Integrated forming method for composite material cabin section

Abstract

The invention provides an integrated forming method for a composite material cabin section, and belongs to the technical field of composite material forming. The integrated forming method comprises the following steps: designing molds corresponding to different area units of an inner molded surface of the cabin section, and taking the partitioned molds as male molds to carry out structural laying such as ribs, bosses, flanges, end frames and inner skins on the outer side surfaces of the partitioned molds; then combining the molds in different areas, and then carrying out outer skin structure laying to form an integrated overall structure; and finally, packaging the outer molded surface of the integrated overall structure by adopting a soft mold, and carrying out curing forming. The forming method adopted by the invention is simple in operation steps, can effectively realize integrated forming of the cabin section with a complex structure, and can guarantee the fiber continuity of the internal characteristic structure of the cabin section; and the prepared cabin section has relatively high inner and outer molded surface size precision, so that the subsequent processing and assembling efficiency is effectively improved, and the integrated forming method has a relatively good application prospect and a relatively good popularization value.

Description

technical field [0001] The invention relates to an integrated forming method for a composite material cabin, and belongs to the technical field of composite material cabin forming. Background technique [0002] With the continuous progress of science and technology and the development of various industries, higher technical requirements are put forward for the lightweight of structural parts. Resin-based composite materials have light weight, high specific stiffness, high specific strength, strong designability, good fatigue fracture resistance, good dimensional stability, and corrosion resistance. They are currently widely used in aviation, aerospace, transportation and other fields. high-performance structural materials. [0003] As the requirements for strength, stiffness and applicability of composite material parts increase, the structure of parts becomes more and more complex. Among them, the special-shaped cross-section cabin structural parts containing ribs, bosses...

AI Technical Summary

Problems solved by technology

The main disadvantages of this method: a. The accuracy of the size and position of the internal feature structure is low, and some complex structures are difficult to form

b. The structural adhesive is used to bond the feature structure and the skin, which makes it difficult to ensure fiber continuity

c. The process is relatively complicated, and the number of follow-up assembly and positioning molds is large; (2) The male mold autoclave forming is to use the male mold to lay up the internal structure and skin of the cabin, and then use the autoclave to cure, and finally use the machine Add trimming surface finish

The main disadvantages of this method are as follows: a. The skin needs to be thickened when laying layers, and a margin is reserved for the machine, resulting in waste of raw materials

b. The surface machining cost is high, the operation is difficult, and it is not suitable for mass production; (3) RTM molding is to fill the dry fiber into the mold cavity, and then inject glue to complete the cabin section molding

The main disadvantages of this method: a. There are many mold modules and the matching relationship is complicated

b. The design of the mold runner is difficult, and the complex structure is prone to dry spot defects after injection; (3) Molding is to use the male mold to lay the layer, and use the female mold to mold and solidify it after the laying is completed

The main disadvantages of this method are: a. The mold design is complex, and it is difficult to control the mold clamping gaps in multiple places, and it is not suitable for the cabin structure with special-shaped cross-sections

b. It is difficult to ensure uniform pressure in some characteristic areas of the inner surface, which affects the molding quality

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