Maximum orbit plane change with heattransferrate considerations
Abstract
Two aerodynamic maneuvers are considered for maximizing the plane change of a circular orbit: gliding flight with a maximum thrust segment to regain lost energy (aeroglide) and constant altitude cruise with the thrust being used to cancel the drag and maintain a high energy level (aerocruise). In both cases, the stagnation heating rate is limited. For aeroglide, the controls are the angle of attack, the bank angle, the time at which the burn begins, and the length of the burn. For aerocruise, the maneuver is divided into three segments: descent, cruise, and ascent. During descent the thrust is zero, and the controls are the angle of attack and the bank angle. During cruise, the only control is the assumedconstant angle of attack. During ascent, a maximum thrust segment is used to restore lost energy, and the controls are the angle of attack and bank angle. The optimization problems are solved with a nonlinear programming code known as GRG2. Numerical results for the Maneuverable Reentry Research Vehicle with a heatingrate limit of 100 Btu/ft(2)s show that aerocruise gives a maximum plane change of 2 deg, which is only 1 deg larger than that of aeroglide. On the other hand, even though aerocruise requires two thrust levels, the cruise characteristics of constant altitude, velocity, thrust, and angle of attack are easy to control.
 Publication:

Journal of Guidance Control Dynamics
 Pub Date:
 June 1990
 DOI:
 10.2514/3.25362
 Bibcode:
 1990JGCD...13..492L
 Keywords:

 Heat Transfer;
 Spacecraft Maneuvers;
 Transfer Orbits;
 Angle Of Attack;
 Circular Orbits;
 Equations Of Motion;
 Gliding;
 Nonlinear Programming;
 Optimization;
 Thrust;
 Astrodynamics