A partitioned pressure forming method for a closed airfoil structure

Abstract

A closed airfoil structure partition press molding method, suitable for composite material structure molding method and mold with large elongation scale, double curvature shape and upper, lower, left and right closed sections of aircraft airfoil Scheme, the airfoil structure scheme consists of upper and lower skin honeycomb sandwich panel structures and multiple longitudinal beam structures arranged in the middle. The forming method includes the use of upper and lower shape control molds and vacuum bags for the panel in the interlayer area between the internal beams. And the combination of threaded pipe torque adjustable auxiliary struts and baffles is used to realize the pressure control of all surfaces of the composite material. The present invention can realize the integrated high-precision molding of the structure through co-curing by adopting the method of unequal pressurization in different regions under the condition of different curing pressures required for pressing different parts such as honeycomb sandwich and laminated board.

Description

technical field [0001] The present invention relates to a closed airfoil structure divisional compression molding method, which is mainly used for the aircraft airfoil structure with larger scale expansion, and the upper and lower skins including honeycomb sandwich and the middle-added beam structure are integrally glued together Cured molding. Background technique [0002] With the rapid development of aircraft, composite materials for lightweight, high-efficiency, low-cost and rapid manufacturing technology have become one of the main solutions for aircraft structural design. The main direction of application, however, is limited by the low section height of the wing structure, resulting in the inaccessibility of the operating space. In particular, most resins require a curing system under pressure or even heating to achieve reliable bonding of the structure. Therefore, the current It is difficult to achieve the integral molding of the wing structure by the manufacturing ...

AI Technical Summary

Problems solved by technology

[0002] With the rapid development of aircraft, composite materials for lightweight, high-efficiency, low-cost and rapid manufacturing technology have become one of the main solutions for aircraft structural design. The most difficult airfoil structure for aircraft structure weight reduction and manufacturing is composite materials. The main direction of application, however, is limited by the low section height of the wing structure, resulting in the inaccessibility of the operating space, especially the vast majority of resins need to be pressurized or even heated to achieve reliable bonding of the structure, so the current It is difficult to realize the integral molding of the wing structure with advanced manufacturing technology

The wing usually adopts a semi-monocoque structure scheme. The structure scheme generally adopts the co-solidification of the upper and lower skins and the longitudinal stringers, and then the transverse ribs and the wing wall structure are mechanically connected on the upper and lower sides respectively or a The structural scheme of side glued and one side mechanically connected leads to the unavoidable use of a large number of fasteners to connect the wing, especially the high cost of single-sided fasteners, because the static strength of composite materials is very sensitive to openings , and has high requirements on the hole-making process, which not only reduces the structural efficiency but also causes the cost and manufacturing cycle to remain high. Therefore, the process requirements and its urgent

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