Grade T800Carbon Fiber Reinforced Resin Matrix Composites Design, Analysis And Forming Process Research

Advanced composite materials are widely used in aerospace structural design.Currently in the field of aerospace primary load-bearing structure of the main applicationof resin-based carbon fiber composite materials, paper draw on relevant research resultsat home and abroad on the basis of combined experience, the new design of a certain typeof aircraft nearly all-composite wing, and use Patran/common commercial Nastranfinite element analysis software for structural analysis and optimization.This design of the wing using autoclave molding technology. Autoclave moldingtechnology is mature, the paper design of the wing to meet manufacturing requirements.Under the premise to meet a variety of constraints, designers always strive for theaerospace vehicle design as light as possible, for continuing to explore a new approach todesign. Is clearly related to the concept, the paper introduces the concept and basicprinciples of optimization of design variables, constraints, objective function, etc. wereexplained. Analysis and optimization of the principle of finite element analysis softwareused herein Nastran were introduced, explained the general process of structuraloptimization using Nastran.Buckling of thin-walled structures common failure mode. Buckling occurs whendamage is often far from static structural damage to the load, the structure of the materialis a tremendous waste. This paper introduces the basic concepts of stability, and brieflydiscusses the principle of buckling analysis of Nastran analysis software. By analysis ofthe stability of a rectangular plate, in contrast with theoretical calculation results confirmthe accuracy of the calculation software. While the typical structure of the wing panelsreinforced an example for analysis, the results of the analysis of the stiffened panelbuckling under different boundary conditions.Based on the design constraints, the use of T800/803composite design of a certaintype of aircraft wing structures. And a whole wing molding process are described.According to the results of the design were to estimate the strength of the wing, the winggot the strain distribution. In order to improve the carrying capacity of the structure,reducing the weight of the structure, the structure of this chapter to the minimum weightfor the target, using Nastran software has been optimized for the wing structure, andultimately nearly full and efficient lightweight composite wing structure design.