1. Mark Baker Mario Botros Terry Huang Erin Mastenbrook Paul Schattenberg David Wallace Lisa Warren Team Ptolemy

2. Outline  Introduction  Mission Statement  Concept of Operations  Trade Trees / Specifications  Structures  Living Units  Launch Vehicle  Propulsion  Power  Controls  Communications  Life Support  Advantages  Questions

3. Introduction Mission Statement: Our mission is to expand the domain of humanity beyond the Earth for the betterment, preservation, and advancement of all humankind by creating a mobile habitat capable of long-duration, exploratory voyages while ensuring the physical and psychological well-being of its inhabitants.

4. Concept of Operation Launch individual components into GEO Assemble components autonomously in GEO Send crew to assembled vehicle Transfer from GEO to Earth-Moon L1 Transfer from Earth- Moon L1 to Earth- Sun L1 Transfer from Earth- Sun L1 to near earth asteroid Leave near earth asteroid and enter LEO Return crew to Earth via capsule

5. Ptolemy 12m 10m 6m 50m 5m Estimated Total Weight: 300MT 16m z xy

6. Living pods Connecting arm Main hub Power generation Main propulsion system Communications z xy

7. Truss design for strength efficiency Inner pressurized tube for crew mobility 50 m length, 3 m outer diameter Connecting Arm

8. Artificial Gravity Calculations

9. Living Units Occupancy: 6 crew members Volume/Weight: 330 m 3 /20MT Radiation Protection: Greater than International Space Station Ballistic Protection: Micrometeorite and Orbital Debris Shield BA - 330 Occupancy: 16 crew members Volume/Weight: 2100 m 3 /65MT Radiation Protection: Greater than International Space Station Ballistic Protection: Micrometeorite and Orbital Debris Shield BA - 2100

10. Launch Vehicle Atlas V-551 Delta IV Heavy Falcon 9 Heavy SLS 130 MT

11. Propulsion Low Thrust Solar SailsIon Thruster High Thrust Solid Rocket Bipropellant Rocket

12. Propulsion System DC Power Required : 200 kW Thrust: 5.7 N Exhaust speed: 50 km/s Specific Impulse: 5000 s Thruster efficiency: 72% Vasimr VX-200Comparison Ion Thruster Effective Exhaust Velocity: 50 km/s Specific Impulse: 5,000 s Fuel Mass: 620 kg Bipropellant Rocket Effective Exhaust Velocity: 5 km/s Specific Impulse: 500 s Fuel Mass: 8,200 kg

13. Power Solar Cells Copper Indium Gallium Selenide Gallium Arsenide Multijunction Dye-sensitized Cells Fuel Cells Nuclear Fast Nuclear Reactor Thermal Reactor

14. Power Specifications Solar Cells Gallium Arsenide Multijunction Cells Clean and renewable energy Typical efficiency of 30% Most efficient type of solar cell Stored in Lithium – Ion batteries Nuclear Reactor TRIGA Mark III Power output up to 1 MW Pulses up to 6 MW Fuel – High or low enriched uranium Negative thermal coefficient

15. Controls Attitude Determination & Control Sensors GPSIMUStar TrackerSun SensorMagnetometer Actuators Reaction JetsReaction WheelsCMGsSolar Sails

16. Controls Specifications Sensors GPS – determine position near Earth IMU – measure attitude, velocity, and acceleration Star Tracker – determine position outside of GPS range Sun Sensor – change angle of solar cells. Actuators Reaction Jets Controls Attitude Controls Nutation Controls Spin Rate Station Keeping Rendezvous Maneuvering

17. Communication systems External Uplink and downlink radios with high data transfer rate Backup systems with low transfer rates for redundancy Satellite with maneuverability to maintain contact with Earth-Based ground systems Internal Internal Audio Subsystems provides intercom, telephone and alarm systems Two-way audio and video communications among crew

18. Life Support Food Farming HydroponicsClay ParticlesPeat-Moss Storing Refrigerated FoodFrozen Food Thermostabilized Food Life Support Systems Elektron: Electrolysis splitting water molecules into oxygen and hydrogen Vika: Burning of solid lithium perchlorate to create oxygen Vozdukh: Uses regenerable absorbers to remove carbon dioxide from the air

19. Life Support Specifications Stored at room temperature Fruits and fish thermostabilized in easy to open cans Entrees in flexible pouches are heated and cut open Dehydrated drinks to be mixed with water or fruit juice Thermostabilized Food Weight of Food per Crew per Day (kg) # Crew Members # Days Estimated Total Food Weight (kg) Total Planned Food Weight (kg) Total Planned Food Storage Surface Area (m²) 0.58127305080.87621.243.07 Food Area Calculations Estimated Volume of 1 Meal (in³)200 # Meals per Day3 # Days730 # Crew12 Total Food Volume (in³)5,256,000 Total Food Volume (m³)86.13 Surface Area Required if stacked 3 meters high (m²) 28.71 Total Agricultural Surface Area needed (m²) 672

20. Advantages Food Reduction in volume and surface area No refrigeration or freezing system needed Solar cells Renewable energy Little maintenance required Nuclear power Lowest cost to power ratio Independent of environment Structure Using existing model for the living units (Bigelow Aerospace Models)

21. Questions?

22. Backup Slides

23. Radiation exposure causes direct damage to DNA and indirect effects on health due to generation of reactive oxygen species. Total area to be shielded: 1460 m 2 MaterialSurface area density Mass required Aluminum55g/cm 2 802500 kg Polyethylene20g/cm 2 291830 kg Radiation Shielding

24. Approximate Days Required to Achieve Required ΔV Number of Engines GEO  EML 1 EML1  C3= 0 C3=0  NEO Asteroid 1507 days51.1 days294.0 days 2254 days25.6 days147.1 days 3169 days17.0 days98.1 days Required ΔV

25. m T : mass of armm C : mass of capsule L ω r Connecting Arm Calculations

26. Launch Vehicle Specifications Atlas V-551 – Payload to LEO: 18,814 kg – Payload to GTO: 8,900 kg Delta IV – Payload to LEO: 22,560 kg – Payload to GTO: 12,980 kg Falcon 9 – Payload to LEO: 53,000 kg – Payload to GTO: 12,000 kg Space Launch System – Payload to LEO: 130,000 kg – Payload to GTO: no data