地心轨道引力波探测无拖曳系统平动控制策略
2024,46(2):36-48
郝立维
哈尔滨工业大学 卫星技术研究所, 黑龙江 哈尔滨 150001，haolw@hit.edu.cn
张锦绣
中山大学 航空航天学院, 广东 深圳 518107，zhangjinxiu@sysu.edu.cn
王继河
中山大学 航空航天学院, 广东 深圳 518107
张谕
中山大学 天琴中心, 广东 珠海 519082
孙玥
上海市空间智能控制技术重点实验室, 上海 201109;
上海航天控制技术研究所, 上海 201109
哈尔滨工业大学 卫星技术研究所, 黑龙江 哈尔滨 150001，haolw@hit.edu.cn
张锦绣
中山大学 航空航天学院, 广东 深圳 518107，zhangjinxiu@sysu.edu.cn
王继河
中山大学 航空航天学院, 广东 深圳 518107
张谕
中山大学 天琴中心, 广东 珠海 519082
孙玥
上海市空间智能控制技术重点实验室, 上海 201109;
上海航天控制技术研究所, 上海 201109
摘要：
探讨了一种针对空间引力波探测任务的在轨无拖曳控制技术,基于未来可行的地心轨道探测任务背景进行分析设计,并对搭载两颗检验质量的在轨无拖曳系统进行航天器与质量块间相对运动动力学及耦合特性建模。同时,初步分析了任务中无拖曳系统指标和摄动,并设计了基于频域H∞最优控制理论的系统相对平动控制律。数值仿真结果表明,当双检验质量在轨无拖曳系统各检验质量按激光测距呼吸角排列时,采用无固定追踪点策略且在非敏感轴无悬浮控制输入的情况下,可以实现航天器对基准点的追踪,并满足系统频域性能指标的要求。同时,每颗检验质量的时域偏移量可以控制在微米级别,从而获得任务所需的纯引力基准。
探讨了一种针对空间引力波探测任务的在轨无拖曳控制技术,基于未来可行的地心轨道探测任务背景进行分析设计,并对搭载两颗检验质量的在轨无拖曳系统进行航天器与质量块间相对运动动力学及耦合特性建模。同时,初步分析了任务中无拖曳系统指标和摄动,并设计了基于频域H∞最优控制理论的系统相对平动控制律。数值仿真结果表明,当双检验质量在轨无拖曳系统各检验质量按激光测距呼吸角排列时,采用无固定追踪点策略且在非敏感轴无悬浮控制输入的情况下,可以实现航天器对基准点的追踪,并满足系统频域性能指标的要求。同时,每颗检验质量的时域偏移量可以控制在微米级别,从而获得任务所需的纯引力基准。
基金项目：
广东省基础与应用基础研究重大资助项目(2019B030302001)
广东省基础与应用基础研究重大资助项目(2019B030302001)
Translational tracking strategy of drag-free system for gravitational wave detection in geocentric orbit
HAO Liwei
Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150001, China,haolw@hit.edu.cn
ZHANG Jinxiu
School of Aeronautics and Astronautics, Sun Yat-Sen University, Shenzhen 518107, China,zhangjinxiu@sysu.edu.cn
WANG Jihe
School of Aeronautics and Astronautics, Sun Yat-Sen University, Shenzhen 518107, China
ZHANG Yu
TianQin Research Center, Sun Yat-Sen University, Zhuhai 519082, China
SUN Yue
Shanghai Key laboratory of Aerospace Intelligent Control Technology, Shanghai 201109, China;
Shanghai Institute of Spaceflight Control Technology, Shanghai 201109, China
Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150001, China,haolw@hit.edu.cn
ZHANG Jinxiu
School of Aeronautics and Astronautics, Sun Yat-Sen University, Shenzhen 518107, China,zhangjinxiu@sysu.edu.cn
WANG Jihe
School of Aeronautics and Astronautics, Sun Yat-Sen University, Shenzhen 518107, China
ZHANG Yu
TianQin Research Center, Sun Yat-Sen University, Zhuhai 519082, China
SUN Yue
Shanghai Key laboratory of Aerospace Intelligent Control Technology, Shanghai 201109, China;
Shanghai Institute of Spaceflight Control Technology, Shanghai 201109, China
Abstract：
An on-orbit drag-free control technique for spaceborne gravitational wave detection missions was discussed. Based on the analysis and design of a possible future geocentric orbit detection mission, the relative motion dynamics and coupling characteristics between the spacecraft and mass blocks of an on-orbit drag-free system with with two test masses were modeled. At the same time, the performance index and perturbation of the drag-free system in the mission were preliminarily analyzed, and a relative translational control law based on frequency domain H∞ optimal control theory was designed. Numerical simulation results show that when the test masses of the two-test-mass on-orbit drag-free system are arranged according to the breathing angle of laser rangefinder, without a fixed tracking point strategy and without suspension control input along the non-sensitive axis, the spacecraft can achieve tracking of the reference point while meeting the frequency domain performance index of the system. At the same time, the time domain displacement of each test mass can be controlled to the micron level, thus obtaining the pure gravitational reference required by the mission.
An on-orbit drag-free control technique for spaceborne gravitational wave detection missions was discussed. Based on the analysis and design of a possible future geocentric orbit detection mission, the relative motion dynamics and coupling characteristics between the spacecraft and mass blocks of an on-orbit drag-free system with with two test masses were modeled. At the same time, the performance index and perturbation of the drag-free system in the mission were preliminarily analyzed, and a relative translational control law based on frequency domain H∞ optimal control theory was designed. Numerical simulation results show that when the test masses of the two-test-mass on-orbit drag-free system are arranged according to the breathing angle of laser rangefinder, without a fixed tracking point strategy and without suspension control input along the non-sensitive axis, the spacecraft can achieve tracking of the reference point while meeting the frequency domain performance index of the system. At the same time, the time domain displacement of each test mass can be controlled to the micron level, thus obtaining the pure gravitational reference required by the mission.
收稿日期：
2022-07-28
2022-07-28
