| 微纳卫星星座的Kuhn-Munkres匹配部署优化方法 |
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| 引用本文： | 刘思阳,蒙涛,雷家坤,金仲和.微纳卫星星座的Kuhn-Munkres匹配部署优化方法[J].宇航学报,2021,42(7):895-906. |
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| 作者姓名： | 刘思阳 蒙涛 雷家坤 金仲和 |
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| 作者单位： | 1. 浙江大学微小卫星研究中心，杭州 310027; 2. 浙江省微纳卫星研究重点实验室，杭州 310027 |
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| 基金项目： | 省级重点研发计划-飞行器及其部组件技术-皮纳遥感卫星星座关键技术攻关及研制（209C05004） |
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| 摘 要： | 针对将半长轴、升交点赤经、纬度辐角均不同的低轨微纳卫星群部署到同一轨道面不同目标相位的星座部署问题，提出一种基于Kuhn Munkres(KM)匹配的星座部署优化方法。通过KM算法实现卫星和目标纬度辐角的优化匹配，充分利用J 2摄动，使升交点赤经借助半长轴和纬度辐角的部署而得到同步修正，从而节约燃料。仿真结果表明，相比于传统部署方法，在相同约束下，优化后的部署方法使各星平均燃耗减少，各星燃耗量均衡性提高。弥补了传统同轨星座部署中将各星初始位置简化为空间一点且忽略部署过程中的升交点赤经漂移的不足。采用有限常值推力实现轨道机动，适用于携带微推力推进系统的微纳卫星。
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| 关 键 词： | 微纳卫星星座 星座部署 相位分离 J2摄动 KuhnMunkres(KM)算法 燃料优化 |
| 收稿时间： | 2020-08-02 |
Kuhn Munkres Matching Deployment Optimization Method for Micro satellite Constellation |
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| LIU Si yang,MENG Tao,LEI Jia kun,JIN Zhong he.Kuhn Munkres Matching Deployment Optimization Method for Micro satellite Constellation[J].Journal of Astronautics,2021,42(7):895-906. |
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| Authors: | LIU Si yang MENG Tao LEI Jia kun JIN Zhong he |
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| Affiliation: | 1.Micro satellite Research Center, Zhejiang University, Hangzhou 310027, China;2.Key Laboratory of Micro satellite Research of Zhejiang Province, Hangzhou 310027, China |
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| Abstract: | An optimization method for constellation deployment based on Kuhn Munkres (KM) matching is proposed in order to deploy the low orbit micro satellites with different semi major axes, right ascension of ascending node (RAAN), and argument of latitude to the different target phases in the same orbit. The KM algorithm is used to optimize the matching of satellites and target phases, to correct the RAAN while adjusting the semi major axis and phase with the help of J 2 perturbation, thereby saving fuel. Simulation result shows that, compared with the traditional deployment method, the optimized deployment method reduces the average fuel consumption of each satellite, and improves the fuel consumption balance under the same constraints. The shortcoming in traditional single plane deployment is made up that simplifies the initial position of each satellite as a point and meanwhile neglects the RAAN drift during deployment. The finite constant thrust is used in orbital maneuvering, which could be adapted by micro satellites with limited propulsion system. |
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| Keywords: | Micro satellite constellation Constellation deployment Phase separation J 2 perturbation Kuhn Munkres (KM) algorithm Fuel optimization |
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