Kate Mitchell - 1

AAE450 Senior Spacecraft Design

Kate MitchellWeek 4: February 8th, 2007

Human Factors – Group Lead

HAB, TV, Integration Group

This Week: Transfer Vehicle Crew Compartment (TVCC)

Kate Mitchell - 2

AAE450 Senior Spacecraft Design

TVCC Configuration

4 m

Consumables Storage

Crew Common Area

2 m

Top

Plumbing/Piping

SPE Shelter

Private Quarters

Outer Walls

4 m

2 m

3.5 m

0.5 m

0.5 m

Side

m3175.9Total Volume

m3100.5Total Habitable Volume

m336.0(Desk/Other Private Space)

m38.0(SPE Shelter)

m344.0Crew Private Area

m318.9Plumbing/Piping

m356.5Consumables Storage

m356.5Crew Common Area

UnitsVolumeSection

m3175.9Total Volume

m3100.5Total Habitable Volume

m336.0(Desk/Other Private Space)

m38.0(SPE Shelter)

m344.0Crew Private Area

m318.9Plumbing/Piping

m356.5Consumables Storage

m356.5Crew Common Area

UnitsVolumeSection

Kate Mitchell - 3

AAE450 Senior Spacecraft Design

TVCC Conclusions

Component Mass (mt) Power (kW)

Consumables* 14.10 -

Crew Accommodations 12.23 16.29

Water Recycling System 0.20 0.24

Atmospheric Supply System 1.04 0.28

Private Quarters - -

Crew Common Area - -

Radiation Shielding 15.20 -

Totals 42.76 16.55

Conservative (120%) Totals 51.32 19.86

Total Mass/Power for each TVCC

Total Mass/Volume/Power: Entire Architecture

*Consumable calculations made assuming water recycling system with 90% efficiency, plus the capability to produce water through use of fuel cells (12 kg/day).

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

TV (x4) 51.32 175.90 19.86

RS (x5) 15.93 48.50 0.00

Totals 284.9 946.1 79.44

Kate Mitchell - 4

AAE450 Senior Spacecraft Design

Backup – Water Calculations

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

• 2nd table shows max water that will need to be stored in TVCC as well as its volume (based on 1095 days)

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]

Max Water on board (at one time) 826 kg

Water Storage Volume 0.83 m 3

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

Kate Mitchell - 5

AAE450 Senior Spacecraft Design

Backup – Water Comparison

• The following slide contains a comparison of two different plans for water– Plan 1: Launch necessary water, then use recycling

system which has efficiency of 90%– Plan 2: Launch necessary water, then use recycling

system which has efficiency of 90%, plus produce all water (12 kg/day) through fuel cells (will be necessary to power 0.5 kW per day)

• Conclusion: Plan 2 cuts the water IMLEO from 117 mt to 3.3 mt– Plan 2 was therefore used in final mass calculations

Kate Mitchell - 6

AAE450 Senior Spacecraft Design

Backup – Water Comparison

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

Plan 2*

*Water calculations done in MATLAB code (attached)

Plan 1*

Launch Mass (kg) Volume (m3)

Each Transfer Vehicle (x4) 826 0.83

Total Water Launched 3,302 3.30

Kate Mitchell - 7

AAE450 Senior Spacecraft Design

Backup – Food Consumption

Max Food on board (at one time) 10074.00 kg

Food Volume 35.04 m3

Freezer mass 7555.50 kg

Freezer volume 39.59 m3

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 max food that will need to be stored in TV as well as its volume and the necessary freezer mass and volume (based on 1095 days)

• 3rd table shows mass and volume of food to be launched in each TV as well as re-supply ships, and total food IMLEO

*Food calculations done in MATLAB code (attached)

Launch Mass (kg) Volume (m3)

Each Transfer Vehicle (x4) 10,074 35.04

Each Resupply (x5) 10,074 35.04

Total Food Launched 90,666 315.36

Kate Mitchell - 8

AAE450 Senior Spacecraft Design

• Atmospheric supply values were based on O2 consumption of 0.835 kg/p/d (1st table)

• 2nd table shows max O2 and N2 that will need to be stored in TV as their tank volumes and masses* (based on 1095 days)

Backup – Atmospheric Supply

Parameter Mass Units

O2 consumed 0.835 kg/p/d

Max O2 on board 710 kg

O2 tank mass 260 kg

O2 tank volume 0.5 m3

Max N2 on board 640 kg

N2 tank mass 355 kg

N2 tank volume 0.45 m3

*Tank mass/volume calculations in MATLAB code (attached)

Kate Mitchell - 9

AAE450 Senior Spacecraft Design

Backup – Atmospheric Supply

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 per Launch as well as total IMLEO through entire architecture*

*Atmospheric supply calculations in MATLAB code (attached)

Total Gases Launched (kg) 15,750

Kate Mitchell - 10

AAE450 Senior Spacecraft Design

Backup – 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 - 11

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

Backup – Atmospheric Supply Calculations*

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

Kate Mitchell - 12

AAE450 Senior Spacecraft Design

Backup – Life Support SystemsWater Recycling System

CO2 Removal/Oxygen Generation 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

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

Kate Mitchell - 13

AAE450 Senior Spacecraft Design

Backup – Crew Accommodations [5]

Mass Mass Units Subtotal (kg) Volume Volume Units Subtotal (m3) Power (kW)

Galley and Food Systems

Cooking/eating supplies (pans, plastic dishes, plates, etc.) 5 kg/p 20 0.0014 m3/p 0.0056 -

Freezers 0.75 kg/kg food 7555.5 0.00393 m3/kg food 39.59082 1.4

Conventional Oven 50 kg 50 0.25 m3 0.25 1.25

Microwave oven 35 kg 35 0.15 m3 0.15 0.9

Sink, spigot for hydration of food and drinking water 15 kg 15 0.00135 m3 0.00135 -

Dishwasher 40 kg 40 0.56 m3 0.56 1.2

Waste Collection System

Waste Collection System (1 toilet) 45 kg 45 2.18 m3 2.18 0.045

Personal Hygiene

Shower 75 kg 75 1.41 m3 1.41 1

Handwash/mouthwash faucet 8 kg 8 0.01 m3 0.01 -

Personal hygiene kit 1.8 kg/p 7.2 0.005 m3/p 0.02 -

Clothing

Washing machine 100 kg 100 0.75 m3 0.75 1.5

Clothes dryer 60 kg 60 0.75 m3 0.75 2.5

Recreational Equipment and Personal Stowage

Personal stowage/closet space 50 kg/p 200 0.75 m3/p 3 0.7

Housekeeping

Vacuum (prime + 1 spare) 8.7 kg 8.7 0.05 m3 0.05 0.4

Trash compactor/trash lock 150 kg 150 0.3 m3 0.3 0.85

Operational Supplies and Restraints

Operational supplies (diskettes, ziplocks, velcro, tape…) 20 kg/p 80 0.002 m3/p 0.008 -

Kate Mitchell - 14

AAE450 Senior Spacecraft Design

Backup – Crew Accommodations [5]

Maintenance: All Repairs in Habitable Areas

Hand tools and accessories 300 kg 300 1 m3 1 -

Spare parts/equipment and consumables - - - - - - -

Test equipment (oscilloscopes, gauges, etc) 500 kg 500 1.5 m3 1.5 1

Fixtures, large machine tools, gloveboxes, etc 1000 kg 1000 5 m3 5 1

Photography

Equipment (still and video cameras, lenses, etc.) 120 kg 120 0.5 m3 0.5 0.4

Film (assumes all digital approach) 0 kg 0 0 m3 0 -

Sleep Accommodations

Sleep provisions (sleep restraints only) 9 kg/p 36 0.1 m3/p 0.4 -

Crew Health Care

Exercise equipment 145 kg 145 0.19 m3 0.19 0.145

Medical/Surgical/Dental suite 1000 kg 1000 4 m3 4 1.5

Medical/Surgical/Dental consumables 500 kg 500 2.5 m3 2.5 -

Recreation

PC's (integrated for use w/ HAB) 4.5 kg/p 18 0.01 m3/p 0.04 0.18

TV Monitors (for common area) 20 kg 20 0.2 m3 0.2 0.08

Couches/Chairs 70 kg 70 8 8 -

Kitchen Table/Chairs 70 kg 70 2 2 -

Lighting

Habitat Lighting 0.5

Total Mass (kg), Volume (m3) and Power (kW) 12228.4 74.37 16.55

Kate Mitchell - 15

AAE450 Senior Spacecraft Design

Backup – Radiation Shielding

• Investigations have suggested that a 30 g/cm2 shield should be sufficient to protect from solar particle events [4].

• Safe-room Shielding– By creating a room to protect the crew from SPEs, we reduced the total mass by eliminating

the necessity to heavily shield the entire TV. The room will be 4 x 2 x 1 m (8m3) and will contain crew beds and necessary provisions. The shielding used will be 16 cm Polyethelyne (ρ = 1 g/cm3) and 5 cm Aluminum (ρ = 2.78 g/cm3), making the total shield arial density 29.9 g/cm2. The total surface area of the safe-room is 28 m2, making the total shield mass 8372 kg.

• TV External Shielding– Approximately an additional 4 g/cm2 shielding will cover the entire habitable part of the crew

compartment in order to shield the crew from long term exposure to radiation. We will use 1 cm Aluminum and 2 cm Polyethelyne to meet this requirement, giving a TV external shielding arial density of 4.77 g/cm2. The surface area of the habitable part of the transfer vehicle crew compartment is 142.8 m2. Using this surface area, the total shield mass is 6826 kg.

• The total mass of the required radiation shielding is therefore 15.20 mt.

Kate Mitchell - 16

AAE450 Senior Spacecraft Design

Backup – 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

Kate Mitchell - 17

AAE450 Senior Spacecraft Design

References

[1] Hanford, Anthony J., ed. NASA Johnson Space Center. Advanced Life Support Baseline Values and Assumptions Document. Aug. 2004. 1 Feb. 2005. 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.