ECLSS System Overview • Subsystems of ECLSS (environment control and life support system) – Atmosphere – Water – Waste – Food
Jan 15, 2016
ECLSS System Overview
• Subsystems of ECLSS (environment control and life support system)– Atmosphere– Water– Waste– Food
Overview of ECLSS subsystems
FOOD
WATER AIR
WASTE
ECLSS System O
Atmosphere System
WasteSystem
FoodSystem
WaterSystem
AtmosphericCondenser
Urine
CompactorSolid Waste
Storage
TCCA
FoodTras
h
washer
hygiene
FoodPreparation
PlantHab
FecalSPWE Vent
to Mars Atm.
H2
EDCCO2
Compactor
Pretreatment Oxone, Sulfuricacid
Pretreated Urine
VCD
AES Brine Water
Ultra Filtration
RO
Milli Q
MCV Iodine
Monitoring
Hygiene Water
Iodine Removal Bed
ISE Monitoring
Potable Water
verview
Human Consumables
• Atmosphere– O2 consumption: 0.85 kg/man-day [Eckart, 1996]
– CO2 production: 1.0 kg/man-day [Eckart, 1996]
– Leakage (14.7psi): 0.11 kgN2/day & 0.03 kgO2/day
• Water– Potable 3 L/person/day [Larson, 1997]
• 1.86 Food Preparation •1.14 Drink
– Hygiene 18.5 L/person/day [Larson, 1997]
• 5.5 Personal Hygiene •12.5 Laundry •0.5 Toilet Flush
Human Consumables
• Waste– Urine: 9.36 kg/day [Eckart, 1996]
– Feces: 0.72 kg/day [Eckart, 1996]
– Technology & Biomass 1.012 kg/day [Eckart, 1996]
• Food– ~ 2,000 kCal per person per day [Miller,
1994]
Atmosphere System Schematic
Specifications Fixed mass
1,965 kg Consumable
4 kg/day Power
3.5 kW
crew cabin
cabinleakage
O2
N2 storagetanks
EDC
N2
FDS
To: hygiene water tank
T&Hcontrol
H2O
To: vent To: trash compactor
SPWE
H2
TCCA
To: vent
H2 & O2
CO2
From: H2O tank
H2O usedfilters & carbon
N2 O2, & H2O
H2O
Water System Schematic
Specifications Fixed mass
942.71 kg Consumable
(technologies)0.36 kg/day
Power2.01 kW
Waste System Schematic
Specifications Fixed mass
279 kg Consumable
2.3 kg/day Power
0.22 kW
To: waste water tank
feces
commodeurinal
compactor
From: TCCA food trash microfiltration VCD
trash
fecalstorage
solid wastestorage
compactor
urine
H2O
Food System Schematic
Specifications Fixed mass
1,320 kg Consumable
4.5 kg/day Power
3.4 kW
To: trash compactor
trash
potablewater
microwave water
food preparation
food & drink
SaladMachine
edible plant massinedible plant mass
foodwaste &
packaging foodstorage
wastewater
H2O
H2O
Habitat Layout
SubsystemAllocated
Volume
CCC 10
ECLSS 60
Structures 160
EVAS 30
Thermal 40
Power 30
Crew Accom. 75
Empty 300
Total 705
Top Floor: personal space and crew accommodations
Bottom Floor: Lab, equipment, and airlocks
Basement: Storage, equipment, supports and wheels
Hatches:One at each end, one in the middle, all on bottom floor
Leakage
• ISS Leakage – 1.24 kg/yr/m3
• Lunar Base Concept – 1.83 kg/yr/m3
• MOB Habitat – 530 m3
• Estimated Habitat Leakage – 657-791 kg/yr• Assume similar:
– Differential pressure– Materials– Thickness of outer shell
Future Tasks
• Load analysis
• Insulation
• Shielding
• Layout – more detail
• Volume Allocation – more detail
Thermal System
Thermal System Overview
• Requirement– Must reject 25 KW (from
Power system)– Must cool each
subsystem– Must use a non-toxic
interior fluid loop– External fluid loop must
not freeze– Accommodating transit to
Mars
• Design– Rejects up to 40 KW via
radiator panels– Cold plates for heat
collection from each subsystem
– Internal water fluid loop– External TBD fluid loop– During transit heat
exchangers will connect to the transfer vehicle’s thermal system
Thermal I/O Diagram
Thermal Schematic
Current Status
• Radiator panels sized for HOT - HOT scenario
• Fluid pumps sized• Initial power usage estimated• Initial plumbing estimates• Initial total mass estimates• System schematics
Thermal Components
Surface Area (m^2) Volume (m^3) Mass (kg) Power (W)
Radiators (4 x 105 m^2) 420 8.4 2226 NAHeat Exchangers (3) NA 0.20 81.73 NAPumps (6) NA 4.18 1179.90 1884.56Cold Plates (TBD) NA TBD 359.81 NAHeat Pumps NA TBD TBD TBDInstruments NA TBD 81.1 TBDPlumbing and Valves NA TBD 243.2 NAFluids NA TBD 81.1 NATOTAL 420.0 12.8 4252.8 1884.6
*Power is for two pumps in operation at one time, not six
Future Tasks
• Cold plates and sizing TBD• External fluid loop TBD• Heat exchangers TBD• Radiator locations TBD• Fluid storage TBD• COLD - COLD scenario TBD• Sensors/Data/Command structure TBD• FMEA• Report
C3 Subsystem
C3 Design Status
• Qualitatively defined data flows• Created preliminary design based on data
flows, mission requirements and existing systems– Command and Control System
• Sizing and architecture based on ISS
• Mass, power and volume breakdowns
– Communications System• Sizing and architecture based on existing systems
• Mass and power breakdowns
• Assuming at least 1 Mars orbiting communications satellite
ISRU ISRU PlantPlant
Nuclear Nuclear ReactorReactor
Mars Mars Env’mtEnv’mt
EVASEVAS
ISRUISRU
PowerPower ECLSSECLSS
ThermalThermal
CCCCCC
Robotics & Robotics & AutomationAutomation StructureStructure
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are needed to see this picture.
CrewCrew
Crew Crew AccommodationsAccommodations
LegendENERGY
Packetized DataTelemetry/DataCommand/Data
VoiceVideo
Electrical powerHeat
Earth
MarsComSat
C3 I/O Diagram
Tier 2 Science
Computers (2)
Tier 2 Subsystem
Computers (4)
Tier 1 Command
Computers (3)
Tier 3Subsystem
Computers (8)
FirmwireControllers
Sensors
Caution &Warning (?)
UserTerminals (6)
FileServer (1)
Tier 1 Emergency
Computer (1)
Control System DiagramV 1.0, 11/8/2003
LegendEthernetRF ConnectionMil-Std 1553B BusTBD
CommSystem
Experiments
RF Hubs (3)
C3 System
Other Systems
Command and Control System
Communications System
• High gain system– Link with Earth and long range rovers– Normally communicates through orbiting satellite– Emergency option for direct Earth communications
• Medium gain system – Emergency to satellite if high gain system fails
• UHF system – Local communications with EVA crew
C3 Future Tasks
• Quantify data flows and adjust preliminary design
• Determine spare parts needs • Estimate cabling mass• Address total system mass overrun • Define maintenance and operational
requirements • FMEA• Report
Mission Operations
• Past– Derived Requirements
• From DRM
– Reviewed Literature• Larson and Pranke• MSIS
Mission Operations
• Past– Created Functional Diagram (Crew
Accommodations)• Diagram goes here
Mission Operations
• Present– Creating lists of operations required for
each subsystem• Crew Operations
– example
• Automated Operations– example
Mission Operations
• Present– Giving input to subsystems
• Based on human factors considerations• Incorporating MSIS, Larson and Pranke, experience
– Determining mass, power, volume requirements for crew accommodations
Mission Operations
• Future Plans– Continue integration of human factors into
subsystems– Create tentative crew schedules
• Equipment Maintenance• Housekeeping• Scientific Tasks• Paperwork• Personal Time
Robotics and Automation
• Number/Functions of rovers– Three classes of rovers
• Small rover for scientific exploration• Medium rover for local transportation• Large pressurized rover for long exploration and
infrastructure inspection
• Power/Mass specs on all rovers
• Power specs on robotic arms
Automation items (in progress)
• Automated doors in case of depressurization• Deployment of habitat• Connection to power plant• Inspection of infrastructure• Site preparation• Communications hardware• External monitoring equipment• Deploy radiator panels• Deployment/Movement of scientific equipment
External Vehicular Activity Systems
• EVA tasks will consist of constructing and maintaining habitat, and scientific investigation
• EVAS broken up into 3 systems– EVA suit– Airlock– Pressurized/unpressurized rovers
EVAS – EVA Suit
• Critical functional elements: pressure shell, atmospheric and thermal control, communications, monitor and display, nourishment, and hygiene
• Current suit is much too heavy and cumbersome to explore the Martian environment
• ILC Dover is currently developing the I-Suit which is lighter, packable into a smaller volume, and has better mobility and dexterity
EVAS – EVA Suit
• I-Suit specs:– Soft upper-torso– 3.7 lbs/in2 (suit pressure can be varied)– Easier to tailor to each individual astronaut– ~65 lbs– Bearings at important rotational points– Greater visibility– Boots with tread for walking on Martian terrain– Parts are easily interchangeable (decrease
number of spare parts needed)
EVAS - Airlock
• Independent element capable of being ‘plugged’ or relocated as mission requires
• Airlock sized for three crew members with facilities for EVA suit maintenance and consumables servicing
• There will be two airlocks each containing three EVA suits
• Airlock will be a solid shell (opposed to inflatable)
• The airlock will interface with the habitat through both an umbilical system and the hatch
EVA – Pressurized Rover
• Nominal crew of 2 – can carry 4 in emergency situations
• Rover airlock capable of surface access and direct connection to habitat
• Per day, rover can support 16 person hours of EVA• Work station – can operate 2 mechanical arms from
shirt sleeve environment • Facilities for recharging portable LSS and minor
repairs to EVA suit• The rover will interface with the habitat through both
an umbilical system and the hatch
EVAS – Umbilical System
• Connections from the habitat to the airlock and rover will be identical
• Inputs from habitat to airlock/rover (through umbilical system)– Water (potable and non-potable)– Oxygen/Nitrogen– Data– Power
• Outputs from airlock/rover to habitat (through umbilical system)– Waste water– Air– Data
External Vehicular Activity Systems
• EVAS is primarily responsible for providing the ability for individual crew members to move around and conduct useful tasks outside the pressurized habitat
• EVA tasks will consist of constructing and maintaining habitat, and scientific investigation
• EVAS broken up into 3 systems– EVA suit– Airlock– Pressurized Rover
EVAS – EVA Suit
• Critical functional elements: pressure shell, atmospheric and thermal control, communications, monitor and display, nourishment, and hygiene
• Current suit is much too heavy and cumbersome to explore the Martian environment
• ILC Dover is currently developing the I-Suit which is lighter, packable into a smaller volume, and has better mobility and dexterity
EVAS – EVA Suit
• I-Suit specs:– Soft upper-torso– 3.7 lbs/in2 (suit pressure can be varied)– Easier to tailor to each individual astronaut– ~65 lbs– Bearings at important rotational points– Greater visibility– Boots with tread for walking on Martian terrain– Parts are easily interchangeable (decrease
number of spare parts needed)
EVAS - Airlock
• Independent element capable of being ‘plugged’ or relocated as mission requires
• Airlock sized for two crew members with facilities for EVA suit maintenance and consumables servicing
• There will be two airlocks each containing two EVA suits
• Airlock will be a solid shell (opposed to inflatable)
• The airlock will interface with the habitat through both an umbilical system and the hatch
EVA – Pressurized Rover
• Nominal crew of 2 – can carry 4 in emergency situations
• Rover airlock capable of surface access and direct connection to habitat
• Per day, rover can support 16 person hours of EVA• Work station – can operate 2 mechanical arms from
shirt sleeve environment • Facilities for recharging portable LSS and minor
repairs to EVA suit• The rover will interface with the habitat through both
an umbilical system and the hatch
EVAS – Umbilical System
• Connections from the habitat to the airlock and rover will be identical
• Inputs from habitat to airlock/rover (through umbilical system)– Water (potable and non-potable)– Oxygen/Nitrogen– Data– Power
• Outputs from airlock/rover to habitat (through umbilical system)– Waste water– Air– Data
ISRU/Mars Environment System
ISRU/Mars Environment I/O Diagram
ISRU Schematic
Current Status
• Mars Environment Information Sheet has been created– The information has been distributed to all
subsystems and located on MOB website
• ISRU plant options have been summarized
• Initial plumbing designs and estimates• Initial total mass estimates• System schematics
ISRU Plant Summary
Zirconia Electrolysis
Zirconia-walled Reactor
1000 °CCO2
CO + CO2
O2
Heat
Advantages•Simple operation•Produces Oxygen
Requires 1562 W-day/kg of Oxygen
ISRU Plant Summary
H2
Sabatier Electrolysis
Nickel Catalyst 400 °C
H2 + CO2
CH4
H2O
Heat
Advantages•Produces methane and oxygen•Energy efficient•High production rates
Disadvantages•Requires hydrogen feedstock•Methane and Oxygen aren’t produced in the ideal mixture ratio for rocket engines
Requires 166 W-day/kg of propellant
Electrolysis O2
Power
ISRU Plant Summary
H2
RVGS Methanol
Nickel Catalyst 400 °C
H2 + CO2
CH4
H2O
Heat
Advantages•Produces methane and oxygen•Energy efficient•High production rates
Disadvantages•Requires hydrogen feedstock•Methane and Oxygen aren’t produced in the ideal mixture ratio for rocket engines
Requires 166 W-day/kg of propellant
Electrolysis O2
Power
ISRU Plant Summary
H2
RVGS Ethanol
Nickel Catalyst 400 °C
H2 + CO2
CH4
H2O
Heat
Advantages•Produces methane and oxygen•Energy efficient•High production rates
Disadvantages•Requires hydrogen feedstock•Methane and Oxygen aren’t produced in the ideal mixture ratio for rocket engines
Requires 166 W-day/kg of propellant
Electrolysis O2
Power
Future Tasks
• ISRU plant trade study finalized• Soil shelter from radiation design TBD• Initial Mass estimates TBD• Pump design and sizing TBD• Thermal control requirements for water pipes
TBD• Interfaces with ECLSS TBD• FMEA• Report
Mars Surface Power Profile
•Allotted ~25kW
•Possibility of using power from other equipment
Power Breakdown
Subsystem Power Available Power needed
• CCC 8kW• ECLSS 8kW 9.1kW• EVA 6kW• Thermal 1kW• Mission Ops 0.5kW 6kW• Mars Env 0.5kW• Robotics 1kW 3kW
Current/Future Tasks
• Current Tasks– Researching hardware
• Volume predictions dependant on hardware
– Power circuit configuration– FMEA
• Future Tasks– Finalize power profile