摘要
为应对未来再入飞行器长时间高超声速飞行的严酷力热环境以及轻质化、多功能化和高可靠性的发展需求,提出以碳纤维树脂基复合材料为代表的大翼面承载结构设计方法,并结合相关的分析和试验,验证了设计的可行性和工艺制备流程,推动了轻质复合材料在再入飞行器承力防热一体化设计中的应用。
To cope with the terrible thermal-mechanical environment acting on the reentry vehicle which needs long time hypersonic flying in the future, a design and research on the reentry vehicle wing based on carbon fiber reinforced composites to meet the requirements of low-density, multifunction and high reliability is presented. And a structure design method of a big wing which is manufactured by resin-based carbon fiber composites is given. Feasibility and technological process by means of the analyses and experiments is also verified. It promotes the application of the low-density composites used in the thermal-mechanical integrated design on the reentry vehicle.
作者
李长春
董超
高志勇
刘赛
秦玉灵
Li Chang-chun;Dong Chao;Gao Zhi-yong;Liu Sai;Qin Yu-ling(Beijing Institute of Space Long March Vehicle,Beijing,100076;Air Force Military Representative Office in CALT,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2019年第5期122-126,共5页
Missiles and Space Vehicles
