中继卫星在轨自动跟踪精度测试方法研究
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摘要
针对中继卫星在轨自动跟踪精度测试基准值建立和有效数据获取的难题,根据在天线电轴跟踪零点附近角误差电压灵敏度正比于波束指向角误差灵敏度的特性,提出了采用角误差电压灵敏度作为基准值,天线稳定跟踪目标时的方位角误差电压和俯仰角误差电压作为测试数据,通过数据处理得出在轨自动跟踪误差,然后与差波束零点(天线电轴)与和波束接收信号最大值轴之差相加,得出在轨自动跟踪精度的测试方法。并制定测试方案和测试流程,在轨进行了实施。与地面测试结果进行比较,数据相近,验证了测试方法的可行性和有效性。采用该方法测试难度小,便于实施,测试结果不受天线安装误差、卫星姿态变化等因素的影响,解决了中继卫星在轨自动跟踪精度测试的难题。
Aiming at the problem of establishing the test benchmark value of in-orbit autotracking accuracy for data relay satellite and obtaining effective data,according to the characteristic that the angle error voltage sensitivity near the tracking zero of the antenna axis is proportional to the beam pointing angle error sensitivity,a test method of in-orbit auto-tracking accuracy is proposed.The method uses the error voltage sensitivity as the benchmark value and the error voltages when the antenna stably tracks the target as the test data,then obtains the results by data processing,and the in-orbit auto-tracking accuracy is obtained by adding the angle difference between the zero of the difference beam and the maximum axis of the sum beam.The test method and scheme are carried out and implemented in-orbit.Compared with the ground test results,the data are comparable,which verifies the feasibility and validity to the method.It is easy to test with this method,and the test results are not affected by error of antenna installation,satellite attitude changes and other factors.The problem of in-orbit auto-tracking accuracy test for data relay satellite is solved.
Aiming at the problem of establishing the test benchmark value of in-orbit autotracking accuracy for data relay satellite and obtaining effective data,according to the characteristic that the angle error voltage sensitivity near the tracking zero of the antenna axis is proportional to the beam pointing angle error sensitivity,a test method of in-orbit auto-tracking accuracy is proposed.The method uses the error voltage sensitivity as the benchmark value and the error voltages when the antenna stably tracks the target as the test data,then obtains the results by data processing,and the in-orbit auto-tracking accuracy is obtained by adding the angle difference between the zero of the difference beam and the maximum axis of the sum beam.The test method and scheme are carried out and implemented in-orbit.Compared with the ground test results,the data are comparable,which verifies the feasibility and validity to the method.It is easy to test with this method,and the test results are not affected by error of antenna installation,satellite attitude changes and other factors.The problem of in-orbit auto-tracking accuracy test for data relay satellite is solved.
引文
[1]王家胜.我国数据中继卫星系统发展建议[J].航天器工程,2011,20(2):1-8Wang Jiasheng.Proposal for developing China‘s data relay satellite system[J].Spacecraft Engineering,2011,20(2):1-8(in Chinese)
[2]张文雅,黄霄腾,何伟平.中继卫星捕获跟踪精度快速评估方法研究及实现[J].仪器仪表学报,2011,32(6):71-73Zhang Wenya,Huang Xiaoteng,He Weiping.Quick evaluation research and implement for tracking and data relay satellite tracking precision[J].Chinese Journal of Scientific Instrument,2011,32(6):71-73(in Chinese)
[3]杨显强.一种航天器单脉冲差模角跟踪系统的标定及测试方法[J].航天器工程,2015,24(5)::131-137Yang Xianqiang.Calibration and test method for spacecraft monopulse difference mode angular tracking system[J].Spacecraft Engineering,2015,24(5):131-137(in Chinese)
[4]王德纯,丁家会,程望东.精密跟踪测量雷达技术[M].北京:电子工业出版社,2007Wang Dechun,Ding Jiahui,Cheng Wangdong.Precision tracking radar technology[M].Beijing:Publishing House of Electronics Industry,2007(in Chinese)
[5]黎孝纯,邱乐德,陈明章,等.星间链路天线跟踪指向系统[M].上海:上海交通大学出版社,2013Li Xiaochun,Qiu Lede,Chen Mingzhang,et al.Intersatellite antenna tracking and pointing system[M].Shanghai:Shanghai Jiaotong University Press,2013(in Chinese)
[6]王家胜.数据中继卫星系统的研制与分析[J].航天器工程,2008,17(5):7-12Wang Jiasheng.Development and analysis of data relay satellite system[J].Spacecraft Engineering,2008,17(5):7-12(in Chinese)
[7]汪晓燕.单通道单脉冲角跟踪系统的研究[J].电讯技术,2005(3):117-120Wang Xiaoyan.Study on single channel monopulse angle tracking systems[J].Telecommunication Engineering,2005(3):117-120(in Chinese)
[8]范子强,刘建功.中继卫星在轨动态捕获跟踪试验方法研究[J].航天器工程,2012,21(1):106-109Fan Ziqiang,Liu Jiangong.Study of method for data relay satellite in-orbit dynamic acquisition and tracking test[J].Spacecraft Engineering,2012,21(1):106-109(in Chinese)
[9]黎孝纯.星间链路角跟踪系统校相分析[J].空间电子技术,2009,6(2):109-114Li Xiaochun.The analysis for phase calibration of angle tracking system in inter-satellite links[J].Chinese Space Science and Technology,2009,6(2):109-114(in Chinese)
[2]张文雅,黄霄腾,何伟平.中继卫星捕获跟踪精度快速评估方法研究及实现[J].仪器仪表学报,2011,32(6):71-73Zhang Wenya,Huang Xiaoteng,He Weiping.Quick evaluation research and implement for tracking and data relay satellite tracking precision[J].Chinese Journal of Scientific Instrument,2011,32(6):71-73(in Chinese)
[3]杨显强.一种航天器单脉冲差模角跟踪系统的标定及测试方法[J].航天器工程,2015,24(5)::131-137Yang Xianqiang.Calibration and test method for spacecraft monopulse difference mode angular tracking system[J].Spacecraft Engineering,2015,24(5):131-137(in Chinese)
[4]王德纯,丁家会,程望东.精密跟踪测量雷达技术[M].北京:电子工业出版社,2007Wang Dechun,Ding Jiahui,Cheng Wangdong.Precision tracking radar technology[M].Beijing:Publishing House of Electronics Industry,2007(in Chinese)
[5]黎孝纯,邱乐德,陈明章,等.星间链路天线跟踪指向系统[M].上海:上海交通大学出版社,2013Li Xiaochun,Qiu Lede,Chen Mingzhang,et al.Intersatellite antenna tracking and pointing system[M].Shanghai:Shanghai Jiaotong University Press,2013(in Chinese)
[6]王家胜.数据中继卫星系统的研制与分析[J].航天器工程,2008,17(5):7-12Wang Jiasheng.Development and analysis of data relay satellite system[J].Spacecraft Engineering,2008,17(5):7-12(in Chinese)
[7]汪晓燕.单通道单脉冲角跟踪系统的研究[J].电讯技术,2005(3):117-120Wang Xiaoyan.Study on single channel monopulse angle tracking systems[J].Telecommunication Engineering,2005(3):117-120(in Chinese)
[8]范子强,刘建功.中继卫星在轨动态捕获跟踪试验方法研究[J].航天器工程,2012,21(1):106-109Fan Ziqiang,Liu Jiangong.Study of method for data relay satellite in-orbit dynamic acquisition and tracking test[J].Spacecraft Engineering,2012,21(1):106-109(in Chinese)
[9]黎孝纯.星间链路角跟踪系统校相分析[J].空间电子技术,2009,6(2):109-114Li Xiaochun.The analysis for phase calibration of angle tracking system in inter-satellite links[J].Chinese Space Science and Technology,2009,6(2):109-114(in Chinese)