Interplanetary trajectory optimization of Mars aerobraking missions with constrained atmospheric entry velocities

Details Interplanetary trajectory optimization of Mars aerobraking missions with constrained atmospheric entry velocities Interplanetary trajectory optimization of Mars aerobraking missions with constrained atmospheric entry velocities

Aug 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991ads..conf.....s&link_type=abstract

AAS and AIAA, Astrodynamics Specialist Conference, Durango, CO, Aug. 19-22, 1991. 18 p.

Astronomy and Astrophysics

Astronomy

Aerobraking, Atmospheric Entry, Hypersonic Reentry, Interplanetary Trajectories, Manned Mars Missions, Trajectory Optimization, Earth-Mars Trajectories, Lift Drag Ratio, Spacecraft Trajectories

Scientific paper

Many current manned Mars mission studies are using low lift-to-drag ratio (L/D) vehicles to aerobrake at both Mars and earth. The use of these low L/D vehicles imposes constraints on the allowable velocity at the atmospheric interface. This paper will demonstrate that if these entry velocity constraints are incorporated into the interplanetary analysis, more opportunities can be achieved for a small increase in initial LEO mass. These additional opportunities result from varying the initial launch date, the encounter dates, and possibly using a powered Venus swingby on either the inbound or outbound transfer. This paper presents results for three atmospheric entry velocity ranges at Mars arrival and one velocity limitation upon Earth return. The results indicate that by carefully selecting the interplanetary trajectory, an optimum initial LEO mass mission can be found for even highly restrictive entry velocity missions in practically all of the 15 years studied.

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