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 exit-state 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