高分辨率航天器姿轨一体化敏捷控制算法

As for high resolution earth observation, one of the key bottlenecks lays on the attitude and orbit coordinate control for agile satellite with observation time, position on orbit, attitude orientation being restricted. Aims at resolving this problem, this project chooses three key points as study objects, which are attitude-orbit coupling dynamic, coordinate control algorithm with multi-kinds of actuators under multi-restrictions, simulation and demonstration. Taking the agile earth observation as research background, with typical spacecraft configuration as reference, the model of attitude-orbit coupling dynamic for agile satellite will be firstly established. Multi-kinds actuator subsystem will be constituted by attitude control engine, moment gyroscope, flywheel, magnetic torque and their backups, based on which attitude-orbit coordinate controller for agile satellite will be designed, considering restrictions including time, angle and stability. Furthermore, control distribution trajectory for multi-kinds actuator will be studied. In order to accomplish the simulation and demonstration of the control trajectory presented, with estimation of agile capacity inspected, the dynamic and control emulation system for agile satellite will also be established. The theories and methods achieved by this project can be used to analyze agile performance and provide theoretical and technical support for the development and deployment of agile satellites.

对观测时间、轨道位置、姿态指向均存在严格约束的敏捷卫星姿轨协同控制是高分辨率对地观测的关键瓶颈之一。针对这一问题，本项目将敏捷卫星姿轨耦合动力学、多异类执行机构多约束姿轨协同控制算法和仿真验证作为研究着力点，以敏捷对地观测为任务背景，以典型航天器构型为结构参考，建立敏捷航天器姿态轨道耦合动力学模型，以姿控发动机、力矩陀螺、飞轮、磁力矩器等及其冗余备份组成多异类执行机构，设计基于多异类执行结构的多约束条件下(时间、角度、稳定度等)的敏捷卫星姿态/轨道协同控制器，设计姿轨控分系统的敏感器和执行机构配置方案，研究多异类执行机构控制分配方法，搭建敏捷卫星动力学与控制仿真系统，完成对控制策略的仿真验证和敏捷能力评估。本申请研究得到的理论和方法可用于敏捷卫星的敏捷方案优选、敏捷性能分析，为敏捷卫星的研制和空间部署提供理论和技术支持。

高分辨率航天器是我国空间遥感方向的重要天基平台，姿轨一体化动力学建模和敏捷控制是一种重要动力学与控制方式。申请人前期研究结果表明，对偶四元数能够有效描述两航天器相对位姿运动，据此设计的控制器能够实现姿轨一体化控制。本项目在前期工作基础上，基于对偶四元数的动力学建模方法建立描述单星姿轨一体化运动和双星姿轨一体化相对运动的动力学模型；基于对偶四元数一体化动力学模型设计了敏捷控制器，实现在有限时间内达到控制期望、满足高分成像精度要求；设计的基于模糊思想的控制分配算法能有效保证控制力矩输出，并有效避免CMG奇异。综上所述结果，本研究为高分辨率航天器的姿轨一体化敏捷控制奠定了坚实的工作基础。同时对于拓展对偶四元数在航天器本体位姿一体化建模方面的应用提供了重要的启示性思路。