双超敏捷卫星载荷舱扰动补偿研究
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摘要
文章针对动静隔离式双超敏捷卫星载荷舱存在活动部件时,载荷舱指向精度下降的问题,依据双超敏捷卫星的特点,对双超敏捷卫星载荷舱进行了扰动补偿研究。首先,建立了载荷舱活动部件扰动模型以及双超敏捷卫星模型,扰动包括反作用飞轮小幅值高频随机扰动和摆镜扫描大幅值规律性扰动;然后,在采用飞轮扰动被动隔振和摆镜扫描主动补偿的基础上,利用双超敏捷卫星磁浮机构带宽高的特点进行二次主动隔振。仿真结果表明:在进行飞轮扰动被动隔振以及摆镜扫描扰动主动补偿后,载荷舱的指向精度提高到6×10~(-3)(deg);磁浮机构进行二次主动隔振后,载荷舱的指向精度提高到2×10~(-4)(deg)。该方法为双超敏捷卫星载荷舱受扰时指向精度下降问题提供解决思路。利用磁浮机构不仅可以隔离平台舱的扰动,而且可以提供高带宽主动控制力来抑制载荷舱的扰动。但在具体实施过程中还需考虑载荷舱与平台舱之间的碰撞问题。
In order to improve pointing accuracy of the payload module,which has moving parts,disturbances compensation of the payload module is investigated in this paper based on the characteristics of the disturbance-free payload agility satellite. Firstly,the dynamics models of disturbances and the disturbance-free payload agility satellite are established,disturbances include random disturbance with small magnitude and high frequency of reaction flywheels and regular disturbance with large magnitude and low frequency of a gimbaled mirror. Then,the active isolation scheme is developed to realize high pointing accuracy based on characteristics of the satellite. Simulation results show that: the pointing accuracy of the payload module is 6 × 10~(-3)(deg) before using the active isolator,and pointing accuracy of the payload module raises to 2 × 10~(-4)(deg) by using the active isolator. This method can be used to improve pointing accuracy of the payload module with disturbances. The maglev mechanism can not only isolate vibrations from the platform module,but also suppress disturbances in the payload module. It must be noted that the collision between the payload module and the platform module should be considered in engineering.
In order to improve pointing accuracy of the payload module,which has moving parts,disturbances compensation of the payload module is investigated in this paper based on the characteristics of the disturbance-free payload agility satellite. Firstly,the dynamics models of disturbances and the disturbance-free payload agility satellite are established,disturbances include random disturbance with small magnitude and high frequency of reaction flywheels and regular disturbance with large magnitude and low frequency of a gimbaled mirror. Then,the active isolation scheme is developed to realize high pointing accuracy based on characteristics of the satellite. Simulation results show that: the pointing accuracy of the payload module is 6 × 10~(-3)(deg) before using the active isolator,and pointing accuracy of the payload module raises to 2 × 10~(-4)(deg) by using the active isolator. This method can be used to improve pointing accuracy of the payload module with disturbances. The maglev mechanism can not only isolate vibrations from the platform module,but also suppress disturbances in the payload module. It must be noted that the collision between the payload module and the platform module should be considered in engineering.
引文
[1]Foster C L,Tinker M L,Nurre G S,et al.Solar-array-induced disturbance of the Hubble Space、Telescope pointing system[J].Journal of Spacecraft and Rockets,1995,32(4):634-644.
[2]Lee A Y,Yu J W,Kahn P B,et al.Space interferometry mission spacecraft pointing error budgets[J].IEEETrans.on Aerospace and Electronic Systems,2002,38(2):502-514.
[3]梁月华,王辉,丁辉兵.卫星姿轨控制对大型柔性索网天线在轨指向影响分析[J].空间电子技术,2018,4:89-94.
[4]王旭艳,李锦伟,李东涛,等.新型星载高分辨率洋流探测雷达技术[J].空间电子技术,2018,4:58-62.
[5]He P,Yang J.Feasibility analysis of near space un-powered guided bomb when attacking aerial target based on genetic algorithm[C]//Information Engineering and Computer Science,2009.ICIECS 2009.International Conference on.IEEE,2009:1-4.
[6]Jones D I,Owens A R,Owen R G.A control system for a microgravity isolation mount[J].IEEE Trans.on Control Systems Technology,1996,4(4):313-325.
[7]张伟,赵艳彬,廖鹤,等.动静隔离主从协同控制双超卫星平台设计[J].上海航天,2014,5:7-11,30.
[8]王俊.扰动隔离载荷与卫星平台一体化控制方法研究[D].哈尔滨:哈尔滨工业大学,2016.
[9]李太平.航天器微振动及其抑制技术研究[D].哈尔滨:哈尔滨工业大学,2013.
[10]Li Q,Liu L,Ma X,et al.Development of Multi-target Acquisition,Pointing and Tracking System for Airborne Laser Communication[J].IEEE Trans.on Industrial Informatics,2018.
[11]Liu C,Jing X,Daley S,et al.Recent advances in micro-vibration isolation[J].Mechanical Systems and Signal Processing,2015,56:55-80.
[12]Markley F L,Bauer F H,Deily J J,et al.Attitude Control System Conceptual Design for Geostationary Operational Environmental Satellite Spacecraft Series[J].Journal of Guidance,Control and Dynamics,1995,18(2):247-255.
[2]Lee A Y,Yu J W,Kahn P B,et al.Space interferometry mission spacecraft pointing error budgets[J].IEEETrans.on Aerospace and Electronic Systems,2002,38(2):502-514.
[3]梁月华,王辉,丁辉兵.卫星姿轨控制对大型柔性索网天线在轨指向影响分析[J].空间电子技术,2018,4:89-94.
[4]王旭艳,李锦伟,李东涛,等.新型星载高分辨率洋流探测雷达技术[J].空间电子技术,2018,4:58-62.
[5]He P,Yang J.Feasibility analysis of near space un-powered guided bomb when attacking aerial target based on genetic algorithm[C]//Information Engineering and Computer Science,2009.ICIECS 2009.International Conference on.IEEE,2009:1-4.
[6]Jones D I,Owens A R,Owen R G.A control system for a microgravity isolation mount[J].IEEE Trans.on Control Systems Technology,1996,4(4):313-325.
[7]张伟,赵艳彬,廖鹤,等.动静隔离主从协同控制双超卫星平台设计[J].上海航天,2014,5:7-11,30.
[8]王俊.扰动隔离载荷与卫星平台一体化控制方法研究[D].哈尔滨:哈尔滨工业大学,2016.
[9]李太平.航天器微振动及其抑制技术研究[D].哈尔滨:哈尔滨工业大学,2013.
[10]Li Q,Liu L,Ma X,et al.Development of Multi-target Acquisition,Pointing and Tracking System for Airborne Laser Communication[J].IEEE Trans.on Industrial Informatics,2018.
[11]Liu C,Jing X,Daley S,et al.Recent advances in micro-vibration isolation[J].Mechanical Systems and Signal Processing,2015,56:55-80.
[12]Markley F L,Bauer F H,Deily J J,et al.Attitude Control System Conceptual Design for Geostationary Operational Environmental Satellite Spacecraft Series[J].Journal of Guidance,Control and Dynamics,1995,18(2):247-255.