耐高温复合材料舱体口盖设计方法研究

Study on Design Method of High Temperature Composite Material Hatch Cover

导弹的舱段壳体已经开始采用耐高温复合材料。对某复合材料舱段壳体进行屈曲载荷仿真分析,壳体开口位置首先发生失稳,且开口位置的应力应变较大。该复合材料的舱段壳体开口位置设计有口盖底座,口盖底座通过紧固件与壳体连接。选择合适的壳体开孔形式和紧固件型号及规格将直接影响复合材料舱体的强度。通过理论分析并设计典型复合材料试验件进行拉伸和压缩试验,获得了复合材料层合板不同的开口类型和不同型号及规格的紧固件对应的连接强度试验数据,为复合材料壳体口盖设计提供数据支持。

The high temperature composite material has been used in the shell section of the missile.The buckling load of a composite cabin shell is simulated and analyzed.It is found that the opening position of the shell is unstable first,and the stress and strain at the opening position are large.The opening position of the shell is designed with a mouth cover base,and the mouth cover base is connected with the composite material shell through a fastener.The selection of suitable shell opening form and the type and specification of fasteners will directly affect the strength of composite shell.Through theoretical analysis and design of typical composite test piece,tensile and compression tests were carried out.The experimental data of the joint strength of the fasteners with different opening types and different types and specifications of composite laminates were obtained,which provided data support for the design of composite shell cover.