| 引用本文: | 刘磊,吴伟仁,唐歌实,等.“嫦娥二号”后续小行星飞越探测任务设计.[J].国防科技大学学报,2014,36(2):13-17.[点击复制] |
| LIU Lei,WU Weiren,TANG Geshi,et al.Design of an asteroid flying-by mission for CHANG’E-2[J].Journal of National University of Defense Technology,2014,36(2):13-17[点击复制] |
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| “嫦娥二号”后续小行星飞越探测任务设计 |
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(1.航天飞行动力学技术重点实验室，北京 100094;2.北京航天飞行控制中心，北京 100094;3.国家探月与航天工程中心，北京 100037)
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| 摘要: |
| 为了实现对4179小行星飞越之后的嫦娥二号卫星的最大限度利用，提出了后续小行星飞越探测计划，研究了相关飞行任务设计。基于嫦娥二号卫星轨道、剩余燃料和测控距离等约束，设计了能量最优的转移轨道，给出了合适的小行星交会目标。研究了不同轨道控制方式下的转移轨道中途修正。基于我国深空测控网分布，分析了嫦娥二号后续小行星飞越探测任务的测控情况。研究结果表明，基于嫦娥二号剩余燃料，合适的飞越探测目标为小行星1997XF11和2005VS，转移过程中我国深空测控站每天可以实现8h以上跟踪，中途修正速度增量小于10m/s。 |
| 关键词: 嫦娥二号 任务设计 飞越探测 小行星 中途修正 |
| DOI：10.11887/j.cn.201402003 |
| 投稿日期：2013-10-20 |
| 基金项目:国家自然科学基金资助项目（11303001）；国家高技术研究发展计划项目（2012AA7034057G） |
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| Design of an asteroid flying-by mission for CHANG’E-2 |
| LIU Lei1,2, WU Weiren3, TANG Geshi1,2, ZHOU Jianliang4 |
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(1.Science and Technology on Aerospace Flight Dynamics Laboratory, Beijing 100094, China;2.
2.Beijing Aerospace Control Center, Beijing 100094, China;3.Chinese Lunar Exploration and Space Project Center, Beijing 100037, China;4.2.Beijing Aerospace Control Center, Beijing 100094, China)
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| Abstract: |
| An asteroid rendezvous plan for CHANG′E-2 was put forward and the corresponding mission was designed to maximize the satellite utilization. First, the satellite status of CHANG′E-2 at present was introduced. Based on the constraint of the current CHANG′E-2 orbit and remaining fuel and TT&C (telemetry, track, and command) capacity, the design of optimal transfer trajectory and the selection of rendezvous asteroid were studied. The suitable asteroids for rendezvous were given as a result. Second, the mid-course correction was studied according to two orbit maneuver modes, i.e., the fixed interval mode and the fixed interval mode with a least velocity increment constraint. Finally, the TT&C condition of the asteroid rendezvous mission was briefly analyzed according to the Chinese deep space network. The results show that the fuel remains can support the rendezvous of CHANG′E-2 with Asteroid 1997XF11 and 2005VS. Furthermore, the Chinese deep space network can provide an 8-h daily VLBI (Very Long Baseline Interferometry) tracking at least in the interplanetary course. The velocity increment for mid- course corrections is less than 10 m/s. |
| Keywords: CHANG’E-2 mission design flying-by exploration asteroid transfer trajectory correction |
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