基于電動力繩系的航天器離軌方式初步研究

Spacecraft de-orbiting by means of electro-dynamic tether

摘要: 為尋找適合近地軌道上使用的航天器離軌技術，文章對目前各種離軌策略的基本原理及優(yōu)缺點作了分析與對比，重點對電動力繩系離軌裝置進行了深入研究，建立了數(shù)學模型，推導出離軌時間預估公式，對離軌的過程進行了數(shù)學仿真，結果證實電動力阻力能使近地軌道上航天器的軌道高度迅速降低，電動力繩系離軌策略具有很高的工程實用性。

Abstract: This paper studies different methods of spacecraft de-orbiting in order to find a proper way for de-orbiting spacecrafts in the low earth orbit (LEO). Advantages and shortcomings of these de-orbiting methods were analyzed to show that the Electro-dynamic Tether de-orbiting system was the most economical and efficient. A mathematic model is proposed for Electro-dynamic Tether, and is used to estimate de-orbiting time. The simulation with MATLAB shows that a fast decay is effected by the electro-dynamic drag for LEO spacecrafts.

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