Optimal control of aeroassisted plane change maneuver using feedback expansions
Abstract
A guidance law for an aeroassisted plane change maneuver is developed by an asymptotic expansion technique using a small parameter which essentially represents the ratio of the inertial forces to the atmospheric forces. This guidance law minimizes the energy loss while meeting terminal constraints on the altitude, flight path angle, and heading angle. By neglecting the inertial forces, the resulting optimization problem is integrable and can be determined in closed form. This zerothorder solution is the first term in an asymptotic series solution of the HamiltonJacobiBellman equation. The remaining terms are determined from the solution of a firstorder, linear partial differential equation whose solution requires only quadrature integration. Our initial results in using this guidance scheme are encouraging.
 Publication:

IN: Atmospheric Flight Mechanics Conference
 Pub Date:
 1986
 Bibcode:
 1986atfm.conf..259M
 Keywords:

 Aeroassist;
 Optimal Control;
 Spacecraft Maneuvers;
 Trajectory Optimization;
 Transfer Orbits;
 Asymptotic Methods;
 Energy Dissipation;
 Partial Differential Equations;
 Series Expansion;
 Trajectory Control;
 Astrodynamics