1. Mars or Bust Management Briefing Subsystem Update 11/19/03

2. 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

3. Environment Control and Life Support System (ECLSS)

4. 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

5. Overview of ECLSS subsystems FOOD WATER AIR WASTE

6. ECLSS System Overview

7. Human Consumables Atmosphere –O 2 consumption: 0.85 kg/man-day [Eckart, 1996] –CO 2 production: 1.0 kg/man-day [Eckart, 1996] –Leakage (14.7psi): 0.11 kgN 2 /day & 0.03 kgO 2 /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

8. 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]

9. Atmosphere System Schematic Specifications Fixed mass 1,965 kg Consumable 4 kg/day Power 3.5 kW crew cabin cabin leakage O2O2 N 2 storage tanks EDC N2N2 FDS To: hygiene water tank T&H control H2OH2O To: vent To: trash compactor SPWE H2H2 TCCA To: vent H 2 & O 2 CO 2 From: H 2 O tank H2OH2O used filters & carbon N 2 O 2, & H 2 O H2OH2O

10. Water System Schematic Specifications Fixed mass 942.71 kg Consumable (technologies) 0.36 kg/day Power 2.01 kW

11. Waste System Schematic Specifications Fixed mass 279 kg Consumable 2.3 kg/day Power 0.22 kW To: waste water tank feces commode urinal compactor From: TCCA food trash microfiltration VCD trash fecal storage solid waste storage compactor urine H2OH2O

12. Food System Schematic Specifications Fixed mass 1,320 kg Consumable 4.5 kg/day Power 3.4 kW To: trash compactor trash potable water microwavewater food preparation food & drink Salad Machine edible plant mass inedible plant mass food waste & packaging food storage waste water H2OH2O H2OH2O

13. Structures

14. Habitat Layout Subsystem Allocated Volume CCC10 ECLSS60 Structures160 EVAS30 Thermal40 Power30 Crew Accom.75 Empty300 Total705 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

15. Leakage ISS Leakage – 1.24 kg/yr/m 3 Lunar Base Concept – 1.83 kg/yr/m 3 MOB Habitat – 530 m 3 Estimated Habitat Leakage – 657-791 kg/yr, or 1.24-1.49 kg/yr/m 3 Assume similar: –Differential pressure –Materials –Thickness of outer shell

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

17. Thermal Control

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 Updated Level 2 Requirements

19. Thermal I/O Diagram

20. Thermal Schematic

21. 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

22. Thermal Components *Power is for two pumps in operation at one time, not six

23. Future Tasks Cold plates and sizing External fluid loop Heat exchangers Radiator locations Fluid storage COLD - COLD scenario Sensors/Data/Command structure FMEA Report

24. Command, Control, Communication (C3)

25. 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

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

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

28. Communications System 1 meter diameter high gain (36 dB) antenna Backup 1 meter diameter high gain antenna Medium gain (10 dB) antenna Amplifier First Back-up Amplifier Second Back-up Amplifier 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

29. 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

30. Mission Operations and Crew Accommodations

31. 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

32. Crew Accommodations Functional Diagram

33. Crew Accommodations Equipment

34. Crew Accommodations Equipment Cont…

36. 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..)

37. 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

38. Robotics and Automation

39. 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

40. 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

41. 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

42. 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

43. 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

44. Extra-Vehicular Activity Systems (EVAS)

45. 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

46. 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

47. EVAS – EVA Suit I-Suit specs: –Soft upper-torso –3.7 lbs/in 2 (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)

48. 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

49. 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

50. 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

51. 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

52. In-situ Resource Utilization/Mars Environment (ISRU)

53. 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

54. ISRU I/O Diagram

55. ISRU Schematic

56. ISRU Plant Trade Study ISRU Plant Type W/kg of product ProductsAdvantagesDisadvantages Zirconia Electrolysis 1710O2O2 Simple operationMany fragile tubes required Sabatier Electrolysis 307CH 4 O 2 (H 2 O) High I sp Requires H 2 Cryogenic Storage Non-ideal mixture ratio RWGS Methane 307CH 4 O 2 (H 2 O) Ideal mixture ratioRequires H 2 Cryogenic Storage RWGS Ethylene 120C 2 H 4 O 2 (H 2 O) Non-cryogenic High I sp Requires ½ x H 2 RWGS Methanol 120CH 3 OH O 2 (H 2 O) Non-cryogenic Low flame Temp. Requires 2 x H 2 Lower I sp

57. 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 O 2, H 2 O & N 2 production from ISRU Plant Review using soil for radiation protection FMEA

58. Power Allocation and Distribution

59. Current Status –Researching hardware Volume predictions dependant on hardware –Power circuit configuration –FMEA

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

61. Power Breakdown Subsystem Power Avail. Power Req.’d CCC8kW ECLSS8kW9.1kW EVA6kW Thermal1kW Mission Ops0.5kW 6kW Mars Env0.5kW Robotics1kW 3kW

62. Future Tasks –Finalize power profile

63. Questions/Comments?