Composite Structure Analysis And Optimization Of Missile With Non-Circular Cross-Sections Shape

Analysis and optimization of composite laminates are important issues early during developing a new-type advanced missile. A missile with non-circle section shape body is chosen as the research object. Its main structural material is composite. The paper can be divided into the following three parts:In the part of finite element (FE) modeling, several ways to simulate the joint interfaces between 3D solid and shell elements are investigated. Using temperature load to simulate the bolts' preload is an effective ways. The author combined it with MPC to model bolt joints. Also effective mesh tech. is considered in this section. Then the whole finite element model of the missile is given.Analysis of composite laminates by FE method and implements in Nastran are discussed firstly in the second parts. Then static strength and normal mode analysis are investigated. A non-linear FE analysis followed with normal model analysis is executed to investigate how aerodynamic loads affected the normal mode. The results show that aerodynamic loads mostly affect the lower rank vibrations.Several available methods to optimize the laminated structures are discussed in the third parts. Then a more effective optimization method fitted to real complexity engineering structures is given. The method makes the FSD and mathematics programming (MP) combined together. And both are integrated to a multi-level optimization chart. Optimization results of the missile's composite structures validate that the method is practicability.