航天运载器支架式主结构承载性能的有限元分析  

Load-bearing Capacity Analysis of Primary Truss Structures of Space Launch Vehicles

作　　者：彭超义[1] 曾竟成[1] 肖加余[1] 杜刚[1] 江大志[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《导弹与航天运载技术》2005年第6期16-20,共5页Missiles and Space Vehicles

基　　金：国家863项目基金(2003AA724052)

摘　　要：航天运载器主结构的功能是把载荷从一种结构传递到另一种结构上。依据对美国可重复使用运载器X-33和Atlas V型火箭上两种典型支架式CFRP(碳纤维增强树脂基复合材料)主结构的分析,建立了两种支架结构的有限元模型,计算了在支架轴向力、横向力和绕纵轴的扭矩及综合载荷作用下支架结构的形变、压缩比、偏心率和CFRP管件的轴向应力,通过计算结果对两种支架式主结构的承载性能特点进行了分析。Primary vehicle structure （PVS） is defined as the structure that carries loads from one to another structure or structures. Based on the analysis of two typical carbon fiber reinforced plastics （CFRP） truss structures used on the X-33 and Atlas V, two finite element analysis （FEA） models were constructed. The FEA models were employed to calculate the deformation, compressive ratio, and eccentricity of the truss structures and the axial compressive stresses of the CFRP cylindrical tubes under axial forces, transverse forces, and torsional forces. Consequently the load-bearing capacity characteristics of the two typical primary truss structures are analyzed.

关 键 词：航天器 支架 主结构 承载性能 有限元分析 

分 类 号：TB332[一般工业技术—材料科学与工程]