Optimal impulsive manoeuvres and aerodynamic braking
Abstract
A method developed for obtaining solutions to the aerodynamic braking problem, using impulses in the exoatmospheric phases is discussed. The solution combines primer vector theory and the results of a suboptimal atmospheric guidance program. For a specified initial and final orbit, the solution determines: (1) the minimum impulsive cost using a maximum of four impulses, (2) the optimal atmospheric entry and exitstate vectors subject to equality and inequality constraints, and (3) the optimal coast times. Numerical solutions which illustrate the characteristics of the solution are presented.
 Publication:

Optimal Control Applications and Methods
 Pub Date:
 March 1985
 Bibcode:
 1985OCAM....6....1J
 Keywords:

 Aerobraking;
 Optimal Control;
 Orbit Transfer Vehicles;
 Spacecraft Maneuvers;
 Trajectory Optimization;
 Atmospheric Entry;
 Constraints;
 Orbital Mechanics;
 Spacecraft Guidance;
 State Vectors;
 Astrodynamics