Entire grid beam optimum design method

Abstract

The invention relates to an optimum design method of an entire grid beam. By use of the electron beam fuse deposition molding technology, the method specifically comprises the following steps: step one, optimizing a structure size of a component according to a grid beam structure design allowable value given by design input to obtain an optimized size parameter; step two, determining force directions of different sections according to the size parameter, and designing that a fiber placement path of each section of the component is consistent with the force direction in combination with the mechanics optimum of a fiber placement direction; step three, lowering stress concentration of a stress region higher than the design allowable value according to the design allowable value; step four, if the entire grid beam is the component with high length ratio and stiffness mutation, first dividing the entire grid beam into a plurality of sections to be synchronously molded, and then performing the centralized molding connection. By use of the optimum design method of the entire grid beam disclosed by the invention, the process feasibility of the entire grid beam based on the electron beam fuse deposition molding technology can be guaranteed, and the strength, rigidity, the life and other design requirements can be satisfied at the same time.

Description

technical field [0001] The invention belongs to the field of aircraft structure design, and in particular relates to an optimal design method for a frame beam integral part. Background technique [0002] The main load-bearing skeleton of the traditional aircraft fuselage structure is composed of the transverse member of the reinforcement frame and the longitudinal member of the fuselage girder through mechanical connection. This combination structure has the following disadvantages: the connection parts, fasteners, and process sink more, and the weight cost is high; the connection area is prone to stress concentration, resulting in structural fatigue failure; various parts require multiple molds and tools to manufacture, and the assembly process is cumbersome. The production cycle is long and the cost is high. These factors are the bottlenecks restricting the development of aircraft fuselage structure design. [0003] Compared with the conventional combined frame, the fram...

AI Technical Summary

Problems solved by technology

This combination structure has the following disadvantages: the connection parts, fasteners, and process sink more, and the weight cost is high; the connection area is prone to stress concentration, resulting in structural fatigue failure; various parts require multiple molds and tools to manufacture, and the ass

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