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卫星推力器模拟器校准技术研究

Research on Satellite Thruster Simulator Calibration Technology
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摘要 依据卫星姿轨控半实物仿真系统的技术要求,提出一种用于推力器模拟器的校准装置设计。校准装置采用网口通信模式模拟动力学计算机的喷气指令。校准装置以FPGA和单片机为控制核心,内置信号调理模块、高精度脉冲采集模块,数据解算模块等。该校准装置已经用于卫星姿轨控地面仿真测试的校准过程中,不仅能提升效率和质量,还能替代目前由多个设备组成的校准测试系统。有效降低成本,模拟推力器的全过程在线校准。 In this article,we studied a calibration device for thruster simulator,according to the technical requirements of the satellite attitude and orbit control hardware-in-the-loop simulation system.The calibration device uses the network port communication mode to simulate the jet command of the dynamic computer.FPGA and single-chip microcomputer are the control core of the calibration device.In addition,the calibration device includes a signal conditioning module,a high-precision pulse acquisition module,a data solving module,etc.The calibration device has been used in the calibration process of satellite attitude and orbit control ground simulation test.It can not only improve efficiency and quality,but also replace the current calibration test system composed of multiple devices,effectively reduce costs,and simulate the entire process of thrusters online calibration.
作者 王凯 王贺迎 富雅琼 武宇婧 孙汇聪 WANG Kai;WANG He-ying;FU Ya-qiong;WU Yu-jing;SUN Hui-cong(Beijing Oriental Institute of Measurement and Test,Beijing 100086,China;China Jiliang University,Hangzhou 310018,China)
出处 《宇航计测技术》 CSCD 2021年第3期97-101,共5页 Journal of Astronautic Metrology and Measurement
关键词 推力器模拟器 在线校准 姿轨控系统 自动测试 Thruster simulator Online calibration AOCS(Attitude and Orbit Control Subsystem) Automatic testing
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  • 1林来兴.最近十年航天器制导、导航与控制(GNC)系统故障分析研究[J].控制工程(北京),2004(1):1-8. 被引量:6
  • 2任海.微小冷气推进技术的应用现状和发展[J].控制工程(北京),2003(5):10-19. 被引量:8
  • 3边炳秀.卫星推进系统的历史、现状和未来[J].控制工程(北京),2001(5):28-39. 被引量:5
  • 4袁磊,周红玲,孙冰.卫星单元肼推进系统落压工作特性的数值仿真与试验[J].上海航天,2007,24(2):42-46. 被引量:6
  • 5Chang Y K, Lee B H, Kim S J, et al. AUSAT-2 nanosatellite ADCS performance analysis and commissioning [C]//IEEE Proceedings of 2nd International Conference on recent advances in space technologies. ATATORK: Founder of Turkish Republic, 2005. USA: IEEE, 2005: 180-184.
  • 6Bang H, Young H L. Sliding Mode Control for Spacecraft Containing Rotating Wheels [C]// AIAA Guidance, Navigation, and Control Conference and Exhibit, Montreal, Canada, 2001. USA: AIAA, 2001: 1-8.
  • 7Hall C D, Tsiotras P, Shen H. Tracking Rigid Body Motion Using Thrusters and Momentum Wheels [J]. The Journal of the Astronautical Sciences (S0021-9142), 2002, 50(3): 311-323.
  • 8Bang H, Choi H D. Attitude Control of a Bias Momentum Satellite Using Momentum of Inertia [J]. IEEE Transactions on Aerospace and Electronic System (S0018-9251), 2002, 38(1): 243-250.
  • 9Morten P T, Jan T G. Nonlinear attitude control of the micro satellite ESEO [C]// 55th International Astronautical Congress, Vancouver, Canada, 2004. Columbia: IAC, 2004: 1-12.
  • 10Antropov N N, Diakonov G A, Kazeev M N, et al. Pulsed plasma thrusters for spacecraft attitude and orbit control system [C]// Proc. 26th International Propulsion Conference, Kitakyushu, Japan, 1999. USA: PEPL, 1999: 1129-1135.

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