Low-Thrust Optimal Orbit Raising with Plane Change

A new guidance scheme for the problem of Low-thrust transfer between inclined orbits is developed within the frame/work of optimal control theory. The objective of the guidance scheme is to provide the appropriate thrust steering program that will transfer the vehicle from an inclined low e-art.h, orbits to the high earth orbits. The presented guidance scheme is determined, using optimal control theory such that minimum time performance measure is determined and boundary conditions for these unspexAfisd final time problems are satisfied. One of the novelties of this work is changing independent, variable from time to thrust angle and considering properties of autonomous system equations to reduce to one where exact analytical solution is obtained.