VEHICLE TRAJECTORY OPTIMIZATION FOR AEROCAPTURE AT MARS

This paper considers joint optimization of trajectory and configuratio n in determining a minimum-mass vehicle for aeroassisted capture of a payload to a specific orbit at Mars. Aerocapture by a vehicle with a b lunt aeroshell is assumed, supplemented by either chemical or nuclear thermal rocket impulses within the planet's sphere of influence. Optim al combinations of aeroshell size and exoatmospheric impulses are calc ulated for a range of entry velocities and constraints on integrated c onvective heating.