An approximate atmospheric guidance law for aeroassisted plane change maneuvers
Abstract
An approximate optimal guidance law for the aeroassisted plane change problem is presented which is based upon an expansion of the HamiltonJacobiBellman equation with respect to the small parameter of Breakwell et al. (1985). The present law maximizes the final velocity of the reentry vehicle while meeting terminal constraints on altitude, flight path angle, and heading angle. The integrable zerothorder solution found when the small parameter is set to zero corresponds to a solution of the problem where the aerodynamic forces dominate the inertial forces. Higher order solutions in the expansion are obtained from the solution of linear partial differential equations requiring only quadrature integration.
 Publication:

AIAA Guidance, Navigation and Control Conference
 Pub Date:
 1988
 Bibcode:
 1988gnc..conf.1006S
 Keywords:

 Aeroassist;
 Aerodynamic Forces;
 Optimal Control;
 Reentry Vehicles;
 Spacecraft Guidance;
 Spacecraft Maneuvers;
 Dynamical Systems;
 Feedback Control;
 Flight Paths;
 Hamiltonian Functions;
 Linear Equations;
 Partial Differential Equations;
 Space Communications, Spacecraft Communications, Command and Tracking