Orbital-Maneuver-Sequence Optimization.

摘要

This 15 month effort developed an orbital maneuver sequence optimization computer program and applied it to the generation of optimal co orbital attack maneuver sequences and to the generation of optimal evasion and return maneuver sequences. Rocket burns were modeled as impulse and coasts as conic arcs, or as near circular orbit approximations thereto. Parameters consisting of impulse components and coast lengths are adjusted iteratively by a variable metric (BFGS) gradient process with projection treatment of constraints. A minimum radius component, not ordinarily included in orbit transfer optimization studies, proved to be important for co-orbital attack maneuver sequences. Families of such sequences are explored and the effects of various operational constraints investigated. Optimal in plane evasive maneuvering is studied subject to return-to-orbit and return-to-position in orbit constraints. keywords: Orbital Maneuvering; Space Defense.