A method for forming an integrally formed airfoil structure

Abstract

The invention provides a forming method of an integrally formed airfoil structure and belongs to the technical field of composite forming. According to the forming method of the integrally formed airfoil structure, the airfoil structure is formed by the combination of a sandwich (for example, a foaming adhesive and foaming aluminum), multiple layers of carbon fiber prepregs and short fiber composites. By adopting the sandwich structure, the quality of the whole structure can be greatly reduced. By adjusting the thickness and the position (passing a load center and an airfoil joint center) of carbon fibers between the multiple layers of carbon fiber prepregs which are wrapped outside the sandwich and the sandwich, the force bearing and transferring performance is improved. As the outline surface of the sandwich is parallel with the outline surface of an airfoil, the structural stability is ensured. According to the integrally formed airfoil structure, the structural form is free of the independent forming design of a main beam and free of the structural design of connecting part metal components, structure forming complexity is reduced, structure weight is reduced, and the whole load carrying and aeropneumatic performance is great.

Description

technical field [0001] The invention relates to a method for forming an integrally formed airfoil structure, which belongs to the technical field of composite material forming. Background technique [0002] At present, in the structural design of missile models, there are many types of airfoil structure, such as skin skeleton airfoil, radiating beam type stiffener integral structure airfoil, beam type honeycomb sandwich structure airfoil, etc., in order to transmit force The reliability of the airfoil generally requires a large number of parts to be processed separately, and the connection parts are generally made of metal parts, resulting in a more complex airfoil structure, a long manufacturing cycle, high weight, and a corresponding increase in cost. [0003] Composite materials have good rigidity, corrosion resistance, and low density, and the scope of application gradually shifts from secondary load-bearing parts to main load-bearing parts; the overall forming structure...

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Problems solved by technology

[0002] At present, in the structural design of missile models, there are many types of airfoil structure, such as skin skeleton airfoil, radiating beam type stiffener integral structure airfoil, beam type honeycomb sandwich structure airfoil, etc., in order to transmit force Generally, there are many parts that need to be processed separately, and metal parts are generally used for the connection parts, resulting in more complex airfoil structure, long manufacturing cycle, high weight and corresponding increase in cost

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