Development of Main Propulsion System for Reusable Sounding Rocket: Design Considerations and Technology Demonstration
Development of Main Propulsion System for Reusable Sounding Rocket: Design Considerations and Technology Demonstration
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可重复使用探空火箭主推进系统研制：设计考虑与技术论证
DOI：
10.2322/tastj.12.tm_1
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发表时间：
2014
期刊：
影响因子：
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通讯作者：
Kimihito Obase
中科院分区：
文献类型：
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作者：
Masaki Sato;Tomoyuki Hashimoto;S. Takada;Toshiya Kimura;Takuo Onodera;Y. Naruo;Tsuyoshi Yagishita;K. Niu;T. Kaneko;Kimihito Obase
日本宇宙航空研究开发机构/日本宇宙航空研究开发机构提出了一种完全可重复使用的探空火箭，目的是以低成本和短周转时间为大气层观测使命提供频繁的机会，并提高可重复使用空间运输系统的技术准备水平。这枚火箭将垂直起飞，到达100多公里的高空，垂直降落在发射场，并在24小时内再次发射。主推进系统是一组液氧/液氢发动机，即使一台发动机发生故障，也具有全时中止能力。为了实现探空火箭的重复使用，主推进系统应具有高可靠性、重复使用性、可维护性和生存性等先进特性。为了满足这些要求，在发动机系统设计中考虑并反映了以下内容，即，优化组件之间的设计裕度，以实现高可靠性和可重用性，垂直着陆的深度节流能力，以及中止操作的健康监测能力，易于检查和维护，周转时间短。这些功能和性能将于2014年在日本宇宙航空研究开发机构的卡库达空间中心通过地面工程测试得到验证和展示。本文介绍了设计考虑，发动机系统和主要部件的设计，以及技术验证试验的现状和计划。
A fully reusable sounding rocket is proposed in JAXA/ISAS to provide frequent opportunities for atmospheric observation mission with low cost and with short turnaround time, and also to improve technology readiness levels for reusable space transportation systems. This rocket will take off vertically, reach to the high altitude more than 100 km, land on the launch site vertically, and be launched again within 24 hours. The main propulsion system is clustered LOX/LH2 engines with full-time abort capability in spite of the one engine fail. In order to realize the reusable sounding rocket, the main propulsion system should have advanced features of high reliability, reusability, maintainability, and survivability. To fulfill those requirements, followings have been considered and reflected in the engine system design, i.e., optimization of design margins among components for high reliability and reusability, deep throttling capability for vertical landing, and health monitoring capability for abort operation, easy inspection and maintenance for short turnaround time. Those functions and performance are going to be verified and demonstrated through ground engineering tests at Kakuda Space Center/JAXA in 2014. This paper shows the design considerations, the engine system and major components design, and the current status and plan of technology demonstration tests.