Today\'s world of space\'s primary concern is the uncontrolled growth of space debris and its probability of collision with spacecraft, particularly in the low earth orbit (LEO) regions. This paper is aimed to design an optimized micro-propulsion system, Cold Gas Thruster, to de-orbit the PSLV debris from 668km to 250 km height after capturing process. The propulsion system mainly consists of a storage tank, pipes, control valves, and a convergent-divergent nozzle. The paper gives an idea of the design of each component based on a continuous iterative process until the design thrust requirements are met. All the components are designed in the CATIA V5, and the structural analysis is done in the ANSYS tool for each component where our cylinder tank can withstand the high hoop stress generated on its wall of it. And flow analysis is done by using the K-$\epsilon$ turbulence model for the CD nozzle, which provides the required thrust to de-orbit PSLV from a higher orbit to a lower orbit, after which the air drag will be enough to bring back to earth\'s atmosphere and burn it. Hohmann\'s orbit transfer method has been used to de-orbit the PSLV space debris, and it has been simulated by STK tools. And the result shows that our optimized designed thruster generates enough thrust to de-orbit the PSLV debris to a very low orbit.
翻译:当今空间世界的主要关切是空间碎片的无节制增长及其与航天器碰撞的可能性,特别是在低地球轨道区域。 本文旨在设计一个优化微推进系统Cold Gas Thruster, 将PSLV碎片从捕获过程后的668公里高度脱轨到250公里高度。 推进系统主要由储油罐、管道、 控制阀门和聚集式分散式喷口组成。 该文件给出了每个部件的设计构想, 其基础是连续迭接程序, 直至设计推进要求得到满足。 所有部件都是在CATIA V5中设计的, 结构分析是在ANSYS工具中进行的, 使每个部件的气罐能够承受其墙壁上产生的高豪华压力。 流分析是通过使用 K- $\ epslon$ 的气流模型完成的, 该模型提供了从更高的轨道脱轨PSLV到更低轨道所需的推力, 之后, 空气拖力将足够回到地球轨道 V5, 并且所有部件都在ANS工具中进行结构分析, 将HS- droad轨道转换为HS- drobal 。 一直由ST- dLVLVLVLV 一直使用该工具进行。