AUTONOMOUS ORBIT CONTROL FOR SPACECRAFT ON ELLIPTICAL ORBITS USING A NON-INERTIAL COORDINATE FRAME

摘要

A method for designing an autonomous orbit controller for spacecraft on elliptical orbits is presented. For the derivation of the linearized differential and difference equations of motion, a non-inertial coordinate frame is utilized which coincides with the one which is applied in the well-known Clohessy-Wiltshire equations for small excentricities. The derivation takes atmospheric drag into account. The resulting time-discrete periodic system is augmented by an integrator state. A control law is obtained by applying linear optimal periodic control. The orbit controller is tested and verified in simulation runs.