U.S. patent number 3,751,727 [Application Number 04/750,031] was granted by the patent office on 1973-08-14 for space suit.
This patent grant is currently assigned to Granted to The United States National Aeronautics and Space. Invention is credited to Ronald J. Bessette, Melvin C. Case, George P. Durney, A. J. Kenneway, III, Richard C. Pulling, Dixie Rinehart, Leonard F. Shepard, Robert C. Wise.
United States Patent |
3,751,727 |
Shepard , et al. |
August 14, 1973 |
SPACE SUIT
Abstract
Disclosed is a pressure suit for high altitude flights and
particularly space missions. The suit is designed for astronauts in
the Apollo Space Program and may be worn both inside and outside a
space vehicle, as well as on the lunar surface. It comprises an
integrated assembly of inner comfort liner, intermediate pressure
garment, and outer thermal protective garment with removable helmet
and gloves. The pressure garment comprises an inner convoluted
sealing bladder and outer fabric restraint to which are attached a
plurality of cable restraint assemblies. It provides versitility in
combination with improved sealing and increased mobility for
internal pressures suitable for life support in the near vacuum of
outer space.
Inventors: |
Shepard; Leonard F. (Dover,
DE), Durney; George P. (Dover, DE), Case; Melvin C.
(Dover, DE), Kenneway, III; A. J. (Dover, DE), Wise;
Robert C. (Dover, DE), Rinehart; Dixie (Dover, DE),
Bessette; Ronald J. (Wyoming, DE), Pulling; Richard C.
(Dover, DE) |
Assignee: |
Granted to The United States
National Aeronautics and Space (Washington, DC)
|
Family
ID: |
25016223 |
Appl.
No.: |
04/750,031 |
Filed: |
August 5, 1968 |
Current U.S.
Class: |
2/2.14; 600/20;
2/81 |
Current CPC
Class: |
B64G
6/00 (20130101) |
Current International
Class: |
B64G
6/00 (20060101); A62b 017/00 () |
Field of
Search: |
;2/2,2.1,2.1A,6,3,81
;128/2.06,2.05,2.1,283,1.01,142,2.95,285,1A |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
957,085 |
|
May 1964 |
|
GB |
|
957,688 |
|
May 1964 |
|
GB |
|
666,671 |
|
Sep 1964 |
|
IT |
|
Other References
International Science and Technology Publication, February 1967
(page 33 relied on), by M. I. Radnofsky.
|
Primary Examiner: Franklin; Jordan
Assistant Examiner: Krizmanich; George H.
Claims
What is claimed and desired to be secured by United States Letters
Patent is:
1. A space suit for high altitude and space environments comprising
a pressure garment having an inner sealing bladder and an outer
restraint convering, a pair of like gas inlet connectors on said
pressure garment connected together in substantially direct fluid
connunication with each other for selective use of either or
simultaneous use of both inlet connectors for passing life
supporting gas into said suit, a pair of like gas outlet connectors
on said pressure garment connected together in substantially direct
fluid communication with each other for selective use of either or
simultaneous use of both outlet connectors for passing gas as
exhaust out of said suit, an electrical connector on said pressure
garment for connection of communications and bio-instrumentation to
the interior of the pressure garment, and a self-sealing biomedical
injection patch on said pressure garment.
2. A space suit for astronauts comprising in combination: a
conformal pressure garment having an inner sealing bladder and an
outer restraint layer, and outer thermal insulating garment over
said pressure garment, said pressure and thermal garments of said
suit having torso and limb covering portions adapted to cover an
astronaut's entire body except for hands and head, a transparent
plastic helmet coupled to the neck of said garments, and a pair of
pressure gloves rotatably coupled to the sleeves of said garments,
said pressure garment including convoluted joints positioned in
said torso and limb covering portions to provide ease of mobility
when said pressure garment is worn, restraint cables secured to
said pressure garment adjacent at least some of said convolutes to
prevent elongation of said convolutes under internal gas pressure,
a pair of like connected together gas inlet connectors on the chest
of said pressure garment for passage into said suit of a life
support gas, a pair of like connected together gas outlet
connectors on the chest of said pressure garment for passage out of
said suit of gas as exhaust, electrical and cooling liquid
connectors on said pressure garment and a self-sealing biomedical
injection patch in said pressure garment.
3. A space suit according to claim 2 including a fecal containment
system, a bio-medical belt, and a urine collection transfer
assembly within said pressure garment.
4. A space suit according to claim 2 including a liquid cooling
garment having cooling liquid inlet and outlet manifolds, flexible
cooling liquid tubing passing through said liquid cooling garment
and connecting said inlet and outlet manifolds, and a connector on
said pressure garment for passing liquid to said liquid cooling
garment.
5. A suit according to claim 2 wherein said gloves comprise a
bladder and an outer restraint fingerless glove, said bladder
having individual fingers and thumb.
6. A suit according to claim 2 including boot portions and having
removable thermal insulating gloves and overshoes received over the
said pressure gloves and boot portions of said suit.
7. A space suit according to claim 2 wherein each of said helmet,
pressure gloves, neck and sleeves contain a metal ring, such rings
respectively adapted for matingly coupling together said helmet
with said neck and said pressure gloves with said sleeves.
8. A space suit for atronauts comprising an undergarment adapted to
cover the astronaut's entire body except for this head, an inner
comfort liner, and outer thermal garment, and an intermediate
pressure garment comprising an inner rubberized bladder and an
outer fabric restraint layer, said comfort liner, pressure garment
and thermal garment being integrally joined and adapted to conform
to the astronaut's body, flexible joint portions in said suit
adapted to fit over at least some of the locations of the
astronaut's joints when the suit is worn, sleeve portions in said
suit, a pair of removable pressure gloves secured to the said
sleeve portions, a removable plastic helmet secured to the neck
portion of said suit, a pair of inlet gas connectors operatively
positioned in said suit for supplying gas under pressure into the
interior of said suit, a pair of outlet connectors operatively
positioned in said suit for removing said gas therefrom as exhaust,
a flexible hose system secured to the interior of said pressure
garment and operatively connected to said inlet gas connectors and
to said outlet connectors for directing pressurized gas over the
interior of said suit, a conduit system in said suit communicating
with said hose system for passing some of said gas directly to the
front of said helmet, a communications carrier within said helmet,
an electrical connector on said suit, an electrical harness in said
suit coupling said electrical connector to said communications
carrier, convolutes at the joint portions, restraint cables secured
to said pressure garment adjacent at least some of said convolutes
to prevent elongation of said ocnvolutes under internal pressure,
and means on said suit for attaching to it a portable life support
module.
9. A space suit according to claim 8 including a block and tackle
assembly secured to the front of said suit for assisting the
astronaut in bending.
10. A space suit according to claim 8 including a cable restraint
assembly secured to said pressure garment and passing through the
crotch of said suit so as to resist the expansion thereof.
11. A space suit according to claim 8 wherein said thermal garment
comprises severl layers of insulation and a metallized fabric outer
layer, said thermal garment including a removable chest cover for
covering said inlet and outlet connectors provided in said pressure
garment.
Description
ORIGIN OF INVENTION
The invention described herein was made in the performance of work
under a NASA contract and is subject to the provisions of Section
305 of the National Aeronautics and Space Act of 1958, Public Law
85-568 [72 Stat. 435, 42 U.S.C. 2457].
This invention is directed to a pressure suit to be worn by human
beings in a hostile environment, and more particularly is directed
to a life support suit to be worn by U.S. astronauts in the Apollo
Space Program. The suit is designed to provide life support not
only within a space vehicle, but also during extravehicular
activities including exploration of the lunar surface. It may also
be used by aircraft pilots during high altitude flights.
The suit of the present invention, in conjunction with a unit
strapped to the astronaut's back, is believed for the first time to
provide a completely self-sustaining system which for a limited
period of time enables the astronaut to freely perform
extravehicular activities, such as external spacecraft corrective
maintenance and lunar surface exploration. A primary feature of the
space suit of this invention involves the retention of a
pressurized atmosphere about the astronaut in the vacuum of free
space, while at the same time providing significantly increased
mobility, both in the torso and the limbs, so that the astronaut
may freely move about and perform useful tasks. At the same time,
the suit incorporates novel constructions and assemblies for
permitting normal body functions, maintains a breathable atmosphere
about the astronaut controlled both as to pressure and temperature,
and affords significant protection from micro-meteroids and other
physical dangers the astronaut may encounter.
The suit comprises, as the principal component, an integrated
three-garment assembly comprising an inner comfort linear, an
intermediate pressure garment assembly providing a controlled
atmosphere within the garment without excessively inhibiting
astronaut mobility, and an outer insulating and protective layer
referred to as an integrated thermal micrometeoroid garment. These
three garments are integrally joined and are of anthropomorphic
construction individually fitted to accommodate the dimensions of
each astronaut. They are designed to cover the entire body in
conjunction with removable gloves and a removable helmet. The suit
of the present invention is worn over specially designed
undergarments which cooperate with the suit, including helmet and
gloves, to completely support normal life functions.
Versatility is built into the suit such that with a minimum of
interchangeable parts the suit can be readily adapted to completely
different astronaut missions. This versatility also makes possible
increased comfort for an astronaut during a mission since it not
only makes it possible for the astronaut to select the most
comfortable and suitable combination for his particular task but
certain elements of the space suit may be completely removed for
increased comfort during times when they are not needed. For
example, both the gloves and helmet are completely removable and
may be taken off by the astronaut within the pressurized cabin of a
space vehicle when it is not necessary to rely on the suit for life
support. Finally, the suit is provided with a redundant pressurized
life support gas connection for increased safety. All of this is
incorporated in a unit which when completely assembled has a total
weight, including helmet and protective shield, of only a little
over 60 pounds.
It is therefore one object of the present invention to provide an
improved space suit particularly designed to be worn by astronauts
in the Apollo Space Program.
Another object of the present invention is to provide a pressurized
suit and an associated assembly adapted to be worn by astronauts
and high altitude aircraft personnel in a hostile and particularly
low pressure environment.
Another object of the present invention is to provide a space suit
particularly adapted with a minimum of modification for both
intravehicular and extravehicular use and particularly designed to
support human life during exploration of the lunar surface.
Another object of the present invention is to provide an improved
pressurized space suit having improved gas sealing qualities and at
the same time providing optimum mobility for the wearer.
Another object of the present invention is to provide a pressurized
space suit assembly particularly designed to be completely
self-contained for sustaining human life independent of any other
life support source for periods of several hours. The suit is
adapted to existing interface equipment and during intravehicular
activity may be completely interfaced with the cabin life support
system of a space vehicle.
These and further objects and advantages of the invention will be
more apparent upon reference to the following specification,
claims, and appended drawings, wherein:
FIG. 1 is a perspective view of the overall space suit and
associated life supporting unit as provided for extravehicular
activity and particularly lunar surface exploration;
FIG. 2 is a perspective view similar to FIG. 1 showing the suit
alone, with extravehicular overshoes, gloves, and a helmet shield
removed;
FIG. 3 is an exploded view showing the major components making up
the extravehicular configuration of the space suit and undergarment
construction of the present invention;
FIG. 4 is an exploded view similar to that of FIG. 3 showing the
major components of the suit usable for intravehicular
activities;
FIG. 5 is an enlarged perspective view of the suit with helmet and
gloves removed and the integrated thermal micro-meteoroid garment
omitted for the sake of clarity;
FIG. 6 is an enlarged view showing the thigh and upper right leg
portion of the basic pressure garment assembly of FIG. 5;
FIG. 7 is a perspective view of the inner liner for the pressure
garment assembly of FIG. 5;
FIG. 8 is a perspective view of the helmet neck ring for the space
suit of this invention;
FIG. 9 is a similar perspective view of the suit neck ring adapted
to be attached to the helmet neck ring of FIG. 8;
FIG. 10 is a perspective view of the transparent pressure helmet
assembly for the space suit of the present invention;
FIG. 11 shows the space suit electrical harness;
FIG. 12 is a perspective view showing the rear portion of the outer
garment or integrated thermal micro-meteoroid garment of the space
suit;
FIG. 13 is a perspective view of one of the pressure gloves of the
space suit;
FIG. 14 is a perspective view of an extravehicular glove adapted to
be worn over the glove of FIG. 13 during extravehicular
activities;
FIG. 15 is a perspective view of the left lunar overshoe for the
suit of the present invention;
FIG. 16 is a perspective view similar to that of FIG. 15 of the
right lunar overshoe;
FIG. 17 is a perspective view with enlarged pertinent cross
sections (17A,17B,17C) showing the extravehicular visor assembly of
the space suit;
FIG. 18 is a perspective view showing an undergarment usable in the
extravehicular configuration, i.e., the liquid cooling garment;
FIG. 19 is a perspective view of the pressurization and ventilation
life support pressure gas system for the suit of the present
invention;
FIG. 20 is a perspective view of one of the locking rings at each
wrist of the suit;
FIG. 21 is a similar view of a locking ring mounted on one of the
gloves and adapted to lock to the wrist ring of FIG. 20; and
FIG. 22 is a schematic cross sectional plan view through the torso
and right wrist portion of the suit taken along line 22--22 of FIG.
2.
Referring to the drawings, the self-contained life supporting
system of the present invention is generally indicated at 10 in
FIG. 1 and illustrates how the astronaut will appear as he explores
the surface of the moon. The system of FIG. 1 is designed to permit
the astronaut substantial mobility and to make him completely
self-sustaining for periods of as much as 6 hours or more outside
the space vehicle and particularly on the lunar surface.
The assembly 10 comprises as its major component a space suit,
generally indicated at 12, to the back of which is strapped a lunar
module 13 including an oxygen purge system, generally indicated at
14, and a portable life support system beneath it containing water,
filters, battery, etc., is generally indicated at 16. Communication
with other astronauts and with the space ship is maintained by way
of an antenna 18.
As illustrated in FIG. 1, the suit 12 comprises a removable helmet
over which is mounted an extravehicular visor assembly 20 to
protect the astronaut both from physical injury or damage and from
the intense rays of the sun outside the space vehicle. Mounted on
the astronaut's upper chest is a portable life support system
control box 22 which is connected by line 24 to the oxygen purge
system 14 and by a second line 26 to the portable life support
system 16, both mounted by straps on the astronaut's back. During
extravehicular activity, the suit is periodically purged by the
astronaut's manual operation of an oxygen purge system actuator 28,
mounted on the control box 22. Oxygen flow to the interior of the
suit is by way of a system umbilical 30 which connects from the
oxygen purge system 14 to the chest of the space suit 12 in a
manner more fully described below. The oxygen connections on the
chest of the suit are closed off by a connector cover 32 in FIG. 1.
Other connections to the apparatus mounted on the astronaut's back
providing for communication, ventilation and liquid cooling are
from additional connectors beneath cover 32 by way of umbilicals
34. For extravehicular activity, the astronaut is provided with a
pair of extravehicular gloves 36 and 38 and a pair of lunar
overshoes 40 and 42 which cooperate to protect extremities from the
hazards of space and particularly provide protection by way of
thermal insulation from intense sunlight and provide physical
protection from micro-meteoroid bombardment. The outer garment
illustrated in FIG. 1, referred to as the integrated thermal
micro-meteoroid garment, is a metallized white or light colored
fabric and is designed to provide thermal insulation and
micro-meteoroid protection.
The suit is provided with a plurality of pockets so that the
astronaut will have ready access to everything that he may need
outside the vehicle. Just below one shoulder of the space suit 12
is a sunglasses pocket 44. A similar pocket 46 adjacent the other
shoulder is a penlight pocket. A utility pocket 48 is provided in
the upper left leg. Finally, the upper right leg of the integrated
thermal micro-meteoroid garment or outer suit garment is provided
with a flap 50 which not only houses the suit donning lanyard, but
also is an access flap for a urine collection and transfer
assembly, for a dosimeter connection, and includes a self-sealing
patch for bio-medical injections.
FIG. 2 shows the astronaut as he might appear inside the space
vehicle either before or after extravehicular activity. In FIG. 2,
the lunar module 13 has been removed from the astronaut's back, and
helmet shield 20 has been removed as have the extravehicular gloves
and lunar overshoes. Also, the front chest cover has been removed
to expose the various connectors for establishing fluid and
electrical communication to the interior of the suit.
Covering the astronaut's head is a pressure helmet assembly 52
including a shell formed of a transparent polycarbonate material.
The helmet is attached to the neck of the suit by an interlocking
metal ring assembly, generally indicated at 54, one ring of which
is attached to the helmet and the other to the suit neck. A neck
dam (not shown) may be inserted into the neck of the suit to act as
a water shield for re-entry or other purposes when it is believed
that the astronaut may land in the ocean or otherwise be exposed to
a water environment.
In FIG. 2, the connector cover is removed exposing four gas
connections comprising two upper inlet connections 56 and 58 and
two lower outlet connections 60 and 62. These connections permit
life support gas, such as oxygen, to be passed into and out of the
space suit which (1) provides oxygen for the astronaut to breath,
(2) maintains the interior of the suit pressurized, and (3)
provides ventilation over the astronaut's entire body. Connector 64
on the astronaut's chest is for circulating cooling liquid, such as
water, through the interior of the space suit which is only
required during extravehicular activity, while connector 66
provides for electrical connection to the interior of the space
suit. Two of the lines passing through electrical connector 66 lead
to a pair of microphones 68 and 70 located adjacent the astronaut's
mouth by means of which he can communicate with other astronauts
and with communication equipment on board the space vehicle.
Removal of the extravehicular gloves 36 and 38 of FIG. 1 exposes in
FIG. 2 the pressure gloves 72 and 74. These gloves are formed in
part from a rubberized fabric and have sufficient flexibility so
that the astronaut can perform a variety of intricate manipulations
with the fingers and hands. Removal of the lunar overshoes 40 and
42 of FIG. 1 exposes in FIG. 2 the boots 76 and 78 which are formed
integral with the remainder of the space suit. On the right-hand
arm above glove 72 is a pressure gage 80 by means of which the
astronaut is able to monitor the pressure within the suit and at
approximately the same location on the left arm is a pressure
relief valve 82 adapted to open at a predetermined pressure to
automatically relieve the pressure within the suit when it becomes
too high. The suit is entered through a slide fastener or zipper
passing over the back from just beneath the neck downwardly between
the shoulders and through the crotch to the front of the suit,
which fastener is covered by an entrance slide fastener flap 84.
Finally, strapped to the astronaut's legs are a scissors pocket 86,
a checklist pocket 88, and a data list pocket 90.
FIG. 3 is an exploded view showing the elements of the space suit
and undergarments of the present invention used for extravehicular
activity. In addition to the suit proper, hereafter referred to as
the pressure garment assembly generally indicated at 12 in FIG. 3,
the astronaut wears beneath the pressure garment assembly a fecal
containment subsystem 92 worn much in the manner of undershorts, a
urine collection and transfer assembly 94, a bio-medical belt 96,
and a liquid cooling garment 98 worn much in the manner of long
underwear. The undergarments 92, 94, 96, and 98 are normally donned
by the astronaut in the order in which they are numbered. Over the
basic pressure garment assembly, the astronaut wears elements
previously described, namely, the extravehicular visor assembly 20,
connector cover 32, extravehicular gloves, such as glove 38, and
lunar overshoes, such as overshoe 42. The suit is put on by the
astronaut with the aid of a pair of removable donning straps 100
and 102, which after the suit has been donned are stored beneath
the access flap 50. Within the helmet 52, the astronaut's head is
surrounded by a communications carrier 104 on which are mounted the
microphones previously described.
FIG. 4 is an exploded view showing all the elements of the space
suit forming the intravehicular configuration. That is, it is
contemplated that at least one astronaut in the Apollo Program
flights will remain in the space vehicle at all times. This
astronaut does not need the extravehicular protection of the others
and for this reason may wear a modified suit of the same basic
construction, but with important modifications. In FIG. 4, like
parts bear like reference numeals, and it will be noted that the
intravehicular configuration of FIG. 4 is quite similar to the
extravehicular configuration of FIG. 3. The principal difference is
that in place of the liquid cooling garment 98 illustrated in FIG.
3, the astronaut wears a constant wear garment 106 beneath the
pressure garment 12 very closely resembling a pair of long
underwear. The constant wear garment 106 is optional and the
astronaut may, if desired, wear the liquid cooling garment 98 of
FIG. 3 so that, in case of an emergency, he too will be prepared to
go outside the vehicle where he will be exposed to intensive
sunlight and the liquid cooling provided by the garment 98 is
required. FIG. 4 also shows various components of the basic
pressure garment assembly, including the pressure helmet assembly
52 and pressure glove 72, previously described. Inside the vehicle,
the astronaut may slip a cover glove assembly 108 over the pressure
glove 72 to protect it and may slip a helmet shield 110 over the
pressure helmet assembly 52 to protect it from contact with the
inside of the space vehicle. As previously mentioned, the basic
pressure garment assembly 12 comprises an outer garment 112,
previously referred to as the integrated thermal micro-meteoroid
garment, which is attached to the pressure sealing and mobility
providing garment, hereafter referred to as the torso limb suit
assembly 114. Communications carrier 104 forms part of the torso
limb suit assembly, whereas the micro-meteriod garment 112 is
provided with a removable chest cover 116.
FIG. 5 is an enlarged perspective view of the torso limb suit 114
which, while shown separately, is worn integrally with an inner
comfort liner described below and the outer micro-meteoriod garment
112, previously described.
The torso limb suit 114 of FIG. 5 forms a basic component of the
space suit of the present invention since, in conjunction with the
helmet and gloves, it provides a life supporting environment for
the astronaut and, more specifically, acts both as the pressure
retaining sealing component for the suit and at the same time
incorporates constructions and assemblies which provide for
increased mobility. That is, when the space suit is inflated to an
internal operating pressure in the neighborhood of 3 to 4 pounds
per square inch, the space suit tends to expand and become rigid so
that it is difficult for the astronaut to move about. In order to
increase the astronaut's mobility, substantially constant volume
bellows-like convolutes are provided at most of the suit joints and
various cable and restraint assemblies are mounted to the exterior
of the suit to permit the astronaut to bend and flex the suit
joints and move about. Pressure sealing is effected by providing
the suit with an inner rubberized fabric layer referred to as a
bladder 118. Over the bladder are several layers of fabric forming
a restraint layer 119 which protect the bladder and also aid in
retraining it.
Referring to FIG. 5, the helmet attaching ring is illustrated at
120 as secured to the neck of the space suit. A pair of covers 122
and 124 overlie a pair of constant volume shoulder convolutes which
permit the astronaut to flex and bend the shoulder joints without
undue effort when the suit is inflated. Similar covers 126 and 128
overlie constant volume convolutes provided in the suit adjacent
the elbow. Covered convolutes are also provided at the hips or
upper thigh as illustrated at 130 and 132 and at the knee joints as
illustrated at 134 and 136.
Unless these constant volume convolutes are in some way restrained,
they tend to elongate and expand under the internal pressure within
the suit. Thus, the thigh convolute 167 is restrained against
expansion by its cover 130 and is longitudinally restrained by a
metal cable 168 attached at its upper end to a reinforced portion
of the suit at the hip and at its lower end to a reinforcing patch
adjacent the knee which cable is covered by a fabric wear sleeve or
cable guide 138. It is understood that a similar cable provides
restraint at hip joint 130 on the inside of the leg, as well as the
outside, i.e., spaced about the astronaut's leg approximately
180.degree. from the cable 138.
The shoulder restraint takes the form of a shoulder cable 140 which
extends continuously from over the astronaut's breast bone through
the shoulder assembly adjacent convolute 122 across the astronaut's
back and back through the other shoulder assembly adjacent
convolute 124 to a shoulder cable disconnect 142. This cable
restrains the shoulders and is continuous except for the two ends
attached to the disconnect 142 which the astronaut, at his option,
may open to disconnect cable 140 and remove the shoulder restraint
should he so desire.
Additional restraint is provided by a crotch wire assembly, partly
illustrated at 144, which assists the astronaut in bending and
other torso movements. One end of the crotch cable assembly 144 is
attached to a reinforcing patch 146 having a loop 148 adapted to
receive straps for supporting the lunar module 13 of FIG. 1. Lunar
module support eyelets are also provided at each hip as illustrated
by the eyelet 150. To assist the astronaut in bending forward and
in sitting down, the front of the torso is provided with a block
and tackle assembly including a torso adjusting strip 152 which the
astronaut may grasp and pull to foreshorten the torso of the suit
and relieve forward bending stresses on his body. The upper end of
this assembly is provided with an upper lunar module supporting
bracket including an eyelet, generally indicated at 154.
The space suit of the present invention is custom designed and
fitted to each astronaut. In order to provide fine adjustment for
the astronaut's limbs, portions of the arms and legs are joined by
interlacing which may be adjusted to slightly shorten or lengthen
the limb portions of the suit in accordance with the astronaut's
preferences. The lacing in the arms is just above the wrist
connector rings 123 and 125, as 156 at 156, and 158, respectively.
Similar lacings are illustrated at 160 and 162 in the legs just
above the boots 78 and 76. Formed in the right legs of the torso
suit 114 of FIG. 5 and adapted to underlie the flap 50 of FIG. 1 is
a urine transfer fitting 164 and a bio-medical injection patch 166.
This patch comprises self-sealing rubber type material which may be
punctured by a hypodermic needle but immediately reseals itself
when the needle has been removed. The purpose of the patch is to
permit the astronaut to inject himself with drugs or other
medicines in the event he becomes sick or is in pain during an
Apollo flight.
FIG. 6 is an enlarged view of the right leg of the torso limb suit
illustrated in FIG. 5 with parts broken away to show portions of
the thigh and knee convolutes. Specifically, the thigh convolute
cover 130a which is sewn to the suit along its upper and lower
edges, is broken away at 165 to show the thigh convolute 167. The
convolute is molded and formed of a rubberized fabric to assume the
natural shape of a convolute or substantially constant volume
bellows. Passing beneath cable guide 138 and overlying the
convolute is a metal wire or cable 168 secured at its lower end by
eyelet 170 to a fabric reinforcement 172 sewn to the thigh cone
174. The other end of cable 168 is similarly attached above the
bellows to the upper part of the leg by an eyelet indicated in
dashed lines at 176. A similar cable (not shown) overlies the
bellows on the inside leg surface, i.e., spaced approximately
180.degree. around the leg from cable 168. These two thigh cables
form an elongation restraint for the convolutes 166 so as to resist
elongation of the convolutes when the suit is inflated. The
substantially constant volume nature of the convolute permits the
suit to be readily flexed in the area of the thigh joint even when
under substantial internal pressure.
Knee convolute cover 134 is similarly broken away at 178 to show a
portion of the knee convolute 180. The convolute is similar to the
thigh convolute and is molded from a rubberized fabric and
similarly is restrained longitudinally by a pair of cables on
opposite sides of the knee, one of which is illustrated in dashed
lines at 182. The cable is joined at its upper end by an eyelet 184
to reinforcement 172 and at its lower end by an eyelet 187 to the
lower leg cone 188. Near the bottom of the lower leg cone is
provided a loop tape 190 and slide fastener 192 for joining the
boot 161 of FIG. 5 to the leg of the torso limb suit. The urine
transfer fitting 164 is shown as formed in the thigh cone 174 as is
the bio-medical injection patch 166.
FIG. 7 is a perspective view of the comfort liner assembly forming
the inner layer of the torso limb suit of FIG. 5. The comfort
liner, generally indicated at 194 in FIG. 7, covers the entire body
with the exception of the head, hands and feet. It includes a neck
portion 196 with a snap flap 198 for the attachment of a
communication lead for the microphones 68 and 70 of FIG. 2. Mounted
on the shoulders of the liner are a pair of cushion pads 200 and
202 and similar pads 204 and 208 are provided on the upper arms.
Sewn into the breast portion of the liner is a communications lead
passthrough 210 and a bio-medical lead passthrough 212. A somewhat
similar water connector passthrough 214 is sewn to the left breast
of the liner. Fastener tapes are provided on the liner at 216, 218,
and 220, and a waste valve lead passthrough 222 is sewn into the
upper portion of the right leg. The fastener tapes, in conjunction
with zippers 224 and 226 at the lower ends of the legs, are used to
connect the liner to the interior of the pressure garment assembly
and specifically to the interior of the torso limb suit of FIG.
5.
FIG. 8 shows the helmet half 228 of the helmet attaching ring
assembly 54 of FIG. 2. FIG. 9 shows the suit half 120 of the helmet
attaching ring assembly. The suit half 120 is formed of a metal
housing 230 on which is mounted a vent channel 232, a resilient
seal 234, and a locking ring 236. On the upper surface of the
locking ring are a pair of index marks 238 and on the outside of
the locking ring is a lock subassembly 240 and a lock stop 242. The
helmet half 228 is similarly made of metal and is provided with a
vent channel 244 adapted to cooperate with the channel 232 of the
suit half 120 of the helmet attaching assembly. Similar index marks
246 are provided on the upper surface of the helmet half of the
assembly. During assembly, the helmet half or ring 228 is
telescopically received within the upper portion of the suit half
or ring 120 and the vent channels are aligned by the index marks
238 and 246. The two rings are then locked together by the lock
subassembly 240 in tight sealing engagement.
FIG. 10 is an enlarged perspective view of the pressure helmet
assembly 52 of FIG. 2. The major portion of this assembly comprises
a transparent shell of polycarbonate material attached at its lower
end to the neck ring 228 of FIG. 8. Mounted in the rear of the
helmet is a vent pad 248 having along its upper surfaces spacers
250 which space the upper end of the vent pad from the top of the
helmet to provide gas channels 252 communicating with gas
passageways 253 through the vent pad. Pressurized life supporting
gas (oxygen) is transmitted upwardly through the passageways in the
vent pad and exhausts through the channels 252 over the head of the
astronaut to impine upon the front area of the helmet so as to
prevent the helmet from fogging in front of the astronaut's face.
Mounted near the front of the helmet is a feed port 256 normally
closed off by feed port cover 258.
FIG. 11 shows the space suit electrical harness by means of which
the astronaut's physical condition is monitored and through which
he communicates with other astronauts and with the space craft. The
bio-medical belt 96, which he wears around his waist and which is
provided with bio-medical sensors, is provided with an upwardly
extending noncrushable lead 260 which is electrically connected
through connector 262 to an electrical harness 264. Approximately
midway of the harness is an electrical jack 266 by means of which
the astronaut is plugged into a suitable power supply, either in
the space craft or in the lunar module previously described, by
means of a multiwire cable passing through the electrical connector
66 of FIGS. 2 and 5. The upper end of the harness is electrically
connected through connector 268 to the communications carrier 104
which fits over the astronaut's head. This harness includes a pair
of earphones 270 and 272, as well as the microphones 68 and 70
previously described, which elements are embedded in or attached to
the relatively soft fabric padding material of the communications
carrier. Electrical connection to the harness from the micro-phones
and earphones is by way of a noncrushable flexible lead 274.
FIG. 12 is a perspective view of the rear of the outer covering or
integrated thermal micro-meteoroid garment 112 of FIG. 4 forming
the outer component of the pressure garment assembly of the space
suit. This garment is designed primarily for heat insulation to
protect the astronaut from the extremes of heat and cold in space
and on the lunar surface and also to protect the astronaut from
micro-meteoroid bombardment. It consists of the integral boots 76
and 78 and covers the entire body with the exception of the hands
and head. Extending from just below the neck is an entrance slide
fastener flap 276 which covers the double slide fastener through
which the space suit is entered. This flap is partly broken away at
278 to show the snap assembly 280 and loop tape 282 for closing it
and lacing garment 112 to the torso limb suit assembly 114. A lumar
module restraint strap 284 is attached over each hip and just above
each knee is an assist strap 286. The outer cover garment 112 is of
multilayer construction comprising a light colored reflective
metallized outer shell and an inner liner separated by several
spaced layers of heat insulating material.
FIG. 13 is a perspective view of the pressure glove 72 of FIG. 4.
This glove is provided with individual fingers 294 and a separate
thumb 296, all formed integral with a hand covering sheath molded
from a rubberized fabric for good flexibility, i.e., Nylon dipped
in a Neoprene compound. Preferably molded at the ends of the
fingers and thumb are metal pieces (not shown) simulating finger
nails to assist the astronaut in performing intricate tasks with
the hands. Overlying the rubberized sheath and cemented to it is a
fabric half glove 298 somewhat resembling in appearance a golf
glove and formed of fabric to provide restraint for the rubberized
fabric or bladder when the glove is inflated. Adjacent the wrist,
the half glove 298 is provided with a fastener tape 300 and over
the top portion with an adjusting belt 302. Glove 72 is provided
with a convolute enclosed by cover 303 and is joined to the space
suit sleeve by a rotatable metal connector assembly as described
below. Restraint cables in the glove cooperate with cover 303 to
restrain the wrist convolute. The glove is molded to size from a
cast of the astronaut's hand. Bladder projections 305 at the finger
joints provide increased flexibility.
Adapted to be received over the pressure glove 72 of FIG. 13 is an
extravehicular glove 38 shown in FIG. 14. This glove is preferably
made of good heat insulating material much in the manner of the
integrated thermal micro-meteoroid garment of FIG. 12, and
comprises an elongated cuff 304 extending upwardly over the forearm
so as to cover the pressure relief valve 82 of FIG. 2. This glove
too is provided with separate fingers 306 and a separate thumb (not
shown). Sewn to the top of the glove is a flap 308. The
extravehicular glove 38 is provided with an adjustable strap 310
for tightening it over the upper portion of the astronaut's hand to
provide restraint for the palm. Flap 308 is then turned down over
the adjustable strap 310 and secured above the wrist by cooperating
hook and pile fasteners 312 on the auxiliary flap 313 attached to
the glove 38 by snap fasteners 314.
FIGS. 15 and 16 are perspective views of the left and right lunar
overshoes 42 and 40, respectively. The lunar overshoes are of
similar construction and each includes a donning strap 316 forming
a loop at the heel which may be grasped by the astronaut to draw
the heel of the overshoe over the space suit boot. Each overshoe
tongue 318 is provided with a snap fastener 320 cooperating with
corresponding snaps 322 for connecting the front of the overshoe to
the tongue. Finally, the overshoe is secured over the instep by a
strap assembly 324 fastened by a latch 326. The lunar overshoe
provides both thermal (insulation) and abrasion protection for the
astronaut's foot on the lunar surface.
FIG. 17 is an enlarged view of the extravehicular visor assembly 20
of FIG. 1. This visor comprises a collar 328 attachable to the neck
of the space suit and a semispherical base 330 adapted to protect
the astronaut's head both against physical damage and against
intense heas and light from the sun. Base 330 is preferably a
multilayer construction comprising an outer tough protective
polycarbonate sheell and an inner membrane separated by several
layers of heat insulating material. The base is cut away in the
front as indicated by the dashed line at 332 so that it may be
slipped over the pressure helmet assembly 52 of FIG. 2. It is then
attached to the neck of the space suit by means of a latching
mechanism (not shown) and the flexible fabric collar 328.
Along the cut away front portion of the base is a visor, generally
indicated at 334, comprising an outer rigid polycarbonate layer 336
forming a sun visor and a spaced inner rigid layer 338 of
transparent polycarbonate forming a protective visor. The outer
layer or sun visor is coated to provide light attenuation and to
reduce heat gain within the helmet. It is provided with a tab 339
on each side so that it may be moved between full up and full down
positions. The visor is pivoted on each side adjacent the
astronaut's ears to the base 330. One of the support pivot
assemblies 340 is illustrated in cross section in FIG. 17A and
comprises a pivot pin 342 secured to the base and biased by a hinge
adjustment spring 344. This spring bears against a friction plate
346 and the two visors are spaced by washers 348 and a central
spacer 350. The upper and lower edges of the visor are closed off
by light seals along its upper and lower edges as illustrated at
352 in FIG. 17B and 354 in FIG. 17C these figures respectively
showing cross-sections of the circled areas A and B in FIG. 17.
Thus, when the astronaut closes the visor assembly 334, he is
completely protected both against physical damage and against the
intense and ultraviolet radiation from the sun existing in space
and on the lunar surface. At the same time, each layer or shield
336 or 338 of the visor may be independently moved upwardly to any
desired position and may be completely slid over the back of the
visor assembly about pivot pins 342 when the protection is not
needed and the astronaut wishes to see through the helmet more
clearly.
FIG. 18 is an enlarged view of the liquid cooling garment 98 of
FIG. 3. This garment is worn by the astronaut underneath the
pressure garment assembly much in the manner of long underwear and
is worn in conjunction with a pair of heavy socks 356 and 358
attached to it. The liquid cooling garment 98 may be worn by all
the astronauts but is only required for extravehicular activity to
provide liquid cooling when the astronaut is outside the space
vehicle and exposed to the intense rays of the sun. The garment is
provided at its front with a zipper 360 through which it is donned
and with snap fasteners 361 for securing to it the bio-medical belt
96 of FIG. 3. A dosimeter pocket 362 is provided in the left leg of
the garment and mounted on the waist is a water line 364 comprising
inlet and outlet pipes terminating at their upper ends in a double
or two-way connector 366. This connector is adapted to pass cooling
water both into and out of the cooling garment by way of the
connector 64 of FIG. 2. The lower ends of the tubes 364 are
connected to inlet and outlet manifolds respectively, generally
indicated at 368, which in turn are coupled to Tygon tubing 370
which passes through the cooling garment and over substantially the
astronaut's entire body.
FIG. 19 is a diagrammatic view of the pressurization and
ventilation system through the space suit of the present invention.
Flow of pressurized life supporting gas, such as oxygen, is
indicated by the arrows in FIG. 19, the light arrows indicating
inward flow and the darker arrows showing the return gas flow
paths. While a preferred direction is illustrated, it is understood
that the air flow, if desired, may be in the reverse direction.
Oxygen may enter through either one of the gas inlet connectors 56
or 58 since these connectors are in fluid communication with each
other by way of an intermediate plenum 372. A similar plenum 374
joins the gas outlet connectors 60 and 62 so that the outlet may be
taken from either of these connectors. A redundant connector
assembly is provided so that the astronaut may attach one set of
connectors to the lunar module before exiting from the space
vehicle without first having to disconnect the other set from the
cabin supply. The double set of connectors is also provided so that
the astronauts may be connected to each other in the event the
supply to one of them for some reason fails.
Gas passes upwardly from one of the inlet connectors 56 or 58 by
way of one of the noncrushable ducts 376 or 378 where it exists
through vent channel 244 in the helmet ring into the vent pad 248
of the helmet shown in FIG. 10 and downwardly over the astronaut's
head onto the front surface of the helmet where it helps to defog
the helmet in front of the astronaut's face. The life supporting
gas is, of course, also breathed by the astronaut.
Incoming gas is also supplied from one of the inlet connectors to
the torso channels 380 and 382. These channels preferably are
pervious to gas along their length so that the gas is distributed
to the astronaut' s torso over substantially the entire length of
both the torso channels to which the gas is supplied. Gas from the
helmet and from the torso under pressure passes over the
astronaut's body and downwardly and outwardly of the limbs as
indicated by the light arrows in the drawings. The gas is returned
from the hands by way of arm channels 384 and 386 and to the
respective outlet connectors 60 and 62. Similarly, gas is returned
from the feet by way of leg channels 388 and 390 to the outlet
connectors 60 and 62. The return channels 384, 386, 388 and 390 are
vented adjacent the extremities so that the return gas may enter
them and be conducted to the outlets. Foot pads 392 and 394 are
also provided to help collect the returning gas and to ventilate
the feet.
Thus, the life supporting gas (1) pressurizes the interior of the
suit to a pressure of from 3 to 4 pounds per square inch, (2)
provides a breathable gas to the astronaut, and (3) ventilates and
helps cool the suit and removes moisture resulting from
perspiration over the astronaut's entire body. Pressure gage 80
provides the astronaut with a visual indication of the pressure
within the suit and a pressure relief valve 82 automatically opens
when the pressure becomes too high to relieve the pressure within
the suit.
FIGS. 20 and 21 show the interconnecting locking rings for
attaching a pressure glove, such as the glove 72 of FIG. 4, to the
suit. FIG. 20 shows the suit half of the assembly, i.e., the suit
ring at the wrist of the suit sleeve, and FIG. 21 shows the glove
half or the metal ring attached to the glove. The suit ring is the
female half and is generally indicated at 396 in FIG. 20. It
comprises a locking ring 400 on a housing 402 to which is mounted a
vent fitting 404. Locking ring 400 is provided with a pair of lock
tabs 406 and 408, a lock button 410, and index marks 412 for
aligning it with the glove ring of FIG. 21.
The glove ring is the male half and is generally indicated at 414
in FIG. 21. It consists of an outer race 416 on which is mounted a
vent fitting 418 and an inner race 420. The rings of FIGS. 20 and
21 are aligned by index marks and locked together in sealtight
relationship to join the gloves to the sleeves of the space suit.
Th glove ring includes a sealed bearing with inner and outer races
to permit 360.degree. of glove rotation.
The torso limb suit 114 of FIG. 5 forms the basic garment since it
provides sealing over the greater part of the body to contain the
life supporting gas and also incorporates restrain mechanisms so
that the astronaut may move about and perform tasks. This torso
limb suit assembly is a custom-sized unit which encompasses the
body exclusive of the head and hands. The integrated thermal
micro-meteoroid garment 112 is laced to the torso limb suit 114 and
acts as a shield for the torso and limbs against the hazards of
free space and lunar regions. The pressure helmet assembly is
constructed of clear polycarbonate plastic and, when secured to the
torso limb suit 114, remains in fixed position. The pressure glove
is basically a conformal molded bladder having a quick disconnect
coupling, restraining features and is retained for intravehicle use
only. The extravehicular glove provides thermal micro-meteoroid
protection layers that are slipped over the basic pressure glove
assembly. The lunar overshoe is similar in cross section to the
extravehicular glove and is donned prior to egress. The slip-on
helmet shield is a lightweight polycarbonate shell which fits over
the pressure helmet assembly and provides scuff protection during
tunnel transfer. The purge valve inserted into the helmet feed port
is used to purge carbon dioxide from the helmet area during
extravehicular operations. Gas connector caps are installed in the
nonutilized gas connectors to prevent inadvertent depressurization
as may be cuased by the accidental opening of the water block
within the connector. A suit donning cloth strap assembly is
inserted into the slide tab of each rear entry slide fastener
assembly, i.e., an inner pressure sealing fastener and an outer
restraint slide fastener, at the back of the suit and these straps
are used to facilitate actuation of the slide fasteners. The neck
dam constructed of Neoprene fits around the neck and over the
helmet attaching ring to prevent the entrance of water into the
suit during water egress.
The torso limb suit 114 is an anthropomorphic pressure envelope
which encloses the torso and limbs of the astronaut, exclusive of
the head and hands. The torso section is customsized to fit the
individual while the limb sections are graduated in sizes and
feature lace adjustment provisions to accommodate individual limb
lengths. Convoluted joints near constant volume are located at the
shoulders, elbows, hips, knees, and ankles (as well as at the glove
wrists) to permit joint movements with a minimum of energy
expenditure.
The suit is a gas retaining restraint assembly. It incorporates
reinforced attachment supports for restraint cables which sustain
axial limb loads during pressurized modes of operation. The front
of the suit employs a block and tackle system having adequate
mechanical advantage to permit the foreshortening of the torso
during extended periods of sitting or bending. An arm assembly is
secured to each torso scye opening. Axial loads across the
shoulders are sustained by the shoulder restraint cable
assembly.
A wrist disconnect assembly is secured to the lower arm extremity
and consists of a mechanical self-sealing coupling designed to
receive the pressure glove. A leg assembly is secured to the torso
thigh opening. Axial loads at this joint are sustained by inner
thigh crotch cables and outer thigh restraint cables. The thigh
restraint cables are custom length and are designed to establish a
proper crotch/limb angle which accommodates the wearer's need for
comfort and mobility. The leg assembly ends at midcalf where it
interfaces with the boot assembly. The boot assembly encloses the
foot and is flexible enough to allow some ankle and foot
movements.
The innermost layer of the torso limb suit is a removable liner
assembly which is designed to promote comfort and to facilitate
donning the suit. A mechanical self-sealing coupling is installed
in the torso neck opening and is held in place by means of a
compression band. The inlet and outlet gas connectors are attached
to each side of the front torso. The dual or redundant connector
installation permits an umbilical transfer between the ventilation
systems of the space craft environmental control system, portable
life supporting system, or test stand, without interrupting the
flow of pressurization and ventilation gas through the suit. A
ball-lock type quick disconnect multiple water connector assembly
provides a dual passage through the suit for connecting the liquid
cooling supply to the liquid cooling garment. When the liquid
cooling garment is not connected, a plug is locked in place to
prevent leakage of gas out of the suit during pressurized modes of
operation. The suit electrical harness provides an electrical
interface between the communications/bio-instrumentation components
of the suit and the communications/bio-instrumentation umbilical of
the space craft, portable life support system, or test stand. A
transfer hose connected to the internal housing of the urine
transfer connector interfaces with it for the transfer of urine to
the waste management system of the space craft. The pressure gage
provides for visual monitoring of the differential pressure.
Mounted to the left wrist cone is a pressure relief valve which
relieves suit pressures in excess of 5.5 p.s.i.
The suit of the present invention is designed to afford pressurized
protection for the astronaut during periods of extravehicular
activity and in the space craft during pressurized modes of
operation. The combination sealing and restraint structure of the
suit accepts a standard operating pressure of 3.75 p.s.i.g. The
assembly is structurally tested at 6.0 p.s.i.g. and is periodically
proof-tested at 8.0 p.s.i.g. The suit is designed to withstand a
burst pressure of not less than 10.0 p.s.i.g. Also, the pressurized
envelope will not permit leakdage in excess of 180 s.c.c. per
minute when pressurized to 3.75 p.s.i.g. under normal conditions.
The gas flow into the helmet passes over the inside surface of the
front of the helmet to facilitate helmet defogging and is then
supplied to the oral-nasal area of the helmet for efficient
respiration and dissipation of carbon dioxide from that area. As
the flow of gas passes down through the neck opening area and over
the body, the gas flow removes heat and transports evolved body
gases, toxicants, and moisture out of the suit. The normal inlet
gas flow temperature is expected to be 35.degree.-85.degree. F.
During extravehicular modes of operation with the inlet gas
connector diverter valves in the closed position, the specified
pressure drop across the ventilation system is a nominal 2.273
inches of waer at 6.0 cubic feet per minute flow rate of oxygen at
3.9 p.s.i.a. having an inlet gas temperature of 77.degree. F.
During intravehicular modes of operation with the inlet gas
connector diverter valves in the open position, a nominal pressure
drop of 4.7 inches of water will exist at 12.0 cubic feet per
minute flow rate of oxygen at 3.5. p.s.i.a. with an inlet gas
temperature of 50.degree. F. The liquid cooling system is designed
as the primary mode for removing body heat from within the suit
during the performance of extravehicular mission tasks. During the
circulation process, the heat within the suit is transferred to the
liquid which returns through the outlet passage of the multiple
water connector to the lunar module for cooling or chilling.
The space suit of the present invention is designed so that trained
personnel may don all the equipment without assistance. The aid of
a technician or fellow crewman, however, does facilitate donning
and insures that the tasks are properly accomplished. After the
undergarments are first plced on, a donning lanyard is attached to
each of the slide fateners, namely, the pressure sealing slide
fastener and the restraint slide fastener which overlies it. The
astronaut then assumes a sitting position and places the suit on
his lap with the rear entry area open. With one hand the astronaut
grasps the helmet attaching ring and with the other hand grasps the
suit donning lanyard. One foot is placed into the suit and
manipulated until the foot is inserted in the boot. This may be
facilitated by grasping the loop at the rear of the boot. This
procedure is then repeated for the other foot. The suit is then
pulled upward into proper position over the legs and well up into
the crotch. The hands are then inserted into the shoulder
convolutes and the head is lowered and positioned into the neck
ring while simultaneously slipping the hands fully into the arms
and through the wrist connectors. The astronaut then stands and
permits the suit to settle over the torso and limbs. One lanyard is
then used to help close first the sealing slide fastener and then
the restraint slide fatener which overlies it. The various
connections to the tubing, gloves and helmet then follow in the
proper order. In removing the suit, the procedure is reversed.
It is apparent from the above that the present invention provides a
novel space suit particularly designed to interface not only with
cabin equipment but also portable equipment mounted on the
astronaut's back so as to render the astronaut completely
self-supporting and mobile in hostile space and lunar surface
environments. Important features of the suit include an inner
comfort liner to be worn over the undergarments, an intermediate
principal garment incorporating both pressure sealing and mobility
rstraints, and finally, an outer protective garment having heat
insulating and a metallized fabric outer layer. The suit covers
substantially the entire body with the exception that it is
provided with readily removable gloves and helmet so that the
astronaut may be completely comfortable in the pressurized
atmosphere of a space vehicle cabin.
The invention may be embodied in other specific forms without
departing from the spirit or essential characteristics thereof. The
present embodiment is therefore to be considered in all respects as
illustrative and not restrictive, the scope of the invention being
indicated by the appended claims rather than by the foregoing
description, and all changes which come within the meaning and
range of equivalency of the claims are therefore intended to be
embraced therein.
* * * * *