Analysis of the Propulsion System for the Reusable Unmanned Spacecraft X-37B

초록

Recently, reusable unmanned spacecraft, capable of performing multi-purpose space missions over extended periods and reusability upon returning to Earth, have garnered global attention. Initially, these reusable unmanned spacecrafts are launched into orbit using space launch vehicles. However, once in space, they execute missions utilizing their own propulsion systems. This study aimed to acquire the design technology and operating concept for reusable unmanned spacecraft by analyzing the operational X-37B propulsion system. Starting from the initial design of the X-37B, various propulsion components, including the main engine, RCS, propellant, and supply methods, were thoroughly examined. The primary engine of X-37B is estimated to be either the AR2-3 or R-42 engine, and we conducted an analysis of the characteristics of each engine, weight estimation when applying each engine, and total delta-v analysis. Additionally, we calculated the nozzle exit diameter based on publicly available images to confirm a more suitable primary engine for X-37B.

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