航天器全控制回路抗干扰控制理论与实验验证

The orbiting spacecraft is usually affected by various disturbances coming from internal and external, modeling error and even component fault and/or failure. Traditional navigation and control system are difficult to meet the increasing requirements of accuracy and reliability for spacecraft, and full loop anti-disturbance control and fault-tolerant navigation and control have become the main bottlenecks for the development of high reliability of navigation, control system and autonomous technology. In this research, to improve the reliability and autonomous operation of new spacecraft in orbit as background and application of objective, attitude determination and attitude control methods under multiple disturbances will be discussed. A novel elegant approach integrating navigation and control together will be developed and the estimatility,compensability and inhibitability of disturbance will also be analyzed. Furthermore, to improve the fault diagnosis ability of spacecraft systems in the design phase, a novel approach to quantitative fault diagnosability evaluation for a class of spacecraft nonlinear systems is proposed, and novel feedback-based fault diagnosis methods for effective fault detection and fault tolerant control technique are also to be developed and deeply discussed. A new semi-physical simulation platform will be established for a spacecraft control system, to verify the effectiveness of the proposed navigation and control theory and methods, which together can provide effective control theory foundations and design references for improving the spacecraft safety and performance. In a word, this project aims to solve the common scientific problems for anti-disturbance and fault-tolerant navigation and control system during the spacecraft mission, and also to provide the theoretical and technical foundation for future application, and also to enhance the ability of independent innovation of China's aerospace industry.

复杂环境下航天器受到来自内、外部干扰、建模误差以及部件故障等多种因素影响，传统的导航和控制系统难以满足航天器日益提高的精度和可靠性要求，从航天器姿态测量到控制的全回路系统的抗干扰导航与控制已经成为一项核心技术。研究多源干扰下航天器姿态确定和基于复合分层控制基础理论的新型精细导航与控制一体化方法，分析航天器系统干扰的可估计性、可补偿性、可抑制度；研究多源干扰下航天器系统故障的可诊断性评价与诊断方法的交互式联合设计方法，发展基于闭环反馈的故障诊断、抗干扰及容错控制理论及技术，提出一套较为系统的完备的多源干扰下全控制回路误差分析、精细抗干扰导航与控制理论方法；研制具有开放性的多源干扰环境下航天器姿态确定与控制一体化综合测试分析平台，完成多指标性能测试与分析。研究成果将推动多源干扰与故障下导航与控制基础理论与应用研究，突破复杂环境下航天器抗干扰容错导航与控制技术，提升我国航空航天领域自主创新能力。

本项目针对新型航天器高精度、高可靠性导航、制导一体化控制技术的迫切需求，充分考虑复杂环境下航天器所受内外部干扰、建模误差以及部件故障等多种影响因素，对航天器全控制回路抗干扰控制理论与实验验证展开深入研究。首先探究了航天器不完备干扰信息的表征和影响机理分析方法，然后提出了不同的航天器不完备、不确定干扰信息的估计与隔离方案，进一步研究了航天器精细抗干扰相对导航方法，提出了航天器故障诊断的智能化方法与控制分配方案，并研制了一套完备的航天器全回路控制一体化系统测试分析及相对运动试验平台。该项目的研究突破了多源干扰下精细导航与控制一体化中的关键技术，有效解决了信息缺失及故障情况下高精度、高可靠性导航和控制难题，显著提升了复杂环境下航天器抗干扰容错导航和控制能力，相关成果已在多个卫星型号任务中获得应用。.通过对项目的深入研究，研究成果获国家技术发明二等奖1项、国防技术发明一等奖1项、军队科学技术奖科学技术类一等奖1项、江苏省科学技术进步二等奖1项、机电系统领域著名国际学术奖-永守赏学术奖1项，且发表学术论文80篇（SCI检索论文54篇，EI检索论文26篇），尤其是在航空航天领域的权威期刊—美国航空航天学会的导航、控制与动力学期刊（AIAA JGCD）上发表7篇，IEEE系列汇刊发表32篇，同时授权国家发明专利41项，计算机软件著作权8项，出版英文专著2部，研制了航天器抗干扰控制一体化系统测试分析及相对运动试验平台，且项目成果成功完成3个应用转化。与此同时，在项目的研究过程中，项目组成员中1人入选教育部长江学者特聘教授，1人获批国家杰出青年科学基金项目，2人获批国家优秀青年基金项目，2人入选IEEE Fellow。