多因素影响下空间飞行器有限时间高精度姿态控制

Spacecraft has important military and civil values. The robustness and precision of attitude control is a prerequisite as well as an important guarantee for spacecraft to accomplish various missions. Besides its nonlinearity and strong coupling, the spacecraft is also restricted by other factors including inaccurate modeling, internal uncertainties, external disturbances, actuators faults and actuators saturation. This project will consider the problem of finite-time attitude control for spacecraft with high accuracy under the influence of various factors, and the research background and the application goal is to improve the characteristics of spacecraft in such aspects as the fast finite-time convergence, high precision control, strong robustness, low energy consumption and autonomy. Firstly, an accurate system model is established based on the comprehensive analysis of different factors and the nonlinearity of the system. Secondly, we focus on the fast finite-time attitude control for spacecraft system under the influence of many factors, the self-regulation of the attitude and the large angle maneuver of finite-time robustness with low energy consumption, and the active real-time fault-tolerant control under actuators faults. Thirdly, an analysis on the stability of finite-time attitude control will be given to show a clear picture about the logical relationship among various adverse factors, the finite time and the stability domains. Finally, the effectiveness of the proposed methods is testified. This project research will enrich the finite-time theory of nonlinear system. The research achievements are expected to provide solid theoretical and technical support for the engineering application of the spacecraft attitude control system.

空间飞行器具有重要的军事和民用价值，姿态控制的鲁棒性和精确性是其完成各项任务的前提和保障。空间飞行器的模型具有非线性耦合特性，其运动性能受到建模不准确、内部不确定、外部干扰、执行器饱和及故障等因素的影响。本项目针对多因素影响下，空间飞行器系统有限时间高精度姿态控制问题，以提高我国空间飞行器未来型号有限时间快速收敛、甚高精度、强鲁棒、低能耗和强自主运行为研究背景和应用目标。首先，综合分析不同因素影响特性和系统结构非线性，建立精确系统模型。其次，研究多因素影响下空间飞行器快速有限时间姿态控制、低能耗下姿态自主调节和有限时间强鲁棒大角度机动、执行器故障下实时主动重构容错控制等问题。再次，完成有限时间姿态控制稳定性分析，并确立各种不利因素与有限时间和稳定域之间的逻辑关系。最后，完成研究成果的有效性验证。项目的研究将丰富有限时间控制理论，有望为空间飞行器姿态控制系统的实际工程应用提供理论和技术支撑。

本项目针对多因素影响下，空间飞行器系统有限时间高精度姿态控制问题。首先，综合分析不同因素影响特性和系统结构非线性，建立精确系统模型。其次，研究多因素影响下空间飞行器快速有限时间姿态控制、低能耗下姿态自主调节和有限时间强鲁棒大角度机动、执行器故障下实时主动重构容错控制等问题。再次，完成有限时间姿态控制稳定性分析，并确立各种不利因素与有限时间和稳定域之间的逻辑关系。最后，完成研究成果的有效性验证。为空间飞行器姿态控制系统的实际工程应用提供理论和技术支撑。