Integral co-curing molding process for multi-beam box sections of composite materials

Abstract

The invention provides an integrated co-curing forming technology method for a composite material multi-beam box section. The integrated co-curing forming technology method comprises the following steps of: arranging a beam flat plate; pre-forming the beam flat plate; vacuumizing; premounting a beam; arranging an upper wall plate and a lower wall plate; combining the beam; arranging spilling bars; closing the upper wall plate; vacuumizing; extracting a core die; curing the core die; and demolding the core die. The technology method is easy to operate and high in repeatability. In a curing process, the core die is pulled out; the openness of a manufactured piece is high; heat conduction and temperature uniformity are facilitated; and the inner quality of the manufactured piece is easy to guarantee.

Description

technical field [0001] The invention relates to the technical field of solidification and molding, in particular to an overall co-curing molding process for multi-beam box sections of composite materials. Background technique [0002] Composite materials have many excellent characteristics such as high specific strength and specific modulus, designable performance, and easy overall forming. The extensive application of composite materials has become the development trend of civil aircraft. With the development of composite material design and application technology, the overall multi-beam box segment structure is more and more widely used in civil aircraft, and the traditional dense rib structure (composed of upper and lower panels, front and rear beams and multiple ribs) Compared with the integral multi-beam box section, the number of parts is reduced from many to one, which simplifies the assembly process of the box section, and reduces the number of fasteners and the numb...

AI Technical Summary

Problems solved by technology

Since the RTM process requires high resin fluidity, it can only be applied to a specific resin system, and the resin content of the molded parts is high and unstable, so it cannot be used for the manufacture of aircraft load-bearing box sections

However, the rubber airbag is inflated and pressurized by the rubber airbag. Because the airbag is in the cavity, the temperature uniformity of the entire part and the mold is poor; and there are problems such as rubber aging and difficulty in calculating the expansion amount, which is easy to cause uneven pressure. , thus causing the position of the beam to shift, and the quality of the overall box section cannot be guaranteed

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