A method for optimizing the preliminary design of spacecraft aerobraking missions

Details A method for optimizing the preliminary design of spacecraft aerobraking missions A method for optimizing the preliminary design of spacecraft aerobraking missions

Aug 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984adans..54.1165h&link_type=abstract

IN: Astrodynamics 1983; Proceedings of the Conference, Lake Placid, NY, August 22-25, 1983. Part 2 (A84-30526 13-13). San Diego,

Other

Aerobraking, Astrodynamics, Spacecraft Orbits, Aerodynamic Heating, Circular Orbits, Computerized Simulation, Mass, Optimization, Orbit Perturbation, Spacecraft Propulsion

Scientific paper

Two codes have been developed in order to find the optimal combination of aerobrake shielding area and initial orbit period which will yield a maximization of spacecraft mass in the final orbit. The first code is a simplified version which assumes that only aerodynamic drag disturbances obtain. The second code is more detailed, and allows any combination of drag with any of three other disturbances. A Venus aerobraking mission is taken as an example.

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