大气阻力摄动下的绳系辅助离轨系统的相对姿态跟踪控制研究

Relative Attitude Tracking Control of Tether-assisted Deorbit System Under Drag Perturbation

以绳系辅助离轨系统为背景,考虑到大气阻力摄动和子星——返回舱的非质点因素,返回舱与绳系辅助离轨系统的相对姿态将产生大幅周期性变化,这将影响或破坏系统的稳定性;同时三自由度下绳系系统的展开控制和绳系系统横向振动抑制控制也对返回舱姿态的稳定性和精度提出了更高的要求。基于此,本文建立了大气阻力摄动下的绳系系统的展开动力学和返回舱姿态动力学模型;并在此基础上,设计了绳系辅助离轨系统的相对姿态跟踪控制策略。通过数学仿真来验证大气阻力摄动下该姿态跟踪控制算法的有效性,结果表明,该控制律能够有效控制绳系辅助离轨系统的相对姿态,满足展开控制的需要。

Under the background of mission on tether-assisted deorbit system, the relative attitude of the tethered system will vary periodically under drag perturbation, which will affect or destroy the stabilization of the system; and more requirements of attitude control are needed for the control of a tethered system with three degrees of freedom and the control on the transverse vibration of tethered satellite. So the dynamic models of the deployment of tether-assisted deorbit system and capsule attitude include drag perturbation are proposed, and based on this model a relative attitude tracking control strategy is given; then a mathematic simulation is provided to validate the control strategy; the results show that the provided method can control the relative attitude of the system and meet the needs of controlling the deployment of tethered system.