Closed form optimal continuous guidance scheme for new dynamic of electrical propulsion plane change transfers

摘要

New guidance policies for the problem of low-thrust transfer between inclined orbits are developed within the framework of optimal control theory. The objectives of this guidance schemes are to provide appropriate thrust steering programmes that will transfer the vehicle from inclined low earth orbits to high earth orbits. The presented guidance schemes are determined by using optimal control theory such that two optimal performance measures are minimized. In this work, the independent variable is changed from time to thrust angle and some properties of autonomous system equations are considered to obtain the exact closed form solutions. Three states are considered, orbital inclination, velocity, and ascending node, to establish this dynamic system. Finally, two performances are investigated for new class of electrical propulsion plane change manoeuvres.