变质心航天器高动态姿态机动控制方法

The complicated space tasks (e.g., confrontation) pose extremely high requirements for the spacecraft attitude maneuver ability including rapid attitude tracking, precise attitude orientation, and agile attitude dodging. However, the structure complexity and flexibility of spacecrafts are ever increasing, and the spacecrafts possess complicated structure characteristics with flexible liquid-filled multi-bodies. As a result, the attitude control system (ACS) of spacecraft is a classic and complicated control system with center-of-mass (COM) variation, inertia variation, and multiple disturbances. Large deviation, fast time-varying, and sudden variation of the COM will be caused by the factors such as non-cooperative target capturing and configuration change, which induces the neutrally uncertainty coupled with unknown angular acceleration. Consequently, performance degradation and even instability of ACS may be caused. The multiple disturbances and uncertainties which come from the COM variation, inertia uncertainty, and unknown coupling torque bring great challenges to the traditional attitude control methods. This project will reveal the influence mechanism of the COM variation to the attitude dynamics. Then, the high-dynamic attitude maneuver control methods based on the refined disturbance estimation will be proposed. Finally, the test, analysis, and evaluation of attitude control performances will be accomplished based on the numerical simulation and semi-physical experiment platform. The bottleneck technology of ACS with fast maneuver and orientation capability will be broken through. The adaptation ability of spacecrafts to the complicated confrontation environment and the autonomous anti-disturbance control ability of spacecrafts will be improved. This research will provide theoretical supports for the attitude control technologies of spacecrafts of our nation.

博弈对抗等复杂空间任务对航天器的快速姿态跟踪、精密姿态对准与灵敏姿态躲避等机动能力需求极高。然而，航天器的结构复杂性与灵活性日益提升，具有大挠性充液多体复杂结构特征，使得航天器姿态控制系统是一个典型的变质心、变惯量、多干扰的复杂控制系统。非合作目标抓取与构型变化等因素会引起航天器质心大偏移、强时变与突变，带来与未知角加速度相耦合的中立不确定性，易导致姿态控制性能下降甚至失稳。来自质心变化、惯量不确定性、未知耦合力矩等环节的多源干扰与不确定性给传统姿态控制方法带来严峻挑战。本项目将揭示质心变化对姿态动力学的影响机理，提出基于干扰精细估计的高动态姿态机动控制方法，完成基于数值仿真与半物理实验平台的姿态控制性能测试分析与评估，突破具有快速机动对准能力的姿态控制系统瓶颈技术，增强航天器对复杂博弈对抗环境的适应能力与自主抗干扰控制能力，为我国航天器姿态控制系统技术提供理论支撑。

随着航天技术的飞速发展，太空博弈性与对抗性态势日益突出。目标侦查、监视与打击等典型博弈对抗任务对航天器的快速姿态跟踪、精密姿态对准、灵敏姿态躲避等姿态机动能力提出迫切需求。然而，航天器结构与环境日益复杂，具有大挠性充液多体结构特征与变构型能力，其姿态控制系统是一个典型的变质心、变惯量、多干扰的复杂控制系统。质心/惯量变化、挠性振动、环境干扰等多来源异质干扰与不确定性严重制约了姿态机动控制的精确性与快速性。同时，非合作目标抓取与构型变化等因素会引起航天器质心大偏移、强时变与突变，带来与未知角加速度相耦合的中立不确定性，易导致姿态控制性能下降甚至失稳。因此，变质心航天器高动态姿态机动控制具有重要的理论研究与工程应用价值。.针对上述问题，本项目按计划开展并完成了多源干扰下变质心航天器高动态姿态机动控制方法研究，包括变质心航天器深耦合动力学建模与干扰可抗性分析、基于精细量化干扰观测器的“省力”姿态机动控制、面向航天器姿态机动的执行机构复合抗干扰控制、基于干扰精细估计的航天器姿轨一体机动控制等研究内容。此外，完成了基于数值仿真和半物理实验平台的姿态控制性能测试分析。本项目揭示了航天器质心变化对动力学特性的影响机理，突破了异质干扰精细分离估计、中立不确定性下多元混合干扰的同时补偿与抑制等理论瓶颈问题，显著提升了多源干扰环境下航天器的自主机动对准能力。在本项目资助下，目前已在IEEE Transactions on Industrial Electronics、Control Engineering Practice等专业领域重要期刊上发表SCI论文4篇。通过本项目研究，增强了航天器在复杂博弈对抗环境下的自主抗干扰控制能力，为干扰对抗环境下航天器自主控制提供了理论与技术支撑。