NONLINEAR ADAPTIVE CONTROL OF A LEO SATELLITE PERTURBED BY ATMOSPHERIC DRAG, J_2 EFFECT, AND MOON GRAVITY

摘要

A nonlinear adaptive control based on the state feedback linearization technique was tested to control the perturbed motion of a LEO spacecraft in a three-body problem. The perturbations were caused by atmospheric drag, J_2 effect, and the Moon gravitational field. The nominal trajectory(reference) of the spacecraft is known and the difference between the output of the system (current trajectory) and the nominal trajectory is the basis of controllers design of this adaptive tracking problem.Two scenarios were considered to validate the performance of the controllers.