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?