoulder clearance; five incnes of clearance requires 11 

percent more time than 10 inches. The curve appears to approach an 

asymptote between five and 10 inches of clearance. The only aborted trials 

(subject stuck in the hatch) occurred with a one-inch shoulder clearance. 

The USAF AP-22s-2 high pressure suit inflated to 2. 5 psi was used for the 

series of tests described in Figure 1-5. 

Figures I-5(A) and (C) indicate that the largest time improvement appears 

to be within the one- to five-inch clearance range, whereas contacts [ Figures 

I-5(B) and (D)] appear to decrease linearly within the one- to 10-inch 

clearance range. 

Figures I-5(F) and (H) indicate that the feetfirst techniques yield the smoothest egress, probably due to the suited subject's ability to see his legs in 

• 
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Figure I-5. Egress Motion (continued) 
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• 

relationship to the hatch, and thus better position his lower torso. Suited 

subjects often reported that they "did not know where their legs were", 

apparently due to poor kinesthetic feedback because of the lack of forces 

on the pressure receptors while suited under pressure and sailing over, 

rather than walking on, the floor. Accuracy of motion, rather than time 

of motion, appears to be a more sensitive measure of operator performance 

for the egress motion. 

2.1.6 Hand Dexterity 

The Purdue Pegboard Dexterity Test has been used to estimate the effects of 

vented and pressurized gloves on finger dexterity; the results in performance 

decrements are shown in Tables 1-3 and 1-4. 

Table 1-3. Dexterity Test Summary and Percentage (n = 17) - AP-22s- 2 Suit 

Conditions Right Hand Left Hand Both Hands Assembly 

Barehanded 100% 100% 100% 100% 

Gloved, no pressure 65% 63% 52% 43% 

Gloved, 2.5 psi 35% 35% 21% 20% 

Table 1-4. Hand Dexterity - X20A Suit - Mean Percentile Totals 

Condition. Right Hand Left Hand Both Hands Assembly 

Barehanded 100% 100% 100% 100% 

Gloved, vent 68% - 67% 61% 57% 

Gloved, 2. 5 psi 49% 40% 3A% 38% 

2. 1. 7 Ballooning Measurements. 

Selected anthropometrics have been made with the Gemini 2C suit inflated 

while in both a standing and a sitting position. The resulting measurements 

are shown in Tables 1-5 and 1-6. 

1-12 
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Table I -5. Gemini Full Pressure Suit 

Pressure Growth Increments - Standing 

• 

Dimensions* Uninflated 

Vent 13 

in. Hg 0.5 psi 1.5 psi 2.5 psi 3.5 psi 

' Total 

Inflation 

Growth 

Axillary Chest Circumference 39.0 42.8 43.2 44.5 44.8- 45.5 +6.5 

Measured Waist Circumference 35.9 40.1 40.5 41.5 41.9 42.4 +6.5 

Axillary Arm Circumference 12.7 12.8 13.0 14.4 . 14.8 14.7 +2.0 

Measured Forearm Circumference 12.2 12.6 12.7 12.8 13.1 13.5 +1.3 

Measured Thigh Circumference 16.8 16.7 17.0 18.3 18.3 18.9 +2.1 

Measured Calf Circumference 14.8 16.0 16.3 18.3 18.6 18.5 +3'.7 

Measured Shoulder Breadth 19.4 20.4 21.3 21.8 22.1 22.3 +2.9 

Elbow-to-Elbow (Pressed) 18.5 19.85 20.4 21.55 22.45 22.45 +3.95 

Hip Circumference 38.9 40.9 41.4 4Z.1 42.7 42.8 +3.9 

Table I-b. Gemini Full Pressure Suit 

Pressure Growth Increments - Seated 

Dimensions* Uninflated 

Vent 13 

in. Hg 0.5 psi 1.5 psi 2.5 psi 3.5 psi 

Total 

Inflation 

Growth 

Axillary Chest Circumference 38.40 43.20 44.00 44.50 45.00 45.20 +6.80 

Measured Waist Circumference ' 37.30 41.50 42.20 42.70 43.30 43.30 +6.00 

Axillary Arm Circumference 12.60 13.50 13.70 .14.60 14.70 14.50 +1.90 

Measured Forearm Circumference 12.20 12.50 13.00 13.30 13.30 13.50 +1.30 

Measured Thigh Circumference 17.50 18.00 17.90 18.40 18.40 18.50 +1.00 

Measured Calf Circumference 16.00 17.15 17.80 18.20 18.20 18.20 +2.20 

Measured Shoulder Breadth 19.70 21.2 21.20 22.00 22.10 22.25 +2.55 

Elbow-to-Elbow (Pressed) 18.60 . 19.3 19.70 21.30 21.45 23.15 +4.55 

Measured Hip Breadth 15.15 13.25 14.30 14.50 14.65 14.85 +1.70 

Posterior Plane of Back-toAnterior Knee Area 24 . 85 25.95 27.85 28.65 29.30 29.75 +4.90 

Thigh Clearance from Floor 23.50 23.55 23.75 24.55 24.70 25.00 +1.50 

Sitting Height 36.00 36.00 36.40 36.95 37.05 37.00 +1.00 

Arm Reach from Wall 33.85 33.55 34.65 33.25 32.05 31.15 -2.70 

Hand Length 8.40 8.40 8.40 8.50 8.55 8.75 +0.35 

Finger Tip to Glove Tip 0.00 0.00 0.50 0.55 0.70 0.70 +0.70 

' measurements in inches. 
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• 

2. 2 Visor Data 

The effect of rapid alterations of high and low illumination levels and the 

effects of viewing a direct working area within a bright surrounding will have 

a critical influence on extravehicular performance. AMRL is currently 

investigating this problem; the results of the investigation will be included 

in this section at a later date. 

2. 2. 1 Clear Visor Properties 

Normally, the refractive power of the visor in any meridian should not exceed 

by more than ±0. 06 diopters the power inherent in a spherical lens with concentric surfaces having the proper radii of curvature and thickness. The 

inherent power of the visor is calculated by use of the following formulae: 

F = F + F —t 

1 2 

- n n - F

1

F

2 F - F _ n= n' 

1 r1 2 r

2 

where 

F = Power of the lens in diopters 

F

1 = Power of the convex surface in diopters 

F

2 = Power of the concave surface in diopters 

n = Index of refraction of air 

= Index of refraction of the material 

r l = Radius of first or convex surface 

r

2 = Radius of second or concave surface 

t = Thickness in meters. 

Figure I -6 illustrates probable optical properties for the visor. 

The vertical prismatic deviation between point "C" for the right eye and point 

"C" for the left eye should not be more than 0.18 diopters nor shall the 

vertical prism at any point in the critical area of vision exceed 0. 18 diopters. 

The algebraic sum of the horizontal prismatic deviation at point "C" for the 

1-14 
VISOR ONLY 1.30 — 

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Optical Areas VisorCritical and Non-Critical 

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right eye shall not exceed 0. 75 diopters. The algebraic differences between 

the horizontal deviation at point "C" for the left eye and at point "C" for the 

right eye shall not exceed 0. 18 diopters. The luminous transmittance should 

not be less than 90 percent throughout the critical area. The non-critical 

area should not vary in transmittance by more than ±2 percent of the critical 

area transmittance. No visible distortion or optical defects detectable by 

the "unaided eye" (20/20) at the typical "as worn" position shall be visible. 

The haze value of the visor should not exceed 5 percent. 

The spectral transmittance may vary with wavelengths between 380 and 770 p.; 

the average percentage deviation within nine spectral bands should be less 

than12 (see Table 1-7). The spectral distribution curve should show a reasonably 

even distribution throughout the visible spectrum to insure that color distortion 

will not be excessive. 

The transmission of ultraviolet radiation in the range of 220 to 320 p. should be 

such that the total energy incident on the cornea and facial skin shall not 

exceed 1. 0 X 105ergs cm

-2 in any 24-hour period. In computing the total 

energy transmission: 

(a) The maximum expected flux in the earth orbital environment, 

including reflected ultraviolet, should be determined for 

each of 10 spectral bands, each band being 10 p. wide, 

between 220 and 320 p.. 

(b) The percentage transmittance of ultraviolet light in each of 

the 10 spectral bands (10 p width) between 220 and 320 p. 

shall be determined for Visor 1 by spectophotometry. 

(c) The following weighting factors are normally used for each 

10 p. band: 

220 - 230 p. 0.10 

230 - 240 p. 0.15 

240 - 250 p. 0. 20 

250 - 260 p. 0.25 

260 - 270 p. 0. 30 
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Table 1-7. Example for Calculation of Spectral Transmittance Deviations 

Wavelength 

(N.) 

Band 

T n 

Wavelength 

Range 

Average 

Transmittance 

Tn 

Percent 

Deviation 

100(1-Tn/Tc) Weight Product 

430 0. 114 

440 0. 118 

450 0. 127 

460 0. 137 1 430-490 0. 133 14 5 70 

470 0. 142 

480 0. 144 

490 0. 145 2 460-520 0. 145 7 10 70 

500 0. 147 

510 0. 149 

520 O. 151 3 490-550 O. 151 3 10 30 

530 0. 153 

540 0. 154 

550 0. 155 4 520-580 0.155 0 10 0 

560 0. 157 

570 0. 158 

580 0. 159 5 550-610 0. 159 2 10 20 

590 0. 160 

600 0. 160 

610 0. 160 6 580-640 0. 160 2 10 30 

620 0. 161 

630 0. 161 

640 0. 160 7 .610-670 0. 160 3 10 30 

650 0. 159 

660 0. 159 

670 0. 158 8 640-700 0. 158 2 5 10 

680 0. 157 

690 0. 156 

700 0. 153 9 670-730 0. 153 1 1 1. 

710 O. 151 

720 0. 149 Totals 71 767 

730 0. 148 

NOTES: 

a. Spectral transmittance, Tc = 0. 155. 

b. T = Transmittance at 10 p. intervals. 

c. Tn = Average transmittance of 60 p. band. 

d. The average transmittance, Tn, for a given band is the average of 

the seven tabulated values within that band, except that the first and 

last values are divided by 2, and the average computed by dividing 

the sum of the values by 6. 

e. Average percentage deviation of spectral transmittance within nine 

spectral bands = 261/71 = 3/7 percent. 

f. This table is based on illuminant "C". 

I- 17 
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• 

270 - 280 p. 0.35 

280 - 290 p. 0.90 

290 - 300 p. O. 50 

300 - 310 p. O. 15 

310 - 320 p. 0.10 

These factors represent differential sensitivity of the 

cornea within the ultraviolet range. 

(d) The flux is multiplied by the transmittance and by the 

weighting factor for each 10 p. band. The resulting 

corrected transmitted fluxes for each 10 p. band shall be 

summed, and the sum multiplied by the maximum time of 

exposure. The resulting energy absorption shall not exceed 

1.0 X 105ergs cm-2, in any one 24-hour period. 

The transmittance of infrared radiation between 770 and 

2500 p. can be as low as possible and not exceed a total 

value of 30 ±5 percent. The transmittance of infrared 

radiation between 2. 5 and 100 p. should not exceed 10 ±5 

percent. 

2. 2. 2 Antiglare Visor 

SAM(USAF) plans to study the NASA/Gemini double-filter concept which uses 

an additional gray and opaque visor, as well as other USAF in-house filters 

before recommending a final filter system. The essential problem seems to 

be the effects of simultaneous and successive contrast on adaptation as the 

worker or vehicle moves between unidirectionally illuminated areas to dark 

areas. The SAM plan will include visor testing and crew training with fullscale mockups illuminated in darkened chambers. 

2. 2. 3 Visor Quality Assurance 

After the visors have been subjected to flight qualification testing, neither the 

spectral (380 - 770 p.) nor the ultraviolet transmittance should change by 

more than 20 percent. The flight qualification testing program may include 

exposure of the visors to a spectrum simulating as closely as possible that 

of the combination of the solar flux in the free space environment plus the 

reflected flux from the earth's atmosphere. Any metallic film should not be 

dislodged or affected in any way when subjected to the adhesion of metallic 

film test. No major damage should be visible in any portion of the rubbed 

I -18 
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area of a coated surface which has been subjected to the abrasion resistance 

test. The critical and non-critical areas of the visors should be free of 

visible striae, waviness, cloudiness, and imperfections such as pits, bubbles, 

scratches, and foreign particles. The visors should have smooth, rounded 

edges and be free from cracks, check marks, or any defects which might 

affect appearance or functionability. The visors will be sampled for: 

(a) Erythemal ultraviolet transmittance (220 - 320 [.1.) 

(b) Spectral transmittance 

(c) Transmittance (380 - 770 4) after accelerated weathering. 

(1) All transmittance tests before flight qualification 

testing. 

(2) All transmittance tests after flight qualification 

testing. 

2. 2. 4 Helmet Angular Visibility 

Visual angles have been measured with the eyes and head fixed; eyes moving, 

head fixed; eyes and head moving; and show the decrements presented in 

Table I -8: 

Table 

Motion 

1-8. 

Fields 

X-20 Full Pressure Suit Field of Vision Test 

Eyes, 

Head Fixed Eyes Moving Eyes, 

R-Eye L-Eye Head Fixed Head Moving 

Horizontal Right 85 55 93 102 

Horizontal Left 52 77 80 100 

Vertical Up 45 47 50 50 

Vertical Down 50 50 -- 70 

•

~ 

• 

Due to the similarity between the X-20 Dyna-Soar helmet and the MOL helmet, 

the data in Table I -8 may be used as a guide to total visual degradation until 

actual data is available. 
NRO APPROVED FOR 

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• 

2. 3 Suit Dimensions 

Dimensions of the inflated suit will be determined after delivery of the first 

prototype MOL suit. Until this data is available, Drawing No. S-964 of the 

G-2C suit, prepared by the David Clark Co. , and obtainable through the 

AFSPO, may be used as a guide. 

2. 4 Environmental Data 

The environmental data shown in tabular form in this section represents 

information abstracted from the NASA G-4C Work Statement, Revision 1, 

dated 12 June 1964. Data contained.herein will be modified as changes are 

implemented or as test results become available. The suit assembly will be 

designed to perform in the applicable conditions specified in Table I-9. 

Pressure 

Proof 8. 0 psig (15 min duration) 

Operating 3. 7 ±0. 2 psia for max duration of 5 hr 

Relief Valves (2) 4. 6 f0. 3 psig (with combined minimum 

total flow of 150 standard LPM) 

Suit Pressure Indicator Absolute type with scale range from 

2 to 10 psia 

Leakage (maximum allowable 

leak rate, standard temperature 

and pressure) 

Complete Suit Assembly 

Components (at 3.7 psia 

or 0.2 psig) 

A. 200 cc/min, with 

Combination Max Time 

Internal 

Pressure 

External 

Pre s s_ur e ,Hr Min, 

3. 7 psia 

5. 6 ± O. 4 psia 

1. 1X 10-7 

TORR 

5. 5 ± O. 4 

psia 

2 

360 

15 

-- 

B. 200 cc/min for spacecraft preinstallation and ground tests. Pressurized 

to 3. 7 psia and 0. 15 psig. 

Gloves (each): 20 cc/min 

Helmet: 30 cc/min 

Torso: 130 cc/min 

1-20 
Extravehicular 

ro 

, 

o 

4 4 

0 

5. 0 CFM @ I 

3. 5 psia 

N 

2 L4 

0.-,o 0 

Min •—• N 

. + 

a. 

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t,..1 

o 

o 

- 

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determined 

O 

---.. 

Z 

 i

2 hours15min 

¢ ' 

-- 

z . •-• 

2 hours15 min 

Ejection 

14. 7 psia 

to12. 9mmHg -69° to+2 50°F 

CurveII 

Tobe 

determined 

..... 

- -..0 

,., 0 

0 

0. 2 psigor 

3. 7 psia 

- - 

__ 4' 

z 

- 

Se0 'D 

, 0 

se 0 0 _, 

0 

- 

40g for1 sec I 

all axes 

820 lb/ft

2 

II aii.inD 

utto st 

5 min @ + 250°F, 

14. 7 psia 10 min @ -69°F, 

33. 6 mm Hg 

CurveII 

Postlanding 

rd 

' a.

- 

. 

0 44 '-'0 o o 

- 

. + 

65° to 105° F 

7. 25 SCFM 

--.. -.... 

_.. 0 

- -..... 

10 min @ + 1 60°F 

36 hr @ - 15°F 

to+ 110°F 

36 hou rs 

f..‘1 

W 

5. 1 to 10-7 

to 15. 5 psia 

Curve 1 

5 0° to90 ° F 

To be 

dete rmined 

0. 2 psigor 

3. 7 psia 

--. 

MAC 

Report 8610 

MAC 

Report 8610 

.0 o 

- 

O 

0 o 

- 

0 

MAC 

Report 8610 

MAC 

Report 8610 

Curve I 

o 

E ON 

Orbit 

N 

o •-• 

: .V. 

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G.4 0 

_, 

0 

. 

0 

0 

50 ° to80° F 

@.> 

4, tso U com 

-; rd 

0. 

L0 

0, 2 psigor 

3. 7 psis 

I 

o 

?., Lr. 

o o 

-. r.1 

, 4- .74- 

...- 

;Z 

--... 

--- 

s'-- 0 ° 

o 

se- o o 

o 

0 o C'■ 

0 0 cr, -.0 

. .--. ■ ,°° @) .0 •--", 

I E 4 c, 

sr CP 

360 hours 360 hours 

Launc h 

h 

0 

—. 

0 

h ,,s 

..,: 7, ■., O. 

c?' 

0 

 •0 

0 

0.4 

0 

50° to 80° F 

7. 25 SCFM 

0. 2 psigor 

3. 7 psia 

";4 

---i 

--- 

MAC 

Report 8610 

MAC 

Report8610 

be0 

0 

0 

.--, 

.6-', 

0 

0 

.--. 

0 

MAC 

Report8610 

MAC 

Report 8610 

0 

.--. 

Pre launch 

—a 

0 ''' 

... a 

N in -- tr; - 15°F to 1 

+ 110°F 40° to 80° F 

0 to 12 SCFM 

M 

... 

a, 

N 

d +1 N 

Ni 

O 

¢ 

z 

Protected 

(Shipping) 

Protected (Shipping) 

es' 

0 _ 

0 

s.. o o 

--. 

0 

Protected 

(Shipping) 

W -.... 

z x 

0 

100 hrs 

4 Months 

L____ 

Env ironment 

Ambie nt Pressure Ambient 

Temperature 

Suit Inlet 

Temperature 

SuitInlet Flow 

Suit Pressure Spacecraft External Su rface Temp. 

Vibration 

Shock 02 Exposure Re lative 

Humidity 

Acoustic 

Noise 

Acceleration 

Dynamic 

Loading 

Time Suit 

Pressurized to 3. 7 +0. 2 psia Time Suit 

Pressurized to 0. 2 psig 

Total Time 

MOL ExtravehicularSpace SuitEnvironmental DesignRequirements 

• 

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1 - 2 1 
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• 

Ventilation Distribution 

System 

Pressure Drop 

Suitably sized subject 

restrained in position 

in orbit 

Pressure drop not to exceed 4.75 in. 

H2O for the following conditions: 

Inlet vent flow rate 11. 5 ACFM 

Inlet vent gas 100% 02 

Inlet temperature 55° F 

Inlet relative 

humidity 65 to 100% 

Ambient pressure 5. 5 ±0. 4 psia 

Suit outlet to 

ambient 0 to 1 in. H2O 

Through components 

Specified for 

Helmet CO2 Removal 

Evaporator 

(c onditional)(Hex) 

Ejector 

Suit 

Ducts, hoses,misc. 

Weight flow (02) 

at suit inlet 

Spacecraft flow 

requirement 

Overboard dump 

- 02 

- CO2 

0. 78 in. H2O drop 

13. 55 in. H2O rise 

9.86 in. H2O drop 

2.91 in. H2O drop 

23. 8 lb/hr 

9. 5 lb/hr 

9. 3 lb/hr 

0.3 lb/hr 

Helmet vent system to provide adequate 

CO2 removal for all mission conditions. 

Normal 3.8 mm Hg 

Maximum 7. 6 mm Hg 

Emergency 15 mm Hg 

Mobility 

Comfort 

Suit pressurized or unpressurized: 

Adequate mobility to perform required 

mission tasks, both normal and 

emergency. 

Suit pressurized at 3. 7 psi: Crewman 

will be capable of unassisted egress 

through spacecraft hatch opening at 

zero-g. 

Comfortable (easily tolerated) for periods 

up to and including: 

Unpre s surized 14 days 

Pressurized 5 hr at 3. 7 psia 
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• 

Donning 

Suit Assembly Life 

Assembly 

Helmet Visor 

Helmet and Glove 

Ventilation Inlet-Outlet 

and Blood Pressure 

Fittings 

Inflight Drinking Port 

Entrance Pressure Sealing 

Closure 

From partial don condition 

Donning time 

(gloves and helmet) 3 min, total 

Capable of being donned and doffed for 

50 consecutive cycles without major 

overhaul or unsatisfactory performance. 

Capable of 5000 cycles of operation 

without failure. 

Capable of being connected and disconnected for 500 cycles. 

Capable of being connected and disconnected for 500 cycles without failure. 

Capable of 500 probe insertions at 3. 5 

psig suit pressure without failure. 

Capable of 500 openings and closures 

without failure. 

2. 5 Life Support Provisions 

Information contained herein was derived, in part, from NASA, MSC document 

"Exhibit 'A' Project Gemini Extravehicular Life Support System (ELSS) 

Statement of Work", dated 4 August 1964, and in part from a Gemini pressure 

suit briefing presented by NASA, MSC on 12 August 1964.. A portable life 

support system acceptable for the MOL mission has not been developed. 

The following information defines the suit, chest pack, and umbilical interface 

problem, and should be used only as a guide. 

Chest Pack This item, described by NASA as "Extravehicular Life Support System" (ELSS), 

is shown schematically in Figure I.- 7. The 

system is basically a semi-open pneumatic 

loop, utilizing spacecraft 02 supplied via 

an umbilical. 02 is provided for metabolic 

needs and ventilation for thermal and 

CO2 control. 

Normal Mode During normal operation, the umbilical 

will supply either 5. 1 lb/hr or 9. 5 lb/hr 

of oxygen. A high-low selector valve 

will enable the crewman to select either 

flow rate. 

I-23 
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• 

I.- 24 

PortableLife Support System Schematic 

N 
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Emergency Mode 

Umbilical 

System Weight 

ELSS emergency 02system automatically 

supplies 02 to the suit if umbilical supply 

line pressure drops below 90 psig.. Emergency 02 supplied by the ELSS is adequate 

for either 5. 1 lb/hr or 9.1 lb/hr for 11 

minutes. Activation of the chest pack will 

be signalled by an audible alarm and by a 

warning light on the panel of the chest 

pack; the extravehicular mission will be 

aborted if the emergency 02 flow is activated. Suit pressure loss (nominal 3.5 

psig) will also activate the audible alarm 

and will signal the crewman to abort the 

extravehicular mission. 

(See Figure I-7.) The umbilical will be 

approximately 25 ft long, and will supply 

02 to the crewman via connection to the 

chest pack. A tetherline and an electrical 

cable for transmission of biomedical and 

suit condition data will also be incorporated 

into the umbilical. The umbilical has two 

interfaces: umbilical-to-spacecraft, and 

umbilical-to-chest pack. 

Weight of the complete ELSS (including 

chest pack, umbilical, and connectors) 

shall not exceed 52 lb. 

2. 6 Instrumentation Provisions 

The bioinstrumentation package will be supplied as an integral part of the 

suit by the suit contractor. Physiological and ECS parameters which may be 

monitored (based on those for which provisions are being made in the NASA 

G-4C pressure suit and associated life support systems) are as shown below: 

Located on chest. Biomed recorder and 

telemetry (T/M). 

Axillary, sternal biomed recorder, and T/M. 

Skin, oral; T/M. 

Left arm; T/M. 

T/M (EVA) in CP wrist gauge (2- 10 psia). 

Suit ventilation inlet (EV) biomed recorder; 

T/M. 

Impedance Pneumograph 

Electrocardiogram 

Temperature 

Blood Pressure 

Suit Pressure 

Temperature 

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• 

2.7 Damage Resistance 

The suit, is a multi-layered garment with a highly tear-resistant 'outer material 

(NOMEX fabric, HT-90-40). Tests conducted during July, 1964, established 

the criteria for both NOMEX and dacron. Dacron is used for the construction 

of the secondary thermal layer. 

Gloves are presently designed for intravehicular operation. A new glove, or 

glove covering, is under development for extravehicular activity. 

The helmet visor is the most susceptible to damage. Current studies indicate 

that a helmet visor constructed of CR-39 is shatterproof when subjected to 

tests by the NASA hypervelocity gun duplicating micro-meteoroid bombardment of a particle 1/64 inch in diameter traveling at approximately 27,000 

ft/sec. This material is being studied for possible use on the MOL suit 

helmet. 

2.8 Waste Disposal Provision 

The G-4C has no internal provision for body waste storage or disposal. The 

suit is equipped with double pressure-sealing zippers extending from the 

abdomen through the crotch. 

2.9 Food Handling Provisions 

A drinking or liquid squeeze-tube feeding port is located on the front lower 

edge of the helmet (see Figure I-8). 

2.10 Interface Provisions 

Suit fittings are of a type compatible with those utilized in the Gemini vehicle 

ECS. Therefore, fittings on the umbilical for extravehicular operations and 

all fittings from all ECS systems will be of a type compatible with those 

existing in the Gemini vehicle-suit-ECS loop. Fittings for extravehicular 

ECS support systems in the Gemini Program will be defined by January, 1965. 

A parachute harness is integrated into the parachute/restraint harness 

assembly. An interface exists between the suit and seat of the Gemini vehicle 

(e. g. , the neck ring of the suit imposes position interference in the area of 

head rest; mobility in the pressurized state is reduced to such a degree in the 

I-26 
/

HELMET DISCONNECT 

NECK BEARING 

MICROPHONES 

TELEMETRY AND 

BLOOD PRESSURE 

FITTING 

HANDKERCHIEF 

AND PENCIL 

STORAGE 

VENT INLET 

SUIT PRESSURE 

INDICATOR 

PRESSURE 

RELIEF VALVE 

PRESSURE SEALING 

CLOSURE 

'SCISSORS 

STORAGE 

PROTECTION LINER 

EARPHONES 

PRESSURIZED 

DRINKING PORT 

HELMET-TORSO 

RESTRAINT SYSTEM 

NECK DAM STORAGE 

LIFE VEST 

PARACHUTE 

HARNESS 

GLOVE DISCONNECT WRIST 

BEARING 

VENT OUTLET 

FINGERTIP GLOVE 

LIGHTING 

KNIFE STORAGE 

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Figure I-8, MOL Type Extravehicular Space Suit 

I-27 

i 
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(e. g. , the neck ring of the suit imposes position interference in the area of 

head rest; mobility in the pressurized state is reduced to such a degree in the 

hip/torso area as to make successful reinsertion into the seat followed by 

hatch closure a complex and difficult maneuver). 

Tethering systems utilizing hook and strap devices integrated into pressure 

suits have been designed, built, and successfully tested. Such a system may 

be provided as an integral part of the suit. 

Fittings requiring actuation by the crewman will present a major vehicle 

interface because of lack of dexterity and reduced mobility in the pressurized 

suit and gloves. 

Subsystems Interface Suit-to-seat interface vented and pressurized. 

Electrical-bioinstrumentation; common. 

Quick-disconnect type. 

Pneumatic-ventilation, blood pressure 

measurement. Vent is locking type. 

BPMS*is insert-bayonet type. 

Harness and restraint-parachute harness acts 

as restraint; lap belt. 

Vehicle attachment points for tethering. 

Types of Fittings Requiring 

Actuation by Crewman 

Suit-to-ECS or Pneumatic, manual-locking, double sealing. 

Suit-to-Chest Pack 

Suit-to-Spacecraft 

or Suit-to-Chest Pack Electrical manual, quick-disconnect. 

Suit-to-BPMS Insert tube; oiling seal; squeeze bulb. 

Lap Restraint Buckle (MA-6 type) Koch fitting. 

Parachute Harness Koch fitting. 

Umbilical-to-Chest 

Pack Snap-tite, quick-disconnect. 

Tether to Spacecraft Snap fitting. 

BPMS = Blood Pressure Measuring System 

I-28 
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S 

2. 11 Bioinstrumentation and Communication 

Electrical leads through the umbilical will be required for the following: 

Parameter No.. of Wires 

Power 3 

Electrocardiogram 2 (shielded) 

Impedance Pneumograph 2 (shielded) 

Microphones 2 (shielded) 

Earphones 2 (shielded) 

Inlet Temperature 2 

Total Suit Pressure 2 

15 
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7 
PART II 

EXTRAVEHICULAR ACTIVITY PERFORMANCE 

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• 

1. 0 INTRODUCTION 

Planning data to be used in the parametric study of extravehicular operations 

supporting the assembly of large space structures for MOL experiments is 

provided herein. Specifically, it includes time allowances and factors for 

determining weight penalties for the following modes of possible extravehicular capability: 

(a) Umbilical Life Support 

Extravehicular suit (recirculating gas wet or dry suit) with backpack 

water boiler and CO2 removal capability. An umbilical will provide 

metabolic and leakage oxygen. 

(b) Self-Contained Life Support 

Above capability with self-contained oxygen. 

(c) Astronaut Stabilization and Maneuvering Unit 

Reaction-jet (liquid monopropellant) backpack with rate gyro stabilization, providing the following command capabilities: up/down, 

right/left, and fore/aft translation accelerations; and pitch, roll, 

and yaw attitude rates. In absence of rate commands, zero rates 

will be held automatically. Automatic attitude hold can be turned 

off by the crewman. The unit will be stored in the airlock. 

(d) Unmanned (remote controlled) Maneuvering Unit 

Stabilized propulsion unit similar to the above, command-controlled 

from within the MOL; will provide a TV sensor with a video data 

link to the MOL. Stored externally;.boom-launched and retrieved 

by remote control; refueled and refurbished by remote control. 

Can be considered for use in positioning structural elements, 

transporting tools or expendables, or remote visual monitoring. 

(e) *Tether /Handhold Locomotion 

Self-powered maneuvering along structural surfaces using appropriate handholds or tetherlines. In considering this mode, the 

user should carefully identify all structural penalties and special 

assembly procedures which may be required to make it feasible. 

O 

An alternate maneuvering mode; however, pertinent weight factors are not 

included herein. 
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• 

The time data presented in Section 2.0 is intended for use in evaluating the 

comparative degree of manned participation in various space assembly schemes; 

it comprises elapsed-time factors for individual excursions and for overall 

station duty times allowable for extravehicular operations. The latter will 

permit evaluation of time-on-orbit consumed in implementing various degrees 

of extravehicular activity (EVA). 

The weight factors given will permit assessment of the weight penalties of 

various operational modes once the user has identified his requirements in 

terms of extravehicular modes, maneuver profiles, and activity (metabolic 

profiles). 

Requirements for work-station attachment devices, tools, and special equipment 

are not reflected herein. The user must establish these requirements for the 

specific task under consideration. 

11-2 
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2.0 ELAPSED TIME 

In determining the elapsed time associated with extravehicular operations, 

allowance must be made for "pre-EVA" and "post-EVA" time increments. 

These should include: 

(a) For the manned AMU: 

40 min: Don and check suit, life support, and/or maneuvering unit; depressurize; refuel maneuvering unit; 

egress. 

20 min: Ingress; pressurize; doff and stow suit. 

3 hr: Post-EVA battery recharge (if life support only has 

been used). If next excursion must be conducted 

sooner, duplicate battery sets (silver-cadmium) 

must be provided (8 lb). 

7 hr: Post-EVA battery recharge (if maneuvering unit 

and life support have both been used). If next EVA 

must be conducted sooner, duplicate battery sets 

(silver-cadmium) must be provided (19 lb). 

(b) For the Unmanned Maneuvering Unit: 

20 min: Refuel maneuvering unit and launch. 

10 min: Dock and retrieve maneuvering unit. 

4 hr: Post-EVA battery recharge. If next EVA must be 

conducted sooner, duplicate battery sets (silvercadmium) must be provided (11 lb). Access to 

unit for replacement of batteries will require 

manned extravehicular operation. Unit could carry 

two battery complements, if necessary. 

11-3 
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3.0 ALLOWABLE DUTY TIME 

During manned extravehicular operation (from airlock depressurization through 

repressurization), safety dictates that a second crewman devote his principal 

attention (50 percent of his time) to monitoring. This is necessary for both 

umbilical and self-contained life support. Sleep constraints (non-simultaneous) 

and other crew duty requirements establish an upper limit of four man-hours 

available per 24 hours for sustained manned extravehicular operations (an 

8-hour excursion may be possible on a non-recurring basis). Figure II-1 

illustrates possible duty cycles for a 2-man station, consisting of: 

(a) One 4-hour excursion, or two 2-hour excursions occurring during 

eight consecutive hours, or 

(b) Two 2-hour excursions separated by a crew sleep period. 

For a four-man operation (separately launched elements), crew sleep can be 

scheduled to provide 24 hours daily of two- or three-man availability. A maximum of 20 extravehicular man-hours can be made available per 24 hours, 

consisting of (see Figure 11-2): 

(a) A one-man, 4-hour excursion during the first 8-hour period, and 

(b) A two-man 4-hour excursion during each of the second and third 

8-hour periods. 

(The 2-hour possibilities indicated previously are also applicable. ) 

Operation of the Unmanned Maneuvering Unit requires one creman inside the 

MOL. If an extravehicular crewman and the Unmanned Maneuvering Unit are 

deployed in the same visual sector, the crewman inside the MOL could also 

act as safety observer for the external crewman; the observer crewman may 

jettison the unmanned unit, if necessary, in an emergency. A second crewman 

must be available and on duty inside the MOL during retrieval of the Unmanned 

II-4 

• 
JOINT 

DUTIES 

JOINT 

DUTIES 

rl/EVA

MON-JOINT 

//// R DUTIES 

JOINT 

DUTIES 

SOLO DUTIES 

SLEEP 

SOLO DUTIES 

SLEEP 

SLEEP 

SOLO DUTIES 

SLEEP 

SOLO DUTIES 

SOLO DUTIES . ii.. EK/A SLEEP 

I 1 

0 4 8 12 16 

TIME, HR 

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CREWMAN 

NO, I 

NO. 2 

NO. I 

N,O. 2 

NO. I SLEEP 

P . ..„ 

MO 

P I•R

N- 

• 

SOLO DUTIES 

,.., ..... 

:::::; 

JONT E VA 

/// DUT

I 

 ES 

40-MIN PRE-EVA PREPARATION TIME 

20-MIN POST-EVA ACTIVITIES 

Figure II-1. Maximum Crew Duty Cycles, 

Two-Man Station (Three Cases) 

. II-5 

NO. 2 JOINT 

DUTIES 

20 24 
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• 

CREWMAN 

•• o• • 

• 

44 

M NITOR 

# 

it ((iA SLEEP 

4 /TA 

EVA SLEEP 

/////// :,--- 

444 4. 4.04 

SLEEP • MONITOR • 4 .. ....„ • E , gt7 

SLEEP 

-,.: E1%'7 / 7 EvAv •-..40414 . .. *01...44 ............ 

0 4 8 12 6 

TIME, HR 

40-MIN PRE-EVA PREPARATION TIME 

20- MIN POST -E VA ACTIVITIES 

Figure II-Z. Maximum Crew Duty Cycles, 

Four Man Station (One Case) 

• II-6 

NO. I 

NO. 2 

NO. 3 

NO.4 
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• 

Maneuvering Unit. It these requirements are met, the Unmanned Maneuvering 

Unit may be operated: 

(a) Instead of any of the manned excursions previously identified, 

(b) In conjunction with any of the manned excursions, or 

(c) For up to four hours of any crew sleep period, ending with the 

second crewman awakened. 

11- 7 
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4. 0 WEIGHT FACTORS 

Weight factors for use in evaluating the umbilical and self-contained modes 

of extravehicular life support are presented in Table II-1. (All items are 

required for the umbilical mode; the umbilical is omitted for the self-contained 

mode. The weight of backpack oxygen tankage for the self-contained mode is 

negligible.) Metabolic oxygen is not allocated since it must be provided anyway; 

leakage is assumed negligible. Total weight will consist of fixed weight plus 

a variable weight increment calculated on the total number of excursions and 

total durations at different metabolic levels. 

Table 11-2 presents weight factors for calculating the additional increment 

required for crewman EVA maneuvering capability; total weight for maneuvering and life support requires use of both Tables II-1 and 11-2. To calculate the 

required variable weight (mainly propellant), the user must determine an 

approximate maneuver profile for the assembly task. Propellant required for 

individual excursions is of interest as well as total propellants; at present, it 

is contemplated that the AMU will carry approximately 15 lb of propellant. 

"Fine Station-Keeping" in Tables II -2 andII -3 refers to the precise (manual) 

control of relative position between the Unmanned Maneuvering Unit and a 

reference object, and the precise (manual plus automatic) control of relative 

attitude. It is representative of station-keeping at 1-2 ft range, or of the 

terminal phase of rendezvous or docking (such as would be involved in a 

transfer, from MOL to an auxiliary object). It would also be typical of propellant 

required during traverse along a large assembly in close proximity (1-2 ft) 

thereto, or that required for untethered assembly operations at a work station. 

"Coarse Attitude Maintenance" is the limit-cycle fuel expended by the automatic stabilization, plus the fuel required to manually (periodically) remove 

the attitude drifts inherent in the automatic system. Position is allowed to 

drift. 

11-8 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Table II-1. Weight Factors, 

Fixed Weight 

Life Support 

Weight 

(lb) 

Extravehicular Suit 30 

Umbilical 5 

ECS Backpack 60 

Communications 20 

Battery Recharge 7 

Tetherline and Reel 15 

Mounting and Wiring 13 

Contingency 14 

Total 164 

Variable Weight 

Airlock Repressurizing (per excursion) 15 

800 BTU/hr 1500 BTU/hr 2000 BTU/hr 

Contaminant Removal 0.93 lb/hr 1.75 lb/hr 2.33 lb/hr 

Battery Recharge 0.27 lb/hr 0.5 lb /hr 0.67 lb/hr 

Water and Tankage 1.12 lb/hr 2.10 lb/hr 2.80 lb/hr 

11-9 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

Table 11-2. Weight Factors, AMU 

(In Addition to Life Support Factors of Table II-1) 

Fixed Weight 

Weight 

(lb) 

Maneuvering Unit (Dry, w/o ECS) 105 

Battery Charger 2 

Refueling System 18 

Mounting and Wiring 26 

Contingency 15 

Total 165 

Variable Weight 

Battery Charge 

Propellant 

Fine Station-Keeping 

(position and attitude) 

Coarse Attitude Maintenance 

300-ft Translation and Single 

Rendezvous (5 min) 

0.67 lb/EVA hr 

2.3 lb/5 min 

3 lb/hr 

2.6 lb 

Other translations should be calculated from mass 

and AV involved, using I of 190 lbf-sec/lb 

sp 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Table 11-3. Weight Factors, Unmanned Maneuvering Unit 

(Life Support Factors of Table II-1 Not Required) 

Fixed Weight 

Weight 

(lb) 

Maneuvering Unit (Dry) 115 

Battery Charger 5* 

Receivers, Displays and Controls 75 

Storage, Launch and Retrieval 70 

Refueling System 15* 

Remote Refueling Console 10 

Mounting and Wiring 65 

Contingency 35 

Total 390 

Variable Weight 

Battery Charge 

Propellant: 

Fine Station-Keeping 

(position and attitude) 

Coarse Attitude Maintenance 

300-ft Translation and Single 

Rendezvous (5 min) 

0.67 lb/EVA hr 

0.67 lb/5 min 

0.4 lb/hr 

0.75 lb 

Other translations should be calculated from the 

mass and AV involved, using I of 190 lbf-sec/lb 

sp 

Can be shared with AMU. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

The propellant figure shown for "300-ft Translation and Rendezvous" is 

dominated by the rendezvous requirement, and hence is virtually independent 

of the translation velocity (and of the translation range) chosen. It is calculated 

for the mass of maneuvering unit, ECS, and man, without payload. 

During tethered operation, the automatic stabilization system can be turned 

off to conserve fuel. 

Table 11-3 shows weight factors for the Unmanned Maneuvering Unit. Note 

that, in both Tables 11-2 and 11-3, there are no allowances for tools, fixtures, 

couplings, or payload carriers. These should be identified by the user as 

specialized requirements for the assembly tasks under study. 

• 

II-12 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

• 

DISTRIBUTION LIST 

External 

Lt. Col. R. R. Regnier (SSMM) (15) 

Maj. E. F. Westlake (AMGB) (30) 

Capt. R. T. Boverie (SSMM) (5) 

Capt. R. S. Zeigen (AMGB) 

Internal 

W. J. Baldau (2) 

A. R. Dare 

B. Gross 

W. C. Hayden (2) 

A. L. Johnson, Jr. 

J. L. Johnson 

H. W. Nordyke (50) 

J. E. Roberts 

R. S. Swope (2) 

S. M. Tennant