An innovative satellite sunlight-reflection staring attitude control with angular velocity constraint

摘要

A so-called sunlight-reflection staring control for spacecraft on low Earth orbit is discussed such that the sunlight, reflected by an on-board reflector, will point to a target point on Earth surface during a short period of time. The new method begins with the establishment of the target reference frame, whose attitude quaternion, angular velocity and acceleration are calculated afterwards. An back-stepping based control technique is adopted to achieve the attitude tracking and guarantee the tracking error angular velocity will be constrained in a predefined region. Moreover, the conditions under which the sunlight-reflection staring is analyzed, and the geographic information of the actual staring point are computed to analyze the accuracy of the method. The simulation section results validate the control performance. (C) 2020 Elsevier Masson SAS. All rights reserved.