Interlaminar enhancement process for composite laminated plate for fuselage and airfoils of unmanned plane

Abstract

The invention discloses an interlaminar enhancement process for a composite laminated plate for a fuselage and airfoils of an unmanned plane. The interlaminar enhancement process comprises the following steps of: (1) preparing carbon fiber-reinforced resin matrix composite pins by utilizing a pultrusion molding process; (2) preparing a foam preform containing the carbon fiber-reinforced resin matrix composite pins; (3) implanting the carbon fiber-reinforced resin matrix composite pins in the foam preform into the composite laminated plate for the fuselage and the airfoils of the unmanned plane; and (4) testing mechanical properties of the composite laminated plate after the carbon fiber-reinforced resin matrix composite pins are implanted. By utilizing the process, the anti-low speed impact capability of the structure of the composite laminated plate for the unmanned plane, in particular the anti-interlaminar shearing strength of a stiffened structure of the composite laminated plate can be improved, and a solid foundation is laid for realizing light weight and low cost of the composite laminated plate.

Description

technical field [0001] The present invention relates to a kind of composite material laminated plate for unmanned aircraft fuselage and wing, more specifically, relates to a kind of composite material laminated plate for unmanned aerial vehicle fuselage and aircraft wing which is more resistant to low-speed impact and interlaminar shear strength. Wing composite laminates and interlaminar reinforcement process. Background technique [0002] In recent years, with the deepening of applied research and the development of molding technology, fiber reinforced resin matrix composites (Fiber reinforced resin matrix composites) have been widely used in aerospace structural parts. However, due to the limitation of the structure of the traditional classic composite laminate (Classic composite laminate) and the limitations of bonding, co-curing and other processes, the interlayer of the composite laminate is weak, so the interlaminar fracture toughness of the composite laminate (Interla...

AI Technical Summary

Problems solved by technology

However, this process can cause the following damage to the preform: fiber breakage, fiber misalignment, fiber bending, resin-rich areas, twisted stitches, microcracks, compaction

In addition, there are obvious deficiencies in the composite material laminated structural parts used in the existing drones, such as weak impact resistance, delamination at the reinforcement-wall board interface, etc.

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