Optimal Hybrid Attitude Control for Spacecraft in Elliptical Orbit Using a New Impulses Control Strategy

In this paper, a hybrid linear quadratic attitude control method is investigated for spacecraft in elliptical orbits. To seek the time instant in an orbital period when the control capability of using magnetic torquer alone is mostly weak. At this moment, the first impulse is applied to compensate for the required control gain. After the initial impulse has been already applied, the moment of using the subsequent impulse is selected according to a cost minimization principle. Simulation results demonstrate that this hybrid linear quadratic control method provides effective attitude control for spacecraft in an elliptical orbit.