Aerodynamics Project Olympus Ballute Material Ballute material is

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 TPS Mass Non-Ablators Carbon phenolic If a Ballute is usable than this Heat shield will work 3. 0 t

Aerobrake Maneuver for Earth Propulsion (EP) Tug Prior to Aerobrake Maneuver: Ø EET Location/Altitude: 256000 km (at Highest Energy Ellipse Orbit) Initial Aerobrake Parameters: Ø Atmospheric Entry Velocity: 10. 94 km/s Ø Constant Atmospheric Entry & Exit Altitude: 150 km (at LEO) Ø Perigee radius (Rp) for all Aerobrake runs: fixed at 115 km EP Parameters: Ø Maximum Diameter: 10 m Ø EET Mass: 29. 1 t Ø Tankage Mass & Size will vary per crew

Aerobrake Maneuver Options: › Aerobrake #1= 3 Runs, Aerobrake # 2 = 7 Runs TOFD (days) Aerobrake # 1 Aerobrake # 2 ≈5 ≈ 10 Ablative Heat Shield Required: › Material: AVOCAT 5026 -39 H/CG Aerobrake Maneuver Total Energy Dissipated (J) Aerobrake # 1 1. 49 x 108 J Aerobrake # 2 9. 40 x 107 J Heat Shield Mass Calculations: Heat Shield Mass (t) Aerobrake # 1 Aerobrake # 2 4. 32 2. 01

Earth - Aerobraking Tug

Mars -Aerocapture Using the Atmospheric Drag to do a ΔV for entering into an Orbit Crew 3 Total Mass 103. 27 t Velocity 6. 4 km/s Ballute Mass 3. 07 t TPS Mass 3 t Max g’s 2. 67 g

Mars -Crew Landing From MLO Crews 1 -7 Mass 100 t 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 14 km and handing over to hovering

Mars -Cargo Entry Cargo Mass 68 t – 91 t 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

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. 1 o Max gs 6. 6 g Heat Shield Mass 0. 64 t

Earth Re-entry Trajectory Landed Mass Entry velocity (h = 150 km) Interface flight path angle Allowable variation max deceleration 4 g+ period Duration Total stag point heating Required TPS mass Ending velocity (h = 4 km) 6 metric tons 12. 57 km/s -7. 065 +0. 1 /-0. 2 6. 58 g 230 sec 486 sec (8 m 6 s) 56. 3 k. J/cm 2 0. 61 t 75. 6 m/s

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)