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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.

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Presentation on theme: "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."— Presentation transcript:

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2 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

3  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

4  Prior to Aerobrake Maneuver:  EET Location/Altitude: km (at Highest Energy Ellipse Orbit)  Initial Aerobrake Parameters:  Atmospheric Entry Velocity: 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 

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

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

8 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

9 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

10  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

11 Landed Mass Entry velocity (h = 150 km) 6 metric tons km/s Interface flight path angle  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

12  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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