充气式减速技术试验器的设计和飞行试验  

Design and Flight Test of Demonstration Aircraft with Inflatable Reentry and Descent Technology

作　　者：曹旭[1] 廖航[1] 许望晶 鲁媛媛[1] 于尧炳[1] CAO Xu;LIAO Hang;XU Wangjing;LU Yuanyuan;YU Yaobing(Beijing Institute of Space Mechanics and Electricity,Beijing 100094,China)

机构地区：[1]北京空间机电研究所,北京100094

出　　处：《载人航天》2018年第6期802-808,共7页Manned Spaceflight

基　　金：载人航天预先研究项目(040101)

摘　　要：为验证充气再入与式减速技术的原理和返回工作程序,研制了基于多充气环结构的飞行试验器,介绍了试验器的设计方案、技术指标、飞行试验方案,并对试验器的核心装置——充气锥的设计进行了说明。开展飞行试验对部分关键技术进行验证,并对地面试验和演示验证飞行试验情况进行了总结。飞行试验结果表明,基于多充气环结构的充气式减速系统方案合理,折叠包装效率较高,与运载平台分离后快速充气展开,返回过程满足气动减速要求,着陆速度达到预期要求;柔性气动减速技术、刚柔耦合结构设计技术、多充气环结构加工制造技术、高效折叠包装及有序展开技术、快速充气技术、地面试验技术等关键技术得到了验证。To demonstrate the technical principle,the working procedure and some key technologies of the Inflatable Reentry and Descent Technology(IRDT),a flight test system based on multi inflatable rings was developed.The system design,the technical parameters,the ground test and the flight test were introduced and summarized in this paper.Then the general design of the core devicethe inflatable cone was illustrated.The flight test was successfully conducted and the results showed that the system design was reasonable,the folding rate could meet the requirement,the rings could deploy in 5 seconds by inflating,and the landing velocity was close to the expected value.Key technologies including the flexible aerodynamic descent,the rigid-flexible coupling structure design,the multi inflatable ring manufacturing,the efficient folding,packing and orderly deployment,the fast inflation,the ground test and so on were verified.

关 键 词：充气式再入与减速技术 充气锥 刚柔耦合 气动减速 

分 类 号：V417[航空宇航科学与技术—航空宇航推进理论与工程] V423