Orbiter Environmental Control and Life Support System.

Orbiter Environmental Orbiter Environmental Control and Life Control and Life Support SystemSupport System

Orbiter ECLSSOrbiter ECLSS

Basic Life Support Needs

•Pressurized gas environment•Oxygen supply•CO2 removal

•Comfortable temperature range

•Comfortable humidity range

•Pure water supply

•Adequate nutrition

•Waste removal

Basic Life SupportBasic Life Support

Human MetabolismHuman Metabolism

RequirementsRequirements kgkg WasteWaste kgkg

OxygenOxygen 0.840.84 Carbon dioxideCarbon dioxide 1.001.00

Food solidsFood solids 0.620.62 Respiration & perspiration waterRespiration & perspiration water 2.282.28

Water in foodWater in food 1.151.15 Urine waterUrine water 1.501.50

Food preparation waterFood preparation water 0.760.76 Feces waterFeces water 0.090.09

Drinking waterDrinking water 1.621.62 Sweat solidsSweat solids 0.020.02

Urine solidsUrine solids 0.060.06

Feces solidsFeces solids 0.030.03

(water subtotal)(water subtotal) 3.533.53 (water subtotal)(water subtotal) 3.873.87

Total massTotal mass 4.994.99 4.984.98

Orbiter ECLSS – Basic Life Support FunctionsOrbiter ECLSS – Basic Life Support Functions

Orbiter’s life support functions can support a crew of 7 for a Orbiter’s life support functions can support a crew of 7 for a typical mission of 10-14 daystypical mission of 10-14 days– In emergencies as many as 10 crewmembersIn emergencies as many as 10 crewmembers

The Orbiter can also support missions up to three weeks by The Orbiter can also support missions up to three weeks by carrying additional Ocarrying additional O22, N, N22 consumables, and expanded CO consumables, and expanded CO22 removalremoval– This addition is called the Extended Duration Orbiter (EDO) This addition is called the Extended Duration Orbiter (EDO)

packagepackage

Crew cabin environment is maintained within specific Crew cabin environment is maintained within specific temperature and humidity limitstemperature and humidity limits– Additional limits are placed on carbon dioxide and toxic gas Additional limits are placed on carbon dioxide and toxic gas

levelslevels

The active thermal control for the crew cabin is a combined The active thermal control for the crew cabin is a combined internal/external systeminternal/external system– Heat removal is also provided for the Orbiter's onboard Heat removal is also provided for the Orbiter's onboard

electrical and avionics systemselectrical and avionics systems

Orbiter ECLSS SubsystemsOrbiter ECLSS Subsystems

1. Cabin Atmosphere1. Cabin Atmosphere– Air Revitalization System (ARS) Air Revitalization System (ARS) – Atmosphere Revitalization Pressure Control System (ARPCS) Atmosphere Revitalization Pressure Control System (ARPCS) – Airlock Support SystemAirlock Support System

2. Active Thermal Control2. Active Thermal Control– Active Thermal Control System (ATCS) Active Thermal Control System (ATCS) – Water Coolant Loop System (WCLS)Water Coolant Loop System (WCLS)

3. Food3. Food– Food Supply and Management System Food Supply and Management System

4. Water supply and Wastewater system4. Water supply and Wastewater system– Water supply and purification Water supply and purification – Waste water storage and disposal Waste water storage and disposal

5. Waste Management 5. Waste Management – Waste Collection System (WCS) Waste Collection System (WCS)

6. Smoke Detection and Fire Suppression6. Smoke Detection and Fire Suppression

7. Space Suits and EVA7. Space Suits and EVA

8. Airlock8. Airlock

Orbiter ECLSS SchematicOrbiter ECLSS Schematic

Orbiter ECLSS LayoutOrbiter ECLSS Layout

1. Cabin Atmosphere1. Cabin Atmosphere

Orbiter ECLSS - Crew ModuleOrbiter ECLSS - Crew Module

Crew module has a total pressurized volume of 65.9 Crew module has a total pressurized volume of 65.9 mm33 (2,325 ft (2,325 ft33))

Additional pressurized areas in the cabin area are Additional pressurized areas in the cabin area are storage lockers, pressurized equipment areas, and storage lockers, pressurized equipment areas, and the airlockthe airlock

The airlock provides an additional 4.3 mThe airlock provides an additional 4.3 m33 (150 ft (150 ft33) of ) of pressurized volumepressurized volume

Cabin pressurization is controlled by the Cabin pressurization is controlled by the Atmosphere revitalization Pressure Control SystemAtmosphere revitalization Pressure Control System– Maintained at one atmosphere (14.7 psi), except Maintained at one atmosphere (14.7 psi), except

for EVA operationsfor EVA operations

Orbiter ECLSS - Crew ModuleOrbiter ECLSS - Crew Module

Crew module environmentCrew module environment

Relative humidityRelative humidity 30 - 75%30 - 75%

TemperatureTemperature 65 - 8065 - 80ooFF

Oxygen partial pressure (PPO2)Oxygen partial pressure (PPO2) 2.29 - 3.45 psi2.29 - 3.45 psi

Crew cabin air flowCrew cabin air flow 330 ft330 ft33/min/min

7 min complete air exchange period7 min complete air exchange period

Orbiter ECLSS - Historical Habitation Volumes (NASA)Orbiter ECLSS - Historical Habitation Volumes (NASA)

Mission Duration (days)

0.1

1

10

100

1000

1 10 100 1000

Mercury

Voskhod

Apollo

LEM

VostokGemini

STSApollo

CM Soyuz

Skylab ISS

Salyut 7

Mir

Total Pressurized

Volume (m3/crew)

Orbiter ECLSS - Orbiter AtmosphereOrbiter ECLSS - Orbiter Atmosphere

Air Revitalization System (ARS)Air Revitalization System (ARS)

Resupplies OResupplies O22 and N and N22, and removes CO, and removes CO22, ,

water, and contaminantswater, and contaminants


Air Revitalization System (ARS)Air Revitalization System (ARS)

The Orbiter's air revitalization system supplies and The Orbiter's air revitalization system supplies and recirculates the Orecirculates the O22 + N + N22 atmosphere components atmosphere components

Controls water vapor (relative humidity) and heat Controls water vapor (relative humidity) and heat within the cabin, airlock and space suitswithin the cabin, airlock and space suits

ARS also monitors and removes COARS also monitors and removes CO22 and other toxic and other toxic gasesgases

Filters airborne particlesFilters airborne particles

Orbiter ECLSS - Cabin Air SystemOrbiter ECLSS - Cabin Air System


Cabin Air RevitalizationCabin Air Revitalization

Five cabin air revitalization loops are used Five cabin air revitalization loops are used for cooling, ventilating, and supplying air to for cooling, ventilating, and supplying air to the Orbiter's cabinthe Orbiter's cabin

Individual loops pass directly or indirectly Individual loops pass directly or indirectly through the cabin air systemthrough the cabin air system

Air revitalization loopsAir revitalization loops– Crew cabin (1) Crew cabin (1) – Avionics bays (3) Avionics bays (3) – Inertial Measurement Units (1) Inertial Measurement Units (1)


Crew cabin air loopCrew cabin air loop

The single crew cabin air loop is designed to circulate air through The single crew cabin air loop is designed to circulate air through the air revitalization components in the cabin air system. the air revitalization components in the cabin air system. Responsible for removing:Responsible for removing:

Heat Heat – Removed by cabin air loop heat exchangerRemoved by cabin air loop heat exchanger

MoistureMoisture– Slurper bar in heat exchanger collects moisture which is pulled Slurper bar in heat exchanger collects moisture which is pulled

into dual centrifugal water separatorsinto dual centrifugal water separators– Removes approximately 4 lb/hr of HRemoves approximately 4 lb/hr of H22O for typical crewO for typical crew– Routed to the wastewater tank Routed to the wastewater tank

Odors and trace contaminants Odors and trace contaminants – Removed by activated charcoal filter located in the cabin air Removed by activated charcoal filter located in the cabin air

systemsystem

Orbiter ECLSS - IMU Air FanOrbiter ECLSS - IMU Air Fan


Crew cabin air loop used to remove:Crew cabin air loop used to remove:

COCO22 – Cabin air circulated through two lithium hydroxide Cabin air circulated through two lithium hydroxide

(LiOH) canisters in the cabin air system (LiOH) canisters in the cabin air system – Lithium hydroxide is used because is the lightest Lithium hydroxide is used because is the lightest

hydroxide available, and is the least solublehydroxide available, and is the least soluble– Approximately 120 lb/hr flows to each of two Approximately 120 lb/hr flows to each of two

lithium hydroxide canisterslithium hydroxide canisters– Each canister is rated at 48 man-hoursEach canister is rated at 48 man-hours– Up to 30 spare canisters are stored under the mid Up to 30 spare canisters are stored under the mid

deck floordeck floor


Crew cabin air loop used to remove:Crew cabin air loop used to remove:

COCO– Ambient Temperature Catalytic Oxidizer (ATCO) Ambient Temperature Catalytic Oxidizer (ATCO)

unit located downstream from the cabin heat unit located downstream from the cabin heat exchanger transforms CO to COexchanger transforms CO to CO22 by catalytic by catalytic oxidation on a platinum-carbon surfaceoxidation on a platinum-carbon surface

– Process combines CO with OProcess combines CO with O22 which forms CO which forms CO22 which is then removed by the LiOH canisterswhich is then removed by the LiOH canisters

Particles and debrisParticles and debris– Removed by 300 micron filter in the fan Removed by 300 micron filter in the fan

circulation unitscirculation units


COCO22 removal removal

Lithium hydroxide (LiOH) – canister formLithium hydroxide (LiOH) – canister form

COCO22 removal in the Orbiter's crew cabin employs removal in the Orbiter's crew cabin employs traditional lithium hydroxide canisterstraditional lithium hydroxide canisters

Used in all manned vehicles with the exception Used in all manned vehicles with the exception of the space stations (Skylab, Salyut, Mir, ISS)of the space stations (Skylab, Salyut, Mir, ISS)

Orbiter cabin air is circulated through two LiOH Orbiter cabin air is circulated through two LiOH canisterscanisters

Orbiter ECLSS - Cabin Fan and LiOH HousingOrbiter ECLSS - Cabin Fan and LiOH Housing


COCO22 removal - Lithium hydroxide removal - Lithium hydroxide

Changed out regularly since COChanged out regularly since CO22 cannot be cannot be removed from the canistersremoved from the canisters– The lithium carbonate and water products are The lithium carbonate and water products are

stable, but incapable of further COstable, but incapable of further CO22 absorptionabsorption

Sufficient LiOH must be carried for the entire Sufficient LiOH must be carried for the entire mission, plus additional canisters for possible mission, plus additional canisters for possible mission extension and emergency reservemission extension and emergency reserve


LiOH canisters are an LiOH canisters are an inexpensive solution to inexpensive solution to COCO22 removal but create removal but create

a weight penalty since a weight penalty since they retain their original they retain their original mass and the absorbed mass and the absorbed mass of COmass of CO22 and some and some

of the respiration waterof the respiration water

Canisters are returned Canisters are returned to Earth for to Earth for disposal/refurbishmentdisposal/refurbishment

Orbiter ECLSS - LiOH ReplacementOrbiter ECLSS - LiOH Replacement


COCO22 removal removal

Regenerable Carbon Dioxide Removal System Regenerable Carbon Dioxide Removal System (RCRS)(RCRS)

RCRS is used for missions longer than 16 days on RCRS is used for missions longer than 16 days on orbit, or for 12 to 16 day duration missions for a orbit, or for 12 to 16 day duration missions for a crew of up to seven astronautscrew of up to seven astronauts

Carbon dioxide removal is accomplished by Carbon dioxide removal is accomplished by passing cabin air through a regenerable COpassing cabin air through a regenerable CO22 removal system instead of the lithium hydroxide removal system instead of the lithium hydroxide canisterscanisters


COCO22 removal - removal - RCRSRCRS

The regenerable system saves weight since the COThe regenerable system saves weight since the CO22 and water are dumped overboard instead of and water are dumped overboard instead of absorbed in the LiOH canisters and stored for return absorbed in the LiOH canisters and stored for return to Earthto Earth

COCO22 removal in the RCRS takes place in one of two removal in the RCRS takes place in one of two identical solid amine resin bedsidentical solid amine resin beds– Commonly called swing beds because of their alternating Commonly called swing beds because of their alternating

use as an absorber then the desorbtion cycleuse as an absorber then the desorbtion cycle– Resin combines with COResin combines with CO22 and water vapor in the air to form and water vapor in the air to form

a hydrated aminea hydrated amine– Water is required for the process since dry amine cannot Water is required for the process since dry amine cannot

react with the carbon dioxide directlyreact with the carbon dioxide directly

RCRSRCRS


CO2 removal - RCRS

While one bed adsorbs carbon dioxide, the other bed desorbs/regenerates using a bed heater while being exposed to space vacuum– Process removes both the CO2 and the water

from the amine granules– Need for a vacuum vent prevents the use of the

RCRS during ascent or entry– LiOH canisters are therefore included on the

RCRS flights

RCRS Unit – Hamilton SunstrandRCRS Unit – Hamilton Sunstrand


COCO22 removal - RCRS removal - RCRS

The adsorption-regeneration process in the RCRS The adsorption-regeneration process in the RCRS runs continuously with the beds automatically runs continuously with the beds automatically swapped every 13 minutesswapped every 13 minutes– Full cycle is made up of two 13 minute cyclesFull cycle is made up of two 13 minute cycles

An RCRS configured vehicle uses a single LiOH An RCRS configured vehicle uses a single LiOH canister for launch and another for entrycanister for launch and another for entry– An activated charcoal canister in the other COAn activated charcoal canister in the other CO22

absorber slot removes odorsabsorber slot removes odors– Changed-out mid mission on 10+ day flightsChanged-out mid mission on 10+ day flights


Atmosphere Revitalization Pressure Atmosphere Revitalization Pressure Control System (ARPCS)Control System (ARPCS)

Controls cabin pressureControls cabin pressure


Cabin pressurizationCabin pressurization

The Orbiter cabin pressure is maintained at 14.7 The Orbiter cabin pressure is maintained at 14.7 ±0.2 psia (or 10.5 psia for EVA) with two ±0.2 psia (or 10.5 psia for EVA) with two independent pressurization systems designated independent pressurization systems designated PCS 1 and PCS 2PCS 1 and PCS 2– Total cabin pressure is regulated separately with Total cabin pressure is regulated separately with

the oxygen and nitrogen supplies, with oxygen the oxygen and nitrogen supplies, with oxygen the primary componentthe primary component

– Nitrogen is regulated to make up the difference Nitrogen is regulated to make up the difference between the 2.95 psi oxygen pressure and the between the 2.95 psi oxygen pressure and the 14.7 psi total pressure14.7 psi total pressure

– The actual oxygen pressure range limit The actual oxygen pressure range limit maintained by the ARPCS is 2.95-3.45 psia maintained by the ARPCS is 2.95-3.45 psia



Crew respiration OCrew respiration O22 consumption is approximately consumption is approximately 0.8 kg (1.76 lb) per day0.8 kg (1.76 lb) per day– Total consumption for crew respiration and cabin loss is Total consumption for crew respiration and cabin loss is

typically 4.1 kg (9 lb) per daytypically 4.1 kg (9 lb) per day

Oxygen is fed to the cabin from the cryogenic Oxygen is fed to the cabin from the cryogenic storage tanks that also serve as reactant storage for storage tanks that also serve as reactant storage for the fuel cellsthe fuel cells– Oxygen is supplied from the cryogenic tanks through a Oxygen is supplied from the cryogenic tanks through a

restrictor and heated with a small heat exchanger on the restrictor and heated with a small heat exchanger on the Freon coolant loop before entering the crew cabinFreon coolant loop before entering the crew cabin

– Maximum flow rate for cabin oxygen is 11.4 kg (25 lb) per Maximum flow rate for cabin oxygen is 11.4 kg (25 lb) per hour is available in case of rapid cabin depressurizationhour is available in case of rapid cabin depressurization

– Nominal ECLSS budget for the crew oxygen is 0.91 kg (2.08 Nominal ECLSS budget for the crew oxygen is 0.91 kg (2.08 lb) per man-daylb) per man-day



Nitrogen is supplied from pressurized gas Nitrogen is supplied from pressurized gas storage tanks located in the payload baystorage tanks located in the payload bay– Consumption rate of approximately 3.5 kg Consumption rate of approximately 3.5 kg

(7.7 lb) per day from cabin loss and (7.7 lb) per day from cabin loss and ventingventing

– Regulation of the nitrogen gas by the Regulation of the nitrogen gas by the ARPCS provides the remainder of the total ARPCS provides the remainder of the total cabin pressure of 14.7 psiacabin pressure of 14.7 psia

– Nitrogen gas is also used to pressurize the Nitrogen gas is also used to pressurize the water storage tanks for positive feed in water storage tanks for positive feed in microgravitymicrogravity



During on-orbit operations the crew cabin is During on-orbit operations the crew cabin is supplied with a single PCS system for Nsupplied with a single PCS system for N22 and O and O22

– Second PCS system configured for backupSecond PCS system configured for backup– Both PCS systems are used during launch and Both PCS systems are used during launch and

reentryreentry– Auxiliary tank of pressurized oxygen is also Auxiliary tank of pressurized oxygen is also

available for contingency crew cabin supplyavailable for contingency crew cabin supply


A cabin vent valve is included in the pressurization A cabin vent valve is included in the pressurization system to equalize the cabin pressure with ambient system to equalize the cabin pressure with ambient pressurepressure– While on the launch padWhile on the launch pad– In extreme emergenciesIn extreme emergencies– On orbit or during reentry for contingencies such On orbit or during reentry for contingencies such

as a cabin fire or to vent the cabin atmosphere to as a cabin fire or to vent the cabin atmosphere to space through the payload bayspace through the payload bay


Cabin pressure limitationsCabin pressure limitations

Atmosphere monitored by caution and warning Atmosphere monitored by caution and warning system for:system for:– Cabin pressure below 14.0 psia or above 15.4 Cabin pressure below 14.0 psia or above 15.4

psiapsia– Partial pressure of oxygen (PPO2) below 2.8 psia Partial pressure of oxygen (PPO2) below 2.8 psia

or above 3.6 psiaor above 3.6 psia– Oxygen flow rate above 45 lb/hrOxygen flow rate above 45 lb/hr– Nitrogen flow rate above 5 lb/hrNitrogen flow rate above 5 lb/hr– Cabin pressure change greater than 0.05 psi/minCabin pressure change greater than 0.05 psi/min

Orbiter ECLSS - Caution and Warning PanelOrbiter ECLSS - Caution and Warning Panel


Cabin pressure limitationsCabin pressure limitations

Cabin over-pressure relief valve is set for 16 psia Cabin over-pressure relief valve is set for 16 psia

Positive and negative pressure relief valves in the Positive and negative pressure relief valves in the ARPCS are used to protect the structural integrity ARPCS are used to protect the structural integrity of the cabin from over- and under-pressurization of the cabin from over- and under-pressurization – Over-pressure relief valve opens at 15.5 psid Over-pressure relief valve opens at 15.5 psid

(differential) with full flow at 16.0 psid (differential) with full flow at 16.0 psid – Under-pressure relief valve opens at -0.2 psid Under-pressure relief valve opens at -0.2 psid

(ambient pressure greater than cabin pressure)(ambient pressure greater than cabin pressure)


Orbiter cabin pressurization – EVAOrbiter cabin pressurization – EVA

The Orbiter's crew cabin pressurization maintains a The Orbiter's crew cabin pressurization maintains a 14.7 psia atmosphere except for EVA and EVA 14.7 psia atmosphere except for EVA and EVA preparationpreparation

During EVA preparation the cabin pressure is During EVA preparation the cabin pressure is reduced to 10.2 psia to minimize the risk of reduced to 10.2 psia to minimize the risk of decompression sickness (bends) for the EVA crewdecompression sickness (bends) for the EVA crew– Standard protocol calls for EVA crew members to Standard protocol calls for EVA crew members to

prebreathe pure Oprebreathe pure O22 before EVA to help flush N before EVA to help flush N22 form their body tissueform their body tissue



Three protocols (options) are available for the mission Three protocols (options) are available for the mission planners and crew for EVA prebreathing routines to planners and crew for EVA prebreathing routines to reduce nitrogen in the blood of the EVA astronautsreduce nitrogen in the blood of the EVA astronauts

Option 1Option 1

60-minute initial O60-minute initial O22 prebreathe on launch and entry prebreathe on launch and entry

suit helmet suit helmet

12 hours at 10.2 psia cabin pressure 12 hours at 10.2 psia cabin pressure

75-minute final O75-minute final O22 prebreathe in EVA suit prebreathe in EVA suit



Option 2Option 2

60-minute initial O60-minute initial O22 prebreathe on launch and prebreathe on launch and

entry suit helmet entry suit helmet

24 hours at 10.2 psia cabin pressure 24 hours at 10.2 psia cabin pressure

40-minute final O40-minute final O22 prebreathe in EVA suit prebreathe in EVA suit



Option 3Option 3

4-hour O4-hour O22 prebreathe in EVA suit prebreathe in EVA suit

For scheduled EVAs, option 1 or 2 are used to For scheduled EVAs, option 1 or 2 are used to minimize the in-suit Ominimize the in-suit O22 prebreathe just prior to the prebreathe just prior to the

EVAEVA

PPOPPO22 levels must be controlled manually during 10.2 levels must be controlled manually during 10.2

psia cabin operationspsia cabin operations

2. Orbiter Active Thermal 2. Orbiter Active Thermal Control System (ATCS)Control System (ATCS)

Orbiter ECLSS - Active Thermal Control SystemOrbiter ECLSS - Active Thermal Control System

The Active Thermal Control System removes heat The Active Thermal Control System removes heat from the interior of the Orbiter during all phases of from the interior of the Orbiter during all phases of the flight, from pre-launch to post-landingthe flight, from pre-launch to post-landing

Operational environment extremes in temperature Operational environment extremes in temperature and temperature require three independent heat and temperature require three independent heat removal subsystems (sinks)removal subsystems (sinks)– Radiator panels Radiator panels – Water flash evaporators Water flash evaporators – Ammonia boilersAmmonia boilers



The Orbiter’s Active Thermal Control System uses a The Orbiter’s Active Thermal Control System uses a total of four coolant loops to remove heat from the total of four coolant loops to remove heat from the interior of the three fuselage sectionsinterior of the three fuselage sections

Dual-redundant interior water loopsDual-redundant interior water loops

Dual-redundant exterior Freon loopsDual-redundant exterior Freon loops

Heat passage from the interior loop to the exterior Heat passage from the interior loop to the exterior loop is through a highly conductive heat exchangerloop is through a highly conductive heat exchanger


Heat from the Heat from the interior of the interior of the Orbiter is Orbiter is transferred to transferred to these these subsystems subsystems using dual using dual independent independent water and Freon water and Freon cooling loopscooling loops

Ground Service Ground Service Equipment is Equipment is used during used during prelaunch and prelaunch and post-landing to post-landing to remove heat remove heat through the T-0 through the T-0 umbilical panel umbilical panel on the aft on the aft fuselagefuselage


Two dual-redundant cooling loops used for safe, Two dual-redundant cooling loops used for safe, effective heat removaleffective heat removal

Water coolant loop (cabin)Water coolant loop (cabin)

Two separate internal water coolant loop systems Two separate internal water coolant loop systems condition the crew cabin by transferring heat from condition the crew cabin by transferring heat from the crew cabin, avionics bays and IMUsthe crew cabin, avionics bays and IMUs– Heat is transferred to the dual external Freon Heat is transferred to the dual external Freon

coolant loops through a heat exchanger called coolant loops through a heat exchanger called the interchangerthe interchanger


Water coolant loopWater coolant loop

Two internal water coolant loops are identical, except that Two internal water coolant loops are identical, except that loop 1 has two water pumps and water loop 2 has oneloop 1 has two water pumps and water loop 2 has one

The separate water coolant loops are laid out side-by-side The separate water coolant loops are laid out side-by-side and can operate at the same timeand can operate at the same time– Only one is active at any given timeOnly one is active at any given time– Loop 2 with a single pump is normally the active loopLoop 2 with a single pump is normally the active loop

The three water pumps are located in the ECLSS bay The three water pumps are located in the ECLSS bay below the forward lockersbelow the forward lockers– ATCS pumps are powered by three-phase, 115-volt ac ATCS pumps are powered by three-phase, 115-volt ac

motorsmotors

Orbiter ECLSS - ATCS Water LoopsOrbiter ECLSS - ATCS Water Loops



Freon Cooling System (FCS) – external loopFreon Cooling System (FCS) – external loop

Freon - chlorofluorocarbon and Freon - chlorofluorocarbon and hydrochlorofluorocarbon refrigerants used in air hydrochlorofluorocarbon refrigerants used in air conditioning and refrigeration systemsconditioning and refrigeration systems– DuPont productsDuPont products– OdorlessOdorless– ColorlessColorless– NonflammableNonflammable– NoncorrosiveNoncorrosive– High thermal conductivityHigh thermal conductivity– High stabilityHigh stability– Environmental hazard because of its ability to Environmental hazard because of its ability to

break down ozone in the upper atmospherebreak down ozone in the upper atmosphere

Orbiter ECLSS - Freon Cooling SystemOrbiter ECLSS - Freon Cooling System

Two independent Freon-21 coolant loops Two independent Freon-21 coolant loops designated A and B are integrated into each Orbiterdesignated A and B are integrated into each Orbiter

Transfers heat from the Orbiter's internal water Transfers heat from the Orbiter's internal water loops and external sources to the heat sinksloops and external sources to the heat sinks– Freon was chosen for its efficient heat transfer, Freon was chosen for its efficient heat transfer,

but poses a toxic gas hazard to the crew if it were but poses a toxic gas hazard to the crew if it were to leak into the cabin moduleto leak into the cabin module

Orbiter ECLSS - Freon Cooling SystemOrbiter ECLSS - Freon Cooling System

Dual-redundant Freon-21 systems provide system Dual-redundant Freon-21 systems provide system redundancy for the Orbiter's external cooling loopredundancy for the Orbiter's external cooling loop– Each of the two Freon loops has a pump package Each of the two Freon loops has a pump package

consisting of two pumps and an accumulator consisting of two pumps and an accumulator used to reduce pressure spikes at pump startup used to reduce pressure spikes at pump startup and shutdownand shutdown

– One pump in each loop is active at all timesOne pump in each loop is active at all times– A separate set of Freon loops (using Freon-40) A separate set of Freon loops (using Freon-40)

transfers heat from the three fuel cells to the transfers heat from the three fuel cells to the Freon-21 outer loops via the fuel cell heat Freon-21 outer loops via the fuel cell heat exchangerexchanger



Freon Cooling System (FCS)Freon Cooling System (FCS)

Avionics and electronics heat removal is Avionics and electronics heat removal is accomplished with conductive cold plate networks accomplished with conductive cold plate networks for increased heat transfer efficientlyfor increased heat transfer efficiently– Forced-air cooling is used for larger Forced-air cooling is used for larger

electronics/avionics heat loads including the electronics/avionics heat loads including the IMUs, TACAN, MSBLS, and GPCsIMUs, TACAN, MSBLS, and GPCs

Liquid-to-liquid heat exchangers are used to transfer Liquid-to-liquid heat exchangers are used to transfer heat from external cooling loops and cold plates to heat from external cooling loops and cold plates to the external Freon 21 cooling loop pairthe external Freon 21 cooling loop pair– The two internal water cooling loops are The two internal water cooling loops are

connected to the outer Freon 21 cooling loop connected to the outer Freon 21 cooling loop through the water/Freon interchanger (heat through the water/Freon interchanger (heat exchanger)exchanger)

Orbiter ECLSS - ATCS Freon LoopsOrbiter ECLSS - ATCS Freon Loops

ATCS Freon Loop Pump PackageATCS Freon Loop Pump Package

Orbiter ECLSS - Heat RemovalOrbiter ECLSS - Heat Removal

Four heat sink systems are used on the Orbiter Four heat sink systems are used on the Orbiter for rejecting internal heat to for rejecting internal heat to space/atmosphere/ground equipmentspace/atmosphere/ground equipment

1. Radiator Panels1. Radiator Panels2. Ammonia Boiler System (ABS)2. Ammonia Boiler System (ABS)3. Flash (water) Evaporator System (FES)3. Flash (water) Evaporator System (FES)4. Ground Service Equipment connections4. Ground Service Equipment connections

Heat is carried to these sinks via the dual Heat is carried to these sinks via the dual internal water loops, through the internal water loops, through the water/Freon interchanger, then to the dual water/Freon interchanger, then to the dual external Freon loopsexternal Freon loops


Heat removal (sinks)Heat removal (sinks)

1. Radiator Panels1. Radiator Panels

Radiation of heat to space from the Orbiter uses Radiation of heat to space from the Orbiter uses three panels on each of the payload bay doors in three panels on each of the payload bay doors in the normal configurationthe normal configuration

– Two of four radiator panels on the forward Two of four radiator panels on the forward section of the payload bay doors can be section of the payload bay doors can be extended (deployed) for increased heat rejectionextended (deployed) for increased heat rejection

– Individual mission requirements determine if the Individual mission requirements determine if the forward radiators are deployed based on the heat forward radiators are deployed based on the heat loadload

– The third and fourth radiator panels are fixed to The third and fourth radiator panels are fixed to the aft underside of the aft right and left payload the aft underside of the aft right and left payload bay doors and are not deployablebay doors and are not deployable

Orbiter ECLSS - ATCS Radiator PanelsOrbiter ECLSS - ATCS Radiator Panels


Radiator panels – ConstructionRadiator panels – Construction

Radiator panels are composed of aluminum honeycomb sheetRadiator panels are composed of aluminum honeycomb sheet– Payload bay doors are composed of composite materialsPayload bay doors are composed of composite materials

Cooling tubes that circulate the Freon 21 are located near the Cooling tubes that circulate the Freon 21 are located near the radiator surfaceradiator surface

Combined surface area of the radiator panels is 111 mCombined surface area of the radiator panels is 111 m33 (1,195 (1,195 ftft33))

The maximum heat rejection capability of the radiator system is The maximum heat rejection capability of the radiator system is 61,100 Btu per hour61,100 Btu per hour

Cold soaking the Freon that circulates in the radiators by Cold soaking the Freon that circulates in the radiators by decreasing the temperature before reentry is used as a heat decreasing the temperature before reentry is used as a heat sink during the later stages of reentrysink during the later stages of reentry

ATCS Radiator PanelsATCS Radiator Panels


2. Ammonia Boiler System (ABS)2. Ammonia Boiler System (ABS)

Ammonia boiler extracts heat from the cooling loop by Ammonia boiler extracts heat from the cooling loop by the evaporation of ammoniathe evaporation of ammonia

Because ammonia has a boiling point lower than water, Because ammonia has a boiling point lower than water, the ammonia evaporator is useful for primary cooling at the ammonia evaporator is useful for primary cooling at higher ambient pressureshigher ambient pressures– Primarily from reentry to landing if the radiators have Primarily from reentry to landing if the radiators have

not been cold-soakednot been cold-soaked– If radiator cooling is used during entry, the ammonia If radiator cooling is used during entry, the ammonia

system is activated post-landing when the radiator system is activated post-landing when the radiator outlet temperatures reach 12.8outlet temperatures reach 12.8ooC (55C (55ooF)F)

– The ammonia boiler is also used post-landing until The ammonia boiler is also used post-landing until the Orbiter is connected to a portable GSE heat sinkthe Orbiter is connected to a portable GSE heat sink


Each of the two Ammonia Boiler Systems Each of the two Ammonia Boiler Systems located in the aft fuselage consists of:located in the aft fuselage consists of:– Boiler/evaporatorBoiler/evaporator– Storage tankStorage tank– Isolation valveIsolation valve– Overboard relief valveOverboard relief valve– Two control valvesTwo control valves– ControllerController– Three temperature sensorsThree temperature sensors– Pressure sensorPressure sensor– Feedline to the boilerFeedline to the boiler


Ammonia Boiler System (ABS)Ammonia Boiler System (ABS)

ABS heat exchanger is a single-pass ammonia and a ABS heat exchanger is a single-pass ammonia and a two pass flow-through Freon coolant looptwo pass flow-through Freon coolant loop

Ammonia flows over the hot Freon coolant lines in Ammonia flows over the hot Freon coolant lines in the evaporator/boiler and is vaporizedthe evaporator/boiler and is vaporized


Ammonia Boiler System (ABS)Ammonia Boiler System (ABS)

Heat and boiler exhaust is vented overboard in the Heat and boiler exhaust is vented overboard in the upper aft fuselage of the Orbiter, next to the bottom upper aft fuselage of the Orbiter, next to the bottom right side of the vertical tailright side of the vertical tail

ABS contains a single boiler that is fed by two ABS contains a single boiler that is fed by two independent ammonia supply subsystemsindependent ammonia supply subsystems

Maximum heat rejection for the ABS is 113,200 Maximum heat rejection for the ABS is 113,200 Btu/hrBtu/hr


3. Flash Evaporator System (FES)3. Flash Evaporator System (FES)

The FES is used to remove heat from the Orbiter's The FES is used to remove heat from the Orbiter's Freon-21 loops by circulating the heated Freon Freon-21 loops by circulating the heated Freon through the FES evaporation radiator sprayed with through the FES evaporation radiator sprayed with potable waterpotable water

Cooling comes from the heat of vaporization of the Cooling comes from the heat of vaporization of the evaporating water vented to spaceevaporating water vented to space– An efficient cooling process until atmospheric pressure An efficient cooling process until atmospheric pressure

becomes significantbecomes significant– Hence are used during ascent while above 140,000 feetHence are used during ascent while above 140,000 feet– FES can also be used to supplement the radiator heat sink FES can also be used to supplement the radiator heat sink

on orbiton orbit– Can also be used during deorbit and entry above Can also be used during deorbit and entry above

approximately 100,000 feetapproximately 100,000 feet

Orbiter ECLSS - Flash Evaporator SystemOrbiter ECLSS - Flash Evaporator System


Flash Evaporator System (FES)Flash Evaporator System (FES)

Cold-soaking is normally used for the Orbiter's Cold-soaking is normally used for the Orbiter's cooling during reentry and descentcooling during reentry and descent

FES is housed in the aft fuselageFES is housed in the aft fuselage

Two evaporation evaporators/boilers are used in the Two evaporation evaporators/boilers are used in the FESFES– High-load evaporator has a higher cooling capacity than the High-load evaporator has a higher cooling capacity than the

topping evaporatortopping evaporatorHas only one overboard vent on the left side of the vehicleHas only one overboard vent on the left side of the vehicle

– Lower-capacity topping evaporator Lower-capacity topping evaporator Has two vents that discharge steam equally to the left and right Has two vents that discharge steam equally to the left and right sides of the Orbiter for reactive force symmetry (non-sides of the Orbiter for reactive force symmetry (non-propulsive)propulsive)

Flash Evaporator SystemFlash Evaporator System



FES characteristics include:FES characteristics include:

1,000 Btu per hour per lb of water consumed1,000 Btu per hour per lb of water consumed

Maximum heat rejection is 148,000 Btu/hr using both Maximum heat rejection is 148,000 Btu/hr using both topping and high-load evaporatorstopping and high-load evaporators

Used from 125 sec after liftoff until payload bay Used from 125 sec after liftoff until payload bay doors are opened on orbit doors are opened on orbit



Used from payload bay closure until 100,000' altitudeUsed from payload bay closure until 100,000' altitude

Water supplied by potable water storage tanks A & B Water supplied by potable water storage tanks A & B – Potable water is used to avoid buildup of deposits Potable water is used to avoid buildup of deposits

on the interior of the evaporatoron the interior of the evaporator

Orbiter ECLSS - ATCS GSEOrbiter ECLSS - ATCS GSE

4. Ground support heat 4. Ground support heat exchangersexchangers

Ground support equipment is Ground support equipment is used to remove heat from the used to remove heat from the Orbiter during ground Orbiter during ground operationsoperations– Post-landing & tow-inPost-landing & tow-in– Orbiter Processing Orbiter Processing

FacilityFacility– Vehicle Assembly Vehicle Assembly

BuildingBuilding– Rollout on Crawler to Rollout on Crawler to

launch padlaunch pad– Launch padLaunch pad

Portable GSE cooler used for Portable GSE cooler used for post-landing is shown being post-landing is shown being attached to the Orbiter’s T-0 attached to the Orbiter’s T-0 panelpanel

3. ECLSS - Food3. ECLSS - Food

Orbiter ECLSS - FoodOrbiter ECLSS - Food

Foods supplied on STS missions are categorized as three Foods supplied on STS missions are categorized as three basic typesbasic types

– MenuMenuMenu foods are stocked for three meals per dayMenu foods are stocked for three meals per dayProvides an average of 2,700 calories for each Provides an average of 2,700 calories for each crewmember per daycrewmember per day

– PantryPantrySnacks and beveragesSnacks and beveragesCan be interchanged with planned menu itemsCan be interchanged with planned menu itemsMake up a 2-day contingency supplyMake up a 2-day contingency supplyFurnishes 2,100 calories per crewmember per dayFurnishes 2,100 calories per crewmember per day

– FreshFreshInclude perishable items such as fruits and Include perishable items such as fruits and vegetablesvegetables


Foods with a longer shelf-life are classified as:Foods with a longer shelf-life are classified as:

– Rehydratable (soups, casseroles, appetizers, Rehydratable (soups, casseroles, appetizers, breakfast foods)breakfast foods)

– Thermostabilized (meats, vegetables, fish, fruit)Thermostabilized (meats, vegetables, fish, fruit)

– Irradiated (meats)Irradiated (meats)

– Intermediate-moisture (dried fruit, dried meat)Intermediate-moisture (dried fruit, dried meat)

– Natural-form (nuts, granola bars, cookies)Natural-form (nuts, granola bars, cookies)


Astronauts choose their meals before the missions far Astronauts choose their meals before the missions far enough in advance for preparation, refrigeration, and enough in advance for preparation, refrigeration, and storage on the Orbiterstorage on the Orbiter

Vitamins and minerals are included in the astronaut's Vitamins and minerals are included in the astronaut's individual diets according to NASA's nutritional individual diets according to NASA's nutritional guidelines and with the assistance of dietitiansguidelines and with the assistance of dietitians


GalleyGalley

A galley is provided for crew meals in the mid deck A galley is provided for crew meals in the mid deck section of the Orbiter that provides:section of the Orbiter that provides:– OvenOven– Rehydration unitRehydration unit– Cold and hot waterCold and hot water– Storage for utensils, condiments and Storage for utensils, condiments and

implementsimplements– Cleanup equipment & storageCleanup equipment & storage


GalleyGalley

Traditional liquid condiments like ketchup, mustard, Traditional liquid condiments like ketchup, mustard, mayonnaise, and hot sauce are provided in familiar mayonnaise, and hot sauce are provided in familiar packetspackets

Powdered condiments like salt, pepper, and sugar Powdered condiments like salt, pepper, and sugar are maintained in liquid form in dispensers to keep are maintained in liquid form in dispensers to keep the contents from floating throughout the cabinthe contents from floating throughout the cabin

Beverages are stored in collapsible containers and Beverages are stored in collapsible containers and consumed using strawsconsumed using straws

Orbiter ECLSS - GalleyOrbiter ECLSS - Galley


GalleyGalley

The galley oven and rehydration station is capable of The galley oven and rehydration station is capable of preparing meals for the entire crew at the same timepreparing meals for the entire crew at the same time

The three one-hour daily meal periods include The three one-hour daily meal periods include cleanup, and waste and packaging storage, usually in cleanup, and waste and packaging storage, usually in the Waste Collection Systemthe Waste Collection System

Breakfast, lunch and dinner are scheduled as close Breakfast, lunch and dinner are scheduled as close to the usual meal times as possibleto the usual meal times as possible

Orbiter ECLSS - GalleyOrbiter ECLSS - Galley

Orbiter ECLSS - Menu Orbiter ECLSS - Menu GuideGuide


Individual meals are selected by each Individual meals are selected by each crewmember for the entire missioncrewmember for the entire mission

Stored in middeck lockersStored in middeck lockers

Color codedColor coded

4. Water and Wastewater 4. Water and Wastewater SystemSystem

Orbiter ECLSS - Water & WastewaterOrbiter ECLSS - Water & Wastewater

Water onboard the Orbiter is generated by the fuel Water onboard the Orbiter is generated by the fuel cells as potable watercells as potable water

Used for crew consumption, crew hygiene, and for Used for crew consumption, crew hygiene, and for the flash evaporator cooling systemthe flash evaporator cooling system– Excess water from fuel cells is normally dumped Excess water from fuel cells is normally dumped

overboard, along with excess waste wateroverboard, along with excess waste water– Supply water dump can also be routed through the Supply water dump can also be routed through the

FES as coolant if neededFES as coolant if needed– Excess water can also be transferred to the Excess water can also be transferred to the

International Space Station when docked International Space Station when docked


Water is stored in five 104 liter (27.5 gal, 165 lb) tanksWater is stored in five 104 liter (27.5 gal, 165 lb) tanks– Designated A, B, C, and D, and one waste water tankDesignated A, B, C, and D, and one waste water tank– Tank A is reserved for potable water for crew Tank A is reserved for potable water for crew

consumption and the first to be filled from the fuel cell consumption and the first to be filled from the fuel cell supplysupply

– B, C, and D are used for excess water storage and are B, C, and D are used for excess water storage and are filled in sequence after Tank A filled in sequence after Tank A

All four of the water supply tanks can be used for the Flash All four of the water supply tanks can be used for the Flash Evaporator SystemEvaporator System– Tanks B, C, and D are normally used for that purposeTanks B, C, and D are normally used for that purpose

All water tanks including waste water tank are pressurized All water tanks including waste water tank are pressurized with nitrogen gaswith nitrogen gas– Drained by a bellows systemDrained by a bellows system

Orbiter ECLSS - Water Tank (Mounted as Pair)Orbiter ECLSS - Water Tank (Mounted as Pair)


Water from the supply water tanks is also used to Water from the supply water tanks is also used to service the water supply for EMU suits in the airlockservice the water supply for EMU suits in the airlock

Fuel cell water production has a maximum production Fuel cell water production has a maximum production of 15.5 l/hr (4.1 gal/hr)of 15.5 l/hr (4.1 gal/hr)– Equivalent to 0.37 kg (0.81 lb) of water per kW-hrEquivalent to 0.37 kg (0.81 lb) of water per kW-hr

Water lines from the fuel cells that are located in the Water lines from the fuel cells that are located in the payload bay to the tanks located in the forward payload bay to the tanks located in the forward fuselage are heated to prevent freezing on orbitfuselage are heated to prevent freezing on orbit– Water dump lines are also heated, as are the dual Water dump lines are also heated, as are the dual

water dump nozzleswater dump nozzles

Orbiter ECLSS - Water Dump Ports & HeatersOrbiter ECLSS - Water Dump Ports & Heaters


Hydrogen separators remove excess hydrogen from Hydrogen separators remove excess hydrogen from the power production process in the fuel cells the power production process in the fuel cells before being routed to the water supply tanksbefore being routed to the water supply tanks

Supply water is passed through a microbial filter Supply water is passed through a microbial filter before entering tank Abefore entering tank A– Microbial filter adds iodine compound to the Microbial filter adds iodine compound to the

water that enters tank A to prevent microbial water that enters tank A to prevent microbial growth in the water supply systemgrowth in the water supply system


Tank A water is filtered before being sent to the Tank A water is filtered before being sent to the galley for chilled water (45-55galley for chilled water (45-55ooF) and heated water F) and heated water (155-165(155-165ooF) supplyF) supply

Inlet valves and outlet valves on the supply water Inlet valves and outlet valves on the supply water tanks allow selective fill and selective water dumptanks allow selective fill and selective water dump– Up to 210 lb of water can be dumped at a timeUp to 210 lb of water can be dumped at a time

76% of the water in tank A must be maintained for 76% of the water in tank A must be maintained for minimum crew requirementsminimum crew requirements


Orbiter potable water purificationOrbiter potable water purification

0.5 ppm iodine solution added to tank A inlet0.5 ppm iodine solution added to tank A inlet

Microbial filter in supply line removes small particles Microbial filter in supply line removes small particles and microbes and microbes

pH sensors monitor water purity pH sensors monitor water purity


Hydrogen separators remove 85% of hydrogen-rich Hydrogen separators remove 85% of hydrogen-rich fuel cell water fuel cell water

– Line to Tank A passes through two hydrogen Line to Tank A passes through two hydrogen separators consisting of a matrix of silver separators consisting of a matrix of silver palladium tubes which have an affinity for palladium tubes which have an affinity for hydrogenhydrogen

85% of hydrogen is removed then dumped 85% of hydrogen is removed then dumped overboard overboard


Orbiter potable water purificationOrbiter potable water purification

The waste water tank drain is not used in flightThe waste water tank drain is not used in flight– Waste water inlet line also acts as the outlet line Waste water inlet line also acts as the outlet line

for dumping excess waste water overboardfor dumping excess waste water overboard– A separate waste water dump line and nozzle is A separate waste water dump line and nozzle is

available, with a crossover for use by the supply available, with a crossover for use by the supply tankstanks

– A collapsible waste water bag is carried on the A collapsible waste water bag is carried on the Orbiter in case the waste water dump nozzle is Orbiter in case the waste water dump nozzle is blockedblocked

5. Waste Collection 5. Waste Collection SystemSystem

Orbiter ECLSS - Waste Collection SystemOrbiter ECLSS - Waste Collection System

The Orbiter's waste collection system is used The Orbiter's waste collection system is used primarily to collect crew fecal and urine waste in a primarily to collect crew fecal and urine waste in a zero gravity environmentzero gravity environment

WCS base is the Orbiter commodeWCS base is the Orbiter commode

WCS is used to: process crew cabin and EMU WCS is used to: process crew cabin and EMU condensate for waste water storagecondensate for waste water storage

Waste collection unit also routes wet trash gas for Waste collection unit also routes wet trash gas for dumping overboard, transfers condensate water to dumping overboard, transfers condensate water to the waste water tankthe waste water tank– Facilitates condensate water overboard dumping, if Facilitates condensate water overboard dumping, if

necessarynecessary


The Orbiter's WCS is The Orbiter's WCS is contained in a module contained in a module that contains the that contains the waste tank, commode, waste tank, commode, and the waste and the waste management (wet and management (wet and dry trash) dry trash) compartmentcompartment


Major components of the WCS include:Major components of the WCS include:

Waste management compartment and privacy curtains Waste management compartment and privacy curtains

Commode Commode – Bag liner used for solid fecal waste storage Bag liner used for solid fecal waste storage – Vacuum exposure of bag liner is used for drying when not in use Vacuum exposure of bag liner is used for drying when not in use

Urinal Urinal – Separate male and female adaptersSeparate male and female adapters– Processed for storage in waste water tank Processed for storage in waste water tank

Fan separators Fan separators – Air flow transport for liquids in waste collection system Air flow transport for liquids in waste collection system

Odor and bacteria filter Odor and bacteria filter – Separated air filtered and mixed with cabin air Separated air filtered and mixed with cabin air – Vacuum vent disconnect Vacuum vent disconnect – Allows ARS waste water to be dumped overboard Allows ARS waste water to be dumped overboard

Waste collection controls Waste collection controls


Orbiter ECLSS Orbiter ECLSS

Waste Collection System Waste Collection System

6. Fire Detection and 6. Fire Detection and Suppression SystemSuppression System

Orbiter ECLSS - Smoke Detection and Suppression SystemOrbiter ECLSS - Smoke Detection and Suppression System

Smoke detection and fire suppression components on Smoke detection and fire suppression components on the Orbiter are located in the crew cabin and the the Orbiter are located in the crew cabin and the avionics baysavionics bays

Ionization detectors that sense smoke particles will Ionization detectors that sense smoke particles will trigger alarms at set concentration levels, or at trigger alarms at set concentration levels, or at concentration change limitsconcentration change limits

Readouts of the smoke detectors are shown on the Readouts of the smoke detectors are shown on the performance monitoring CRTs, as well as on lighted performance monitoring CRTs, as well as on lighted panels and on the caution and warning illuminated panels and on the caution and warning illuminated panelspanels


Two groups of smoke sensors identified as A Two groups of smoke sensors identified as A and B provide information on the general and B provide information on the general locationlocation– Specific ionization detector can be identified on the Specific ionization detector can be identified on the

CRTsCRTs

Group A detectors located in the ECLSS cabin Group A detectors located in the ECLSS cabin fan outlet and left return duct, as well as one fan outlet and left return duct, as well as one each in the avionics bays 1, 2, and 3each in the avionics bays 1, 2, and 3

Group B are located in the right cabin return Group B are located in the right cabin return duct and the three avionics baysduct and the three avionics bays


Fire suppression on the Orbiter is divided into two Fire suppression on the Orbiter is divided into two areas with two separate chemicals – avionics areas with two separate chemicals – avionics extinguishers and crew cabin extinguishersextinguishers and crew cabin extinguishers– Freon-1301 (bromotrifluoromethane) extinguisher bottles Freon-1301 (bromotrifluoromethane) extinguisher bottles

used for the three avionics baysused for the three avionics bays– Three portable extinguishers in the cabin are charged with Three portable extinguishers in the cabin are charged with

Halon-1301 (monobromotrifluoromethane) for the crew Halon-1301 (monobromotrifluoromethane) for the crew cabincabin

Halon-1301 is chosen for its effectiveness in controlling Halon-1301 is chosen for its effectiveness in controlling smoke, heat, oxygen depletion, and its ability to reduce smoke, heat, oxygen depletion, and its ability to reduce pyrolysis products such as carbon monoxidepyrolysis products such as carbon monoxide

Avionics bay extinguishers are fired by switches on Avionics bay extinguishers are fired by switches on the L1 panelthe L1 panel

Halon-1301 portable extinguishers are discharged Halon-1301 portable extinguishers are discharged manuallymanually

7. Spacesuits and EVA7. Spacesuits and EVA

Orbiter EVAOrbiter EVA

Spacewalks, or extravehicular activity (EVA), requires Spacewalks, or extravehicular activity (EVA), requires a self-contained, pressurized space suit that a self-contained, pressurized space suit that provides the same essential life support functions provides the same essential life support functions as the crew vehicleas the crew vehicle

Space suit life support functions include:Space suit life support functions include:Oxygen supplyOxygen supplyCarbon dioxide removalCarbon dioxide removalThermal controlThermal controlOdor and trace gas removalOdor and trace gas removalWater supplyWater supplyFoodFoodWaste removalWaste removal

Orbiter EVAOrbiter EVA

The crew space suit, called the The crew space suit, called the Extravehicular Mobility Unit (EMU), supplies Extravehicular Mobility Unit (EMU), supplies life support basics, and:life support basics, and:– Rechargeable battery electrical powerRechargeable battery electrical power– Duplex UHF communicationsDuplex UHF communications– Biological and instrument telemetryBiological and instrument telemetry– InstrumentationInstrumentation– Caution and Warning (C/W) electronicsCaution and Warning (C/W) electronics

Orbiter EMUOrbiter EMU

The Orbiter EMU is divided into three main partsThe Orbiter EMU is divided into three main parts– Hard Upper Torso (HUT)Hard Upper Torso (HUT)– Lower Torso assembly (LTA)Lower Torso assembly (LTA)– Portable Life Support System (PLSS)Portable Life Support System (PLSS)

Many of the features and subsystems on the EMU Many of the features and subsystems on the EMU have evolved from the earlier NASA space suits, have evolved from the earlier NASA space suits, including the self-contained PLSS, and the including the self-contained PLSS, and the sublimator cooling unit that came from the Apollo-sublimator cooling unit that came from the Apollo-era suitera suit


Typically, two EMUs are available for Typically, two EMUs are available for missions that require EVAmissions that require EVA

EMUs are tailored to the astronaut and EMUs are tailored to the astronaut and stored in the airlock except when in use on stored in the airlock except when in use on EVAEVA

Design lifetime of the EMU is 15 yearsDesign lifetime of the EMU is 15 years



Pure oxygen is used for suit pressurization which Pure oxygen is used for suit pressurization which is maintained at 4 psidis maintained at 4 psid

Oxygen capacity of the EMU is seven hours, with a Oxygen capacity of the EMU is seven hours, with a 30 minute emergency reserve30 minute emergency reserve

Pressurized OPressurized O22 bottles contained in the PLSS bottles contained in the PLSS includeinclude– 1.2 lb @ 8,500 psi1.2 lb @ 8,500 psi– Secondary oxygen pack with 2.6 lb @ 6,000 psiSecondary oxygen pack with 2.6 lb @ 6,000 psi


A replaceable lithium hydroxide cartridge is A replaceable lithium hydroxide cartridge is used for carbon dioxide removalused for carbon dioxide removal

Odor and trace gases are removed with an Odor and trace gases are removed with an activated charcoal filter placed in the activated charcoal filter placed in the air/oxygen circulation lineair/oxygen circulation line– Powered by a circulation fanPowered by a circulation fan


Major componentsMajor components

Liquid Cooling and Ventilation Garment (LCVG)Liquid Cooling and Ventilation Garment (LCVG)

The LCVG is worn by the astronauts as an The LCVG is worn by the astronauts as an undergarment to remove excess body heatundergarment to remove excess body heat

Heat removed via a network of tubes that Heat removed via a network of tubes that distributes oxygen and cool water throughout distributes oxygen and cool water throughout the garmentthe garment

Water pump circulates the water through a Water pump circulates the water through a thermal control valve assembly and thermal control valve assembly and sublimatorsublimator


– Sublimator allows the passage of the warm water Sublimator allows the passage of the warm water through channels in the porous blockthrough channels in the porous block

– As the water seeps towards the outer surface, the As the water seeps towards the outer surface, the cold vacuum conditions in space freezes that cold vacuum conditions in space freezes that waterwater

– Frozen water exposed to space sublimates, which Frozen water exposed to space sublimates, which cools with an equivalent heat loss of both the heat cools with an equivalent heat loss of both the heat of vaporization and the heat of fusion of vaporization and the heat of fusion

– Liquid water is not allowed to reach the surface Liquid water is not allowed to reach the surface because of the ice formed in the outer block, because of the ice formed in the outer block, which cools the liquid water flowing through the which cools the liquid water flowing through the interior channelsinterior channels

Orbiter EMU Liquid Cooling and Ventilation GarmentOrbiter EMU Liquid Cooling and Ventilation Garment

Bruce McCandless on STS-31 shown entering the Lower Torso Assembly and wearing the Liquid Cooling and Ventilation Garment


Hard Upper Torso (HUT)Hard Upper Torso (HUT)

The Hard Upper Torso is the single-piece EMU rigid The Hard Upper Torso is the single-piece EMU rigid above-the-waist structure used to mount the space above-the-waist structure used to mount the space suit attachments and components that are movable, suit attachments and components that are movable, removable, or replaceableremovable, or replaceable– Includes the arms, gloves, helmet, lower torso, Includes the arms, gloves, helmet, lower torso,

PLSS, display and control module, and electrical PLSS, display and control module, and electrical harnessharness

– HUT arms contain a shoulder joint and elbow HUT arms contain a shoulder joint and elbow joint, along with mobility bearings in the upper joint, along with mobility bearings in the upper arm and wristarm and wrist


Lower Torso Assembly (LTA)Lower Torso Assembly (LTA)

The Lower Torso Assembly, roughly everything The Lower Torso Assembly, roughly everything on the space suit below the waist, is attached to on the space suit below the waist, is attached to the Hard Upper Torso at the top and boots at the the Hard Upper Torso at the top and boots at the bottombottom

LTA is composed of a number of layers that make LTA is composed of a number of layers that make up the flexible pants, as well as hip, knee and up the flexible pants, as well as hip, knee and ankle jointsankle joints


Portable Life Support System (PLSS)Portable Life Support System (PLSS)

The PLSS is a fiberglass structure attached to the HUT The PLSS is a fiberglass structure attached to the HUT and used to mount the internal and external and used to mount the internal and external components. components. – Fiberglass construction Fiberglass construction – Water storage bladder tanks (3) Water storage bladder tanks (3)

10 lb capacity10 lb capacity– Air circulation fan Air circulation fan – Sublimator Sublimator – Contaminant control cartridge Contaminant control cartridge

LiOH for COLiOH for CO22 removal removalActivated charcoal for odor & contaminant Activated charcoal for odor & contaminant removal removal

– Communications antenna Communications antenna

Orbiter EMU - PLSSOrbiter EMU - PLSS


The EMU also contains power, The EMU also contains power, communications, and life-support communications, and life-support essentials that include: essentials that include: – Communications carrier assemblyCommunications carrier assembly– Two UHF transmittersTwo UHF transmitters– Three single channel receiversThree single channel receivers– Liquid cooling and ventilation garmentLiquid cooling and ventilation garment– Urine collection deviceUrine collection device– Operational bioinstrumentation systemOperational bioinstrumentation system– Display and control moduleDisplay and control module– Silver-zinc battery electrical supply Silver-zinc battery electrical supply


EMU-EVA life support durationEMU-EVA life support duration

Total durationTotal duration 7 hr7 hrEVAEVA 6 hr6 hrCheckout/donningCheckout/donning 15 min15 minDoffingDoffing 15 min15 minReserveReserve 30 min30 min

An additional 30 minutes is available from secondary oxygen An additional 30 minutes is available from secondary oxygen supply if the primary system failssupply if the primary system fails

Orbiter EMU - Power and Display SectionOrbiter EMU - Power and Display Section

8. Airlock8. Airlock

Orbiter AirlockOrbiter Airlock

The Orbiter's airlock assembly is used prepare two The Orbiter's airlock assembly is used prepare two astronauts for EVAastronauts for EVA

Provides for crew egress, and for their ingress in a Provides for crew egress, and for their ingress in a controlled-pressure, pure oxygen environmentcontrolled-pressure, pure oxygen environment

Pressurized airlock chamber is located either in the Pressurized airlock chamber is located either in the crew cabin mid deck, or in the payload bay, depending crew cabin mid deck, or in the payload bay, depending on mission and payload requirementson mission and payload requirements

The 4.3 mThe 4.3 m33 (150 ft (150 ft33) cylindrical airlock chamber ) cylindrical airlock chamber includes two pressure hatches with windows, one on includes two pressure hatches with windows, one on the cabin side, and one on the payload bay sidethe cabin side, and one on the payload bay side

Latch and gearbox assembly is placed on both sides Latch and gearbox assembly is placed on both sides of both hatches to allow EVA and cabin crew access of both hatches to allow EVA and cabin crew access to the airlockto the airlock


Two complete EMUs are stored in the airlock, along with Two complete EMUs are stored in the airlock, along with a portable oxygen systema portable oxygen system

Handholds, footholds and seating are furnished in the Handholds, footholds and seating are furnished in the airlock for maneuvering in and out of the airlockairlock for maneuvering in and out of the airlock

Service connections are also provided forService connections are also provided for– OxygenOxygen– COCO22 removal for airlock and suits removal for airlock and suits– Liquid-cooled garment waterLiquid-cooled garment water– OO22 recharge for suits recharge for suits– Electrical powerElectrical power– Airlock and suit communicationsAirlock and suit communications– LightingLighting


ECLSS Control Panel R1ECLSS Control Panel R1



References:References:

NASA ECLSS Shuttle Crew Operations Manual - ECLSS, NASANASA ECLSS Shuttle Crew Operations Manual - ECLSS, NASA

NASA Food Shuttle Crew Operations Manual - Food, NASANASA Food Shuttle Crew Operations Manual - Food, NASA

ECLSS 21002 - Environmental Control and Life Support System ECLSS 21002 - Environmental Control and Life Support System Training Manual, Mission Operations Directorate, Space Flight Training Manual, Mission Operations Directorate, Space Flight Training & Facility Operations, Shuttle Systems Training Branch, Training & Facility Operations, Shuttle Systems Training Branch, NASA, June 1999 NASA, June 1999

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Orbiter Environmental Control and Life Support System.

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