1. ECLSS System Overview
Subsystems of ECLSS (environment control and life support system)
Atmosphere
Water
Waste
Food

2. Overview of ECLSS subsystems
FOOD
WASTE
WATER
AIR

3. Pretreatment Oxone, Sulfuricacid
ECLSS System O
Atmosphere
System
Waste
Food
Water
Atmospheric
Condenser
Urine
Compactor
Solid Waste
Storage
TCCA
Trash
washer
hygiene
Preparation
Plant
Hab
Fecal
SPWE
Vent to Mars Atm. H2
EDC
CO2
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

4. verview

5. Human Consumables Atmosphere Water
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

6. Human Consumables Waste Food Urine: 9.36 kg/day [Eckart, 1996]
Feces: 0.72 kg/day [Eckart, 1996]
Technology & Biomass kg/day [Eckart, 1996]
Food
~ 2,000 kCal per person per day [Miller, 1994]

7. Atmosphere System Schematic
crew cabin
cabin
leakage O2
N2 storage
tanks
EDC N2
FDS
To: hygiene
water tank
T&H
control
H2O
To: vent
To: trash
compactor
SPWE H2
TCCA
H2 & O2
CO2
From: H2O tank
used
filters & carbon
N2 O2, & H2O
Specifications
Fixed mass
1,965 kg
Consumable
4 kg/day
Power
3.5 kW

8. Water System Schematic
Specifications
Fixed mass kg
Consumable (technologies)
0.36 kg/day
Power
2.01 kW

9. Waste System Schematic
To: waste
water tank
feces
commode
urinal
compactor
From: TCCA
food trash
microfiltration
VCD
trash
fecal
storage
solid waste
urine
H2O
Specifications
Fixed mass
279 kg
Consumable
2.3 kg/day
Power
0.22 kW

10. Food System Schematic Specifications Fixed mass 1,320 kg Consumable
4.5 kg/day
Power
3.4 kW
To: trash
compactor
trash
potable
water
microwave
food preparation
food &
drink
Salad
Machine
edible plant mass
inedible
plant mass
food
waste &
packaging
storage
waste
H2O

11. Habitat Layout Allocated Volume Subsystem Hatches:
One at each end, one in the middle, all on bottom floor
Top Floor: personal space and crew accommodations
Subsystem
Allocated Volume
CCC 10
ECLSS 60
Structures
160
EVAS 30
Thermal 40
Power
Crew Accom. 75
Empty
300
Total
705
Bottom Floor: Lab, equipment, and airlocks
Basement: Storage, equipment, supports and wheels

12. Leakage ISS Leakage – 1.24 kg/yr/m3 Lunar Base Concept – 1.83 kg/yr/m3
MOB Habitat – 530 m3
Estimated Habitat Leakage – kg/yr
Assume similar:
Differential pressure
Materials
Thickness of outer shell

13. Future Tasks Load analysis Insulation Shielding Layout – more detail
Volume Allocation – more detail

14. Thermal System

15. 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
25 KW from Power System estimates.
Each subsystem’s electronics must not exceed 40°C (hot to touch - potential failure).
Non toxic fluid for inner loop so humans are not killed.
External fluid must not freeze under Martian extremes.
Cold Plates for heat collection. Radiators for heat rejection. Water is non-toxic.

16. Thermal I/O Diagram

17. Thermal Schematic
Misc. Avionics - Crew Accommodations and ISRU Avionics

18. 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
All systems on, all crew exercising on hottest day (approx 263 K). Radiators operating at 290 K. 15% degradation levels (first guess) and 25% safety factor. Means radiators are probably oversized.

19. Thermal Components
4 radiator panels. Hab can be fully operational using 3 panels. Hab can be mostly operational using 2 panels. Minimal operation with 1 panel. Each panel rejects approximately 10,000 W operating at 290 K.
Note that thermal system uses 2 KW in this case and that only two pumps are in operation at a time. The other 4 pumps provide the 2 levels of required redundancy (2 per fluid loop).
*Power is for two pumps in operation at one time, not six

20. 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

21. C3 Subsystem

22. 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

23. C3 I/O Diagram Earth Robotics & Automation Structure EVAS Mars Com Sat
CCC
Crew Accommodations
Legend
Mars Env’mt
Power
ECLSS
ENERGY
Packetized Data
Telemetry/Data
Command/Data
Voice
Video
Electrical power
Heat
Thermal
Nuclear Reactor
Crew
ISRU
ISRU Plant

24. Command and Control System
Tier 1
Command
Computers (3)
RF Hubs (3)
User
Terminals (6)
Tier 1
Emergency
Computer (1)
Tier 2
Subsystem
Computers (4)
Tier 2
Science
Computers (2)
File
Server (1)
Tier 3
Subsystem
Computers (8)
Caution &
Warning (?)
C3 System
Sensors
Firmwire
Controllers
Experiments
Other Systems
Control System Diagram
V 1.0, 11/8/2003
Legend
Ethernet
RF Connection
Mil-Std 1553B Bus
TBD

25. 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

26. 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

27. Mission Operations Past Derived Requirements Reviewed Literature
From DRM
Reviewed Literature
Larson and Pranke
MSIS

28. Mission Operations Past
Created Functional Diagram (Crew Accommodations)
Diagram goes here

29. Mission Operations Present
Creating lists of operations required for each subsystem
Crew Operations
example
Automated Operations

30. 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

31. Mission Operations Future Plans
Continue integration of human factors into subsystems
Create tentative crew schedules
Equipment Maintenance
Housekeeping
Scientific Tasks
Paperwork
Personal Time

32. 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

33. 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

34. 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

35. 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

36. 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)

37. 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

38. 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

39. 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

40. 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

41. 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

42. 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)

43. 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

44. 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

45. 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

46. ISRU/Mars Environment System

47. ISRU/Mars Environment I/O Diagram

48. ISRU Schematic
Misc. Avionics - Crew Accommodations and ISRU Avionics

49. 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
All systems on, all crew exercising on hottest day (approx 263 K). Radiators operating at 290 K. 15% degradation levels (first guess) and 25% safety factor. Means radiators are probably oversized.

50. ISRU Plant Summary Zirconia Electrolysis Advantages CO + CO2
Zirconia-walled Reactor
1000 °C
CO2
CO + CO2 O2
Heat
Advantages
Simple operation
Produces Oxygen
Requires 1562 W-day/kg of Oxygen
4 radiator panels. Hab can be fully operational using 3 panels. Hab can be mostly operational using 2 panels. Minimal operation with 1 panel. Each panel rejects approximately 10,000 W operating at 290 K.
Note that thermal system uses 2 KW in this case and that only two pumps are in operation at a time. The other 4 pumps provide the 2 levels of required redundancy (2 per fluid loop).

51. Sabatier Electrolysis
ISRU Plant Summary
Sabatier Electrolysis
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
CH4
H2 + CO2
Nickel Catalyst 400 °C
Heat
Electrolysis
H2O O2
4 radiator panels. Hab can be fully operational using 3 panels. Hab can be mostly operational using 2 panels. Minimal operation with 1 panel. Each panel rejects approximately 10,000 W operating at 290 K.
Note that thermal system uses 2 KW in this case and that only two pumps are in operation at a time. The other 4 pumps provide the 2 levels of required redundancy (2 per fluid loop).
Power H2
Requires 166 W-day/kg of propellant

52. ISRU Plant Summary RVGS Methanol Advantages Disadvantages CH4 H2 + CO2
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
CH4
H2 + CO2
Nickel Catalyst 400 °C
Heat
Electrolysis
H2O
4 radiator panels. Hab can be fully operational using 3 panels. Hab can be mostly operational using 2 panels. Minimal operation with 1 panel. Each panel rejects approximately 10,000 W operating at 290 K.
Note that thermal system uses 2 KW in this case and that only two pumps are in operation at a time. The other 4 pumps provide the 2 levels of required redundancy (2 per fluid loop). O2
Power H2
Requires 166 W-day/kg of propellant

53. ISRU Plant Summary RVGS Ethanol Advantages Disadvantages CH4 H2 + CO2
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
CH4
H2 + CO2
Nickel Catalyst 400 °C
Heat
Electrolysis
H2O O2
4 radiator panels. Hab can be fully operational using 3 panels. Hab can be mostly operational using 2 panels. Minimal operation with 1 panel. Each panel rejects approximately 10,000 W operating at 290 K.
Note that thermal system uses 2 KW in this case and that only two pumps are in operation at a time. The other 4 pumps provide the 2 levels of required redundancy (2 per fluid loop).
Power H2
Requires 166 W-day/kg of propellant

54. 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

55. Mars Surface Power Profile
Allotted ~25kW
Possibility of using power from other equipment

56. 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

57. Current/Future Tasks Current Tasks Future Tasks Researching hardware
Volume predictions dependant on hardware
Power circuit configuration
FMEA
Future Tasks
Finalize power profile