机身复合材料加筋板壳的稳定性及强度分析系统

Analysis System of Stability and Strength for Airframe Composite Stiffened Plate/Shell

随着先进复合材料在飞机主承力结构(如机身结构)中的大量应用,工程上迫切需要大型复合材料加筋板壳的快速建模打样计算、稳定性(刚度)和强度分析的理论和程序支持。基于稳定性理论,并综合复合材料任意加筋板壳有限单元和复合材料层合板壳失效理论等方面的成果,开发了一个机身复合材料加筋板壳结构的稳定性及强度分析程序(CSSAP)。该程序系统不仅可以进行复合材料(加筋)板壳的线性稳定性和强度分析,还可进行非线性稳定性和强度分析;可对较粗的网格划分,得到临界屈曲应变和后屈曲时的应力。通过一些算例与文献结果的对比,表明本程序系统能够满足工程上的精度要求。并且,通过对实际机身一个典型复合材料加筋板壳的计算,表明本程序系统也可用于飞机工程复杂结构的分析。

With more and more wide application of composite materials as the main carrier structures of aircraft （for example airframes）, theories and procedures of their speedy simulation and layout calculation as well as their stability （stiffness） and strength analysis are needed urgently in engineering. Based on the theory of stability and recent advances in research about composite stiffened plate/shells with arbitrary direction rib elements as well as the failure theories of laminated composite plate/shells, this article developed a new procedure for the stability and strength analysis （CSSAP） of airframe composite stiffened plate/shells. This analysis system can not only be used to analyze the linear stability and strength of composite plate/shells with ribs, but also their nonlinear stability and strength. Both the critical buckling strain and the stress in post buckling can also be obtained on a fairly coarse （not too fine） mesh scale. A comparison with the results of existing methods shows that this procedure can better satisfy the demands of precision in engineering. Moreover, according to the calculation results of a typical example of a real airframe, this procedure can be effectively used to analyze complex structures.