Pulsed Plasma Thruster for Cubesat Propulsion (PPTCUP) is an ablative pulsed plasma thruster designed with the aim of providing translational and orbital control to Cubesat platforms. The qualification model presented in this paper has been developed by Mars Space Ltd, Clyde Space Ltd and the University of Southampton to produce a versatile “stand-alone” module that can be bolted on the Cubesat structure, allowing the orbital control along the X or Y-axis of the satellite. An extensive and complete test campaign to qualify the unit for space flight, which includes electromagnetic compatibility (EMC) characterization, thermal cycling and mechanical tests, has been performed according to the NASA GEVS procedures. PPTCUP is characterized by an averaged specific impulse of 655±58 s and a deliverable total impulse of 48.2±4.2 Ns. Finally, it has been found that the unit is compliant with the EMC requirements and can successfully withstand the thermal and mechanical loads typical of a Cubesat space mission.
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机译：立方推进器脉冲等离子推进器（PPTCUP）是一种消融脉冲等离子推进器，旨在为Cubesat平台提供平移和轨道控制。本文提出的鉴定模型是由Mars Space Ltd，Clyde Space Ltd和南安普敦大学开发的，用于生产通用的“独立”模块，该模块可以用螺栓固定在Cubesat结构上，从而可以沿X轴或X轴进行轨道控制。卫星的Y轴。根据NASA GEVS程序，已进行了广泛而完整的测试活动，以使该装置具有太空飞行资格，包括电磁兼容性（EMC）表征，热循环和机械测试。 PPTCUP的特点是平均比脉冲为655±58 s，可交付总脉冲为48.2±4.2 Ns。最后，我们发现该装置符合EMC要求，并可以成功承受Cubesat太空飞行任务的典型热负荷和机械负荷。
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