Mars or Bust Preliminary Design Review 12/8/03. 2 ASEN 4158/5158 Design of Martian habitat Based on the Design Reference Mission (DRM) from NASA [Hoffman

Mars or Bust Preliminary Design Review

12/8/03

2

ASEN 4158/5158

• Design of Martian habitat• Based on the Design Reference Mission

(DRM) from NASA [Hoffman and Kaplan, 1997; Drake, 1998]

– Overall plan for a human Mars mission– Gives outline but no detail– Top level requirements

• Modified to narrow scope of project

3

DRM Schedule

4

5

Key Assumptions for Design

• Only first Surface Habitat (Hab-1)– Designed for Mars gravity

• Focusing on surface operations– Launch, transit, Mars entry not designed

• Interfaces with external equipment– Rovers, power supply, ISRU unit

• Crew will use Habitat on arrival

6

Overall Project Goal

• Establish a Martian Habitat capable of supporting humans

• Level 1 Requirements– Support crew of 6– Support 600 day stay without re-supply– Maintain health and safety of crew– Minimize dependency on Earth

[DRM]

7

Key Level 1 Requirements

• 80 metric ton launch vehicle– Recommended Total Habitat Mass < 34,000 kg

(includes payload)

• Deploys 2 years before first crew• Standby mode for 10 months between crews• Mission critical: 2-level redundancy• Life critical: 3-level redundancy• Integrate In-Situ Resource Utilization System

8

Organizational Chart

Project Manager

Systems Engineering and Integration

Structures CCC ECLSS EVASRobotics

and Automation

Power Thermal

Mission Operations

ISRUCrewAccom.

9

Systems Engineering and Integration Team

• Primary:– Juniper Jairala– Tim Lloyd– Tyman Stephens

• Support:– Jeff Fehring– Keith Morris– Meridee Silbaugh

10

Systems Engineering and Integration Responsibilities

• Establish habitat system requirements

• Delegate top-level subsystem requirements

• Review and reconcile all subsystem design specifications

• Ensure that all habitat subsystem requirements are met

• Ensure proper subsystem interfaces

11

Key Design Drivers

• Design rationale

• Human factors & automation

• Preliminary subsystem integration

• 10.2 psi habitat

• Light delay

• Minimize mass

12

DRM Mass Recommendations

Subsystem Mass Estimate [kg]

Structure 20,744

Power 3250

ECLSS 4661

Thermal 550

Crew Accommodations 5000

C3 320

EVAS 1629

Total 34,000

14

Mission Operations Team

• Primary:• Christie Sauers

• Support:• Tim Lloyd• Tyman Stephens

15

Mission Ops Responsibilities

• Identify and coordinate crew operations• Create and modify the operations schedule• Support the mission objectives through crew

activities• Establish clear hardware operational

requirements and facilitate changes• Identify and deliver relevant system status data

to onboard crew• Develop procedures for failure scenarios• Respond to unexpected off-nominal conditions

16

Mission Ops Level 2 Requirements

• Operate & maintain surface systems• Support crew operations for entire mission

– Programmatic activities– Planning, long-term and real-time*

• Ease of learning/similar subsystems*• Create and maintain computer/video library• Encourage smart habitat/automation*

– Utilize auto fault detection and correction*

• Minimize dependence on Earth*

* From DRM

17

• Primary design drivers– Consider human

factors from the beginning

• A growing concern in manned mission design

– Communication delay with Earth

• Ensure that all tasks are completed without dependence on Earth control

Mission Ops/ CA Design Rationale

18

Results of MO Integration

• Hab at 10.2 psi– EVA protocol time considerations

• Structural Layout– On side = fewer stairs, open layout, emergency

egress

• C3 data flow driven by Mission Ops• Hardware choices

– Radiators will be chosen to minimize maintenance• Cleaning sand, etc

19

Representative Mission Ops Operations List

20

Representative Subsystem Operations List

Item # Operation Description

Duration Frequency Earth Control

Auto-mated

# of Crew

Safety Concerns

ThermalOPS 6.1 Inspect and clean

radiators2 hr After each

dust storm- ? 2 EVA Required

OPS 6.3 Inspect heaters and cold plates

2 hr 1x/2 weeks - ? 2

OPS 6.4 Inspect external fluid loops/levels

N/A 1/hr X X 0 Toxicity of Fluid, EVA Required

OPS 6.5 Inspect internal fluid loops/levels

N/A 1/hr X X 0 Accessibility

OPS 6.6 Maintenance of thermal system components

1 hr 1x/week X X 1

21

Mission OpsRepresentative Daily Timeline

Science/Hab Maintenance Day

Crewmember 07:00 08:00 09:00 10:00 11:00 12:00 13:00 14:00 15:00 16:00 17:00 18:00 19:00 20:00 21:00 22:00 23:00 24:00 25:00 to 25:40 01:00 02:00 03:00 04:00 05:00 06:00

CREW MC

CREW SIC

CREW MS1

CREW MS2

CREW MS3

CREW MS4

Wak

e-U

p&

Exe

rcis

eW

ake-

Up

& E

xerc

ise

Wak

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p&

Exe

rcis

eP

rep

& c

ln q

trsB

reak

fast

Bre

akfa

st

Bre

akfa

stP

rep

& c

ln q

trsP

rep

& c

ln q

trsE

arth

mis

sion

up

date

& p

lan

SLEEP

SLEEP

SLEEP

Sle

epS

leep

Pre

-Sle

epP

re-S

leep

Pre

-Sle

ep

Rec

reat

ion

Rec

reat

ion

Rec

reat

ion

SCIENCE SCIENCE

Lunc

hSCIENCE/Telerobotic

Rover

SCIENCE SCIENCE

Mis

sion

upd

ate

to E

arth

Lunc

h

Din

ner P

rep

Din

ner &

cl

ean-

upD

inne

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Hab

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aint

enan

ceH

ab

Mai

nten

ance

Hab

M

aint

enan

ce

Con

tinge

ncy

Ops

Con

tinge

ncy

Ops

Con

tinge

ncy

Ops

Con

tinge

ncy

Ops

Con

tinge

ncy

Ops

SCIENCE/Telerobotic

Rover

22

MO Verification of Requirements

Requirement Description DesignOperate & maintain surface systems Crew Ops list and schedulesSupport crew operations for full mission Crew Ops list and schedulesProgrammatic activities Crew Ops list and schedulesComputer/video library DVD players, etc in Crew Accom.Smart habitat/automation Ops list ID's potential automationPlanning, long-term and real-time Schedule includes contingency Minimize dependence on Earth Thorough Ops list, planningAuto fault detection and correction C3 subsystem + FMEAEase of learning/similar subsystems Future task

23

Future Considerations

• Alternate Implementations– Increase Automation

• Develop Documentation– Proficiency Training Tools– Operational Procedures– System Manuals/Tutorials – Troubleshooting Library– Malfunction Procedures– Flight Data File Templates

• Training– Crew– Earth support team

• Continue Iterations

24

Lessons Learned

• Operations List is key– Drives scheduling, mission and hardware designs

25

Mars Environment and In-Situ Resource Utilization (ISRU) Team

Primary

• Heather Chluda

Support

• Keagan Rowley

• Keric Hill

26

Mars Environment Summary

• Responsible for collecting data on the Mars Environment

• Provides a consistent data set on the Mars Environment for the Habitat design group to use.

• Thermal, Radiation, Pressure, Atmosphere, Wind, etc.

27

Characteristics of the Mars Surface Environment

• Low gravity ~1/3 of Earth’s• Low atmospheric pressure ~1% of

Earth’s• Cold and dry • Windy• Lots of Fine Dust• More Radiation• Less sunlight• Day length about the same as Earth

28

Temperature

• Daily variation at Viking Lander sites: ~60°C • Seasonal variation for low temperature: -107 to -18°C

[http://www-k12.atmos.washington.edu/k12/resources/mars_data-information/temperature_overview.html]

29

Radiation

• Skin dose on Mars surface would be about 30 rem/yr during high solar activity– about 5 rem/year from Solar Proton Events– about 25 rem/year from Galactic Cosmic rays

• In Colorado, we get about 0.36 rem/yr• The limit for skin dose established for

astronauts in Low Earth Orbit is 300 rem/yr.

30

Martian Atmospheric Constituents

0.24

1.6

2.795.32

Carbon Dioxide

Nitrogen

Argon

Oxygen

Carbon Monoxide

Water Vapor

Neon

Krypton

Xenon

Ozone

[Larson and Pranke, 2000]

31


• More detailed temperature and radiation data for specific landing site

• Determination of topography of landing site and exploration area

• More detailed information from upcoming Mars missions

32

In-Situ Resource Utilization Subsystem Summary

• Demonstrate the use of all possible Martian resources for future missions

• Responsible for interface between habitat and ISRU plant

• ISRU will provide additional oxygen, nitrogen, and water for habitat use

• Non-critical system (i.e. No backups)– Demonstration of the ISRU plant

consumable production will be a key driver for future missions

33

ISRU Level 2 Requirements

• Provide additional oxygen, nitrogen, and water for the Habitat (from byproducts of propellant production)

• All Interfaces for the ISRU shall tolerate leaks within limits

• Propellant production shall be automated• Acceptable temperatures shall be maintained in all

interfaces (pipes, valves, and connections)• Storage interfaces must be compatible with Habitat• Pumping systems shall have adequate power to

transport oxygen, nitrogen and water to the Habitat• Piping must have adequate protection for Mars

Environment• Interfaces to Habitat storage tanks and ISRU tanks

can be performed using robots or humans

34

35

ISRU Subsystem Schematic

36

ISRU Requirement Verification

Requirement Description Design

Provide additional oxygen, nitrogen, and water from byproducts of propellant production

Extract N2 and O2 from the Martian atmosphere, provided by In-Situ Resource Propellant Production

All interfaces for the ISRU shall tolerate leaks within limits

Estimated .1 kg/day N2 and .03 kg/day O2 leakage, will purge pipes when not transfering to Habitat

Propellant production shall be automatedCommands and telemetry sent to ISPP plant when extra consumables are needed

Acceptable temperatures shall be maintained in all interfaces

Heaters will be supplied to the water pipe line to ensure no freezing

Interfaces must be compatible with Habitat Proper female/male connections on the pipes Pumping systems shall have adequate power to transport oxygen, nitrogen and water to Habitat

500 Watts provided to the ISRU subsystem is adequate for the low mass flowrate pumping needs

All external pipes must have adequate protection from Mars Environment Insulation coating or bury method for pipes as a future task

Interfaces to Habitat storage tanks and ISRU tanks can be connected by robots or humans Robot capability, EVA required by crew

37

ISRU Plant Trade Study

ISRU Plant Type

W/kg of product

Products Advantages Disadvantages

Zirconia Electrolysis

1710 O2Simple 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

DRM uses Sabatier Electrolysis and RWGS Methane processes

Future design iterations should consider using other propellant production methods

38


• Use Martian soil as building material for Radiation shielding – Safe haven soil shelter designs

• Consider more efficient ISRU plant methods for propellant and consumable production

• Mass benefits of using ISRU plant for consumables on future missions

39

Structures Subsystem Team

• Primary:– Jeff Fehring– Eric Schleicher

• Support:– Jen Uchida– Sam Baker

40

Structures Responsibilities

• Overall layout

• Volume allocation

• Pressurized volume

• Physically support all subsystems

• Radiation shielding

• Micro-meteoroid shielding

• Withstand all loading environments

41

Structures Level 2 Requirements

• Fit within the dynamic envelope of the launch vehicle– Launch Shroud Diameter = 7.5 m– Length = 16.3 m

• Structurally sound in all load environments – Acceleration– Vibration– Pressure

• Easily repairable• Stably support all other systems• Interface with other systems• Structures Mass < 20744 kg

42

43

Structures Overview

Pressure Shell

RadiatorRadiator

Radiator

Radiator

Airlock

Airlock

Airlock

• Horizontal Orientation– Emergency exit– Stability– Expansion

• Challenges– Landing/Setup– Center of Mass– Using volume

efficiently

Internal truss structure

Chassis, Wheels, Supports

(not shown)

44

Overall Layout

Airlock

Airlock

SafeHaven

Sto

rage

Sto

rage

Sto

rage

Sto

rage

Med.Suite

LabLab

Lab

Stairs

Airlock

Kitchen/Crew Accom.

Sto

rage

Sto

rage

Sto

rage

Hygiene

Top Floor Bottom FloorPersonal Space

– Bed– Storage– Desk

Safe Haven– C3

Airlock Space– Lab– Exercise– Recreation

Volume = 615 m3

Empty = 215 m3

45

Volume Comparison

• Habitat Volume = 615 m3– Usable = 215 m3

• Integrity Volume = • Aurora Volume = • ISS Volume =• Explore Mars Now• Mars Desert Research

Station• Flashline Mars Arctic

Research Station = • Submarine• Biosphere• Shuttle

MOB

46

Structure Sizing Rationale

• Aluminum– High strength-weight ratio– Ease of Manufacturing

• Hollow Cylinder– Mass efficient – Column– Truss members

• Assume– Atlas V launch loads (5 g’s)– Mars Gravity = 3.758 m/s2

P

t

r

L

P*rσy

t =

[http://www.ilslaunch.com/missionplanner/pdf/avmpg_r8.pdf][Larson and Pranke, 2000]

47

Requirements Verification

Requirement Description DesignDynamic Envelope 0.25 m buffer Shroud Diameter = 7.5 m Habitat Diameter = 7 m Length = 16.3 m Length = 16 mLoad Environments 1.4 factor of safety Pressure Pressure Shell Acceleration Internal trusses Vibration Chassis

Leg SupportsEasily repairable AccessibilitySubsystem Component Support Airlock, radiator, and ECLSS tanksStructures Mass < 20744 kg Predicted mass = 21000 kg

48


• Design for launch loads from Magnum vehicle

• Balance Habitat for launch

• Optimize truss structure

• Fully design supports for all components

• Define setup procedure/mechanism

49

Power Distribution and Allocation Subsystem Team

• Primary:– Tom White– Jen Uchida

• Support:– Nancy Kungsakawin– Eric Dekruif

50

Power Responsibilities

• Interface with the nuclear power source and other external equipment

• Safely manage and distribute power throughout Martian habitat

51

Level 2 Requirements

• Supply and transfer power to the habitat from the nuclear reactor (DRM)

• Supply power with 3-level redundancy (Derived)

• Distribute power on a multi-bus system (Derived)

• Provide an emergency power cutoff (Derived)• Mass must not exceed 3249 kg (including in-

transit power) (DRM)

52

53

Mission Mode Time in Mode Total (W )Landing 6918

Set-up 11443Survival (battery) 6133

Survival (Nonbattery) 12 hours 6133Day:

Active 24947Non-active 9134

Survival (battery)Time dependent process=> energy balance required 10417

Survival (Nonbattery) 12 hours 12427Night:

Active 26947Non-active 11134

Survival (battery)Time dependent process=> energy balance required 10417

Survival (Nonbattery) 12 hours 12427

Power Consumed by Habitat During Specific Mode

Non-crew

Crew

Time dependent process => energy balance required

Overview of System - Power Profile

54

System Schematic

Reactor

ChargeControl

Storage

ConditioningRegulation

Distribution

ECLSS ThermalEVAS

Robotics

StructuresMission

OpsCCC

Life/Mission Critical Sys.

Reactor

Bus 3

Bus 2

Bus 1

55


Requirement Description Design3-level redundancy Back up reactor, solar panels, batteriesTransfer power from reactor to habitat CablingDistribute power on a multi-bus system Multi-bus systemInterface with transit vehicle power sources ConnectorsRegulate voltage to a usable level Voltage regulatorInclude a fault protection system Circuit breakersProvide an emergency power cutoff Emergency power cutoffMass must not exceed 3249 kg (including in-transit power) Mass = 2046.77 kg

56


• More detailed power profile

• Specified hardware

• Decrease system mass

• Electromagnetic interference

57

Environmental Control and Life Support (ECLSS) Team

• Primary– Teresa Ellis – Nancy Kungsakawin– Meridee Silbaugh

• Support– Bronson Duenas– Juniper Jairala– Christie Sauers

58

ECLSS Responsibilities

• Provide a physiologically acceptable environment for humans to survive and maintain health

• Provide and manage the following:• Environmental conditions• Food• Water• Waste

59

ECLSS Level 2 Requirements

• Provide adequate atmosphere (derived)• Gas storage (derived)• Provide Trace Contaminant Control (derived)• Provide Temperature and Humidity Control

(derived)• Fire Detection and Suppression (derived)• Provide potable water (derived)• Provide hygiene water (derived)• Provide food (derived)• Collect and store wastes (derived)• Targeted mass of 4661 kg for the technologies

(not including consumable) (DRM)

60

61

Human Inputs and Outputs

O2 0.636 – 1 kg/p/d

Potable H2O 2.27 – 3.63 kg/p/d

Food (dry ashes based)0.5 – 0.863 kg/p/d(2200 kCal/p/d)

Hygiene H2O1.36 – 9 kg/p/d

N2

Heat 0.1 kW/p/d

CO2 0.726 – 1.226 kg/p/d

Respired & Perspired H2O 2.28 kg/p/d

Sweat Solids 0.02 kg/p/d

Urine (solid & liquid) 1.27 – 2.27 kg/p/d

Feces (solids & liquids) 0.12 kg/p/d

Atmosphere SystemWater SystemWaste SystemFood System

* All information is from Spaceflight Life Support and Biospherics, Eckart (1994)

62

Atmospheric System Design

crew cabin

cabinleakage

N2 & O2

O2

N2 storagetanks

EDC

N2

FDS

To: hygiene water tank

T&Hcontrol

H2 O

To: vent CO2

To: trash compactor

SPWE TCCA

To: ISRU H2

H2 & O

2

From: H2O tank

SPWE = Solid Polymer Water ElectrolysisEDC = Electrochemical depolarized concentrator

63

Water System Design

VCD = Vapor Compression DistillationAES = Air Evaporation SystemMCV = Microbial Check ValvesRO = Reverse Osmosis

64

Food System Design

To: trash compactor

Waste

potablewater

microwave water

Kitchen (Crew Accommodation)

food & drink

foodwaste &

packaging

foodstorage

H2O

refrigerator

Food

Note: Refrigerator in Crew Accommodation is not for food storage

65

Waste System Design

To: waste water tank

feces

CommodeUrinal

compactor

From: TCCA food trash microfiltration VCD

trash

fecalstorage

solid wastestorage

compactor

urine

H2O

66

Representative of Operation

Fecal matter Storage outside

the habitat ( for future usage)

Crew member dumps

non-fecal trashAir Lock

Commode withbuilt-in Fecal Compactor

Feces inUV-degradable bags

Feces in Storage bags

EVA dump

UV

Compactor Compacted Trash

Trash in Storagebags

Crew member is taking out the trash

Non-Fecal matter Storage Structure outside the

habitat

67

ECLSS Integrated Design

Atmosphere System

WasteSystem

FoodSystem

WaterSystem

AtmosphericCondenser

Urine

CompactorSolid Waste

Storage

TCCA

FoodTrash

Crew Accommodations (shower, washer, etc.)

& EVA (EMU cooling)

FoodPreparation

FecalSPWE

Vent to

Mars Atm.

H2

EDC

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

68


Requirement Description DesignProvide adequate atmosphere YES, with SPWE & EDCGas Storage N2 tank, O2 tankProvide Trace Contaminant Control. TCCAProvide Temperature and Humidity Control. Thermal Heat ExchangerFire Detection and Suppression. FDS N2 extinguisherProvide potable water YESProvide food YES, based on 2200 kCal/p/dCollect wastes YES, with waste compactorsProvide hygiene water. YES

Target Mass of 4661 kg.NO, exceed the mass by approximately 200 kg

69


• More detailed calculations of consumables• Consider other technologies that currently have low

TRL which will lead to more trade study (ex. Waste Management)

• More research on information about the technologies (M,P,V, FMEA (affect the mass), safety etc.)

• Optimize the integrated design to minimize power, mass, volume

• Consider other psychological effects which will factor into the design of the ECLSS subsystem (type of food, location of each subsystem and waste processing procedure etc.)

70

Thermal Control Subsystem Team

• Primary– Keagan Rowley– Sam Baker

• Support– Heather Chluda– Heather Howard

71

Thermal System Requirements

• Maintain a heat balance with all subsystems over all Martian temperature extremes (derived)

• Keep equipment within operating limits (derived)• Must be autonomous (DRM)• Accommodate transit to Mars (derived)• Auto-deploy and activate if it is inactive during transit (derived)• Report status for communication to Earth at all times (for safety

concerns) (derived)• Mass shall not exceed 5000 kg (Derived)• Thermal Protections System shall be provided by the

launch shroud system (Derived)

72

Thermal I/O Diagram

73

Design Drivers and Scenarios

• Heat Load Balance• Heat Rejection

Capacity• Peak Power• Mars Environment• Transit to Mars

• Hot - Hot– Occurs on hottest day– Peak power usage– No structure heat losses– Crew highest metabolic

output

• Cold - Cold– Occurs on coldest day– Minimal power usage– Maximum structure heat

losses– No crew

74

Thermal Schematic

75

Thermal Heat Balance

Equations

Est. Heat Load = Power Load + Human Load + Structures Load

Heat Load = 1.15*Est. Heat load (degradation)

Total Heat Load = 1.1*Heat Load (safety factor)

Total Heat Load = 39 KW

HOT COLDHeat Load (KW)

Heat Load (KW)

ECLSS 9.6 3.53ECLSS Air/HE 10.85 0CCC 1.9 1.3EVAS 0 0Robotics & Auto 2 0Mission Ops 0 0Crew Accomodation 4.4 0Thermal 2 1.5Structures TBD TBDTOTAL 30.75 6.33

76

Area of Radiators

Q = 39000 W

= 5.67e-8 W/(m2K4)

= 0.9, = 0.85

Tr = 290 K, Te = 263 K

A = 391.9 m2

AQ

(Tr4 Te

4 )Human Spaceflight pp 519 - 524 http://www.swales.com/contract/iss.html

77

Mass and Vol. of Radiators

Mass: 8.5 kg/m2 for two sided deployableVolume: 0.06 m3/m2 for two sided deployable

QuickTime™ and aTIFF (Uncompressed) decompressor

are needed to see this picture.

Require deployable radiators due to transit stowage and need for autonomous set up on Mars surface

Mass = 8.5 * Area = 8.5 * 391.9Mass = 3330.9 kg

Volume = 0.06*Area = 0.06*364.2Volume = 23.51 m3

Human Spaceflight pp 519 - 524http://www.space.com/missionlaunches/sts112_update_021014.html

Example of a Deployable Radiator Panel

78

Thermal System Sizing

Hot Hot Cold Cold

Mass (kg)

Volume (m^3) Power (W) Power (W)

Radiators 3330.9 23.5 0.0 0.0Heat Exchangers 80.2 0.2 0.0 0.0Pumps 1120.3 2.5 1789.3 1241.4Cold Plates 444.5 1.0 0.0 0.0Instruments 248.8Plumbing and Valves 746.4Fluids 248.8 0.0 0.0Totals 6219.8 27.2 1789.3 1241.4

79

Requirements Verifications

Requirement Description DesignMust maintain a heat balance with all subsystems over all Martian temperature extremes.

System sized for max heat load plus degradation and safety factor

Keep equipment within operating limits Cold plates collect heat for transfer to radiators via fluid loops

Must be autonomous. Radiators automatically deploy, pumps turned on by C3, operation monitored by C3

Accommodate transit to Mars. Radiators stowed for trip, launch vehicle provides thermal cooling

Auto-deploy and activate if it is inactive during transit

Deployable radiator design used

Report status for communication to Earth at all times (for safety concerns).

Temperature, flow rate, video, and power sensors interface with C3 for status monitoring and transmission to Earth.

Mass shall not exceed 5000 kg. Mass of 6220 kg. Not met. Recommend re-evaluation of requirement

Thermal Protections System shall be provided by the launch shroud system.

80


• Heat rejection method

• Radiator Dust Accumulation– Study accumulation on radiations and

effects on performance

• Radiator Mass– Reduce mass

• Structures Thermal Analysis

81

Crew Accommodations Team

• Primary:• Christie Sauers

• Support:• Tim Lloyd• Tyman Stephens

82

Crew Accommodations Requirements

• Crew hygiene

• Hab cleanliness

• Psychological support

• Crew physical health– exercise & monitoring– medical services

• Efficient,comfortablecrew operations

http://www.robots.org/images/CyberArts/hablower1.jpg

history.nasa.gov/ SP-4213/ch4.htm

gospelcom.net/rbc/ ds/cb922/point8.html

liftoff.msfc.nasa.gov/academy/ astronauts/exercise.html

http://msis.jsc.nasa.gov/sections/section03.asp*HSMAD

John Frassanito & Associates

83

84

Crew Accommodations Equipment

• Galley Maintenance and Food Supplies

• Waste Collection System Supplies

• Personal Hygiene– Shower, Faucet, Personal Hygiene kits

• Clothing, Washer, & Dryer

• Recreational Equipment and Personal Stowage

• Housekeeping

• Operational Supplies & Restraints

• Maintenance: Tools for all repairs in habitable areas

• Photography (All Digital)

• Sleep Accommodations

• Crew Health Care– Exercise Equipment– Medical/Surgical/Dental suite & Consumables *HSMAD

85

CrewAccommodations

Active Equipment

Dishwasher

Shower

Faucet

Washer Dryer VacuumCleaners

ExerciseEquip.

PhotographyEquip.

Kitchen Sink

Heater

Heater

Heater

Heater

Heater

DVDPlayers

ClosetLighting

Test equip & tools

COMM,CNTRL,

&CMND

power commanddata telemetry

T, P

T, P

T, P

A, D

A, D

LEGEND: liq waste pot H20 non-pot H20P=press A=analogT=Temp D=discrete

* note: all components have manual control capability

A

A

T, P

A, DPOWER

H20(pot)

H20(non-pot)

ECLSS (LIQ. WASTE)

MedicalEquip.

Dishwasher

Shower

Faucet

Washer Dryer VacuumCleaners

ExerciseEquip.

PhotographyEquip.

Kitchen Sink

Heater

Heater

Heater

Heater

Heater

DVDPlayers

ClosetLighting

Test equip & tools

COMM,CNTRL,

&CMND

power commanddata telemetry

T, P

T, P

T, P

A, D

A, D

LEGEND: liq waste pot H20 non-pot H20P=press A=analogT=Temp D=discrete

* note: all components have manual control capability

A

A

T, P

A, DPOWER

H20(pot)

H20(non-pot)

ECLSS (LIQ. WASTE)

MedicalEquip.

86

CA Trade Study

• Clothes/Linens Options:– Bring All– Hand wash– Washing Machine

• Trade-offs:

• Decision: Washing Machine

* HSMAD

* http://www.shoalwater.nsw.gov.au/1yourwater/audit.html

* theguardians.com/space/orbitalmech/stationoutput.html* HSMAD

* http://www.shoalwater.nsw.gov.au/1yourwater/audit.html

Bring All Hand Wash Washing Machine

Total Mass: 2250 to 5400 kg Total Mass: 1554 kg Total Mass: 1604 kg

Washing Ops: 0 hrs/month Washing Ops: 12 hrs/month Washing Ops: 1 hr/month

87


*HSMAD

Brief Description of Requirement Verified

Scheduling to support Crew physically and psychologically yes - Mission OpsCrew Clothing: Supply & Refresh yes - washer & dryer

Cleansing of Crewmember Body: Body Cleansing Nails, Teeth, Hair, etc…

yes - shower, faucetyes - hygiene kit

Housekeeping yes - vacuum, wipes, trash bags

Exercise equipment to maintain physical health yes - exact hardware to be selected/designedMedical Support: Routine medical exams Diagnostic and surgical equipment Training, procedures, and troubleshooting

yes - Mission Opsyes - exact hardware to be selectedyes - Mission Ops

Provide equipment for recreation some - DVD player, laptop, cameras

Personal space for sleep & stowage: Provisions for sleep and stowage Control environment through light, temp, sound, odor

yes - beds, restraints, storage, deskssome - needs better definition

Workstation designs: Comfortable and consider human reach profiles no - haven't reached that level of design

Adequate lighting for crew members some - mass estimate not included

Mass Requirement - less than 5,000 kg no - 5,988 kg

Power Requirement yes - 11.75 kW

Volume Requirement - less than 50 m3 (not including personal qtrs) yes - 49.6 m3

88


• Equipment Design and Operation in Mars Gravity– Washing Machine– Clothes Dryer– Shower– Dishwasher

• Further incorporation of human factors into subsystem designs

• Incorporate CA FMEA into Hab Design– Improve Redundancy– Modify Hardware Designs

89

Command, Communications, and Control (C3) Subsystem Team

• Primary:– Heather Howard– Keric Hill

• Support:– Tom White

90

C3 Responsibilities

• C3 supports and manages data flows required to:– Monitor and control the habitat – Monitor and maintain crew health and safety– Achieve mission objectives

• Design based on:– Qualitative data flows – Level 2 requirements derived from the DRM– Flight-ready technology

91

C3 Level 2 Requirements

• Allow checkout of habitat prior to crew arrival. (Derived)

• Include a computer-based library. (DRM) • Support a "smart" automated habitat. (Derived)• Include audio/visual caution and warning alarms.

(Derived)• Facilitate Earth-based control and monitoring of the

habitat’s subsystems. (Derived)• Provide communication with crewmembers working

outside the habitat and rovers. (Derived)• Mass must not exceed 320 kg. (DRM)

92

93

C3 Design Overview

• Command and control subsystem• Based on ISS C3 subsystem• Habitat interface: 3 tiered architecture connected by

Mil-Std-1553B data bus• User interface: personal workstations, file server,

caution and warning subsystem

• External communications subsystem• Based on ISS, shuttle and Mars probes• High gain communications via Mars orbiting satellite• Local area UHF communications

94

Tier 2 Science

Computers (2)

Tier 2 Subsystem

Computers (4)

Tier 1 Command

Computers (3)

Tier 3Subsystem

Computers (8)

FirmwareControllers

Sensors

Caution &Warning (4)

UserTerminals (6)

FileServer (1)

Tier 1 Emergency

Computer (1)

LegendEthernetRF ConnectionMil-Std 1553B BusTBD

CommSystem

Experiments

RF Hubs (3)

C3 System

Other Systems

Command and Control Architecture

95

Communications Architecture

1 meter diameter high gain (36 dB) antenna

Backup1 meter diameter high gain antenna

Medium gain (10 dB) antenna

Amplifier

1st Backup

2nd Backup

Control Unit

1st Backup

2nd Backup

Data from CCC

2nd Backup

1st Backup

EVA UHF

96

Communication Data Rates

Telemetry downlinkedPower

(W)Data rate

(kbps)Required Availability

High gain to Mars Sat 20 10000 0.1%

High gain direct to Earth 124 50 23%

Medium gain to Mars Sat 70 500 2.3%

Telemetry generated Number of SensorsTime averaged data

rate (kbps)

ECLSS 238 0.079

Power 200 0.067

Thermal 105 0.35

Structures 60 0.002

ISRU 96 0.005

Mission Ops 69 11.07

Totals 768 11.6

97


Requirement Description Design

Checkout habitat prior to crew arrival

Monitors and transmits habitat information at all times

Include computer-based library Included on file server

Support automated habitat Telemetry/command interface with all subsystems

Audio/visual caution and warning alarms

Includes caution and warning capabilities

Earth-based control and monitoring

High gain comm. interface with control subsystem

Communication with rovers and EVA crew

High gain and UHF communication capabilities

Maximum mass 320 kg Estimated mass 500 kg

98


• Better definition of quantitative data flows– Adjust C3 subsystem sizing

• Consider technological advances– Decrease mass

• Wireless technologies• Less massive components

– May alter subsystem architecture

• Evaluate Earth-based communications architecture– Support human activities outside Earth’s vicinity

• Communication delays• Throughput requirements

– DSN currently over-subscribed (http://deepspace.jpl.nasa.gov/dsn/faq-dsnops.html)

99

Extravehicular Activity Systems (EVAS) and Interfaces Team

• Primary – Dax Matthews– Bronson Duenas

• Support – Teresa Ellis

100

Extravehicular Activity Systems and Interfaces Responsibilities

• Responsible for providing the ability for individual crew members to move around and conduct useful tasks outside the habitat

• EVAS tasks– Construction and maintenance of the habitat

– Scientific investigation

• EVAS systems – EVA suit– Airlock– Pressurized Rover

101

102

EVAS – EVA Suit

• Requirements driven by habitat operations• Minimal mass• Minimal storage volume• Maximize mobility and dexterity• Maintain 4.3 lbs/in2 internal pressure • Regenerable non-venting heat sink • Durable, reliable, and easy to maintain

• Interfaces with habitat– Water - from/to ECLSS

• Potable – ‘ankle pack’ - 0.53 to 1.16 kg per person per EVA• Non-potable – PLSS - 5.5 kg per person per EVA

– Oxygen – from/to ECLSS• PLSS – 0.63 kg person per EVA

– Waste water – from/to ECLSS• Urine – 0.5 kg per day per astronaut

– Power – from power• PLSS – 26 Ahr @ 16.8 V dc

– Data – to C3• Consumables level

103

EVAS – Umbilical System

Rover

• Connections from the habitat to the airlock will be identical systems (including male/female connections)

• Rovers will have specific hatch and umbilical system

Habitat

Airlock

O2 and N2

Power

Cooling H2O

Food

Waste Garment

Urine

Potable H2O

Air

O2 and N2

Cooling/Potable H2O

Power

Food

Solid Waste

LiOH

Dust Filters

Waste Water

Air

Dust Filters

Data

LiOH

Data

104

EVAS – Pressurized Rover

• Requirements driven by habitat operations – 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 crew hours of EVA

– 20 day maximum excursion duration

– Facilities for recharging PLSS and minor repairs to EVA suit

Courtesy of Larson, WJ. Human Space Flight

105

EVAS – Pressurized Rover

• Rover interfaces driven by habitat operations (all numbers are for an extended excursion of 20 days)– Oxygen

• From ECLSS – 136.7 kg

– Nitrogen• From ECLSS – 28.5 kg

– Water• From ECLSS – Potable – 220 kg• From ECLSS - Non-potable – TBD• To ECLSS – Waste water - TBD

– Data• From/To C3 – Consumables level, telemetry, audio, video, systems status

– Physical• From ECLSS Food – 202.4 kg• LiOH - TBD• Dust filters - TBD• EVAS Equipment - NA• Waste garment ~ 40

106

EVAS/LPR Exploration Mission Schedule and Protocol

LPR Protocol• Charge Fuel Cells• Check Vehicle• Load Vehicle• Plan Excursion• Drive Vehicle• Navigate• Don Suits (X 20)• Pre-breathe (X 20)• Egress (X 20)• Unload Equip• Set up Drill (X 10)• Operate Drill• Collect Samples• In Situ Analysis• Take Photos• Communicate• Disassemble Equip• Load Vehicle• Ingress (X 20)• Clean Suit (X 20)• Stow Suit, Equip• Inspect Vehicle• Secure for night• (Sleep, eat, cleanup hygiene,

etc.)

•Local Excursions•Analysis •Week Off

X1

•Distant Excursion•Analysis•Week Off

•Sys Shutdown•Departure Preparation

X1

X7

STOP EVA’s

EVA Protocol

107

EVAS - Airlock

• Independent element capable of being relocated

• Three airlocks– Two operational– One emergency/back up

• Sized for three crew members – Two operational EVA suits– One emergency/back up

EVA suit

• Airlock will be a solid shell

108

EVAS - Airlock

• Total Volume: 35 m^3 (4L x 3.5W x 2.5H)

• Interface with habitat through both an umbilical system and hatch

• Facilities for EVA suit maintenance and consumables servicing

• Sufficient storage space (EVAS and scientific equipment)

• Small scientific work station

• 4-stage turbo pump (ISS)

Courtesy of Eric Schliecher

109

EVAS – Airlock

• Airlock interfaces driven by habitat operations (all numbers are for a single egress/ingress cycle)– Oxygen (initial cycle)

• From ECLSS (initial cycle) – 9.6 kg• From ECLSS (after initial cycle) – 0.96 kg

– Nitrogen (initial cycle)• From ECLSS (initial cycle) – 9.8 kg• From ECLSS (after initial cycle) – 0.98 kg

– Air (after initial cycle)• To/From ECLSS – 17.5 kg (10% loss)

– Data• From/To C3 –Audio, systems status, pump functions, hatch status, total pressure,. Partial

pressure of 02

– Power• From power – 5 kW

– Physical• LiOH - NA• Dust filters - NA• EVAS Equipment • Waste garment ~ 40

110

Airlock - Operational protocols

Airlock egress/ingress timeline

**Prebreath time of 40 minutes starts during prep for donning

[Larson and Pranke, 2000]

111


• Design suit for Martian environment

• Design rover for Martian environment

• Find appropriate technologies to fit requirements Courtesy of aerospacescholers.jsc.nasa.gov

112

Automation and Robotic Interfaces Subsystem Team

• Primary – Eric DeKruif

• Support – Eric Schliecher– Dax Matthews

113

Automation and Robotic Interfaces Level 2 Requirements

• Provide for local transportation• Deploy scientific instruments• Deploy and operate various mechanisms on

habitat• Automate time consuming and monotonous

activities

114

115

Robotics and Automation

• Number/Functions of rovers– Three classes of rovers, each have power

requirements driven by their range and the systems they must support

• Minimum of two small rovers for scientific exploration• One medium rover for local transportation• Two large pressurized rovers for long exploration and

infrastructure inspection

• Automation of structural components, maintenance, and site preparation

116

Small Scientific Rover

• Scientific rover will be fully autonomous and self recharging

• Interfaces with habitat– Data

• Telemetry• Video• Data from other scientific instruments

• Requirements driven by habitat operations– Deploy scientific instruments – Determine safe routes for crew travel– Collect and return samples– Communications relay in contingency situations – Can be telerobotically controlled from shirt sleeve

environment or preprogrammed

117

Local Unpressurized Rover

• Interfaces with habitat– Power

• 12.5 hour charge time – 2kW allocated power

– Data• Telemetry

• Audio

• Requirements driven by habitat operations– Local transport (~100 km)– Max operation time - 10 hours– Transport EVA tools

118

Large Pressurized Rover (LPR)

• Functional aspects of the LPR are covered here – EVA aspects will be covered by EVAS

• Interfaces with habitat– Data

• Telemetry• Video• Audio • Physical

• Requirements driven by habitat– Site preparation– Deploy, move, and reorient infrastructure– Inspect infrastructure– Operate 2 mechanical arms from telerobotic workstation or

preprogrammed with earth observers– Connection to power plant and ISRU (to each other and habitat)– Inspection of ISRU and power plant

119

Automated Items

• Automated doors in case of depressurization• Deployment of communications hardware• External monitoring equipment• Deployment of radiator panels• Leveling of habitat• Compaction of waste• Deploy airlock• Assumptions – small automated processes such as

gas regulation will be taken care of by their subsystem

120

Automation Solutions

• Habitat leveling system– 12 linear actuators

• two on each leg for redundancy six will work to level habitat• 720 mm of travel – needs to lift habitat 1 meter off ground• Mass – 60 kg each• Power - 35 watts each

• Deployment of Radiator panels– 8 linear actuators

• two per panel for redundancy• Mass – 9 kg each• Power – 5 watts each

• Reference COTS technology

[www.intelligentactuator.com]

121


Medium rover must be recharged Charged via external male/female cable

Medium rover charge discharge cycle must be less than one day

Using 2 kW rover can be recharged in 12.5 hours and run down in 10 hours

Large rover must directly mate with habitat

Habitat hatch mates directly to large rover

Rovers must deploy and inspect habitat Large rover will reorient and inspect habitat using arms

Rovers must be capable of moving habitat

Large rover will have towing capabilities

Rovers must provide for local transportation

Medium unpressurized rechargeable rover can travel up to 100 km over 10 hrs

Rovers must deploy scientific instruments

Small rovers will be capable of deploying instruments

Must deploy and operate various mechanisms on habitat

Motors and actuators will allow for deployment/movement

Time consuming and monotonous activities need to be automated

Mechanical devices, such as motors and valves, will be implemented for these activities

122


• More complete design specifications of rovers will allow for more complete interface designs. (i.e. large rover)

• Better definition of what data is being transferred and the quantity of data

• Specifications and definitions on automated tasks will allow hardware selection

123

Habitat Design Summary

• Mass 61,801 kg - Exceeds DRM recommendation by 27,801 kg- Exceeds max allowable by 11,801 kg

• Overall Volume 615 m3

- Meets DRM max allowable

• Subsystem Volume 298.5 m3

- 316.5 m3 of open space in habitat

• Maximum Power 37.5 kW

- Exceeds DRM recommendation by 12.5 kW

- Overall Martian base power = 160 kW

• ESA Aurora:

Subsystem

Total Mass (kg)

Total Power (kW)

Total Volume

(m3)

ISRU 325 0.5 0.7Structures 15789 N/A 149.3Power 2047 11.3 4.1ECLSS 31248 9.6 83.5Thermal Control 4996 2.0 13.7Mission Ops/Crew Accomm 5988 11.8 46.4C3 532 1.9 0.3Robotics/Automation 876 0.5 0.6EVAs TBD TBD TBD

Grand Totals 61801 37.5 298.5

124

Comparison

Mars or Bust ESA Aurora

Subsystem

Total Mass (kg)

Total Power (kW)

Total Volume

(m3)

(ISRU) unavail. 0.50 unavail.Habitat Module 25293.50 N/A unavail.Power 5781.70 unavail.Life Support 10861.50 9.56 unavail.(Therm al Control) unavail. 2.00 unavail.Hum an Factors 5037.60 11.75 unavail.Com m /Data Managem ent 545.50 1.90 unavail.(Robotics /Autom ation) unavail. 0.53 unavail.EVA 858.50 unavail.10% Margin (Mass) 4837.83 N/A N/A20% Margin (Power) N/A 5.25 N/AGrand Totals 53216.13 31.49 441.70

Subsystem

Total Mass (kg)

Total Power (kW)

Total Volume

(m3)

ISRU 325 0.5 0.7Structures 15789 N/A 149.3Power 2047 11.3 4.1ECLSS 31248 9.6 83.5Thermal Control 4996 2.0 13.7Mission Ops/Crew Accomm 5988 11.8 46.4C3 532 1.9 0.3Robotics/Automation 876 0.5 0.6EVAs TBD TBD TBD

Grand Totals 61801 37.5 298.5

125

Conclusions

• Summarized,derived,documented DRM requirements/constraints

• First iteration design, subsystem functionalities, integration factors:

- i.e. structural layout, mass flows, power distribution, data transmission

• Human factors emphasis:

- Crew Accommodations/Mission Operations

- crew health, well-being

126

Conclusions (continued)

• Human spacecraft design requirements, as applicable: Man-Systems Integration Standards [NASA STD-3000 Rev. B, 1995]

• Architectural habitat concepts - compatibility of floor plans

• Unique merger of:

- systems engineering

- architecture

- human factors

127

Suggestions for Future Work

• Optimize subsystems- reduce mass, power

- redundancy vs. contingency (FMEA’s)

- trade studies• Detailed architectural layout of subsystems • Further iteration• Requirements re-evaluation• Levels 3,4 requirements - design solutions• Detailed Interface Control Documents

Report Available

December 17, 2003

http://www.colorado.edu/ASEN/project/mob

129

ISRU Interface Technologies

Component #Mass (kg)

Add. Mass (kg)

Total Mass (kg)

Power (W)

Total Power

(W)Volume

(m3)

Total Volume

(m3)

Water Pump 1 70.50 70.50 70.50 70.50

Oxygen Pump 1 0.94 0.94 1.50 1.50

Nitrogen Pump 1 0.94 0.94 1.50 1.50

Water Pipe 1 70.00 10.00 80.00 0.00 0.00 0.65 0.65

Oxygen Pipe 1 70.00 70.00 0.00 0.00 0.65 0.65

Nitrogen Pipe 1 70.00 70.00 0.00 0.00 0.65 0.65

Hydrogen Pipe 1 70.00 70.00 1.50 1.50 0.65 0.65

Valves and Connections 9 42.00 42.00 5.00 5.00 0.00

Grand Totals 404.38 80.00 2.60

130

Structures Mass, Power, and Volume Estimates

Component #

Unit Mass (kg)

Growth Factor

Total Mass (kg)

Unit Volume

(m3)Growth Factor

Total Volume

(m3)

Pressure shell 1 3400 1.5 5100 1.25 1.25 1.56Raidiation shielding* 1 2100 1.5 3150 0.8 1.25 1Safe haven 1 3800 1.5 5700 1.4 1.25 1.75Top floor structure** 1 360 1.5 540 26 1.25 32.5Bottom floor structure** 1 360 1.5 540 26 1.25 32.5Center truss** 1 140 1.5 210 10 1.25 12.5Chassis** 1 110 1.5 165 7.5 1.25 9.4Wheels 8 50 1.5 600 0.24 1.25 2.4Leg supports 6 5 1.5 45 0.12 1.25 0.9Secondary floors 2 40 1.5 120 0.52 1.25 1.3Secondary walls 30 5.5 1.5 225 0.075 1.25 2.8Airlock structure 3 800 1.5 3600 0.2 1.25 0.75Radiator supports 4 80 1.5 480 0.5 1.25 2.5

Supports for other subsystem components 1 350 1.5 525 10 1.25 12.5

Totals 21000 114

* In addition to pressure shell and storage ** Volume includes empty space in truss

131

Volume Allocation

Subsystem Volume (m3)Structure 150.00

ECLSS 65.00

Thermal 40.00

EVAS 40.00

Robotics 15.00

Power 30.00

ISRU Interface 4.00

CCC 5.00

Crew Accommodations 50.00

Empty 216.75

Totals 615.75216

132

Power Mass/Volume

Wires/Cabling

Component #Weight

(kg)

Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kW)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Wires/Cabling 150 2.5* 0.1

Totals 150 2.5 0.1*Amount of heat generated

Batteries

Component #Weight

(kg)

Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kW)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Li-ion 1412 10* 3

Totals 1412 10 3*Amount of power produced, not needed

Regulated System

Component #Weight

(kg)

Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kW)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Regulated System 285 25 1Spares (breakers, etc.) 200

Totals 485 25 1

Grand Totals 2047 37.5 4.1

133

ECLSS Total M,P,V Estimates

Subsystem

Mass technology

(kg)

Mass consumable

(kg)

Volume technology

(m^3)

Volume consumable

(m^3)Power (kW)

Atmosphere 3335.97 4892.74 16.588 5.589 3.533

Water 890.935 9607.42 3.255 19.0087 2.01

Food 327.91 11088 2.42 31.68 3.8

Waste 277.765 828 2.063 2.88 0.22

Total 4832.58 26415.88 24.326 59.157 9.563

134

Thermal System Sizing

Hot Hot

NumberMass (kg)

Volume (m^3) Power (W)

Radiators 4 3087.2 21.8 0.0Heat Exchangers 3 78.0 0.2 0.0Pumps 15 1038.3 2.3 1658.4Cold Plates 8 442.9 1.0 0.0Instruments n/a 232.3Plumbing and Valves n/a 697.0Fluids n/a 232.3 0.0Totals 5808.1 25.3 1658.4

135

Thermal Components HOT

Design Total Watts Watt/ PanelHOT/ HOT 36053 9013.1

Item #Power (W)

Surface Area (m^2)

Volume (m^3)

Mass (kg)

Radiators 4.0 0.0 363.2 21.79 3087.2Heat Exchangers 3.0 0.0 n/a 0.18 78.0Pumps External 12.0 829.2 n/a 1.84 519.2Pumps Internal 3.0 829.2 n/a 0.46 519.2ECLSS Cold Plates 1.0 9100.0 n/a 0.25 109.20ECLSS Air/ Heat Exchanger1.0 5000.0 n/a 0.14 60.00CCC Cold Plates 1.0 1909.0 n/a 0.05 22.91EVAS Cold Plates 1.0 6000.0 n/a 0.17 72.00Robotic & Auto Cold Plates1.0 3000.0 n/a 0.08 36.00Mission Ops Cold Plates 1.0 6000.0 n/a 0.17 72.00Thermal Cold Plates 1.0 1658.4 n/a 0.05 19.90Instruments n/a n/a 229.8Plumbing and Valves n/a n/a 689.3Fluids n/a n/a 229.8Heat Pumps n/a n/a

TOTALS: 32667.4 363.2 25.18 5744.5

136

Thermal Components COLD

Design Total Watts Watt/PanelCOLD/COLD 26988.0 6747

Item #Power (W)

Surface Area (m^2)

Volume (m^3)

Mass (kg)

Radiators 4.0 0.0 363.2 21.79 3087.2Heat Exchanger 2.0 0.0 n/a 0.18 78.0Pumps External 12.0 620.7 n/a 1.38 388.6Pumps Internal 3.0 620.7 n/a 0.34 388.6ECLSS Cold Plates 1.0 9100.0 n/a 0.25 109.20ECLSS Air/Heat Exchanger 1.0 1500.0 n/a 0.04 18.00CCC Cold Plates 1.0 1388.0 n/a 0.04 16.66EVAS Cold Plates 1.0 6000.0 n/a 0.17 72.00Robotic & Auto Cold Plates 1.0 3000.0 n/a 0.08 36.00Mission Ops Cold Plates 1.0 6000.0 n/a 0.17 72.00Thermal Cold Plates 1.0 1241.4 n/a 0.03 14.90Instruments n/a n/a 214.1Plumbing and Valves n/a n/a 642.2Fluids n/a n/a 214.1Heat Pumps n/a n/a

TOTALS: 28229.4 363.2 24.48 5351.6

137

Crew Accommodations

Mass, Power, and Volume

Estimates

Crew Accommodations

#

Weight (kg)

Total Weight

(kg)

Total Power (kW)

Volume (m3)

Total Volume

(m3)

Galley and Food System

Kitchen cleaning supplies (per day) 600 0.25 150.00 0.0018 1.08

Dishwasher 1 40 40.00 1.20 0.5600 0.56

Cooking/eating supplies (per person) 6 5 30.00 0.0140 0.08

Waste Collection System

WCS supplies (toilet paper, etc... ~ per person per day) 3600 0.05 180.00 0.0013 4.68

Contingency fecal and urine collection bags (per person) 6 3 18.00 0.0120 0.07

Personal Hygiene

Shower 1 75 75.00 1.00 1.4100 1.41

Handwash/mouthwash faucet 1 8 8.00 0.0100 0.01

Personal Hygiene kit (1 per person) 6 1.8 10.80 0.0050 0.03

Hygiene supplies (per person per day) 3600 0.075 270.00 0.0015 5.40

Clothing

Clothing (per person) 6 99 594.00 0.3360 2.02

Washing Machine 1 100 100.00 1.50 0.7500 0.75

Clothes Dryer 1 60 60.00 2.50 0.7500 0.75

Recreational Equipment and Personal Stowage

Personal stowage/closet space (per person) 6 50 300.00 0.70 0.7500 4.50

DVD player and DVDs (per person) 6 2 12.00 0.40 0.0010 0.0060

Housekeeping

Vacuum (prime + 2 spares) 3 4.333 13.00 0.40 0.0233 0.0700

Disposable Wipes (per person per day) 3600 0.05 180.00 0.0015 5.4000

Trash bags (per person per day) 3600 0.03 108.00 0.0010 3.6000

Operational Supplies & Restraints

Supplies(diskettes, velcro, ziplocks, tape ~ per person) 6 20.00 120.00 0.0200 0.1200

Restraints and Mobility aids 1 100.00 100.00 0.5400 0.5400

Maintenance: All repairs in habitable areas

Hand tools and accessories 1 300.00 300.00 1.00 1.0000

Test equipment (oscilloscopes, gauges, etc…) 1 500.00 500.00 1.00 1.50 1.5000

Fixtures, large machine tools, gloveboxes, etc… 1 1000.00 1000.00 1.00 5.00 5.0000

Photography (All Digital)

Equipment (still and video cameras, lenses, memory, etc) 1 120.00 120.00 0.40 0.50 0.5000

Sleep Accommodations

Personal quarters with sleep accommodations (per person) 6 1.5 9

Stowage space for personal equipment (per person) 6 0.63 3.78

Sleep restraints (per person) 6 9.00 54.00 0.10 0.6000

Crew Health Care

Exercise Equipment 1 145.00 145.00 0.15 0.19 0.1900

Medical/Surgical/Dental suite 1 1000.00 1000.00 1.50 4.00 4.0000

Medical/Surgical/Dental consumables 1 500.00 500.00 2.50 2.5000

Totals 5987.799 11.75 59.15

• Total Mass: 5,988 kg• Total Power: 11.75 kW• Total Min. Volume: 60 m3

138

C3 Mass, Power and Volume

ComponentIn-Line Units

Total Units

Total Mass (kg)

Unit Volume (m^3)

Total Volume (m^3)

Occupied Power (W )

Unoccupied Power (W )

Tier 1 Command Computers 3 6 18 0.003 0.02 180 180Tier 1 Emergency Computers 1 2 6 0.003 0.01 60 60Tier 2 Science Computers 2 4 12 0.003 0.01 120 120Tier 2 Subsystem Computers 4 8 24 0.003 0.03 240 240Tier 3 Subsystem Computers 8 16 49 0.003 0.05 480 480RF Hubs 3 12 4 0.001 0.01 38 0C&W Panels 4 12 1 0.001 0.01 20 0User Terminals 6 12 37 0.003 0.04 360 0File Server 1 2 6 0.003 0.01 60 60Batteries 0 2 1 0.000 0.00 0 0Ethernet Cable 1300 1310 39 0.000 0.03 0 0Coaxial Cable 2300 2320 70 0.000 0.05 0 0Minor Components NA NA 27 NA 0.03 0 0Safety Factor NA NA 59 NA 0.06 312 228Communications Subsystem NA NA 146 NA 0.05 40 20

Totals 499 0.41 1910 1388

Estimates based on specs for IBM 760XD ThinkPad laptops, Linksys Wireless Access Point WAP54A and cable manufactured by 4S Products, Inc.