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RESISTOJET Propulsion System for Small Satellite

机译:小型卫星的RESISTTOJET推进系统

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摘要

Due to the launch safety constraints placed on Space companies built microsatellites, designing a simple and reliable propulsion system with performance and characteristics in line with the typical requirements of microsatellites presents a significant challenge to aspiring engineers. This paper presents the design process of a low-cost, propulsion system with a two-phase high density propellant. The aim of this study is the preliminary design of a 50mN RESISTOJET system operating at low pressure. The preliminary design and the optimization of the thruster dimensions are presented.
机译:由于航天公司建造微卫星的发射安全性受到限制,因此,设计一种性能可靠且性能符合微卫星典型要求的简单可靠的推进系统,对有抱负的工程师提出了严峻的挑战。本文介绍了具有两相高密度推进剂的低成本推进系统的设计过程。这项研究的目的是在低压下运行的50mN RESISTOJET系统的初步设计。介绍了推进器尺寸的初步设计和优化。

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