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Published byJonatan Caron Modified over 2 years ago

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By Richard O’Connor Ballute material is Kapton Filled with Helium Gas to Mars surface Pressure for landing and 100 Pa for Aerocapture Tethers are PBO

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Low Heating Rates with Ballutes Non-Ablators Carbon phenolic If a Ballute is usable than this Heat shield will work TPS Mass 3.0 t

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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 (R p ) 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

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Heat Shield Mass (t) Aerobrake # 1Aerobrake # 2 4.322.01 Aerobrake ManeuverTotal Energy Dissipated (J) Aerobrake # 11.49 x 10 8 J Aerobrake # 29.40 x 10 7 J Aerobrake Maneuver Options: › Aerobrake #1 = 3 Runs, Aerobrake # 2 = 7 Runs Ablative Heat Shield Required: › Material: AVOCAT 5026-39H/CG Heat Shield Mass Calculations: TOFD (days)Aerobrake # 1Aerobrake # 2 ≈ 5≈ 10

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Using the Atmospheric Drag to do a ΔV for entering into an Orbit Crew 3 Total Mass103.27 t Velocity6.4 km/s Ballute Mass3.07 t TPS Mass3 t Max g’s2.67g

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Crews 1-7 Mass100t Velocity3.5 km/s TPS Mass3.0 t Ballute Mass2.93 t Max gs4.07 Working on pinpoint landing Working on last 14km and handing over to hovering

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Cargo Mass68t – 91t Velocity6.0 km/s TPS Mass3.0 t Ballute Mass4.89 t Some of the Cargo Missions will be Aerocaptured to LMO Increased Mass gives a better ballute efficiency

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Direct Re-entry into Earth Use of Capsule with Subsonic Parachutes similar to Apollo/Orion PICA-X ablator Conditions Initial Velocity12.6 km/s Flight Path Angle-7.1 o Max gs6.6 g Heat Shield Mass 0.64 t

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Landed Mass Entry velocity (h = 150 km) 6 metric tons 12.57 km/s Interface flight path angle -7.065 Allowable variation +0.1 /-0.2 max deceleration6.58g 4g+ period230 sec Duration486 sec (8m 6s) Total stag point heating56.3 kJ/cm 2 Required TPS mass0.61 t Ending velocity (h = 4 km)75.6 m/s

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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)

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