Deorbiting Strategies: Comparison between Electrostatic Plasma Brake and Conventional Propulsion
Deorbiting Strategies: Comparison between Electrostatic Plasma Brake and Conventional Propulsion
复制标题
离轨策略：静电等离子制动与传统推进的比较
DOI：
10.2514/6.2011-5920
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发表时间：
2011
期刊：
影响因子：
--
通讯作者：
Gonzalez del Amo
中科院分区：
文献类型：
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作者：
Urmas Kvell;D. D. Cara;P. Janhunen;M. Noorma;Gonzalez del Amo
空间碎片日益引起人们的关注，促使世界各地的空间用户更加坚定地承诺在未使用的平台寿命结束时使其脱离轨道。在电动太阳风帆推进领域的最新进展引入了静电等离子体制动的概念，主要是针对重达100公斤的小卫星脱离轨道。其工作原理是在电离层等离子体环境中用带负电荷的细长缆绳产生阻力。离轨舱的设计相对简单，由高压电源、抗空间碎片系绳和尖端质量组成。缆绳是利用重力梯度力展开的。本文将重点讨论静电等离子体制动器概念在大型卫星脱轨中的适用性，其中静电等离子体制动器可以为固体和电力推进脱轨模块提供无推进剂的替代方案。从任务分析的角度详细研究了重达1000千克的各类卫星的不同低地球轨道任务情景。针对这几种卫星类型提出了最优的离轨模块参数，并与已有的离轨解进行了比较。
Space debris is a growing concern, pushing worldwide space users to commit more strongly to deorbiting unused platforms at the end of life. Recent advances in the area of the Electric Solar Wind Sail propulsion have introduced the concept of electrostatic plasma brake, mostly aimed for deorbiting small satellites weighing up to 100 kg. The operating principle is to produce drag with a negatively charged long thin tether in the ionospheric plasma environment. A relatively simple design of the deorbit module consists of a highvoltage power supply, space debris resistant tether and a tip mass. The tether is deployed using gravity gradient force. This paper will focus on the applicability of the electrostatic plasma brake concept for deorbiting larger class satellites where the electrostatic plasma brake could provide a propellantless alternative to the solid and electric propulsion deorbiting modules. Dierent low Earth orbit mission scenarios for satellite classes weighing up to 1000 kg are studied in detail from a mission analysis point of view. Optimal deorbit module parameters are proposed for these generic satellite classes and the results are compared with existing deorbiting solutions.