Vehicle/trajectory optimization for aerocapture at Mars

Details Vehicle/trajectory optimization for aerocapture at Mars Vehicle/trajectory optimization for aerocapture at Mars

Jan 1994

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1994jansc..42...71w&link_type=abstract

Journal of the Astronautical Sciences (ISSN 0021-9142), vol. 42, no. 1, p. 71-89

Astronomy and Astrophysics

Astronomy

Aeroassist, Aerocapture, Interplanetary Spacecraft, Spacecraft Design, Spacecraft Trajectories, Trajectory Optimization, Convective Heat Transfer, Mars (Planet), Spacecraft Structures

Scientific paper

This paper considers joint optimization of trajectory and configuration in determining a minimum-mass vehicle for aeroassisted capture of a payload to a specific orbit at Mars. Aerocapture by a vehicle with a blunt aeroshell is assumed, supplemented by either chemical or nuclear thermal rocket impulses within the planet's sphere of influence. Optimal combinations of aeroshell size and exoatmospheric impulses are calculated for a range of entry velocities and constraints on integrated convective heating.

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