星载高精度天线指向机构设计仿真分析
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摘要
在卫星与地面站的可见弧段时间内,为实际控制指向机构进行对地数据传输提供参考条件,包括为指向机构对地通信时提供指向的角度、速度、加速度以及通信时间段。使用STK仿真软件,根据太阳同步轨道卫星的姿态场景数据实现指向机构跟踪地面站的理论仿真。采用MATLAB详细分析了指向机构与地面站建立通信时的角度、速度、加速度及时间段。仿真结果表明,该仿真系统设计合理,基于STK的场景建模具有通用性和可扩展性,具有一定的推广使用价值。
Control of high precision satellite antenna pointing mechanism tracking ground station,providing theoretical input conditions for the transmission of ground data during the communication time period,including providing the pointing angle,rate and acceleration for pointing mechanism pointing to the ground station. Through the simulation and calculation,the communication time between the pointing mechanism and the ground station is analyzed,and its calculation model is established. The scene is modeled by STK software,according to the attitude scene data,the theoretical simulation of pointing mechanism tracking ground station is realized. The angle,speed,acceleration and time period when the pointing mechanism establishes communication with the ground station are analyzed in detail by MATLAB,. The simulation results show that the design of the simulation system is reasonable,the scene modeling based on STK is universal and extensible,and has certain popularization and application value.
Control of high precision satellite antenna pointing mechanism tracking ground station,providing theoretical input conditions for the transmission of ground data during the communication time period,including providing the pointing angle,rate and acceleration for pointing mechanism pointing to the ground station. Through the simulation and calculation,the communication time between the pointing mechanism and the ground station is analyzed,and its calculation model is established. The scene is modeled by STK software,according to the attitude scene data,the theoretical simulation of pointing mechanism tracking ground station is realized. The angle,speed,acceleration and time period when the pointing mechanism establishes communication with the ground station are analyzed in detail by MATLAB,. The simulation results show that the design of the simulation system is reasonable,the scene modeling based on STK is universal and extensible,and has certain popularization and application value.
引文
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[3]张锋.星载天线指向机构误差分析与建模[J].电子机械工2011,26(1):57-61.
[4]吴昊,王宇.基于STK的MEO卫星通信系统的仿真与覆盖分析[J].电子设计工程,2017,25(22):120-123,127.
[5]杜玉萍.基于STK/Matlab的航天器可见性仿真分析[J].光电技术应用,2014,29(6):80-83.
[6]徐俊,白向峰,周晓华.基于STK的侦察卫星覆盖仿真分析[J].软件导刊,2016,15(8):156-158.
[7]刘辉,许松,杜鹏飞,等.STK仿真工具在航天装备教学中的运用[J].空军预警学院报,2017,31(1):70-72,75.
[8]王尔申,岳孝东,李轩,等.基于STK的卫星导航原理与应用课程教学方法研究[J].实验技术与管理,2016,33(5):129-131,138.
[9]左霖,尹增山,程蛟,等.STK在太阳同步轨道降交点地方时仿真中的应用[J].航天控制,2016,34(1):70-74.
[10]Shota Kikuchi,Kathleen C. Howell,Yuichi Tsuda,Jun'ichiro Kawaguchi. Orbit-attitude coupledmotion around small bodies:Sun-synchronousorbits with Sun-tracking attitude motion[J]. ActaAstronautica,2017:140.
[11]万向成,魏春,陈筠力.基于倾角修正的太阳同步轨道降交点地方时主动控制及应用[J].上海航天,2016,33(2):63-67.
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[13]章仁为.卫星轨道理论与应用[M].北京:电子工业出版社,2015.
[14]Peng Lin,Guobin Chang,Jingxiang Gao,et al. Helmert transformation with mixed geodetic and Cartesian coordinates[J]. Advances in Space Research,2017.
[15]窦长勇,岳昔娟.轨道坐标系到地心固定坐标系的直接转换方法[J].航天返回与遥感,2016,37(5):86-94.
[16]张大伟,程卫强.大椭圆轨道卫星姿态基准坐标系与运动学研究[J].上海航天,2017,34(2):67-73.
[2] Oh H U,Jeon S H,Kim T H,et al. Experimentalfeasibility study for micro-jitter attenuation ofstepper-actuated X-band antenna-pointingmechanism by using pseudoelastic SMA meshwasher[J]. Smart Materials and Structures,2015,24(4):045010.
[3]张锋.星载天线指向机构误差分析与建模[J].电子机械工2011,26(1):57-61.
[4]吴昊,王宇.基于STK的MEO卫星通信系统的仿真与覆盖分析[J].电子设计工程,2017,25(22):120-123,127.
[5]杜玉萍.基于STK/Matlab的航天器可见性仿真分析[J].光电技术应用,2014,29(6):80-83.
[6]徐俊,白向峰,周晓华.基于STK的侦察卫星覆盖仿真分析[J].软件导刊,2016,15(8):156-158.
[7]刘辉,许松,杜鹏飞,等.STK仿真工具在航天装备教学中的运用[J].空军预警学院报,2017,31(1):70-72,75.
[8]王尔申,岳孝东,李轩,等.基于STK的卫星导航原理与应用课程教学方法研究[J].实验技术与管理,2016,33(5):129-131,138.
[9]左霖,尹增山,程蛟,等.STK在太阳同步轨道降交点地方时仿真中的应用[J].航天控制,2016,34(1):70-74.
[10]Shota Kikuchi,Kathleen C. Howell,Yuichi Tsuda,Jun'ichiro Kawaguchi. Orbit-attitude coupledmotion around small bodies:Sun-synchronousorbits with Sun-tracking attitude motion[J]. ActaAstronautica,2017:140.
[11]万向成,魏春,陈筠力.基于倾角修正的太阳同步轨道降交点地方时主动控制及应用[J].上海航天,2016,33(2):63-67.
[12]Elliott D Kaplan,Christopher J Hegarty. GPS原理与应用[M].北京:电子工业出版社,2010.
[13]章仁为.卫星轨道理论与应用[M].北京:电子工业出版社,2015.
[14]Peng Lin,Guobin Chang,Jingxiang Gao,et al. Helmert transformation with mixed geodetic and Cartesian coordinates[J]. Advances in Space Research,2017.
[15]窦长勇,岳昔娟.轨道坐标系到地心固定坐标系的直接转换方法[J].航天返回与遥感,2016,37(5):86-94.
[16]张大伟,程卫强.大椭圆轨道卫星姿态基准坐标系与运动学研究[J].上海航天,2017,34(2):67-73.