Optimal Continuous Thrust Orbital Evasive Maneuvers from Geosynchronous Orbit
Abstract
A satellite under attack by another orbiting body relying on an explosive device to effect a kill has the problem of avoiding a volume space, in which its destruction is highly likely. To avoid this volume, the attackee could use continuous low thrust, such as that provided by electric propulsion or attitude control thrusters, if its warning time and orbital parameters were appropriate. A model is developed using optimal control theory and is solved numerically for the thrust direction using various magnitudes of thrust. The model progresses from a one satellite solution (where the threat is a fixed sphere in space) to a two satellite solution in which the distance between the threat and the target satellite is maximized. A minimum time solution for the single satellite problem is included. The results are given for several values of thrust, several maneuvering times, the optimized time-of-maneuver, and for circular and non-circular end orbits. Keywords: Evasive Maneuvers; Thrust controls; Geosynchronous satellite orbits; Optimization; Continuous thrust programming.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1986
- Accession Number
- ADA179413
Entities
People
- Robert D. Preissinger
Organizations
- Air Force Institute of Technology