An approximate optimal guidance law for the aeroassisted plane change problem is presented which is based upon an expansion of the Hamilton-Jacobi-Bellman 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 zeroth-order 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.
An approximate atmospheric guidance law for aeroassisted plane change maneuvers
AIAA Guidance, Navigation and Control Conference ; 1988 ; Minneapolis, MN, United States
1988-01-01
Conference paper
No indication
English
Optimal aeroassisted maneuvers for orbital plane change
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