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

QuickTime™ and aTIFF (Uncompressed) decompressor

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