星敏感器在轨姿态测量精度指标归属因子分析与评估

High precision star tracker’s attitude measure is the foundation for high precision attitude determination and control in satellite’s high resolution imaging and high precision tridimensional mapping. Currently, the research to improve star tracker’s attitude measure precision focuses on error analysis, error modeling, precision compensation and so on. The analysis and evaluation of index distribution factor for attitude measure precision of star tracker is researched in this project. The limit and restriction for each error influence factor is analyzed, based on the given attitude measure precision requirement of star tracker. The research idea of this project is to combine two opposite processes. The first process called positive process is as follows: the precision integrated analysis model for star tracker’s attitude measure is constructed at first, which is obtained by combining error source influence principle analysis and design parameter analysis, based on the star tracker’s on-orbit attitude measure course. And then the influence of each error factor to star tracker’s attitude measure precision is discussed. The main error factors called principal component factors for star tracker’s attitude measure are deduced by some methods including multiresponse - mulitfactorial experiment design, sparsity constraint and principal component analysis. The second process called inverse process is as follows: the error transfer mechanism for principal component factor to attitude measure precision is analyzed at first, and then the error transfer matrix is established. Moreover, the precision response function between principal component factors and star tracker’s attitude measure precision is presented by multiresponse - mulitfactorial experiment design, as well as nonlinear regression and model identification. Then, in the given attitude measure precision index requirement, the response boundary for each principal component factor is solved. This project can provide some feedback effect and technology support for attitude measure scheme design, error control method optimization and ultimate high precision attitude control.

高精度星敏感器姿态测量是满足高分辨率成像、高精度立体测绘等卫星姿态控制的前提。当前星敏感器姿态测量的研究工作主要集中在误差分析与建模、测试标定、误差校准等精度提升技术上。本项目研究星敏感器在轨姿态测量精度指标归属因子分析与评估问题。采用正-逆过程相结合的研究思路，正过程主要是建立基于误差源影响机理分析与设计参数分析相结合的星敏感器在轨姿态测量精度综合分析模型，通过多响应多因素精度评估试验的最优设计，吸收稀疏约束、主成分分析等方法，研究各误差因素对姿态测量精度的影响，确定主成分因素；逆过程则研究主成分因素对星敏感器在轨姿态测量精度的误差传播机理，通过多响应多因素试验优化设计，结合多元非线性回归分析，建立星敏感器在轨姿态测量精度与主成分因素间的一体化精度响应模型，进而以设定的精度指标为基础，反解各主成分因素的响应边界。为高精度姿态测量方案设计与优化及最终实现高精度姿态控制提供反馈及技术支撑。

本项目研究星敏感器在轨姿态测量精度指标归属因子分析与评估问题。采用正-逆过程相结合的研究思路，正过程是建立基于误差源影响机理分析与设计参数分析相结合的星敏在轨姿态测量精度综合分析模型，研究内部/外部误差对姿态测量精度的影响，确定影响在轨姿态测量精度的主成分因素；逆过程则研究主成分因素对星敏在轨姿态测量精度的误差传播机理，建立星敏在轨姿态测量精度与主成分因素间的综合精度响应模型，进而以设定的精度指标为基础，反解各主成分因素的响应边界。获得的主要研究成果如下：.（1）针对星敏研制及在轨姿态测量应用情况，结合星敏姿态测量全过程，建立了星敏在轨姿态测量精度分析空间及精度影响因素的层次及体系，构建了星敏在轨姿态测量过程中由各种抖动、振动等引起的扰动误差模型，形成了一套具有自主知识产权的星敏感器综合误差仿真分析模型。.（2）兼顾星敏输出数据稳定性、数据输出频率等指标体系，针对星敏姿态测量精度试验评估面临的响应关系复杂，试验区域复杂以及评估目的的多样等问题，研究了基于参数模型以及基于非参数模型的含定量定性因素的最优试验设计方法，确定了影响星敏姿态测量精度的外部误差因素中的主成分因素，并通过异方差回归分析方法构建了主成分因素与姿态测量精度之间的精度影响函数模型。.（3）系统研究了甚高精度（1角秒）星敏近零误差机理，建立了星敏在轨姿态测量精度与主成分因素间的一体化精度响应模型，对1角秒星敏的各项误差响应边界进行了计算，给出了各主要误差项的分配表，形成了1角秒星敏设计的响应边界。.（4）开展了星敏在轨姿态测量精度指标归属因子分析与评估的半物理仿真试验，从理论上证明了1角秒星敏的可实现性，为下一步星敏的设计奠定了基础。.通过四年的研究，项目组培养博士生3名，硕士生7名；参加学术交流25人次，发表学术论文35篇，其中SCI检索20篇，提交调研报告1份，出版专著2部，授权国家发明专利8项，1人获得省自然科学基金杰出青年基金资助。