小行星探测及采样返回任务电推进系统方案设计
|
摘要
离子电推进具有高比冲、长寿命、多工作点可调的优势,能够很好的适用于小行星探测器巡航阶段主推进任务,可以大幅提升探测器的有效载荷比和空间进入能力。通过调研国外电推进在深空探测任务中的应用情况,结合我国小行星探测任务规划,在充分借鉴国外成功经验和全面继承我国电推进研制经验的基础上,依据任务需求,对可选用的多种电推进系统开展了对比分析,可以看出离子电推进系统具有显著优势。在此基础上,以既定任务为例,设计了不同配置的小行星探测离子电推进系统方案,对比分析了各方案的优劣势,最后对小行星探测离子电推进的关键技术进行了分析讨论。研究结果将为我国小行星探测任务提供参考。
Ion electric propulsion with advantages of multiple high specific impulse, long lifetime, multi-operating-mode adjustable feature can be used for the main propulsion task at the asteroid probe cruise stage. The effective load ratio and spatial ability of the detector can be thus improved greatly. By reviewing the application of electric propulsion in the asteroid mission in other countries, and in combination with the asteroid mission plan of our country, we summarized foreign successful experience and inheritance of our own electric propulsion development experience. On the basis of mission requirements, we analyzed a variety of electric propulsion systems. The results show that ion electric propulsion system has significant advantages. Taking the given task, we designed different schemes of ion electric propulsion system, and analyzed the advantages and disadvantages of each scheme. At last, we analyzed and discussed the key technologies of ion electric propulsion used in asteroid exploration mission. The results may provide a reference for the asteroid exploration mission in China.
Ion electric propulsion with advantages of multiple high specific impulse, long lifetime, multi-operating-mode adjustable feature can be used for the main propulsion task at the asteroid probe cruise stage. The effective load ratio and spatial ability of the detector can be thus improved greatly. By reviewing the application of electric propulsion in the asteroid mission in other countries, and in combination with the asteroid mission plan of our country, we summarized foreign successful experience and inheritance of our own electric propulsion development experience. On the basis of mission requirements, we analyzed a variety of electric propulsion systems. The results show that ion electric propulsion system has significant advantages. Taking the given task, we designed different schemes of ion electric propulsion system, and analyzed the advantages and disadvantages of each scheme. At last, we analyzed and discussed the key technologies of ion electric propulsion used in asteroid exploration mission. The results may provide a reference for the asteroid exploration mission in China.
引文
[1]Rawlin V K,Sovey J S,Hamley J A.An ion propulsion system for NASA'S deep space missions[R].Albuquerque,New Mexico:AIAA,1999.
[2]Rayman M D.The successful conclusion of the deep space 1 mission:important results without a flashy title[R].California:Jet Propulsion Laboratory,2003.
[3]Brophy J R,Marcucci M G,Ganapathi C B,et al.The ion propulsion system for dawn[C]∥The 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.[S.l]:AIAA,2003:1-8.
[4]Jet Propulsion Laboratory.Deep Space 1 Technology Vali-dation Reports[R].2011-07-17.http://trs-new.Jpl.Nasa.Gov/dspace/bitstream.
[5]KUNINAKA H,NISHIYAMA K,SHIMIZU Y,et a1.Reignition of microwave discharge ion engines on hayabusa for homeward journey[C],//30th International Electric Propulsion Conference.Florence,Italy:IEPC,2007:9-16.
[6]Kuninaka H,Shimizu Y,Yamada T,et al.Flight report during two years on HAYABUSA explorer propelled by microwave discharge ion engines[C]∥The 41th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.[S.l]:AIAA,2005:1-8.
[7]Zhang T P.Initial elight test results of the LIPS-200electric propulsion system on SJ-9A satellite[C]//The33nd International Electric Propulsion Conference,[S.l]:[s.n.],2013:1-9.
[8]Zhang T P.The LIPS-200 ion electric propulsion system development for the DFH-3B satellite platform[J].IAC-13-C4,2013,4(10).
[2]Rayman M D.The successful conclusion of the deep space 1 mission:important results without a flashy title[R].California:Jet Propulsion Laboratory,2003.
[3]Brophy J R,Marcucci M G,Ganapathi C B,et al.The ion propulsion system for dawn[C]∥The 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.[S.l]:AIAA,2003:1-8.
[4]Jet Propulsion Laboratory.Deep Space 1 Technology Vali-dation Reports[R].2011-07-17.http://trs-new.Jpl.Nasa.Gov/dspace/bitstream.
[5]KUNINAKA H,NISHIYAMA K,SHIMIZU Y,et a1.Reignition of microwave discharge ion engines on hayabusa for homeward journey[C],//30th International Electric Propulsion Conference.Florence,Italy:IEPC,2007:9-16.
[6]Kuninaka H,Shimizu Y,Yamada T,et al.Flight report during two years on HAYABUSA explorer propelled by microwave discharge ion engines[C]∥The 41th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.[S.l]:AIAA,2005:1-8.
[7]Zhang T P.Initial elight test results of the LIPS-200electric propulsion system on SJ-9A satellite[C]//The33nd International Electric Propulsion Conference,[S.l]:[s.n.],2013:1-9.
[8]Zhang T P.The LIPS-200 ion electric propulsion system development for the DFH-3B satellite platform[J].IAC-13-C4,2013,4(10).