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Aerodynamics. Project Olympus. Ballute Material. Ballute material is Kapton Filled with Helium Gas to Mars surface Pressure for landing and 100 Pa for Aerocapture Tethers are PBO. By Richard O’Connor. Mars Thermal Protection System (TPS). Low Heating Rates with Ballutes
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Aerodynamics Project Olympus
Ballute Material • Ballute material is Kapton • Filled with Helium Gas to Mars surface Pressure for landing and 100 Pa for Aerocapture • Tethers are PBO By Richard O’Connor
Mars Thermal Protection System(TPS) • Low Heating Rates with Ballutes • Non-Ablators Carbon phenolic • If a Ballute is usable than this Heat shield will work
Aerobrake Maneuver for Earth Propulsion (EP) Tug • Prior to Aerobrake Maneuver: • EET Location/Altitude: 256000 km (at Highest Energy Ellipse Orbit) • Initial Aerobrake Parameters: • Atmospheric Entry Velocity: 10.94 km/s • Constant Atmospheric Entry & Exit Altitude: 150 km (at LEO) • Perigee radius (Rp) for all Aerobrake runs: fixed at 115 km • EP Parameters: • Maximum Diameter: 10 m • EET Mass: 29.1 t • Tankage Mass & Size will vary per crew
Aerobrake Maneuver Options: • Aerobrake #1= 3 Runs, Aerobrake # 2 = 7 Runs • Ablative Heat Shield Required: • Material: AVOCAT 5026-39H/CG • Heat Shield Mass Calculations:
Mars -Aerocapture Using the Atmospheric Drag to do a ΔV for entering into an Orbit
Mars -Crew Landing From MLO • Working on pinpoint landing • Working on last 14km and handing over to hovering
Mars -Cargo Entry • Some of the Cargo Missions will be Aerocaptured to LMO • Increased Mass gives a betterballute efficiency
Earth Descent Vehicle (EDV) • Direct Re-entry into Earth • Use of Capsule with Subsonic Parachutessimilar to Apollo/Orion • PICA-X ablator
Earth Entry Capsule - Geometry • Heat shield: 3 m radius, 3 m nose radius, 3.6 cm thickness • Capsule total mass: 6.6 t • Crew compartment: cylindrical pressure vessel, 2.25 m tall x 3 m diameter • Docking/crew entry port on top side (for attaching to Transit Hab)