纳型卫星StudSat2推进系统设计
Design of the Propulsion System of Nano satellite: StudSat2
摘要：
卫星应用的增加使卫星数量激增，特别是在低地球轨道。今天的主要关切是，这些卫星在寿命结束后会变成碎片，对空间环境产生不利影响。根据欧洲航天局的国际准则，卫星必须在寿命结束后25年内脱轨。StudSat1于2010年7月12日成功发射，是印度第一颗Pico卫星，由来自印度南部七所不同工程学院的本科生开发。现在，该团队正在开发StudSat2，这是印度第一个双卫星任务，拥有两颗总质量小于10公斤的纳米卫星。本文旨在设计推进系统，冷气推力器，使StudSat2从其原始轨道，即600公里，到较低的轨道，即400公里。推进系统主要由贮箱、管路、收敛发散喷管和电子作动器组成。本文还介绍了冷气推力器的组成部分，在CATIAV5中进行了设计，并在ANSYS中进行了结构和流动分析。Hohmann转移的概念被用于使卫星脱离轨道，STK被用于模拟它。
英文摘要：
The increase in the application of the satellite has skyrocketed the number of satellites, especially in the low earth orbit. The major concern today is after the end of life, these satellites become debris which negatively affects the space environment. As per the international guidelines of the European Space Agency, it is mandatory to deorbit the satellite within 25 years of the end of life. StudSat1, which was successfully launched on 12th July 2010, is the first Pico satellite developed in India by undergraduate students from seven different engineering colleges across South India. Now, the team is developing StudSat2, which is India's first twin satellite mission having two nanosatellites whose overall mass is less than 10kg. This paper is aimed to design the propulsion system, cold gas thruster, to deorbit StudSat2 from its original orbit i.e. 600 km to lower orbit i.e. 400km. The propulsion system mainly consists of a storage tank, pipes, Convergent Divergent nozzle, and electronic actuators. The paper also gives information about the components of cold gas thruster, which have been designed in the CATIA V5, and the structural and flow analysis of the same has been done in ANSYS. The concept of Hohmann transfer has been used to deorbit the satellite and STK has been used to simulate it.
机构、总结、中文摘要均由AI分析而来，可能存在错误，请以论文正文为准。
