新型载人飞行器轻质化机身结构的概念设计研究
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摘要
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 design,the mechanics analysis and the structural performance tests of a scale model,a light-weight conceptual design of the fuselage structures of a novel manned spacecraft was presented. The flexible composite membranes were employed to construct the large-area thermal protect structure of the manned spacecraft fuselage. A spatial truss structural system and a novel joint connection form were used to design the light- weight bearing structure of the manned spacecraft fuselage. An integrated scheme including the rigid bars and the flexible cables was proposed to design the connection system between the manned spacecraft fuselage and the fuel tank. The design scheme was analyzed with FEM software ANSYS,and the mechanical properties of the structure were evaluated. The scale model of the bearing structure of the manned spacecraft fuselage was developed for the structural performance tests,and the FEM analysis model and results were validated. The research achievements may provide a design reference for the light-weight fuselage structures of a novel manned spacecraft.
Based on the study results of the structure conceptual design,the mechanics analysis and the structural performance tests of a scale model,a light-weight conceptual design of the fuselage structures of a novel manned spacecraft was presented. The flexible composite membranes were employed to construct the large-area thermal protect structure of the manned spacecraft fuselage. A spatial truss structural system and a novel joint connection form were used to design the light- weight bearing structure of the manned spacecraft fuselage. An integrated scheme including the rigid bars and the flexible cables was proposed to design the connection system between the manned spacecraft fuselage and the fuel tank. The design scheme was analyzed with FEM software ANSYS,and the mechanical properties of the structure were evaluated. The scale model of the bearing structure of the manned spacecraft fuselage was developed for the structural performance tests,and the FEM analysis model and results were validated. The research achievements may provide a design reference for the light-weight fuselage structures of a novel manned spacecraft.
引文
[1]Mark Hempsell.A phased approach to orbital public access[J].Acta Astronautica,2010,66(1):1639-1644.
[2]邓扬晨,孙颖,曾惠华,等.大展弦比飞机翼身结构不同刚度对结构响应的影响[J].飞机设计,2006(4):1-6.Deng Yangchen,Sun Ying,Zeng Huhua,et al.Effects of different stiffness between wing and fuselage structures on structura l responses for high aspect ratio airplanes[J].Aircraft Design,2006(4):1-6.(in Chinese)
[3]王永恒,陈五一.基于结构仿生的飞行器支架轻量化设计[J].机械设计,2014,29(4):77-79.Wang Yongheng,Chen Wuyi.Lightweight design of aircraft support based on structural bionics[J].Journal of Machine Design,2014,29(4):77-79.(in Chinese)
[4]Varvill R,Bond A.Application of carbon fibre truss technology to the fuselage structure of the SKYLON spaceplane[J].Journal of the British Interplanetary Society,2004,57(1):1-13.
[5]梁波,易建政,周志强,等.飞行器防热研究概况及其发展趋势[J].装备环境工程,2008,5(4):41-44.Liang Bo,Yi Jianzheng,Zhou Zhiqiang,et al.General situation and development trend of aircraft thermal protection research[J].Equipment Environmental Engineering,2008,5(4):41-44.(in Chinese)
[6]Smith B P,Tanner C L,Mahzari M,et al.A historical review of inflatable aerodynamic decelerator technology development[C]//Big Sky,Montana,USA:2010 IEEE Aerospace Conference,paper#1276,2010.
[7]杨华保,王建.重复使用飞行器双层式结构连接研究[J].航空计算技术,2013,43(2):9-11.Yang Huabao,Wang Jian.Study on joint of reusable launch vehicle’s double-shell structure[J].Aeronautical Computing Technique,2013,43(2):9-11.(in Chinese)
[2]邓扬晨,孙颖,曾惠华,等.大展弦比飞机翼身结构不同刚度对结构响应的影响[J].飞机设计,2006(4):1-6.Deng Yangchen,Sun Ying,Zeng Huhua,et al.Effects of different stiffness between wing and fuselage structures on structura l responses for high aspect ratio airplanes[J].Aircraft Design,2006(4):1-6.(in Chinese)
[3]王永恒,陈五一.基于结构仿生的飞行器支架轻量化设计[J].机械设计,2014,29(4):77-79.Wang Yongheng,Chen Wuyi.Lightweight design of aircraft support based on structural bionics[J].Journal of Machine Design,2014,29(4):77-79.(in Chinese)
[4]Varvill R,Bond A.Application of carbon fibre truss technology to the fuselage structure of the SKYLON spaceplane[J].Journal of the British Interplanetary Society,2004,57(1):1-13.
[5]梁波,易建政,周志强,等.飞行器防热研究概况及其发展趋势[J].装备环境工程,2008,5(4):41-44.Liang Bo,Yi Jianzheng,Zhou Zhiqiang,et al.General situation and development trend of aircraft thermal protection research[J].Equipment Environmental Engineering,2008,5(4):41-44.(in Chinese)
[6]Smith B P,Tanner C L,Mahzari M,et al.A historical review of inflatable aerodynamic decelerator technology development[C]//Big Sky,Montana,USA:2010 IEEE Aerospace Conference,paper#1276,2010.
[7]杨华保,王建.重复使用飞行器双层式结构连接研究[J].航空计算技术,2013,43(2):9-11.Yang Huabao,Wang Jian.Study on joint of reusable launch vehicle’s double-shell structure[J].Aeronautical Computing Technique,2013,43(2):9-11.(in Chinese)