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Analysis of Nanosatellite Formation Establishment and Maintenance Using Electric Propulsion

机译：电动推进建立和维持纳米卫星的分析

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摘要

Nanosatellite clusters are one of the current and future trends in space technology. To maintain a satellite cluster over a long period of time, the nanosatellites need to mitigate the alongtrack drift created by the initial orbit injection. In the mass range of 1-10 kg, CubeSats have strict constraints on allowed mass, volume, and electrical power; and they are equipped with only limited sensor and actuator capabilities. A state-of-the-art miniaturized electric propulsion system is one option to realize the required orbit control capability. Due to the low thrust provided by an electric propulsion system, long orbit control maneuvers are required. Therefore, mission design is highly affected by long-term attitude and power constraints. Assuming a cyclic thrust controller, four methods are developed to allocate the satellite power and attitude resources for orbit control. Two time division methods are presented that allocate dedicated time slots for each of the satellite's main tasks. Alternatively, two cosine methods are presented that use an error cone, around the required attitude, as a criterion for selecting when to operate the thruster. It is demonstrated that the proposed methods are capable of maintaining a realistic CubeSat formation-flying mission using low-power electric propulsion. For a CubeSat with deployable solar panels, the double cosine method shows the best performance.
机译：纳米卫星簇是空间技术当前和未来的趋势之一。为了长时间维持卫星群，纳米卫星需要减轻由初始轨道注入产生的沿轨漂移。在1-10 kg的质量范围内，CubeSat对允许的质量，体积和电功率有严格的限制。而且它们仅配备有限​​的传感器和执行器功能。最先进的微型电力推进系统是实现所需轨道控制能力的一种选择。由于电动推进系统提供的推力低，因此需要长时间的轨道控制演习。因此，任务设计在很大程度上受到长期态度和动力约束的影响。假设采用周期性推力控制器，则开发了四种方法来分配卫星功率和姿态资源用于轨道控制。提出了两种时分方法，它们为每个卫星的主要任务分配专用的时隙。或者，提出了两种余弦方法，这些方法使用误差锥（围绕所需姿态）作为选择何时操作推进器的标准。结果表明，所提出的方法能够使用低功率电力推进来维持现实的CubeSat编队飞行任务。对于具有可展开太阳能电池板的CubeSat，双余弦方法显示出最佳性能。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2017年第3期|731-742|共12页
  • 作者

    Edlerman Eviatar; Kronhaus Igal;

  • 作者单位

    Technion Israel Inst Technol, Distributed Space Syst Lab, IL-32000 Haifa, Israel;

    Technion Israel Inst Technol, Fac Aerosp Engn, IL-32000 Haifa, Israel;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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