Accession Number:

ADA179413

Title:

Optimal Continuous Thrust Orbital Evasive Maneuvers from Geosynchronous Orbit

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1986-12-01

Pagination or Media Count:

78.0

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.

Subject Categories:

  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE