基于导星电子星图模拟器的卫星控制系统半物理试验方法  被引量:2

Semi-physical Test Method of Satellite Control System Based on Fine Guidance Sensor Electronic Star Map Simulator

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作  者:李津淞 刘爽 李东 秦根健 王磊 LI Jin-song;LIU Shuang;LI Dong;QIN Gen-jian;WANG Lei(Innovation Academy for Microsatellites of CAS,Shanghai 201210,China)

机构地区:[1]中国科学院微小卫星创新研究院,上海201210

出  处:《科学技术与工程》2021年第17期7369-7376,共8页Science Technology and Engineering

基  金:中法天文卫星项目(YOXGFA1001)。

摘  要:为了实现卫星的高精度高稳定度控制,中法天文卫星建立了卫星姿轨控半物理仿真试验系统。对该系统采用导星电子星图模拟器引入仿真闭环进行研究。首先,将导星敏感器作为高精度姿态测量部件引入控制系统,地面动力学为其提供输入信息。接着,高精度测量单机和高精度控制机构引入到闭环中。然后,粗测量敏感器和粗控执行机构由数学模型替代。最后,通过地面实时系统将控制系统、星务计算机、载荷计算机和整星电源系统组成了实时仿真验证系统。实验结果表明:在地面半物理条件下,可以达到导星进入开小窗条件,y、z轴稳定度达到2(″)/10 s及5(″)/100 s。导星敏感器可以提高姿态测量精度和姿态控制的稳定度。满足控制稳定度在亚角秒级别卫星的要求。In order to control the satellite with high precision and stability,a semi-physical simulation system for satellite attitude and orbit control was established by Chinese and French astronomical satellite.The simulation closed-loop of the fine guidance sensor electronic star map simulator used in the system was studied.Firstly,the fine guidance sensor was introduced into the control system as a high precision attitude measurement component,and the input information was provided by ground dynamics.Secondly,the high precision measuring sensors and high precision control actuators were introduced into the closed loop.Thirdly,the rough measuring sensors and rough control actuators were replaced by mathematical model.Finally,the real-time simulation verification system was composed of the control system,the satellite management unit,the payload computer and the satellite power system through the ground real-time system.The experimental results show that under the condition of semi-physical test,small open window conditions of fine guidance sensor can be achieved,and the y and z axis stability can reach 2(″)/10 s and 5(″)/100 s.The attitude measurement accuracy and attitude control stability can be improved by the fine guidance sensor.It meets the requirement of satellite with control stability of sub-angular second.

关 键 词:高精度高稳定度 导星电子星图模拟器 卫星控制系统 半物理试验 实时系统 

分 类 号:V474.11[航空宇航科学与技术—飞行器设计]

 

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