摘要
基于电推进器运用于微纳卫星的可行性探讨,仿真分析了微纳卫星轨道控制性能。通过将综合性能更优的电阻加热型电推进器作为微纳卫星的动力装置,给出一种电阻加热型电推进器在微纳卫星上的整体布局方案,建立了带电推进器微纳卫星的轨道模型,推力计算验证了布局可实现卫星的六自由度控制。最后,针对不同的卫星变轨需求,分析了实现卫星变轨控制所需的推进剂量,从而为提升微纳卫星完成空间任务能力,拓展微纳卫星的应用空间提供一定的参考。
Based on the feasibility of using the electric thruster in the micro/nano satellite,the performance of the micro/nano satellite orbit control is simulated. By using the resistance heating type electric thruster with better overall performance as the power plant of the micro/nano satellite,a layout scheme of the resistance heating type electric thruster on the micro/nano satellite is given,and the micro-nano satellite with charged thruster. The orbit model and the thrust calculation verify that the layout can realize satellite six-degree-of-freedom control. Finally,according to different satellite orbit requirements,the amount of propulsion needed to achieve satellite orbit control is analyzed,which will provide some references for improving the capability of micro/nano satellite in space mission and expanding the application space of micro and nano satellites.
作者
韩寅奔
董泉润
HAN Yin- ben;DONG Quan- run(Department of Educational Af]hirs, Northwestern Polytechnical University, Xi＇an 710072, China;School of Power and Energy, Northwestern Polytechnical University, Xi＇an 710129, China)
出处
《航空计算技术》
2018年第2期22-25,共4页
Aeronautical Computing Technique
基金
国家自然科学基金项目资助(51506179)
中央高校基本科研业务专项资金资助(3102016ZY018)
关键词
电推进
太阳帆
微纳卫星
姿态控制
轨道计算
electric push
solar sail
micro- nano satellite
gesture control
orbit calculation
