| 编队队形的等交点周期设计方法 |
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| 引用本文： | 陈永志,曾国强.编队队形的等交点周期设计方法[J].上海航天,2003,20(1):9-12. |
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| 作者姓名： | 陈永志 曾国强 |
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| 作者单位： | 装备指挥技术学院,北京,101416 |
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| 基金项目： | 国家高技术 863 2资助项目 (863 2 5 1 1.2 ) |
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| 摘 要： | 在分析编队构形一般设计方法设计效果的基础上，提出一种等交点周期法，对一般方法进行了改进。该法编队中卫星以一个相等的角速率运行在轨道上，能实现长期的编队飞行，并给出了编队设计算例及J2摄动下的队形演变，仿真表明，用等交点周期法设计的构形，能部分地消除J2摄动的影响。
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| 关 键 词： | 设计方法 编队飞行 队形设计 等交点周期 微小卫星 |
| 文章编号： | 1006-1630(2003)01-0009-04 |
Equal-Nodal Period Based Method of Formation Flying Configuration Design |
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| CHEN Yong zhi,ZENG Guo qiang.Equal-Nodal Period Based Method of Formation Flying Configuration Design[J].Aerospace Shanghai,2003,20(1):9-12. |
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| Authors: | CHEN Yong zhi ZENG Guo qiang |
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| Abstract: | On the basis of analyzing the effect of common configuration design method for the general method, the equal nodal period design method is introduced to improve the general method in this paper. The long term flying configuration could be realized since the designed satellites by new method run at the same angular velocity in orbit. The examples of formation flying configuration design and configuration evolvement under J 2 are given. The simulation result shows that the configuration designed by new method can partially decrease the influence of J 2 . |
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| Keywords: | Formation flying Configuration design Equal nodal period Micro satellite |
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