PHARI Base Phobos
Timothy Bishop, Thomas Lagarde, Zachary Taylor, Victor Kitmanyen SASAKAWA INTERNATIONAL CENTER FOR SPACE ARCHITECTURE (SICSA)
Contents › Competition Overview › Flight Planning
› Base Architecture › Space Port Architecture › Atmosphere Regulation › Crew Health › Power Systems › Q&A
AIAA Design Competition Requirements Competition Core Requirements › A fully functioning base on the Martian moon of Phobos › Site location must be the Stickney Crater › Accommodate a 12 person crew max for a duration of 24 months max
› Fully utilized RECLSS with at least 50% growable food › Microgravity / Radiation / Dust / Micrometeorite countermeasures › Spaceport for Earth / Mars crew transport › Planned rations for one missed re-supply mission
Flight Planning - Construction Location Location Requirements: Replacement hardware delivery Reliable communication Fuel cost vs payload mass
LEO
Cis-Lunar
Mars
Easy hardware replacement Communication reliable 1:24 Payload to Fuel ratio
Easy hardware replacement Communication reliable 1:66 Payload to Fuel ratio
Difficult hardware replacement Communication less reliable 1:136 Payload to Fuel ratio
Flight Planning – Launch Plan YEAR 1 - 4
YEAR 5
Crew Rotation
YEAR 6
YEAR 7
YEAR 8
YEAR 9
Expedition 1
Expeditions 2 & 3
Expedition 4 & 5
Expedition 6
On Orbit Activities
Satellite deployment
Truss extension TLA assembly
Support – Crew module dock Crew arrival / Outfitting (ongoing)
Crew – Command module dock Stock water and dry foods
VASIMR – Power – Support module dock Systems verification
Transit
Cargo
GPS Satellite (12)
TLA
Support Module / Crew Module / Supplies
Command Module / Supplies / Water
VASIMR / Power module /
Crew / Supplies
Location
Phobos
Phobos
LEO
LEO
LEO
Transit
Flight Planning – Transit Injection into HMO Altitude: 7,000 km Inclination: 7O
Earth gravity assist 2 month duration Delta-v: 4.3 m/s
Transit: 6 months
Phobos Altitude: 6,000 km Velocity: 2.1 km/s Inclination: 7O Phase Locked with Mars
Architecture – Truss Design
Architecture – Truss Landing Assembly
Architecture – Command Module
Systems Monitoring Greenhouse Galley / Ward Room Food Storage Storage, Laundry, Hygiene Secondary ECLSS
Architecture – Crew Module Crew Quarters Crew Quarters
Crew Quarters Crew Storage
Architecture – Support Module
Medical & ECLSS Astrobiology Lab Transfer Floor
Workshop Workshop storage
Architecture – Power Module Power Control Room Battery Bay Stator / Rotor Nuclear Reactor Chamber
Architecture - Greenhouse
Architecture - Greenhouse
Architecture - Spaceport
Atmosphere - ECLSS
ISRU and Refueling
Electrical Systems - Solar
Crew Health – Centrifuge Module
FC
Direction of Motion
Crew Health – Centrifuge Module
Crew Health – Centrifuge Module
Electrical Systems – Nuclear Module › Fluoride Salt cooling loop › Some excess heat fed to other modules › Battery compartments include: › Lithium-ion cells › DC-AC rectifier › Inverters Turbine › Voltage regulator › Batteries are removable / repairable Compressor › Radiation Barrier made from polyethylene Intercooler Heat Exchanger
Control Room Battery Bay Stator / Rotor Recuperator
Radiators
Radiation Barrier
Reactor
Electrical Systems – Reactor Cell Covering Pumps Secondary salt cycle pipes Outer steel casing Solid steel inner casing Heat Exchanger
Performance › 2.1 MWe › Assumptions › 80 MWt / m3 › 45% efficiency › Closed loop › 7 – 10 year life span › Thorium based reactor › No Proliferation concerns › Easily interchangable
Molten salt mixed with radioactive fuels Salt buffer Graphite core
Based on reactor design by Terrestrial Energy http://terrestrialenergy.com/
Conclusion
Question & Acknowledgements