Minimumfuel aerodynamic orbital plane change maneuvers
Abstract
Several minimumfuel, aerodynamically controlled, orbital plane change problems are formulated and solved as optimal control problems. A gradient projection algorithm is used to iteratively modify both the control functions, angle of attack and bank angle, and two control parameters to obtain the optimal trajectory. The atmospheric flight profile is combined with two Keplerian (twobody vacuum flight) arcs so that a complete orbittoorbit analysis results. The vehicle used in this investigation is the Space Transportation System Shuttle Orbiter. The effects of heat load constraint level and plane change angle are analysed.
 Publication:

AIAA, Aerospace Sciences Meeting
 Pub Date:
 January 1981
 Bibcode:
 1981aiaa.meetR....J
 Keywords:

 Aerodynamic Characteristics;
 Optimal Control;
 Space Shuttle Orbiters;
 Space Transportation System;
 Spacecraft Maneuvers;
 Trajectory Optimization;
 Angle Of Attack;
 Earth Orbits;
 Fuel Consumption;
 Orbital Servicing;
 Reentry Vehicles;
 Astrodynamics