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首页> 外文期刊>Journal of Spacecraft and Rockets >Small Mission Design for Testing In-Orbit an Electrodynamic Tether Deorbiting System
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Small Mission Design for Testing In-Orbit an Electrodynamic Tether Deorbiting System

机译：用于在轨测试电动系链去轨系统的小任务设计

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The need to limit the population of artificial debris in near-Earth space motivates the development of efficient deorbiting propulsion systems. Electrodynamic tethers offer a valid and attractive alternative to conventional chemical thrusters because they impose a penalty in terms of deorbiting time rather than additional launch mass. A low-cost demonstration mission is designed, where a reduced-scale deorbiting system will be carried, deployed, and controlled by a microsatellite. Numerical simulations show that the proposed configuration of the electrodynamic system allows, even in absence of active tether current control, to maintain a stable tether attitude motion. This is obtained through a careful combination of bare and insulated tether segments. When active current control is applied, the tether libration angles are bounded to within 10 deg. The closed-loop control laws make use of the in-plane and out-of-plane libration angles and rates, which are estimated through a newly developed extended Kalman filter. The estimator's measurements are provided by two three-axis magnetometers mounted on the spacecraft structure and at the lower tether endpoint, respectively. It is shown that this microsystem is able to deorbit a low-Earth-orbit carrier spacecraft in about two months, demonstrating salient features of tether technologies and associated electrodynamic effects.
机译：限制近地空间中人造碎片的数量的需求推动了高效脱轨推进系统的发展。电动系绳是常规化学推进器的一种有效且有吸引力的替代方案，因为它们会在脱轨时间而不是额外的发射质量方面造成损失。设计了一个低成本的演示任务，在该演示任务中，将由微卫星携带，部署和控制缩小规模的定轨系统。数值模拟表明，即使没有主动系绳电流控制，电动系统的建议配置也可以保持稳定的系绳姿态运动。这是通过裸线和绝缘绳段的仔细组合来实现的。当应用有源电流控制时，系链释放角限制在10度以内。闭环控制定律利用了平面内和平面外的自由角和比率，它们是通过新开发的扩展卡尔曼滤波器估算的。估算器的测量值分别由两个安装在航天器结构上和系绳下端的三轴磁力计提供。结果表明，该微系统能够在大约两个月的时间内使低地球轨道的载人航天飞机脱离轨道，这证明了系绳技术的显着特征以及相关的电动效应。

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