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Cost analysis of solar thermal propulsion systems for microsatellite applications

机译：用于微卫星应用的太阳热推进系统的成本分析

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摘要

In recent years, satellite design has extended towards miniaturisation to reduce associated cost with launching and conducting space missions. Small satellites provide low-cost platforms for space missions. However, this lower cost comes at the expense of the removal of key sub-systems, such as the propulsion system, due to the small available onboard volume and mass restrictions. For this reason, small, lightweight, high-performing and affordable propulsion systems are necessary. However, there is limited research available on the comparison of propulsion technologies with regards to cost. Motivated by the above challenges the objective of this paper is to provide a comparison of propulsion technologies that are compatible with small satellites with respect to cost and application. The different propulsion systems are investigated for three mission scenarios, a small on-orbit manoeuvre, a station-keeping, and a lunar orbit transfer mission. Each system is evaluated in terms of a total figure of merit which incorporates nine variables such as propellant mass, safety, and hardware price, that affect the total cost of a propulsion system. This figure of merit is used to quantitatively compare the propulsion systems to identify cost-effective solutions as a function of various mission scenarios. Solar thermal propulsion has been proposed for small satellite applications, but information regarding the concepts are not available in a single report. Therefore, a secondary objective of this paper is to provide the reader with a review of the current status of solar thermal propulsion. An important finding of this research is the classification of propulsion systems in terms of thrust, specific impulse, cost, and application.
机译：近年来，卫星设计已朝着小型化发展，以降低与发射和执行太空任务有关的成本。小型卫星为太空飞行任务提供了低成本的平台。但是，由于机载体积和质量限制较小，因此这种较低的成本是以拆除关键子系统（例如推进系统）为代价的。因此，需要小型，轻便，高性能和负担得起的推进系统。但是，关于成本方面的推进技术比较研究有限。受上述挑战的推动，本文的目的是就成本和应用方面对与小型卫星兼容的推进技术进行比较。针对三种飞行任务场景，小型在轨机动，驻地保管和月球轨道转移飞行任务，研究了不同的推进系统。每个系统均根据总品质因数进行评估，该品质因数包含九个变量，例如推进剂质量，安全性和硬件价格，这些变量会影响推进系统的总成本。该性能指标用于定量比较推进系统，以根据各种任务场景确定具有成本效益的解决方案。已经提出将太阳能热推进器用于小型卫星应用，但是关于这些概念的信息在单个报告中不可用。因此，本文的第二个目的是为读者提供有关太阳热推进的现状的综述。这项研究的重要发现是按推力，比冲量，成本和应用对推进系统进行分类。

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  • 来源
    《Acta astronautica》 |2019年第2期|90-110|共21页
  • 作者

    Leverone Fiona; Cervone Angelo; Gill Eberhard;

  • 作者单位

    Delft Univ Technol, Fac Fac Aerosp Engn, Space Syst Engn, Kluyverweg 1, NL-2629 HS Delft, Netherlands;

    Delft Univ Technol, Fac Fac Aerosp Engn, Space Syst Engn, Kluyverweg 1, NL-2629 HS Delft, Netherlands;

    Delft Univ Technol, Fac Fac Aerosp Engn, Space Syst Engn, Kluyverweg 1, NL-2629 HS Delft, Netherlands;

  • 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
  • 中图分类
  • 关键词

    Small satellites; Solar thermal propulsion; Low-cost propulsion systems;

    机译：小型卫星;太阳能热推进;低成本推进系统;

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