Hypervelocity orbital intercept guidance
Abstract
Terminal guidance of a hypervelocity exo-atmospheric orbital interceptor with free end-time is examined. The pursuer is constrained to lateral thrusting with the evader modeled as an ICBM in its final boost phase. Proportional navigation, optimal control using certainty equivalence, dual control, and control with optimum thrust spacing are all examined. Also, a new approach called certainty control is developed for this problem. This algorithm constrains the final state to a function of projected estimate error to reduce control energy expenditure. All methods model the trajectories using splines and employ eight state Extended Kalman Filters with line-of-sight and range updates. The relative effectiveness of these control strategies is illustrated by applying them to various intercept problems.
- Publication:
-
Ph.D. Thesis
- Pub Date:
- April 1988
- Bibcode:
- 1988PhDT........16A
- Keywords:
-
- Aerospace Vehicles;
- Orbital Velocity;
- Satellite Interceptors;
- Spline Functions;
- Terminal Guidance;
- Trajectory Optimization;
- Algorithms;
- Hypersonic Speed;
- Interception;
- Kalman Filters;
- Missile Control;
- Optimal Control;
- Proportional Control;
- Thrust;
- Space Communications, Spacecraft Communications, Command and Tracking