AAE450 Senior Spacecraft Design Kate Mitchell - 1 Kate Mitchell Week 6: February 22 nd, 2007 Human Factors – Group Lead HAB & TV Vehicle Groups This Week:

Kate Mitchell - 1

AAE450 Senior Spacecraft Design

Kate MitchellWeek 6: February 22nd, 2007

Human Factors – Group LeadHAB & TV Vehicle Groups

This Week: Updated Mass/Power/Volume for HAB & TV, HAB Layout

Kate Mitchell - 2

AAE450 Senior Spacecraft Design

HAB & TV

Mass (m t) Volum e (m 3) Pow er (kW)

HAB Totals (em pty) (per HAB) 36.76 301.6 20.82

HAB 1 Totals (w / Consum ables) 77.13 301.6 20.82

HAB 2 Totals (w / Consum ables) 94.49 301.6 20.82

Mass (mt) Volume (m3) Power (kW)

Totals 68.74 175.9 19.86

Totals for each TV Crew Cab

Totals for each HAB Crew Cab

Mass (mt) Volume (m3) Power (kW)

Totals 22.11 73.60 -

• Requirements– HAB: sized for crew of 6, fits 4 nominally, and must be able to support 8 in an emergency– TV: must be able to support crew of 4 for 3 years (in case of free return)

• Capabilities– HABs are stocked with consumables to support first 2 crews

– All water and O2 to support HAB crews is produced on Mars beginning in 6th synodic period (3rd crew)

– TVs contain enough consumables to re-supply HABs with food and other misc. consumables

Totals for Re-supply Launches to TV (x5)

*Total masses for HAB and TV include consumables, crew accommodations, radiation shielding, and LSS.

Kate Mitchell - 3

AAE450 Senior Spacecraft Design

HAB Layout

Kate Mitchell - 3

3 m Consumables Storage/Plumbing/Piping

3 m Crew Living Quarters

Side

Nominal Configuration (4 crew)Section Volume (m

3)

Crew Common Area 96.4(SPE Shelter) 12.0(Other Common Space) 57.16Crew Private Area (4 crew) 54.4(Private quarters per crew) 13.6Consumables Storage 150.8Total Habitable Volume 150.8

Total Volume 301.6

Section Volume (m3)

Crew Common Area 69.2(SPE Shelter) 12.0(Other Common Space) 57.16Crew Private Area (6 crew) 81.6(Private quarters per crew) 13.6Consumables Storage 150.8Total Habitable Volume 150.8

Total Volume 301.6

Contingency Configuration (6 crew)

4 m

Crew Common Area

1.25 m

Top

Crew Private Area

2 m

2 m

SPE Shelter

Retractable Walls

Kate Mitchell - 4

AAE450 Senior Spacecraft Design

Back-up Slides

Kate Mitchell - 5

AAE450 Senior Spacecraft Design

TV Layout

Kate Mitchell - 5

4 m

Consumables Storage 1 (40%) (Food, Miscellaneous Consumables)

Crew Common Area (60%)

2 m

Top

3.5 m

4 m

2 m

1.0 m

SideConsumables Storage 2 (Water, Life Support Systems, Plumbing/Piping)

Section Volume (m3)

Crew Common Area 56.5

Crew Private Area 44.0

(SPE Shelter) 8.0

(Crew Rooms) 36.0

Consumables Storage 75.4

(Consumables Storage 1 (food and misc. consumables)) 52.8

(Consumables Storage 2 (water, life support systems, and plumbing/piping)) 22.6

Total Habitable Volume 108.5

Total Volume 175.9

Consumables Storage

SPE Shelter

Private Quarters

Outer Walls

Kate Mitchell - 6

AAE450 Senior Spacecraft Design

Habitable Volume Comparison

*TV and HAB unobstructed habitable volume falls b/w performance and optimal values recommended in the NASA ALS Baselines Document.

Comparison of Unobstructed Habitable Volume

NASA Advanced Life Support Baselines Recommended Assumptions for Unobstructed Habitable Volume [1]

Case Volume (m 3) Volume (m 3/person) Time in Volume

ME 117 (20' x 30' x 10' estimate) 169.9 6.07 3 hours

TV Crew Cab 47.28 11.82 170 days (each w ay)

HAB Crew Cab (6 crew ) 73.95 12.32 782 days

HAB Crew Cab (4 crew ) 73.95 18.49 1329 days

Mission Units Tolerable Performance Optimal

Mars Habitat m3/person 5.1 9.91 18.41

Mars Transit Phase m3/person 5.1 9.91 18.41

*Breakdown of HAB and TV Habitable Volume attached

Kate Mitchell - 7

AAE450 Senior Spacecraft Design

Totals BreakdownComponent Mass (mt) Volume (m3) Power (kW)

Consumables (HAB1) 40.38 101.38 -

Consumables (HAB2) 57.73 101.38

Crew Accommodations 19.38 - 16.55

Water Recycling System 0.40 1.60 0.24

Atmospheric Supply System 5.87 20.39 0.56

Private Quarters - 90.00 -

Crew Common Area - 90.00 -

Radiation Shielding 4.98 - -

HAB Totals (empty) (per HAB) 36.76 301.6 20.82

HAB 1 Totals (w/ Consumables) 77.13 301.6 20.82

HAB 2 Totals (w/ Consumables) 94.49 301.6 20.82

Component Mass (mt) Volume (m3) Power (kW)

Consumables 28.53 52.62 -

Crew Accommodations 12.23 - 16.29

Water Recycling System 0.20 0.80 0.24

Atmospheric Supply System 1.13 8.05 0.28

Private Quarters - 44.00 -

Crew Common Area - 56.50 -

Radiation Shielding 15.20 - -

Totals 68.74 175.90 19.86

HAB

TV

Kate Mitchell - 8

AAE450 Senior Spacecraft Design

Water Consumption

Max Water on board (at one time) 25022.624 kg

Water Storage Volume 25.02 m3

• 1st table* is a breakdown of all components of crew water consumption

• 2nd table shows max water that will need to be stored in TV and HAB and as well as its volume

Parameter Mass Units

Crew Drinks 2 kg/p/dTotal Metabolic and Related Consumption 2 kg/p/dUrinal Flush 0.5 kg/p/dOral Hygiene 0.37 kg/p/dHand Wash 4.08 kg/p/dShower 2.72 kg/p/dLaundry 12.47 kg/p/dDish Wash 5.44 kg/p/dFood Processing and Prep 1.9 kg/p/dTotal Hygiene Consumption 27.48 kg/p/dDaily Water Consumption (per person) 29.48 kg/p/dTotal Daily Water Consumption 117.92 kg/d

Crew Consumption of Water per day[1]

*Crew water consumption table first used in presentation on 1/25/07

HAB

Max Water on board (at one time) 13,030 kg

Water Storage Volume 13.03 m3

TV

Kate Mitchell - 9

AAE450 Senior Spacecraft Design

Water Launched

Launch Mass (kg) Volume (m3)

Each Transfer Vehicle (x4) 13,030 13.03

Each Resupply (x5) 13,030 13.03

Total Water Launched 117,270 117.27

TV

Launch Mass (kg) Volume (m3)

HAB1 18,561 18.56

HAB2 25,023 25.02

Total Water Launched 59,267 59.27

HAB

*Water calculations done in MATLAB code

HAB Code: attached to week 2 presentation (HAB_consume.m – 3 pages

TV Code: attached to week 4 presentation (TV_consume.m) – 3 pages

Kate Mitchell - 10

AAE450 Senior Spacecraft Design

Food Consumption

Launch Mass (kg) Volume (m3)

HAB1 14,389 50.05

HAB2 19,430 67.58

Parameter Mass Mass Units Volume Volume Units

Food 2.3 kg/p/d 0.008 m3/p/d

Crew Consumption of Food per day• 1st table shows mass and

volume of food consumed per crew member per day

• 2nd table shows mass and volume of food to be launched in each TV as well as re-supply ships

• 3rd table shows mass and volume of food to be launched in each HAB

*Food calculations done in MATLAB code

HAB Code: attached to week 2 presentation (HAB_consume.m) – 3 pages

TV Code: attached to week 4 presentation (TV_consume.m) – 3 pages

Launch Mass (kg) Volume (m3)

Each Transfer Vehicle (x4) 12,100 41.28

Each Resupply (x5) 12,100 41.28

Food Launched in TV

Food Launched in HAB

Kate Mitchell - 11

AAE450 Senior Spacecraft Design

Atmospheric Supply Values

Launch Mass O2 (kg) Mass N2 (kg) Mass H2 (kg) Gas Sum per Launch (kg)

Each Transfer Vehicle (x4) 710 640 400 1750

Each Resupply (x5) 710 640 400 1750

Total Launched 6390 5760 3600 15750

Total Gases Launched (kg) 15,750

Launch Mass O2 (kg) Mass N2 (kg) Mass H2 (kg) Gas Sum per Launch (kg)

HAB1 1715.04 3245.68 568.73 5529.45

HAB2 3099.31 6994.06 768 10861.37

Total Launched 4814.35 10239.74 1336.73 16390.82

Total gases per Launch as well as total IMLEO through entire architecture*

*Atmospheric supply calculations done in MATLAB code

HAB Code: attached to week 2 presentation (HAB_consume.m – 3 pages

TV Code: attached to week 4 presentation (TV_consume.m) – 3 pages

TV

Total Gases Launched (kg) 16390.82

HAB

Kate Mitchell - 12

AAE450 Senior Spacecraft Design

Atmospheric Supply System Schematic

H2 Tank

422 2

Sabatier Reac

2

t r

4

o

H OCO H CH CH4

22 2

Electrolysis Machine

H 2 2H O O

H2O

H2

O2

CO2

(from atmosphere in vehicle)

HAB or TV

Condenser

Martian Atmosphere (HAB) or Vacuum Environment (TV)

Kate Mitchell - 13

AAE450 Senior Spacecraft Design

Atmospheric Supply Calculations*

• Atmospheric pressure: 101 kPa

• Partial pressures: 80 kPa N2

21 kPa O2

• Volume of 1 mole of gas (101 kPa and 298 K): 0.02445 m3/mole

• Mass of gas needed to fill the pressurized volume:

• Mass of gas needed assuming 0.14% mass per day leakage rate:

• Using Sabatier/electrolysis reaction:

• Oxygen consumption rate: 0.835 kg/p/d

• Total oxygen consumed by crew:

3

Partial Pressure 1kg 1Mass of Ambient Gas (kg) *Molar Mass (g/mol)* * *Pressurized Volume

Total Pressure 1000g 0.02445

mol

m

Days

Mass of Ambient Gas (kg)Mass of Needed Gas (kg) =

(1-0.0014)

2 2 4 2CO H CH O

2 2Total O consumed = O consumption rate (kg/person/day)*person*days

*Slide first used in presentation on 1/25/07

Kate Mitchell - 14

AAE450 Senior Spacecraft Design

2 2Total CO produced (kg) = CO production rate (kg/person/day)*person*days

22 2 2

2 2

1 kmol O1 reclaimed (kg) = Total CO produced (kg)* * *O molar mass (kg/kmol)

CO molar mass (kg/kmol) 1 kmol COO

2 2 2 2 tankage (kg) = needed (kg)*O tankage value (kg tank/kg O )O O

2 2 2 2 tankage (kg) = N needed (kg)*N tankage value (kg tank/kg N )N

33

1Tank volume (m ) = Gas needed (kg)*

Gas density (kg/m )

Find Mass of O2 Tank (using O2 tankage value of 0.364 kg tank/kg O2 [1] ):

Find Mass of N2 Tank (using N2 tankage value of 0.556 kg tank/kg N2 [1] ):

Volume of tanks (Assuming density of gases to be 1440 kg/m3):

Total oxygen reclaimed:

Total carbon dioxide produced by crew:

CO2 production rate: 1 kg/p/d

Atmospheric Supply Calculations*

*Slide first used in presentation on 1/25/07

Kate Mitchell - 15

AAE450 Senior Spacecraft Design

H2 Tank Calculations

2

2 22 2

2 2

2 mol O H Molar Mass1H Mass, ( ) ( Reclaimed w/ LSS)

O Molar Mass 1 mol H 1LHM kg O

Mass of H2 needed by Atmospheric Supply System:

H2 Tank Volume and Mass Calculations:

2

2

LH3

LH

3

2

MTank Volume, ( ) =

Tank Radius, ( ) = 43

Tank Thickness, ( ) = 2

(where is the LH Internal Pressure ( 151,700 ),and is the tensile yield strength

of the tank structure (

y

y

y

V m

Vr m

Prt m

P P Pa

r

s

s

s 6

3 3 3

tank Al

3 3Al

520 10 ))

4 4Wall Volume, ( ) = ( )

3 3Tank Mass, ( ) =

(where =2.59 10 / )

wall

wall

x Pa

V m r r t

M kg V

x kg m

r

r

*H2 Tank Calculations for the HAB and TV are attached

Kate Mitchell - 16

AAE450 Senior Spacecraft Design

Life Support Systems

Components Mass (kg/p) Mass (kg) Volume (m3/p) Volume (m3) Power (kW-h/p) Power (kW)

Sabatier Reactor (2x) [5] 76 304 0.14 0.56 0.02 0.08

O2 Tankage [1] - 260 - 0.5 - -

N2 Tankage [1] - 355 - 0.45 - -

Contaminant Control System [5] 20 80 0.15 0.6 0.05 0.2

Redundant Parts (10% system hardware) - 40 0.2 - -

Totals 1039 2.31 0.28

Water Recycling System Mass Units Mass (kg) Volume Units Volume (m3) Power Units Power (kW)

Vapor Compression Distillation (VCD) (2x)[5] 50 kg/p 400 0.2 m3/p 1.6 0.06 kW/p 0.48

TV Water Recycling System

TV CO2 Removal/Atmospheric Supply System

Water Recycling System Mass Units Mass (kg) Volume Units Volume (m3) Power Units Power (kW)

Vapor Compression Distillation (VCD) (2x)[5] 50 kg/p 200 0.2 m3/p 0.8 0.06 kW/p 0.24

HAB Water Recycling System

HAB CO2 Removal/Atmospheric Supply SystemComponents Mass (kg/p) Mass (kg) Volume (m3/p) Volume (m3) Power (kW-h/p) Power (kW)

Sabatier Reactor (2x) [5] 76 608 0.14 1.12 0.02 0.16

O2 Tankage [1] - 1128.15 - 2.15 - -

N2 Tankage [1] - 3888.7 - 4.86 - -

H2 Tankage - 12.29 - 10.83 - -

Contaminant Control System [5] 20 160 0.15 1.2 0.05 0.4

Redundant Parts (10% system hardware) - 76.8 0.232 - -

Totals 5873.94 20.392 0.56

Kate Mitchell - 17

AAE450 Senior Spacecraft Design

TV Radiation Shielding

Material Thickness (cm) Density (g/cm3) Arial Density (g/cm2)

Aluminum 5 2.78 13.9

Polyethelyne 16 1 16

Totals 12 - 29.9

Arial Density (g/cm2) 29.9

Shielded Surface Area (m2) 28

Total Shield Mass (kg) 8372

Material Thickness (cm) Density (g/cm3) Arial Density (g/cm2)

Aluminum 1 2.78 2.78

Polyethelyne 2 1 2

Totals 12 - 4.78

Arial Density (g/cm2) 4.78

Shielded Surface Area (m2) 142.8

Total Shield Mass (kg) 6826

Total Mass of Radiation Shielding (mt) 15.20

SPE Shelter Shielding

Entire Crew Compartment Shielding

*TV Radiation shielding tables first used in presentation on 2/5/07

Kate Mitchell - 18

AAE450 Senior Spacecraft Design

HAB Radiation Shielding

Arial Density (g/cm2) 15.56

Shielded Surface Area (m2) 32

Total Shield Mass (kg) 4979.2

Material Thickness (cm) Density (g/cm3) Arial Density (g/cm2)

Aluminum 2 2.78 5.56

Polyethelyne 10 1 10

Totals 12 - 15.56

SPE Shelter Shielding

Total Mass of Radiation Shielding (mt) 4.98

Entire Crew Compartment Shielding

None (16 g/cm2 shielding provided by Martian Atmosphere is

sufficient)

Kate Mitchell - 19

AAE450 Senior Spacecraft Design

References

[1] Hanford, Anthony J., ed. NASA Johnson Space Center. Advanced Life Support Baseline Values and Assumptions Document. Aug. 2004. http://ston.jsc.nasa.gov/collections/TRS/_techrep/CR-2004-208941.pdf

[2] Landau, Dr. Damon F., “Strategies for the Substained Human Exploration of Mars.” Thesis Submitted to the Faculty of Purdue University, Dec. 2006.

[3] Niziolek, Paul, Project Legend - Final Report - Appendix. April 2005. p. 478-480.

[4] Reed, Ronald D., and Gary R. Coulter. "Physiology of Spaceflight." Human Spaceflight: Mission Analysis and Design. Ed. Wiley J. Larson and Linda K. Prank. New York: McGraw-Hill, 1999. 113-115.

[5] Stilwell, Don, Ramzy Boutros, and Janis H. Connolly. "Crew Accomodations." Human Spaceflight: Mission Analysis and Design. Ed. Wiley J. Larson and Linda K. Prank. New York: McGraw-Hill, 1999. 575-606.

[6] Tribble, Alan C. "The Space Environment: Hazards and Effects." Human Spaceflight: Mission Analysis and Design. Ed. Wiley J. Larson and Linda K. Prank. New York: McGraw-Hill, 1999. 65-73.