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

这个第一阶段项目的更广泛的影响/商业潜力是通过提供一个具有扩展能力的推进器平台来显著改变电力推进的当前状态。这样的改变将允许霍尔推进器跨越更广泛的操作参数范围，并增加提高效率、降低成本、探索深空以及通过放射性同位素电力系统(RPS)提供后备电源等好处。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。加热功率将使锌等高密度金属推进剂的使用成为可能。电力将为太阳能发电提供后备，并有可能为基本的卫星系统提供电力。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，并将有助于培训高度多样化的劳动力。这个小型企业技术转让(STTR)第一阶段项目解决了空间推进中的一个长期问题：依赖氙气作为燃料。拟议工作的主要目标是利用锌燃料和RPS单元生产霍尔效应推进器原型。热管理系统将管理RPS单元产生的热量，以向推进器输送燃料。最初的工作将使用一个电气模块，该模块将充当RPS单元的占位符；后者可以在必要时插入。样机的设计将遵循霍尔效应推进器的定标规律，以降低风险。测试样机的结果将提供有关发射离子、推进器效率和推进器羽流发散的信息。更广泛地说，这些结果将提供作为改进的推进器平台的一部分实现用于空间推进的氙气燃料替代品的数据。这一奖励反映了NSF的法定使命，并通过使用基金会的智力优势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.