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Mark Baker Mario Botros Terry Huang Erin Mastenbrook Paul Schattenberg

Team Ptolemy. Mark Baker Mario Botros Terry Huang Erin Mastenbrook Paul Schattenberg David Wallace Lisa Warren. Outline. Introduction Mission Statement Concept of Operations Trade Trees / Specifications Structures Living Units Launch Vehicle

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Mark Baker Mario Botros Terry Huang Erin Mastenbrook Paul Schattenberg

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

  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

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

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

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

  8. Artificial Gravity Calculations

  9. Living Units BA - 330 • Occupancy: 6 crew members • Volume/Weight: 330 m3/20MT • Radiation Protection: Greater than International Space Station • Ballistic Protection: Micrometeorite and Orbital Debris Shield BA - 2100 • Occupancy: 16 crew members • Volume/Weight: 2100 m3/65MT • Radiation Protection: Greater than International Space Station • Ballistic Protection: Micrometeorite and Orbital Debris Shield

  10. Launch Vehicle

  11. Propulsion

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

  13. Power

  14. Power Specifications Solar Cells Nuclear Reactor • Gallium Arsenide Multijunction Cells • Clean and renewable energy • Typical efficiency of 30% • Most efficient type of solar cell • Stored in Lithium – Ion batteries • 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

  16. Controls Specifications Sensors Actuators • 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. • 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

  19. Life Support Specifications Thermostabilized Food • 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

  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 Shielding • 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 m2

  24. Required ΔV Approximate Days Required to Achieve Required ΔV

  25. Connecting Arm Calculations ω mT: mass of arm mC: mass of capsule r L

  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

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