| 摘要: |
| 航班化航天运输系统的应用需求日趋迫切，基于液氧/甲烷（LOX/LCH4）发动机的可重复使用运载火箭成为国内外研究热点。面向某型运载火箭对一级返回辅助动力系统的需求，提出了基于电动泵的主辅一体化液氧甲烷系统方案和独立挤压式液氧甲烷系统方案，开展了方案比选和应用优势分析，并介绍了液氧甲烷轨姿控发动机和低温表面张力贮箱的研究基础，以及国内首款液氧甲烷轨姿控推进系统集成演示试验情况。液氧甲烷辅助动力系统可以实现全箭推进剂的统一和无毒化，助力运载火箭走向高效及完全可重复使用。选择切实可行的“分步走”策略，优先开展挤压式液氧甲烷辅助动力系统的工程化研制与飞行应用，逐步实现基于电动泵的主辅一体化液氧甲烷辅助动力系统在重复使用运载火箭和低温上面级等领域应用。 |
| 关键词: 运载火箭 重复使用 液氧/甲烷 辅助动力系统 姿控发动机 |
| DOI： |
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| 基金项目:上海空间发动机工程技术研究中心资助项目（Fc373S-1） |
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| Scheme and Development of Reusable Auxiliary Propulsion System Using Liquid Oxygen and Liquid Methane |
| CHENG Cheng,YANG Minglei,ZHOU Haiqing,XIONG Jingyu,ZHU Wenjie |
| (1. Shanghai Institute of Space Propulsion, Shanghai 201112，China;2. Shanghai Engineering Research Center of Space Engine, Shanghai 201112，China) |
| Abstract: |
| The application demand of airline-flight-mode aerospace transportation system is becoming more and more urgent. The reusable launch vehicle based on liquid oxygen/liquid methane (LOX/LCH4) engine has become the first choice at home and abroad. For requirements of auxiliary propulsion system of the reusable launch vehicle first stage, an integrated auxiliary propulsion system with main engine based on electric pump and an independent pressurizing auxiliary propulsion system using LOX/LCH4 are proposed. Meanwhile, the comparative selection and application advantage analysis of auxiliary propulsion systems using different propellants are carried out. The research basis of LOX/LCH4 engines for orbit maneuver and reaction control system and cryogenic tank are introduced, as well as the first integrated LOX/LCH4 propulsion system prototype in China. The auxiliary propulsion system using LOX/LCH4 engines will truly realize the propellant unity and non-toxic of launch vehicle, and help the vehicle to move towards rapid and fully reusable. The ′step by step′ strategy is chosen to give priority to the development and flight application of the pressurizing auxiliary propulsion system using LOX/LCH4, and gradually realize the application of the integrated main-auxiliary propulsion system based on electric pump, which is more practical and feasible. |
| Key words: Launch vehicle Reuse Liquid oxygen/liquid methane Auxiliary propulsion system Reaction control engine |