| 基于椭圆轨道的绳系卫星伸展及释放过程仿真研究 |
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| 引用本文： | 崔乃刚,刘暾.基于椭圆轨道的绳系卫星伸展及释放过程仿真研究[J].哈尔滨工业大学学报,1996,28(4):117-122. |
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| 作者姓名： | 崔乃刚 刘暾 |
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| 作者单位： | 哈尔滨航天工程与力学系 |
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| 摘 要： | 采用拉格朗日方法建立了基于椭圆轨道的绳系卫星动力学模型，通过模型分析证明面内伸展运动是稳定的．选择匀速和指数型展开控制律对面内伸展运动进行了仿真．给出了子卫星释放后其轨道半长轴及偏心率的计算公式．计算结果表明利用系绳可实现于卫星的轨道机动．
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| 关 键 词： | 绳系卫星 仿真 椭圆轨道 释放过程 卫星 |
Research on Simulation Deployment and Release Process of Tethered Satellite System in Elliptic Orbit |
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| Cui Naigang,Liu Dun,Lin Xiaohui,Zhao Chenzhu.Research on Simulation Deployment and Release Process of Tethered Satellite System in Elliptic Orbit[J].Journal of Harbin Institute of Technology,1996,28(4):117-122. |
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| Authors: | Cui Naigang Liu Dun Lin Xiaohui Zhao Chenzhu |
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| Abstract: | he lagrangian procedure is adoptal to establish the dynamic model of a tethered satellite system in an elliptic orbit.It is demonstrated by analysing the model that the deplpgyment motion in the orbital plane is stable. The uniform and exponential deployment schemes are selected and the deployment process is simulated The formulas used to calculate the orbital elements of semimajor axis and eccentricity of the subsatellite are given.The calculation results show that the orbit change of the subsatellite can be realized by a tether. |
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| Keywords: | Tethered satellite dynamics orbit deployment process simulation |
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