Neighboring optimal guidance for aeroassisted orbital plane change
Abstract
The neighboring extremal method is used here to develop the neighboring optimal guidance laws for aeroassisted orbital plane change. The space vehicle is assumed to enter the earth's atmosphere from GEO. The nominal optimal trajectory for maximizing the orbital plane change is computed with specified initial and final conditions. Two cases are investigated, both having the same initial conditions but with different final exit speeds, one for a supercircular exit and the other for a circular exit. In both cases, the perturbed trajectories converge to their corresponding nominal optimal trajectories in a not too long time.
- Publication:
-
Dresden International Astronautical Federation Congress
- Pub Date:
- October 1990
- Bibcode:
- 1990dres.iafcV....C
- Keywords:
-
- Aeroassist;
- Orbit Transfer Vehicles;
- Satellite Guidance;
- Trajectory Optimization;
- Optimal Control;
- Reentry Trajectories;
- Spacecraft Guidance;
- Astrodynamics