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EXTRAVEHICULAR MOBILITY UNIT
(EMU)
Crew and Thermal Systems Division, NASA
Johnson Space Center
2101 NASA Road 1
Houston, Texas 77058
281-483-9230
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EXTRAVEHICULAR MOBILITY UNIT
INTRODUCTION
The Extravehicular Mobility Unit (EMU) provides a crewmember with the life support
equipment and mobile pressure enclosure necessary to perform Extravehicular Activity
(EVA) while in an earth orbit. The EMU consists of two major subsystems; the Life
Support Subsystem (LSS) and the Space Suit Assembly (SSA).
SPACE SUIT ASSEMBLY (SSA) provides:
Atmosphere containment
High mobility body joints
Thermal insulation
Cooling distribution Drinking water
Waste collection
Sunlight and solar radiation protection
Micrometeoroid/Orbital Debris (MMOD) protection
Interfaces for attachment of other EVA-related equipment
LIFE SUPPORT SUBSYSTEM (LSS) provides:
Primary oxygen supply
Suit pressurization and ventilation
Communications
Breathing gas purification
Temperature control
Power
An interface for servicing
Interfaces for attachment of other EVA-related equipment
Suit health display feedback
Independent emergency oxygen supply
Suit health check instrumentation and telemetry data
The Shuttle Extravehicular Mobility Unit (EMU) has dramatically demonstrated theability of humans to work effectively in space. EVA highlights include the refueling and
repair of satellites on orbit, retrieval of satellites for refurbishment on earth, and the
assembly of Space Station structures. The EMU has and will continue to play a vital role
in allowing Americas Space Shuttle to fulfill a wide spectrum of space tasks such as
inspection, maintenance, repair, construction and if necessary, rescue operations. In
addition, the present Shuttle EMU is used for International Space Station (ISS) EVA
activities assembly and operations.
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The EMU is designed to fit both men and women. The space suit/life support system,
which serves as a one-person spacecraft, provides protection and earth-like mobility for
astronauts working in space.
The EMU is designed to accommodate an EVA mission consisting of the followingcharacteristics:
a) Total duration of 7 hours maximum or 6 hours maximum under the worst-casesolar exposure.
b) An average metabolic rate of 1000 Btu/Hr for 7 hours.
c) Peak metabolic rates of 2000 Btu/Hr for 15 minutes and 1600 Btu/Hr for 1 hour atanytime within the EVA.
d) Minimum rate of 400 Btu/Hr for 30 minutes after an average work rate of 1000Btu/Hr and followed by a rate of 700 Btu/Hr for up to 30 minutes.
e) Prebreathe (a process which flushes Nitrogen from the blood, thereby reducing therisk of experiencing Decompression Sickness (DCS)) can be as short as 40 minutes
with a 10.2 psia cabin pressure or as long as 4 hours with a 14.7 psia cabin
pressure.
f) System will provide 2 hours DCS Treatment with a cabin pressure of 14.7 psia.
LIFE SUPPORT SUBSYSTEM (LSS)
The Life Support Subsystem (LSS) consists of subsystems, which are briefly described in
the following paragraphs:
1) Primary Life Support Subsystem (PLSS)
2) Secondary Oxygen Pack (SOP)
3) Display and Control Module (DCM)
4) Service and Cooling Umbilical (SCU)
5) EMU Electrical Harness (EEH)
6) Airlock Adapter Plate (AAP)
7) Contaminant Control Cartridge (CCC)
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8) Battery
9) Bends Treatment Adapter (BTA)
10)Secondary Oxygen Pack Checkout Fixture (SCOF)
11)Helmet Holding Fixture (HHF)
12) Power Harness
PRIMARY LIFE SUPPORT SUBSYSTEM (PLSS)
The PLSS is made up of four distinct circuits:
1) Oxygen Ventilation Circuit
2) Primary Oxygen Circuit3) Feedwater Circuit4) Liquid Transport Circuit
These circuits provide suitable breathing environment and
thermal control for the crewmember inside the Space Suit
enclosure. The Primary Oxygen Circuit supplies oxygen at
regulated pressure to the Oxygen Ventilation Circuit for
crewmember breathing, SSA pressurization, and Water
Tank water expulsion. The fan portion of the
Fan/Pump/Separator, located in the Oxygen Ventilation
Circuit, circulates the oxygen and gas exhaled by thecrewmember through connecting ducts and items. The
exhaled CO2 is removed from the breathing environment by
a CCC or a METOX cartridge. Cooling and humidity
removal occurs as the oxygen circulates through the
sublimator. Additionally, primary oxygen is also directed
through ducting to pressurize the water storage tanks
located in the Feedwater Circuit. The water storage tanks
supply expendable water at regulated pressure to the
sublimator. The feedwater circuit in the sublimator is open
to atmosphere (vacuum), and, as the expandable water is
fed into the sublimator, it freezes and then sublimates to
space. This sublimation removes heat from the Liquid
Transport Circuit. The pump circulates cooling water
through the Liquid Transport Circuit, which includes the
Liquid Cooling and Ventilation Garment of the SSA, worn
by the crewmember. The water removes heat from the
crewmember and is cooled by the sublimator.
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SECONDARY OXYGEN PACK (SOP)
The SOP attaches to the bottom of the PLSS and
provides 30 minutes of back-up pressure regulated
oxygen in the event that:
1) The primary oxygen supply is exhausted
2) Primary pressure regulation is lost, via a regulator failure of excessive oxygendemand
3) One of the Purge Valves are opened due to: a) The PLSS fails to removecontaminates in the ventilation circuit, heat, or humidity; b) Ventilation flow
drops below acceptable levels.
DISPLAY AND CONTROL MODULE (DCM)
The DCM provides EVA crewmembers electrical and
mechanical controls required for one person operation
of the EMU, and contains a Liquid Crystal Display
(LCD). The LCD, in conjunction with the Cautions
and Warning System (CWS) displays EMU operational
information in alphanumeric format to the EVA
crewmember.
SERVICE AND COOLING UMBILICAL (SCU)
The SCU connects the EMU to the orbiter service panel
and is used to 1) replenish PLSS consumables, 2) supply
cooling and expendables during umbilical operations,
and 3) allow wastewater drainage. The CCC is the only
consumable not recharged by the SCU.
EMU ELECTRICAL HARNESS (EEH)
The EMU Electrical Harness is located within the Hard Upper
Torso (HUT) and connects the Communication Carrier
Assembly (CCA) and the biomedical sensors to the EMU
Electrical System.
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AIRLOCK ADAPTER PLATE (AAP)
The AAP is a mounting structure used to attach the EMU to the
orbiter airlock wall. The EMU is secured to the AAP by four
mounting pins and the AAP is retained to the orbiter airlock wall
by three supports.
CONTAMINATION CONTROL CARTRIDGE (CCC)
The CCC is a crewmember replaceable module used in the
PLSS to remove CO2, odors, particulate and other
contaminants from the Oxygen Ventilation Circuit.
BATTERY
The battery supplies all power to the EMU excluding EMU
lights when it is not operating on vehicle power via the SCU.
BENDS TREATMENT ADAPTER (BTA)
The BTA is an emergency device, which is used on orbit in the
event of an EVA crewmember contracting decompression sickness.
It permits EMU usage as a hyperbaric (8 psi above airlock
pressure) bends treatment chamber.
SECONDARY CHECKOUT FIXTURE (SCOF)
The SCOF is a device used in place of the Helmet to seal
off the Oxygen Ventilation Circuit and provide over
pressurization protection during pre-EVA activity (SOP
checkout, fan checkout and water discharge/recharge).
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HELMET HOLDING FIXTURE (HHF)
The HHF provides for the storage of a Helmet/EVVA. The HHF
mounts to the airlock floor during launch and landing.
POWER HARNESS
The Power Harness is designed to reduce the profile of
the glove by moving the power source for the heating
elements from its original location on the back of the
EMU glove to the PLSS. Each glove contains one heater
element per fingertip powered by the Rechargeable EMU
battery Assembly (REBA) located on the right side of
the PLSS. The battery, which will provide up to eighthours of operation, is connected to the heater elements
via 8 to 10 feet of copper cabling that runs under the
TMG from the battery, down through the arms of the
EMU. The Power Harness provides an electrical
connection between the Electronic Cuff Checklist, TV
Camera, and the REBA.
SPACE SUIT ASSEMBLY (SSA)
The Space Suit Assembly (SSA), consists of nine subassemblies which are describedbelow:
1) Communications Carrier Assembly (CCA)
2) Hard Upper Torso (HUT)
3) Arm Assembly
4) Lower Torso Assembly (LTA)
5) Helmet
6) Gloves
7) Liquid Cooling and Ventilation Garment (LCVG)
8) Extravehicular Visor Assembly (EVVA)
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9) Disposable In-Suit Drink Bag (DIDB)
The SSA interfaces with the Primary Life Support Subsystem (PLSS) and the Display and
Controls Module (DCM) at the HUT. The PLSS provides mechanical, electrical, and
fluid interfaces where it joins the HUT.
The SSA components are designed to closely approximate the natural anthropometric
joint movements. This is accomplished with low-torque mobility joints at the hip, knee,
ankle, and hand and with low-torque mobility bearings at the shoulder, waist, elbow and
wrist.
COMMUNICATIONS CARRIER ASSEMBLY (CCA)
The CCA is a cloth aviator-type cap worn under the pressure suit
helmet. It fits over the crewmembers head and snaps into place
with a chin or neck strap. It contains microphones and
headphones for communicating with crewmembers and receivingcaution and warning tones.
HARD UPPER TORSO (HUT)
The HUT is the portion of the pressure suit that
encloses the upper torso of the body. It provides
the structural mounting interface for most of the
EMU; Helmet, Arms, Lower Torso Assembly,
Primary Life Support Subsystem, Display and
Control Module, Power Harness, and the Electrical
Harness. It is made of a fiberglass shell. Integral
to the HUT are passageways for fill and drain
water, vent air, and cooling water. Tubing for vent
air and cooling water is attached to these
passageways, leading to the Multiple Water
Connector. The Multiple Water Connector
interfaces to the Liquid Cooling Vent Garment
(LCVG) with its cooling water and vent systems.
The Thermal Micrometeoroid Garment (TMG)
provides protection for the HUT.
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ARM ASSEMBLY
The left and right Arm Assemblies are
flexible, anthropomorphic pressure
vessels made of heat sealed, urethane-
coated, nylon bladder fabric enclosed inpolyester restraint fabric. The assembly
contains the shoulder joints, upper arm
bearings, elbow joints, and wrist bearings
that permit joint mobility. Thermal
protection for the arm assemblies is
provided by TMG.
The lower arm assembly uses adjustable
arm brackets as well as a metal Arm
Sizing Ring for sizing. These items were
designed to allow crewmembers toperform sizing tasks on-orbit. There are
four adjustable arm brackets (cams), two
at each end of the arm segment. Each
cam can adjust .025 for a total of .5.
The Arm Sizing Ring adds an additional
0.5 of length to the lower arm.
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LOWER TORSO ASSEMBLY (LTA)
The LTA encompasses the lower torso, legs, and feet of the
crewmember. It is composed of an Adjustable Waist
Assembly, Trouser Assembly, Leg Assembly and BootAssembly. The adjustable waist allows the crewmember to
make two, one-inch adjustments to the length of the waist on
orbit, when other crewmembers need to wear the same suit.
These fabric elements are joined through attachment to
hardware, and in all cases the attachment is by flange
mounting. Boots are joined to the Trousers by the Boot
Disconnects; Trousers are joined to the Waist Assembly
through the Waist Bearing, and the Waist Assembly is
attached to the Body Seal Closure (BSC). Interface of the
LTA to the HUT is accomplished via the BSC. Thermal
protection for the LTA is provided by TMGs. The TMGelements for the LTA are the Boot, Leg, Brief, and Waist
TMG Assemblies. The TMG components are sized to fit the
corresponding Restraint Assemblies.
The LTA can be sized with adjustable le brackets and sizing rings. The leg assemblies
contain brackets that can be adjusted in .5 increments for a total of 1.0. Crewmembers
with long legs can be accommodated by adding a 0.5 Thigh Sizing Ring. The distance
between the knee and the foot can also be adjusted with Leg Sizing Rings in 0.5
increments from 0.5 to 1.5 rings.
HELMET
The Helmet is the portion of the pressure suit providing a
pressure vessel for the head. It is made of clear
polycarbonate bubble with a neck disconnect and
ventilation pad. The Helmet contains the following
subassemblies: Bubble, Neck Ring, Combination Purge
Valve (CPV), and Vent Pad. The Bubble, Neck Ring and
Vent Pad are permanently secured while the CPV, attached
to the left side of the Bubble with three screws, is
removable. The Neck Ring provides for quick disconnect
of the Helmet from the HUT. The Vent Pad, mounted inthe back of the helmet, directs vent flow oxygen from the
HUT to the front areas of the Helmet Bubble. The CPV
provides redundancy for O2 circulation in the event that
your O2 vent flow fan fails. The Helmet provides for semi-
permanent attachment of a supplemental Extravehicular
Visor Assembly (EVVA) for all extravehicular operations.
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GLOVES
The Gloves are the active interface between the
crewmember and the work being performed. As
such, they must perform a variety of functionswhile preserving an effective degree of tactility.
The glove must also provide a protective barrier
against the natural environment, as well as work
place hazards. The gloves have electrical heaters
in the tips of the fingers that can be turned on by
the crewmember, when desired. The EV glove is
comprised of the following basic components:
Restraint, Bladder, and TMG.
LIQUID COOLING AND VENTILATION GARMENT (LCVG)
The LCVG is a conformal garment worn under the pressure suit to
maintain body temperature. It has ethylene vinyl acetate tubing woven
through the spandex restraint cloth. Cooling water LCVG also
contains the ducts for returning vent air to the HUT for transfer to the
PLSS, and retains the dosimeter, signal conditioner, biomedical leads,
and an electrical grounding lead for the crewmember. The multiple
water connector interfaces to the HUT with its cooling water and vent
systems.
EXTRAVEHICULAR VISOR ASSEMBLY (EVVA)
The EVVA fits over and attaches to the Helmet to
provide the crewmember with visual, thermal,
impact, and micrometeoroid protection in space. It
has a polycarbonate shell, stationary polycarbonate
Protective Visor, movable polysulfone Sun Visor,
and movable fiberglass/epoxy Center and Side
Eyeshades. The Sun Visor and the Center Eyeshade
are manually adjustable by rotating the supporting
hubs. Grasping a tab with the hand moves each Side
Eyeshade. A Thermal Micrometeoroid Garment
covering is attached to the outside of the shell.
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IN-SUIT DRINK BAG (DIDB)
The IDB is a re-useable heat-sealed, flexible
container made of polyester based polyurethane film
and comes in two sizes. It can hold up to either 21
oz. Or 32 oz. of drinking water for use during EVA.It is mounted to the inner front wall of the HUT with
Velcro and has a tube extending to the neck area.
There is a Drink Valve, which can be adjusted to a
position within reach of the lower right corner of the
mouth. Sucking on the mouthpiece opens the valve
and permits the crewmember to drink water from the
IDB.
DISPOSABLE IN-SUIT DRINK BAG (DIDB)
The DIDB is an expendable heat-sealed flexible
container made of polyethylene film. It holds 32 oz. of
drinking water for use during EVA and is mounted to the
inner front wall of the HUT with Velcro. There is a tube
extending from the drink valve to the neck area that can
be placed in either the lower right or lower left corner of
the mouth. Netting in the bag creates a wicking action in
0-G so water propagates to the drink valve. Sucking on
the mouthpiece opens the diaphragm valve and permits
the crewmember to drink water from the DIDB.
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SUPPORT AND ANCILLARY EQUIPMENT
EMU Support and ancillary equipment includes:
-EMU light An incandescent lamp and batteryassembly that mounts on the EVVA to provide
the EVA crewmember with light as needed.
- EMU TV A small EVVA mounted
modularized television transmission assembly,
including camera that provides the EVA
crewmember with mobile camera capability.
- Electronic Cuff Checklist a computer-based device attached to the glove garmentthat provides menu driven instructions and information to the crewmember.
- Tethers Strap like devices used to tether tools and other items to the EMU and theEMU to anchor points on the Orbiter and the International Space Station (ISS).
35 Foot Tether Waist Tether Wrist Tether
- Airlock stowage bag A bag used to store items during suit donning or doffing.
- EMU prep kit A kit containing items used in preparing the EMU for EVA or for
storage after an EVA.
- Antifog wipes
- Package of tissue-type wipes
- Scissors with a lanyard
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- EMU maintenance kit A kit containing items used in normal and contingency
maintenance of the EMU as well as spares for some items in the prep kit.
- Valsalva devices
- Stericide wipes
- Lubricant wipes- Antifog wipes
- SOP removal tool
- Thermal cover lacing cord and needle
- LTA Donning handles Devices used during suitdonning to aid the crewmember in mating the lower torso
to the upper torso.
- Wrist mirror A mirror attached to the wrist of the EMUfor viewing EMU controls out of crewmembers normal
field of view.
- Cuff checklist A short form checklist of EVAprocedures and EMU malfunction procedures attached
to the wrist of the EMU for use during EVA.
- EMU scissors A pair of scissors located in an EMUpocket. They are tethered to the EMU for use as
needed to cut tethers, thermal blankets and other
items.
- Adjustable Thermal mittens Mittens
that fit over the gloves of the EMU to
provide additional thermal protection.
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- Mini-work station (MWS) A device
that attached to the HUT and is used in
the transport and management of tools.
- Maximum Absorbency Garment (MAG)
- A disposable device used for collecting
crewmember urine.
- Thermal Comfort Undergarment (TCU) -A crewmember garment worn under the LCVG
used to enhance physical comfort and to allow
LCVG to remain clean for a longer period of
time.
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NASA EVA PATCH
The theme of the patch is Extending the Dimensions of Man. It is derived from the
Leonardo da Vinci sketch entitled The Dimensions of Man and is meant to be an
expansion of the dimensional, medical, and scientific aspects of the original work. It is
fitting that the theme of the patch is associated with the original da Vinci work since the
evolution of the Space Shuttle EMU from its Gemini, Apollo, and Skylab originsrepresents the closest achievement of the ultimate EMU design goal. That of providing
EVA mobility limited not by hardware but by mans natural range.
The three stars represent the three historic milestones in U.S. extravehicular activity
Americas first EVA by Ed White during Gemini IV, mans first steps on the lunar
surface by Neil Armstrong and the EVAs performed by Pete Conrad and Joe Kerwin to
repair and eventually save the Skylab Space Station. The NASA EVA patch is located on
the right shoulder of the space suit and represents the EVA community.
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EMU CONTRACTORS
The EMU design, development and manufacturing program is being accomplished by
many companies located across the United States with all of them working closely with
the NASA. Four of the major contractors are:
Prime contractor for the EMU:
Hamilton Sundstrand
One Hamilton Road
Windsor Locks, Connecticut 06096
Phone: (860) 654-2854
Contact: Bob Poisson
Subcontractor for the Space Suit:
ILC Dover, Inc.
One Moonwalker RoadFrederica, Delaware
Phone: 302-335-3911
Contact: Phil Spampinato
Subcontractor for the Space Suit Hardware:
Air-Lock Inc.
Wampus Lane
Milford, Connecticut 06460
Phone: (203) 878-4691
Contact: Jim Edwards
Subcontractor for the Space Suit Visor Coatings:
Deposition Research Laboratory, Inc.
530 Little Hills Blvd.
St. Charles, Missouri 63301
Phone: (314) 940-0768
Contact: Steve Chelli
The following four pages contain additional information on these companies.
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SPECIFICATIONS
Mission Duration: 7 hours EVA
Operating Environment: 0 psia (pounds per square iabsolute) to 14.7 psia
Suit OperatingPressure: 4.3 psid (pounds per squareinch differential)
Emergency Life Support: 30 minutes
Useful Life: Up to 30 years with appropriate
maintenance
Modular Components: 18 different items -7 Life Support System 11 Space SuitAssembly
Sizing: Modular assembly fits5th to 95th percentile maleand female astronauts
Construction: Space Suit Assembly Urethane-coated, nylon pressurebladder Orthofabric and aluminized mylarthermal/meteoroid garment Fiberglass hard upper torso Ball-bearing joints
Polycarbonate helmet and visors On-orbit resizingLife Support System Interchangeable subsystem modulefor ease of maintenance and servicin Expendables replaceable orrechargeable on orbit
Weight: Approximately 275 pounds
Donning: 15 minutes
Workaids: Compatible with
- Work stations- Manual and power tools- Helmet-mounted videocamera and lights- Tethers- Foot restraints- Simplified Aid for EVARescue (SAFER)- Electronic Cuff Checklist(ECC)
Hamilton Sundstrand provides theExtravehicular Mobility Unit for NASA. Thisintegrated space suit/ life support systempermits astronauts to work comfortably andsafely in space.
The EMU is modularized to fit both men andwomen. The space suit/life support system,which serves as a one-person spacecraft,provides protection and earth-like mobility forastronauts working in space.
Space Suit Assembly (SSA) provides: Atmosphere containment High-mobility and Iow-torque body joints Thermal insulation Cooling distribution Drinking water Waste collection Sunlight and solar radiation protection Micrometeoroid and debris protection
Life Support System (LSS) provides:
Oxygen supply Suit pressurization and ventilation Communications Breathing gas purification Temperature control Independent emergency life support
For safety, the EMU is constantly monitored bya Caution and Warning System, which
monitors 17 sensors, contaminant levels andremaining expendables such as oxygen, waterand power.
EXTRAVEHICULAR MOBILITY UNIT
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Apollo Used for IVA During Trans Lunar Flight Used for All Lunar EVA & Transfer Vehicles Custom Fit, Pure O2, Water Cooled, 3.8 psi 160 hrs on Lunar Surface Operational Environment: -250F to +250F,
Dust
Shuttle Designed for Standard Sizing, 4.3 psi Continuing Glove Improvements Operational Environment: Payload Bay - Deep
Space
Cross Section of Ex erience
NASA Space Suit Design Highlights
Space Station Redesigned for Higher Mobility, On Orbit
Changeout
Heated Glove with Better Tactile Capabilities Greatly Increased Cycle Life
Mark III TechnologyDemonstrator
Benchmark Suit for Mobility High Pressure 8.3 psi Hardsuit (No Prebreathing
Lunar/Mars Suit Prototype Designed for Lightweight, High Mobility Operational Environment: Fractional Gravity,
Dust
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AIR-LOCK, INC.EXTRA VEHICULAR ACTIVITY SUPPORT
DESIGN & MANUFACTURING EXPERTISE
-GEMINI
Air-Lock's design and manufacturing expertise was
directed towards supplying Gemini Suit Hardware, whichincluded Glove and Helmet Disconnects, Wrist Bearings as
well as Oxygen and Biomedical Connectors.
- APOLLO/SKYLAB
Air-Lock designed and manufactured all of the suit
hardware for the Apollo program. Additionally, when the need
became apparent in the beginning of the Apollo Program for
an advanced helmet. Air-Lock using'lR&D funds, over a 12
month period, designed and fabricated the equipment required
to manufacture polycarbonate helmets. This R&D effort
produced functional helmets which were flown on all of the
Apollo and Skylab missions. They are still manufacturing
these helmets today in support of the Shuttle Program.
- SHUTTLE
All of the Wrist, Arm, Scye and Waist Bearings,
Wrist Disconnects, Helmet Assemblies, Suit Side Neck Ring
Assemblies. Waist Disconnect (Body Seal Closure), EWA
(Extra Vehicular Visor Assembly) and many of the valve, gas
and electrical connectors currently used on the Space Shuttle
were designed and manufactured by Air-Lock.
ADVANCED EVA R&D HARDWARE
JOINT NASA/AIR-LOCK EFFORTS
Experimental space suit proto-types were designedand manufactured by Air-Lock for both the Johnson Space
Center and the Ames Research Center. In 1977, Air-Lock
designed and manufactured a Bi-planar suit closure for the
Ames Research Center. Over that past twenty years, All of the
Hard Upper Torso (HUTs) suits made for NASA, including
the Space Shuttle Suit, the ILC ZPS, ZPS Mark III, and the
Ames AX5, have closure systems designed and manufactured
by Air-Lock. In 1987 the high costs associated with machining
a HUT from a solid aluminum billet and the long lead times
associated with the hand lay up of fiberglass epoxy HUT
assemblies, prompted Air-Lock into using IR&D funds to
independently developed a Iow cost HUT by utilizing
investment casting technology. This
process was used to produce the Cast Aluminum MK I
HUT and Hatch which was delivered to Lockheed in 198
This technology gained the interest of NASA and in tur
they directed Hamilton Standard to purchase a Shutt
compatible unit from Air-Lock. A second cast aluminuHUT was furnished to Hamilton Standard in 1990. Th
HUT, a proto-type for the Shuttle EMU, is still successfull
being used in the WETF at NASA/JSC.
In 1990, in an unsolicited proposal, Air-Locattempted to convince NASA to consider an advanceIow cost solution to the 'pivoted shoulder" problemThey submitted a pivotless planar HUT model with nearm hole geometry to NASA and Hamilton StandardAs a direct result of this submission, the Shuttprogram is now replacing all Shuttle pivoted flight HUTwith planar HUTs.
NASA became interested in a developmeeffort for overall weight reduction of future HUstructures. In 1990, Air-Lock independently establisheon-site capabilities to support the fabrication of carbofiber/graphite composite hardware. In 1991 NASselected Air-Lock as the sole source for the design anfabrication of a carbon composite rear entry HUTUnder a January 1992 CPFF contract to NASA, AiLock designed, manufactured, tested and delivered thall composite Bi-planar rear entry HUT/Hatcassembly. This HUT is currently in use in JSCAdvanced Suit Laboratory.
From the beginning of the Shuttle program, AiLock's ideas have consistently contributed to thimprovement of the hardware used on the Shuttle SuAssembly. These design improvements include thLow Torque Lip Seals, the cast aluminum Shuttle HUTthe Acme Threaded Sizing Elements, (used in the Arand LTA of the SSA), and the current In-suit Drink BaValve Assembly.
In 1994 Air-Lock began a joint IR&D programwith Deposition Research Laboratory, Inc., to developenvironmentally robust Sun Visor coating which alshad exceptional optical/thermal properties. This coatindesign was subsequently delivered to NASA and hasince flown on STS-76, 79, 86, 88, and 90. This coatindesign has been certified for flight and replaced thprevious Sun Visor design in April 1999.
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