AAE 450 – Spacecraft Design 1 Mars Entry Aerodynamic Design Mark W. Vahle 18 January 2005 Aerodynamics Team Also working with Propulsion, Thermal, and Structures teams Mars Entry Method

AAE 450 – Spacecraft Design Problem - Entry Aerodynamics  L/D and Ballistic Coefficient Consideration  Blunt Conical Shape  Multiple descent systems  Aero Entry Body  Parachute  Rocket Assist Descent

AAE 450 – Spacecraft Design Useful Information  L/D between.2 and 1  Parachute Terminal Velocity (180 m/s)  Weight ≈ 100,000 kg  Diameter ≈ 45 m Parachute Diameters at Various Atmospheres* *Figure from Neumann, Temple. “Preliminary Design of a Mars Excursion Module,” AIAA Journal.