Robust Tracking Guidance for Zero Propellant Maneuver, Part 2: Simulation Verification

摘要

In order to enhance the performance of the Zero Propellant Maneuver (ZPM) for the space station large angle attitude maneuver, a robust tracking guidance strategy is proposed in Part 1 of this paper. Here ZPM simulations, under typical scenario of initial state errors, environmental torque modeling error and parameter uncertainty, are carried out. It is shown that the disturbance effects arising from different sources are attenuated or even eliminated, and the maneuver target may be successfully reached, which verifies the capacity of the proposed approach in enhancing the robustness of the ZPM.