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Aerodynamics Project Olympus

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**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

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**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 TPS Mass 3.0 t

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**Aerobrake Maneuver for Earth Propulsion (EP) Tug**

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 (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

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**Total Energy Dissipated (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 # 1 Aerobrake # 2 ≈ 5 ≈ 10 Aerobrake Maneuver Total Energy Dissipated (J) Aerobrake # 1 1.49 x 108 J Aerobrake # 2 9.40 x 107 J Heat Shield Mass (t) Aerobrake # 1 Aerobrake # 2 4.32 2.01

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**Earth - Aerobraking Tug**

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Mars -Aerocapture Using the Atmospheric Drag to do a ΔV for entering into an Orbit Crew 3 Total Mass t Velocity 6.4 km/s Ballute Mass 3.07 t TPS Mass 3 t Max g’s 2.67g

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**Mars -Crew Landing From MLO**

Crews 1-7 Mass 100t Velocity 3.5 km/s TPS Mass 3.0 t Ballute Mass 2.93 t Max gs 4.07 Working on pinpoint landing Working on last 14km and handing over to hovering

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Mars -Cargo Entry Cargo Mass 68t – 91t Velocity 6.0 km/s TPS Mass 3.0 t Ballute Mass 4.89 t Some of the Cargo Missions will be Aerocaptured to LMO Increased Mass gives a better ballute efficiency

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**Earth Descent Vehicle (EDV)**

Direct Re-entry into Earth Use of Capsule with Subsonic Parachutes similar to Apollo/Orion PICA-X ablator Conditions Initial Velocity 12.6 km/s Flight Path Angle -7.1o Max gs 6.6 g Heat Shield Mass 0.64 t

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**Earth Re-entry Trajectory**

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 deceleration 6.58g 4g+ period 230 sec Duration 486 sec (8m 6s) Total stag point heating 56.3 kJ/cm2 Required TPS mass 0.61 t Ending velocity (h = 4 km) 75.6 m/s

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**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)

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