STTR Phase I: Metal Fueled Hall Effect Thruster Using A Radioisotope Heater

第一阶段项目的更广泛的影响和商业潜力是，通过提供一个具有扩展功能的推进器平台，显著改变电力推进的现状。这样的改变将使霍尔推进器能够跨越更大范围的工作参数，并带来效率提高、成本降低、探索深空以及通过放射性同位素动力系统（RPS）提供备用电源的额外好处。通过使用RPS，推进器平台每9瓦的加热功率将产生1瓦的电力。加热功率将使高密度金属推进剂（如锌）的使用成为可能。电力将为太阳能发电提供备用，并可能为基本卫星系统供电。这项工作将提供有关核燃料回收、发电和相关空间技术的科学知识。最后，这项工作将是高度协作的，将有助于培养高度多样化的劳动力。这项小企业技术转让（STTR）第一阶段项目解决了太空推进领域一个长期存在的问题；对氙作为燃料的依赖。提出的工作的主要目标是生产一个原型霍尔效应推进器利用锌燃料和RPS单元。热管理系统将管理RPS单元产生的热量，将燃料输送到推进器。初始工作将使用电气模块作为RPS单元的占位符；后者可以在必要时插入。原型机的设计将遵循霍尔效应推力器缩放定律，以降低风险。测试原型的结果将提供有关喷射离子、推进器效率和推进器羽流散度的信息。更广泛地说，研究结果将为实现空间推进的氙燃料替代品提供数据，作为改进的推进器平台的一部分。该奖项反映了美国国家科学基金会的法定使命，并通过使用基金会的知识价值和更广泛的影响审查标准进行评估，被认为值得支持。

The broader impact/commercial potential of this Phase I project is to significantly alter the current state of electric propulsion by providing a thruster platform with extended capabilities. Such a change would allow Hall thrusters to span a wider range of operating parameters with added benefits of increased efficiency, lower cost, exploration of deep space, and backup power via a radioisotope power system (RPS). By using a RPS, the thruster platform will produce one watt of electrical power for every nine watts of heating power. The heating power will enable the use of high-density metal propellants such as zinc. The electrical power will provide a backup for solar generation and can potentially power basic satellite systems. This work will provide scientific knowledge regarding nuclear fuel recycling, power generation, and related space technologies. Lastly, this work will be highly collaborative and will contribute to the training of a highly diverse workforce. This Small Business Technology Transfer (STTR) Phase I project addresses a longstanding issue in space propulsion; the reliance on xenon as a fuel. The primary objective of the proposed work is to produce a prototype Hall Effect thruster utilizing zinc fuel and a RPS unit. A thermal management system will manage the heat produced by the RPS unit to deliver fuel to the thruster. Initial work will use an electrical module that will act as a placeholder for the RPS unit; the latter can be inserted when necessary. Design of the prototype will follow Hall Effect thruster scaling laws to reduce risk. The results of the tested prototype will provide information on the expelled ions, thruster efficiency, and divergence of the thruster plume. More broadly, the results will provide data on realizing an alternative to xenon fuel for space propulsion as part of an improved thruster platform.This award reflects NSF's statutory mission and has been deemed worthy of support through evaluation using the Foundation's intellectual merit and broader impacts review criteria.