1. AAE450 Senior Spacecraft Design Kate Mitchell Week 2: January 25 th, 2007 Human Factors – Team Lead Habitat (HAB), Crew Transfer Vehicle (CTV) This Week: HAB

2. AAE450 Senior Spacecraft Design Definition of HAB Mission Requirements [2] –2 HABs on Mars Surface (MS) by the beginning of 4 th synodic period –Each HAB support crew of 4 (8 in emergency) Launch Specifications –HAB 1: 1564 days consumables –HAB 2: 2112 days consumables –Re-supply (RS) 1-5: 1330 days consumables Re-supplies launched with crews 4-8

3. AAE450 Senior Spacecraft Design HAB Conclusions LaunchMass (kg)Volume (m 3 )Power (kW) HAB 193178.56339.7120.17 HAB 2114005.18339.7120.17 RS (1-5)40495.63108.13- Totals409662122141 ComponentMass (kg)Volume (m 3 )Power (kW) Consumables*57730.57126.84- Crew Accommodations4994.9027.0716.29 Water Recycling System200.000.800.24 Atmospheric Supply System5440.858.370.28 Private Quarters-60.00- Crew Common Area-60.00- Radiation Shielding26638.00-- Totals95004.32283.0816.81 Conservative (120%) Totals114005.18339.7020.17 Total Mass/Volume/Power for HAB 2 Total Mass/Volume/Power Entire Architecture *Consumable calculations made assuming water recycling system with 90% efficiency, plus the capability to produce all water (9225 kg per synodic period) through ISPP beginning in 7 th synodic period.

4. AAE450 Senior Spacecraft Design Backup - Totals ComponentMass (kg)Volume (m3)Power (kW) Consumables40375.05126.84- Crew Accommodations4994.9027.0716.29 Water Recycling System200.000.800.24 Atmospheric Supply System5440.858.370.28 Private Quarters-60.00- Crew Common Area-60.00- Radiation Shielding26638.00-- Totals77648.80283.0916.81 Conservative (120%) Totals93178.56339.7120.17 Total Mass/Volume/Power for HAB 1 ComponentMass (kg)Volume (m3)Power (kW) Consumables33746.3690.11- Conservative (120%) Totals40495.63108.13- Total Mass/Volume/Power for each re-supply

5. AAE450 Senior Spacecraft Design Backup – Water Calculations 1 st table is a breakdown of all components of crew water consumption 2 nd table shows max water that will need to be stored in HAB as well as its volume (based on 2112 days) Crew Consumption of Water per day [1]

6. 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 (9225 kg per synodic period) through ISPP beginning in 7 th synodic period Conclusion: Plan 2 cuts the water IMLEO in half –Plan 2 was therefore used in final mass calculations

7. AAE450 Senior Spacecraft Design Backup – Water Comparison Plan 2* *Water calculations done in MATLAB code (attached) Plan 1*

8. AAE450 Senior Spacecraft Design Backup – Food Consumption Crew Consumption of Food per day 1 st table shows mass and volume of food consumed per crew member per day 2 nd table shows max food that will need to be stored in HAB as well as its volume (based on 2112 days) 3 rd tables shows mass and volume of food to be launched in both HABs as well as re- supply ships, and total food IMLEO *Food calculations done in MATLAB code (attached)

9. AAE450 Senior Spacecraft Design Backup – Atmospheric Supply Atmospheric supply values were based on O2 consumption of 0.835 kg/p/d (1 st table) 2 nd table shows max O2 and N2 that will need to be stored in HAB as their tank volumes and masses* (based on 2112 days) *Tank mass/volume calculations in MATLAB code (attached)

10. AAE450 Senior Spacecraft Design Backup – Atmospheric Supply Total gases per Launch as well as total IMLEO through entire architecture* *Atmospheric supply calculations in MATLAB code (attached)

11. AAE450 Senior Spacecraft Design Backup – Atmospheric Supply Atmospheric pressure: 101 kPa Partial pressures: 80 kPa N 2 21 kPa O 2 Volume of 1 mole of gas (101 kPa and 298 K): 0.02445 m 3 /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:

12. AAE450 Senior Spacecraft Design Backup – Atmospheric Supply 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

13. AAE450 Senior Spacecraft Design Backup – Life Support Systems Water Recycling System CO 2 Removal/Oxygen Generation System

14. AAE450 Senior Spacecraft Design Backup – Crew Accommodations [5]

15. AAE450 Senior Spacecraft Design Backup – Crew Accommodations

16. AAE450 Senior Spacecraft Design Backup – Radiation Shielding Investigations have suggested that a 50 g/cm 2 shield should be sufficient to protect from solar particle events [4]. The Mars atmosphere provides 16 g/cm 2 of shielding, which can be subtracted from the 50 g/cm 2, making it necessary to provide the crew with 34 g/cm 2 of additional shielding. 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 HAB. The room will be 2 x 2 x 2 m (8m 3 ) and will contain crew beds and necessary provisions. The shielding used will be 16 cm Polyethelyne (ρ = 1 g/cm 3 ) and 5 cm Aluminum (ρ = 2.78 g/cm 3 ), making the total shield arial density 29.9 g/cm 2. The total surface area of the safe-room is 24 m3, making the total shield mass 7176 kg. HAB External Shielding –An additional 4 g/cm 2 shielding must be provided to meet the 50 g/cm 2 shielding requirement. This will be done by shielding the entire habitat with 4 g/cm 2 shielding. We will use 1 cm Aluminum and 2 cm Polyethelyne to meet this requirement, giving a HAB external shielding arial density of 4.77 g/cm 2. Since the surface area of the HAB is not yet known, a conservative (large) estimate was made: 408 m 3 (assuming cylindrical shape with 10m diameter, 8m height). Using this surface area, the total shield mass is 19,462 kg. The total mass of the required radiation shielding is therefore 26,638 kg.

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.