NRO AF$PROVED FOR REPORT NO. 

RELEASE 1 JULY 2015 TOR-469(5107-45)-1 

MOL Extravehicular Space Suit 

Data Book 

NOVEMBER 1964 

Prepared by R. S. SWOPF.: 

Sioastronauties 

Special Studies Directorate 

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 • A EROS PACE CORPORATION 

CONTRACT NO. AF 04(695)-469 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Report No. 

TOR-469(5107-45)- 1 

MOL EXTRAVEHICULAR SPACE SUIT DATA BOOK 

November 1964 

Prepared by 

R. S. Swope 

BioaStronautics 

Special Studies Directorate 

Manned Systems Division 

Prepared for 

COMMANDER SPACE SYSTEMS DIVISION 

AIR FORCE SYSTEMS COMMAND 

LOS ANGELES AIR FORCE STATION 

Los Angeles, California 

Contract No. AF 04(695)-469 

El Segundo Technical Operations 

AEROSPACE CORPORATION . 

El Segundo, California 
/Z71.1,4 4, 

S. M. T nnant 

Assoc. Group Director 

Special Studies Directorate 

Manned Systems Division 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Report No. 

TOR-469(5107-45)-1 

MOL EXTRAVEHICULAR SPACE SUIT DATA BOOK 

Prepared by 

Swope 

Bioastronautic 

MOL Studies Directorate 

Manned Systems Division 

Approved by 

J. E. Ro 

Bioastro utics 

MOL Studies Directorate 

Manned Systems Division 

The information in a Technical Operating 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 
INTRODUCTION 

Page 

1 

1. 1 Scope 1 

1.2 History 1 

1.3 Criteria 1 

PERFORMANCE AND DESIGN DATA 2 

2. 1 Motion Limitations 2 

2. 1. 1 Neutral Position 2 

2. 1. 2 Motion Limits 2 

2. 1. 3 Mobility 2 

2. 1. 4 Arm Mobility 4 

2. 1. 5 Egress Motion 8 

Z. 1. 6 Hand Dexterity 11 

2. 1. 7 Ballooning Measurements .11 

2. 2 Visor Data 13 

2.2. 1 Clear Visor Properties 13 

2. 2. 2 Antiglare Visor S 17 

2. 2. 3 Visor Quality Assurance 17 

2. 2. 4. Helmet Angular Visibility .18 

2. 3 Suit Dimensions 19 

2.4 Environmental Data 19 

2. 5 Life Support Provisions 22 

2. 6 Instrumentation Provisions 24 

2. 7 Damage Resistance 24 

2. 8 Waste Disposal Provision 25 

2. 9 Food Handling Provisions 25 

2. 10 Interface Provisions 25 

2. 11 Bioinstrurnentation and Communication 28 

1. 0 

2. 0 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

CONTENTS 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

FIGURES 

1. Total Number of Contacts for Each Body Segment for 

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

Page 

and (C) Conditions 3 

2. Spatial Configuration of Console Array Distances 

with Average Performance Scores for Each Location 5 

3. Total Performance Time for the Push Button 

(% Decrement in Performance vs Control Location) 6 

4. AP-22s-2 Arm Reach Envelope 7 

5. Egress Motion 9 

6. Visor Critical and Non-Critical Optical Areas 14 

7. Portable Life Support System Schematic 23 

8. MOL Extravehicular Space Suit 26 

-iv- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

TABLES 

1. Reach Capability Wearing G-3C Full Pressure 

Suit (One Subject) 

Z. Functional Arm-Reach Test - X-20 Full Pressure 

Suit (Three Subjects) 

3. Dexterity Test Summary and Percentage 

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

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

Totals 

5. Gemini Full Pressure Suit - Pressure Growth 

Increments - Standing 

Page 

4 

8 

11 

11 

12 

6. Gemini Full Pressure Suit - Pressure Growth 

Increments - Seated 12 

7. Example for Calculation of Spectral 

Transmittance Deviations 

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

9. MOL Extravehicular Space Suit Environmental 

Design Requirements 20 

16 

18 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

1. 0 INTRODUCTION 

1. 1 Scope 

This document contains design and performance data for the MOL Extravehicular Space Suit. Interface areas and related hardware are included 

for the Gemini B, laboratory vehicle, and subsystems, where applicable. 

The space suit assembly described herein' is capable of providing MOL 

crew members with ventilation distribution and environmental protection 

for all MOL missions requiring limited mobility when using the suit in an 

inflated condition. 

Most of the material contained herein was derived from NASA G-4C suit 

specifications, or tests on suits of a similar type. 

1.2 History 

The MOL extravehicular space suit is an outgrowth of the USAF high-altitude 

pressure suit AP-22s-2. Suit evolution under NASA progressed through the 

G-1C to the G-4C. The latter is tentatively planned as the MOL suit with 

modification to facilitate a more extensive extravehicular program. 

1.3 Criteria 

The MOL extravehicular space suit will be designed to withstand launch, 

on-orbit, and re-entry environment as defined in the MOL General System 

Specification and associated Work Statement. 

-1- 
0 

3 

ui 1.00 

4 

2.0 

ZERO G 

1 5 , 10 1 1 5 10 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

HATCH CLEARANCE, IN. HATCH CLEARANCE, IN. 

(A) (B) 

• 

4.0 

5 

3.0 

Sf 

1 5 10 

HATCH CLEARANCE, IN. 

(C 

HATCH CLEARANCE, IN. 

(D) 

Figure 5. Egress Motion 

• - 9- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

128 

••••• • I IN. HATCH CLEARANCE 

 5 IN. HATCH CLEARANCE 

24 10 IN. HATCH CLEARANCE 

32 

-a W W 

V 2 

------ HEADFIRST - SIDE HANDHOLD 

HEADFIRST - BOTTOM HANDHOLD 

 FEET FIRST- SIDE HANDHOLD 

 FEET FIRST- TOP HANDHOLD 

(A) 

(B) 

(C) 

• 

Figure 1. Total Number of Contacts for Each Body Segment for Suit: 

(A). Body Clearance; (B) Egress Configuration; 

and (C) Conditions 

-3- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

2. 1. 4 Arm Mobility 

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

left hand for the unsuited subject. Such baseline data is available for 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 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 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. 

An astronaut's reach capability while wearing the Gemini 3C suit is shown in 

Table 1. The X-20 suit functional arm-reach test results are shown in 

Table 2. 

Table 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 

• -4- 
(501.1301 01) 

4.110d 9312910)08 leas am:qe nueislo 

0 

2 

ic 

a

.- -0 

K O N 

. 

; E e.' 

.2 in 'f. . 

,,, 

Si a 

„, .c.) 

te r 

< 

0 0 

0 tc) 

{S91.13111 U1) 

iU1Od 03110.10ja8 Ras aim a3uels!0 

— 5— 

0 

O 

-1 

0 0 

Cr 

LL 

Cr 

I- Z 

LL1 0 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

(S0(43111 U1) 

)1110d 0111040M MS NOIR 03UP4S113 
0 

In 

ANGLE TO THE L E FT OF THEMID SAGITTALPLANE IN DE

GREES 

O 

4•J 

0 

r-f 

0 

a) 

U 

Fi 

0 

4-1 

O 

4:(it 

U 

0 

0, 

U) 

U

Fa 

0 

O 0 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

S3HONI NI 1NIOd 33N3e13338 1V3S 3A08V 1H913H 

In In 

- 

N .7 _

NIIII 1/4.%:"Nlik** 9 ■

i 

al 

0 N 

e 

LO 

... 

f... 

• 

N 

N 

. 

...... 0 0 

0 

• • 

-..., 

o 

to 

• 

e 

O N 

..... 

r•-\InJ° 

te) 

. 

10 r`i N 

N 

• • 

-O 

In 

• —6— 
LEGEND OF REACH CONDITIONS 

SHIRTSLEEVE 

2 V2 psi AP-22S-2 FULL 

3 1/2 psi PRESSURE SUIT 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

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 4. AP-22s-2 Arm Reach Envelope 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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

(Three Subjects) 

Suited - 

Shirtsleeves Unpressurized 

Suited - 

Pressurized 

(5 psi) 

Volume 

Grasping Reach 

Envelope 

Percent Decrement 

from Shirtsleeves 

Radius of Sphere of 

Equal Volume 

Percent Decrement 

from Shirtsleeves 

31.94 cu ft 23. 59 cu ft 11.95 cu ft 

26. 2 percent 62. 6 percent 

23.61 in. 21.32 in. 17. 03 in. 

-- 9. 7 percent 27.8 percent 

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 

for 10 inches of shoulder clearance; five inches 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 5- 

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

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

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

range. 

Figures 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 

-8- 
Iz 

X 

• 

ZER 1000.: 

2,00 

too 

3.00 

4.00 

z 

cg 

13.00 

rc 0 

0 

O. ta 

• 

• 

&a 1.00 2.00 

ZERO 

• • 

1.00 

HEADFIRST HEADFIRST FEETFIRST FEETFIRST 

SIDE BOTTOM SIDE . TOP 

POSITION- HANDHOLD 

HEADFIRST HEADFIRST FEETFIRST FEETFIRST 

SIDE BOTTOM SIDE TOP 

POSITION- HANDHOLD 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

6.00 

• 

3.00 

or-SUITED 

I2.00 4.00 

6- 

• 

• • 

• 

3.00 SUITED-7 

• 

8 

Lei 

• • 

100 • • 5 2.00 - UNSUIT20060■44 • 

Iz 

• bl 

UNSUITED 1.00 

(F) 

HFADFIRST HEADFIRST FEETFIRST FEETFIRST 

SIDE BOTTOM SCE 113P 

POSITION -HANDNOLO 

HEADFIRST HEADFRST FEETFIRST FEETFIRST 

SIDE BOTTOM SIDE TOP 

POSITION - HANDHOLD 

(E) 

(G) (H) 

Figure 5. Egress Motion (continued) 

• -10- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 3 and 4. 

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

Condition Right Hand Left Hand Both Hands Assembly 

Barehanded 100% 100% 100,0 100% 

Gloved, vent 68% 67% 61% 57% 

Gloved, 2.5 psi 49% 40% 36% 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 5 and 6. 

• 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Table 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 42.1 42.7 42.8 .43.9 

Table 6. 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 c:ircumference 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-to- • Anterior 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 Reich 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 

*All measurements in inches . 

• 

-12- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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: 

n -n n - n 

F = F + F2- n 

—

t F

I

F

2 F

l = F

2 - 

1 r

l 

r2 

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 i= Radius of first or convex surface 

r2= Radius of second or concave surface 

t = Thickness in meters. 

Figure 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 

-13- 
0-1 

.L1 

• o ,n 0 

u cs. u 

4-$01 T,' $- 

g 

• 

$r$ E 

C ; 

ba 

.r. '

▪ 

• I1) Z c-.3 ®

▪ 

(mot} -0 u, ,9 -o 

re0. 

4. 

m.0 ns 

u 

E 

z 

/u E0. 

E 

.0 t 0 

2

-4,u34) 

• 0.0u 0 

CL 

: 2 > • —■ (,) 6' -0 

• (U 0 

:;;; Cl.) NI 4 

od • ..U.! 6 

0) " 

-0 0 

(e. a. 'a' g 

CL 

v 

Z

• 

cl) 

VisorCritical and Non-Critical OpticalAreas 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• - 14- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 

than 12 (see Table 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 103 

ergs 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 μ 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 

• -15- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Table 7. Example for Calculation of Spectral Transmittance Deviations 

Wavelength 

(p.) 

Band 

T n 

Wavelength 

Range 

Average 

Transmittance 

Tn 

Percent 

Deviation 

100(1-Tn/Tc) Weight Product 

430 0. 114 

440 O. 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 0. 151 3 490-550 O. 151 3 10 30 

530 O. 153 

540 0. 154 

550 O. 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. 16 1 

630 0. 16 1 

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 26T 

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". 

-16- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

270 - 280 p. 0.35 

280 - 290 p. 0.90 

290 - 300 p. O. 50 

300 - 310 p. 0.15 

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 i. 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 15 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 and 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 astronaut training with full scale 

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 .) 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 

-17- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 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 p.) 

(b) Spectral transmittance 

(c) Transmittance (380 - 770 .) 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 8: 

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

Fields 

Eyes, 

Head Fixed 

R-Eye L-Eye 

Eyes Moving 

Head Fixed 

Eyes, 

Head Moving 

Right 85 55 93 102 

Left 52 77 80 100 

Up 45 47 50 50 

Down 50 50 70 

Motion 

Horizontal 

Horizontal 

Vertical 

Vertical 

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

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

actual data is available. 

-18- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 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 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 ±0.3 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 sue Hr Min 

3.7 psia 

5.6 ± 0.4 psia 

1.1X 10-7 

TORR 

5.5 ± 0.4 

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 

-19- 
5. 0 CFM @ 

3. 5.psia 

3. 7psia 

Tobe 

determined 

2 hours 15 mill 

Ejection 

14. 7 psia 

to12. 9mm Hg -69° to+250°F 

CurveII 

Tobe 

dete rmined 

.0. 2psigor 

3. 7 psia 

40g for 1 sec 

all axes 

820 lb/ft

z 

15 min 

CurveII 

5 min @+ 250°F, 

14.7 psia 10 min @ -69°F, 33. 6 mmHg 

CurveII 

15. 5 psia 

7. 25 SCFM I 

10 min @ + 160°F 

36 hr @- 15°F 

to+ 110°F 

36 hours 

ra . ... 

5. 1 to 10 -7 

to15. 5 psia 

Curve I 

50° to90° F 

Tobe 

determined 

0. 2 psigor 

3. 7 psia 

nl 

14 ,I .1. ...... 0 2 ro tr, o ..... ,-« Z 1-. a, o o ...... ...... 0 0 c, a -.... . .4 - 

MAC 

Report8610 

,.., a a. -, Tr 44 -- 0 0 _. .--- e. ul < 

MAC 

Report8610 

, Ln 0 0 0 MAC Report 8610 MAC Report8610 a i 

Curve I 

I 

5. 1 to 10-7 

psia 

-4 .0 

r..4 

.0 .0 0 

so 

C; 

0

'+ 

0. 2 psigor 

3. 7 psia 

.... — g 

0 

g-s' -

0 4. 0 

0 ^ .: 0 4.4.0 .., 4

. 

 ...., 

... 

4.4 r./ .0 

00 44-. 

O ...... "..' 0 C) 

ro o o 

pp -... -4.... 

--.. 

.Z- . Z ." 

0 .._ 

4hr @ 60- 90°F 

90 min @ 160°F 

360 hours 

360 hours 

c4 A

N 

b

o 

b 

O 

O 0 Lei @.) 0 O 0 E2 '"". 40 O 0 P. 

. .4- 

7. 25 SCFM 

O 

 -. o _.; „I - 4.1 "" c> 0 

0. 2 psigor 

3. 7 psia 

41 

-, 

z

.Z- o o 

...« 

W , ul 0 Z - 

.- M.-, 

u.0 2 54 .4 ° o ..... 

MAC 

Report8610 

MAC 

Report 8610 

..... . e_ 

o o 

ez 

o o 

o o --. ..... o o -.,. MAC Report 8610 MAC Report 8610 

G 

Prelaunch 

' 14. 7 to 

15. 5 psia 

r- 44 

_ 

.... 

«1 'ya o .r., 

0 

-. -« 

40° to80° F 

0to12SCFM 

0

w et 

ro: 

o 

0 0 0 0 0 

' 44 0 <4 ti ... e ,..„, 

1 + P. "n o o 

-. 0 0 0 .... r- 0 o « 0 o - Protected (Shipping) 

o a., ‘3. 0 0 4 0 

0 0 +i 

.i. 4.4 0. 0 0 0 

10 .... . r- 

-..- 2 ..E' 

..., 

-. 

Ln ....« 

o 

o o - 0 — . 

0.

NI a, ',F k 

Protected (Shipping) 

w 

.c 

4Months 

Environment Ambient 

Pressure 

Ambient 

Tempe rature 

0/ ,., 

A Q. 

..-. 5 5 w 

U') H 

V 

A 3 

tn 

Suit 

Pressure 

Spacecraft 

External Sur- faceTemp. Vibration 

4.% 

o .4 cn 

0 2 Exposure 

›. 01 .4 

> 44. 

... 

-0 4. 

'A E 

61 0 c4 

. , 

„.., 

... 

0, , a, 

5 .2 

U 0 -4 Z 

Acc [ eleration 

Dynamic 

Loading Time Suit 

Pressuriied 

to 3. 7 +0. 2 psia 

• 

Time Suit 

Pressurized to 0. 2 psig 

0) 

...4 

E. 

' 74 

..-. 0 

H 

a) 

715 

cd 

a) 

a) 

cr' 

a) 

an 

En 

a) 

Cd 

a) 

0 

a) 

0 

cd 

UD 

fd •re 

a) 

Cd 

;.4 45-' 4 

0 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• -20- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Ventilation Distribution 

System 

Pressure Drop 

Suitably sized subject 

restrained in position 

in orbit 

Through components 

Specified for 

Helmet CO2 Removal 

Mobility 

Comfort 

Pressure drop not to exceed 4.75 in. 

H2O for the following conditions: 

Inlet vent flow rate 

Inlet vent gas 

Inlet temperature 

Inlet relative 

humidity 

Ambient pressure 

Suit outlet to 

ambient 

Evaporator 

(conditional)(Hex) 

Ejector 

Suit 

Ducts, hoses, misc. 

Weight flow (02) 

at suit inlet 

Spacecraft flow 

requirement 

Overboard dump 

- 02 

- CO2 

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 

Suit pressurized or unpressurized: 

Adequate mobility to perform required 

mission tasks, both normal and 

emergency. 

Suit pressurized at 3. 7 psi: Astronaut 

will be capable of unassisted egress 

through spacecraft hatch opening at 

zero-g. 

Comfortable (easily tolerated) for periods 

up to and including: 

Unpressurized 14 days 

Pressurized 5 hr at 3. 7 psia 

-21- 

11. 5 ACFM 

100% 02 

55°F 

65 to 100% 

5. 5 ± O. 4 psia 

0 to 1 in. H2O 

0. 78 in. H2O drop 

13. 55 in. H2O rise 

9.86 in. H20 drop 

2.91 in. H2O drop 

23.8 lb/hr 

9. 5 lb/hr 

9.3 lb/hr 

0.3 lb/hr 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 3 min, total 

(gloves and helmet) 

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. 

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

is shown schematically in Figure 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 

CO2control. 

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 astronaut to select either 

flow rate. 

-22- 

Chest Pack 

Normal Mode 
—23— 

Portable Life Support System Schematic 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 
ELSS emergency 02 system 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 astronaut to abort the 

extravehicular mission. 

(See Figure 7. ) The umbilical will be 

approximately 25 ft long, and will supply 

02 to the astronaut via connection to the 

check 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. 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Emergency Mode 

Umbilical 

System Weight 

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: 

Impedance Pneumograph Located on chest. Biomed recorder and 

telemetry (T/M). 

Electrocardiogram Axillary, sternal biomed recorder, and T/M. 

Temperature Skin, oral; T/M. 

Blood Pressure Left arm; T/M. 

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

Temperature Suit ventilation inlet (EV) biomed recorder; 

T/M. 

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 

-24- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 helthet 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 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 

• 

-25- 
PROTECTION LINER 

EARPHONES Jill 

RESTRAINT SYSTEM 

HELMET-TORSO 41.44 

Npr 

1044 

;14 

PRESSURIZED 

DRINKING PORT 

NECK DAM STORAGE 

LIFE VEST 

PARACHUTE 

HARNESS 

GLOVE DISCONNECT WRIST 

BEARING 

VENT OUTLET 

FINGERTIP GLOVE 

LIGHTING 

KNIFE STORAGE 

/

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 

Figure 8. MOL Extravehicular Space Suit 

• -26- 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 
• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 astronaut actuation 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 

Astronaut Actuation 

Suit-to-ECS or 

Suit-to-Chest Pack 

Suit-to-Spacecraft 

or Suit-to-Chest Pack 

Suit-to- BPMS 

Lap Restraint 

Parachute Harness 

Umbilical-to-Chest 

Pack 

Tether to Spacecraft 

Pneumatic, manual-locking, double sealing. 

Electrical manual, quick-disconnect. 

Insert tube; oiling seal; squeeze bulb. 

Buckle (MA-6 type) Koch fitting. 

Koch fitting. 

Snap-tite, quick-disconnect. 

Snap fitting. 

BPMS = Blood Pressure Measuring System 

-27- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 

• 

-28- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

DISTRIBUTION 

External 

Col A. I. Karstens, AMGB (10) 

Internal 

Amster, W. H. 

Bernstein, H. 

Coppage, J. E. 

Halenbeck, A. D. 

Hussman, T. A. 

Johnson, J. L. 

Nordyke, H. W. 

LaPorte, E. L. 

Olson, C. L. 

Roberts, J. E. 

Scrooc, D. J. 

Swope, R. S. 

Tennant, S. M. 

Weeks, L. M.