新型载人飞行器轻质化机身结构的概念设计研究

Study on Conceptual Design of Light-weight Fuselage Structures in Novel Manned Spacecraft

针对新型载人飞行器,基于结构方案设计、力学分析和模型结构性能测试等研究,提出了轻质化机身结构的设计方案。采用柔性层合薄膜实现机身大面积防热结构;采用空间桁架结构体系和新型节点连接形式,确定了飞行器机身的轻质承载结构设计方案;采用刚性杆-柔性索段组合方案,设计了机身结构和燃料储罐之间的连接系统。利用有限元软件ANSYS评估了结构体系的力学性能。利用机身典型承载结构的缩比模型进行了力学试验,验证了有限元分析模型和结果。研究结果可为新型载人飞行器的轻质化机身结构提供设计参考。

Based on the study results of the structure conceptual d e s ig n,the m echanics analysis andthe stru ctu ra l perform ance tests of a scale m o d e l, a lig h t-w e ig h t conceptual design of the fuselagestructures of a novel m anned spacecraft was presented. The flexible com posite m em branes were employed to construct the large-area the rm a l pro te ct structure of the m anned spacecraft fuselage. A spatial truss structural system and a novel jo in t connection form w ere used to design the lig h t - w eightbearing structure of the m anned spacecraft fuselage. An integrated scheme in c lu d in g the rig id barsand the fle x ib le cables was proposed to design the connection system betw een the m anned spacecraftfuselage and the fueltank . The design scheme was analyzed w ith F E M software ANSYS ,and them ech an ical properties of the structure w ere e va lu ated . The scale m odel of the bearing structure of them anned spacecraft fuselage was developed fo r the structural perfor ance tests, and the FEManalysism odel and results were validated . The research achievem ents m ay provide a design reference for the light-weight fuselage structures of a novel m anned spacecraft.