Mars or Bust Management Briefing
Subsystem Update
11/19/03
Current Status - all Subsystems
• Revised Systems Requirements Document
• Block diagrams indicating inputs/outputs
• Requests for Information (RFI’s) written and responded
• Iterating technology equipment lists with mass, power and volume estimates
Environment Control and Life Support System (ECLSS)
Current Status
• All technologies selected with optimum mass, power, volume considerations
• Functional diagrams completed:– Atmosphere– Water– Waste– Food
• Human Consumables estimates completed:– Air– Water– Waste– Food
Overview of ECLSS subsystems
FOOD
WATER AIR
WASTE
ECLSS System Overview
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
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
Structures
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/Airlocks:One at each end, on bottom floor
4 Radiators:One on each “corner” of Hab
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, or 1.24-1.49 kg/yr/m3
• Assume similar:– Differential pressure– Materials– Thickness of outer shell
Future Tasks
• Load analysis
• Insulation
• Shielding
• Layout – more detail
• Volume Allocation – more detail
Thermal Control
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• Updated Level 2 Requirements
Thermal I/O Diagram
Thermal Schematic
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 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 • External fluid loop • Heat exchangers • Radiator locations • Fluid storage • COLD - COLD scenario • Sensors/Data/Command structure • FMEA• Report
Command, Control, Communication (C3)
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
CrewCrew
Crew Crew AccommodationsAccommodations
LegendENERGY
Packetized DataTelemetry/DataCommand/Data
VoiceVideo
Electrical powerHeat
Earth
MarsComSatC3 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 DiagramLegendEthernetRF ConnectionMil-Std 1553B BusTBD
CommSystem
Experiments
RF Hubs (3)
C3 System
Other Systems
Command and Control System
Communications System
1 meter diameter high gain (36 dB) antenna
Backup1 meter diameter high gain antenna
Medium gain (10 dB) antenna
Amplifier
First Back-upAmplifier
Second Back-upAmplifier
Control Unit
1st Back-up Control Unit
2nd Back-up Control Unit
Data from CCC Computers
EVA UHF Com
1st Back-up EVA UHF Com
2nd Back-up EVA UHF Com
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 and Crew Accommodations
Current Status
– Completed initial Functional Diagram for Crew Accommodations
– Iterating lists of operations received for each subsystem
• Crew Operations• Automated Operations• Earth Controlled Operations
– Giving input to subsystems• Based on human factors considerations• Incorporating MSIS, Larson and Pranke, experience
– Iterating mass, power, & volume parameters
Crew Accommodations Functional Diagram
Crew Accommodations Equipment
Mass (kg) Vol (m3)Avg. Power
(kW)Galley and Food Sys
Kitchen cleaning supplies 125.00 0.90Dishwasher 40.00 0.56 1.20Cooking/eating supplies 30.00 0.08
Waste Collection SystemWCS supplies 150.00 3.90Contingency fecal and urine collection bags 20.00 0.07
Personal HygieneShower 75.00 1.41 1.00Handwash/mouthwash faucet 8.00 0.01Personal Hygiene kit 10.80 0.03 Hygiene supplies 225.00 4.50
Crew Accommodations Equipment Cont…
Mass (kg) Vol (m3)Avg. Power
(kW)Clothing
Clothing 594.00 2.02Washing Machine 100.00 0.75 1.50Clothes Dryer 60.00 0.75 2.50
Rec equip and Personal StowagePersonal stowage/closet space 300.00 4.50 0.70
HousekeepingVacuum (prime + 2 spares) 13.00 0.07 0.40Disposable Wipes 0.00 0.00Trash compactor/trash lock 150.00 0.30 0.85trash bags 150.00 3.00
Operational Supplies & RestraintsOperational supplies(diskettes, velcro, ziplocks, tape) 120.00 0.24Restraints and Mobility aids 100.00 0.54
Crew Accommodations Equipment Cont…
Mass (kg) Vol (m3)Avg. Power
(kW)Maintenance: All repairs in habitable areas
Hand tools and accessories 300.00 1.00Spare partstest equip (gauges, etc…) 500.00 1.50 1.00Fixtures, large machine tools, gloveboxes, etc… 1,000.00 5.00 1.00
PhotographyEquipment 120.00 0.50 0.40Film 0.00 0.00
Sleep Accomodationssleep restraints 54.00 0.60
Crew Health CareExercise Equipment 145.00 0.19 0.15Medical/Surgical/Dental suite 1,000.00 4.00 1.50Medical/Surgical/Dental consumables 500.00 2.50
Total 5,889.80 38.92 12.20
Mission Operations Activities
Mission Ops/Crew Accommodations:
Publicity events
Mission updates
Activity planning
Food preparation
Food and drink consumption
Socialization during meals
Recreation/Exercise
Clean-up following meals
Crew preparation at start of day
Straighten personal quarters
Break-time
Collect trash and deliver to waste processing sys
General Housekeeping (vacuum, dust, etc.)
Optimization of integrated Hab systems
Personal text and photo downlink
Personal text and photo uplink
Personal video downlink
Personal video uplink
Programmatic text and audio downlink
Programmatic text and audio uplink
Programmatic video downlink
Programmatic video uplink
All Habitat health telemetry downlink
Habitat health overview telemetry downlink
Habitat emergency situation: all associated data downlinked
Crew health data ‘real time’ downlink
Crew exercise medical data ‘real time’ downlink
Medical emergency situation: all related medical data downlinked
Thorough medical check-up data downlink
Science Video downlink
Science Data downlink (text data and photos)
Crew Accommodations equipment telemetry downlink (P,T,V,I..)
Future Tasks
– Continue integration of human factors into subsystems
– Create Data Flow Diagram– Create preliminary crew schedules
• Equipment Maintenance• Housekeeping• Proficiency Training• Scientific Tasks• Programs/Paperwork• Personal Time
– Integration with subsystems regarding resulting schedules
Robotics and Automation
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
Robotics and Automation
• Small Rover– Deploy scientific instruments for analysis
and monitoring of Mars– Determine safe routes for crew travel– Collect and return samples– .64 kW power requirement
• Calculated using data from Pathfinder• Solar arrays needed for power/recharging of batteries
– Mass 440 kg
Robotics and Automation
• Local unpressurized rover– Transport crew up to 100 km– Operate continuously for up to 10 hours– Must transport crew as well as EVA tools– 2.8 kW power requirement
• 14 hours charge time using 2 kW allocated power
– Mass 4000 kg
Robotics and Automation
• Large pressurized rover– Must deploy and inspect infrasturcture
• Power station, antennas, solar arrays, etc.
– Nominal crew of two but must be able to carry four– Support 16 person hours of EVA per day– Will operate 2 mechanical arms from workstation
or telerobotically – Uses separate power source– Ten day max work time– 500 km range– 10 kW power output– Mass 14000 kg
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
Extra-Vehicular Activity Systems (EVAS)
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 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
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
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
Future Tasks
• Airlock• atmosphere sensors, systems data and command
structure TBD• Airlock layout and volumes allocation TBD• Initial mass estimates TBD• Relocation requirements• Define airlock ingress/egress protocols
• Pressurized Rover• Define pressurized rover ingress/egress protocols• Airlock and pressurized rover I/O quantities TBD
• Power Requirements
In-situ Resource Utilization/Mars Environment (ISRU)
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• Extraction of Oxygen, Nitrogen, and Water • Initial functional diagram and system
schematics
ISRU I/O Diagram
ISRU Schematic
ISRU Plant Trade Study
ISRU Plant Type
W/kg of product
Products Advantages Disadvantages
Zirconia Electrolysis
1710 O2 Simple operation Many fragile tubes required
Sabatier Electrolysis
307 CH4
O2 (H2O)
High Isp Requires H2
Cryogenic Storage
Non-ideal mixture ratio
RWGS Methane
307 CH4
O2 (H2O)
Ideal mixture ratio Requires H2
Cryogenic Storage
RWGS Ethylene
120 C2H4
O2 (H2O)
Non-cryogenic
High Isp
Requires ½ x H2
RWGS Methanol
120 CH3OH
O2 (H2O)
Non-cryogenic
Low flame Temp.
Requires 2 x H2
Lower Isp
Future Tasks
• Total mass estimates for interfaces• Pump design and sizing• Thermal control requirements for water
pipes• Interfaces with ECLSS• ISRU plant trade study finalized• Total Mass savings for O2, H2O & N2
production from ISRU Plant• Review using soil for radiation protection• FMEA
Power Allocation and Distribution
Current Status
– Researching hardware• Volume predictions dependant on hardware
– Power circuit configuration– FMEA
Mars Surface Power Profile
•Allotted ~25kW
•Possibility of using power from other equipment
Power Breakdown
Subsystem Power Avail. Power Req.’d
• CCC 8kW
• ECLSS 8kW 9.1kW
• EVA 6kW
• Thermal 1kW
• Mission Ops 0.5kW 6kW
• Mars Env 0.5kW
• Robotics 1kW 3kW
Future Tasks
– Finalize power profile
Questions/Comments?