Machining method and structure of composite material wing cover

Abstract

The invention discloses a machining method and a structure of a composite material wing cover. The structure comprises multiple paving layers, wherein an access hole is formed in the wing cover, a slope surface matched with the edge of an access cover is arranged at the edge of the access hole, and the paving layers comprise manual paving layers and automatic paving layers which are paved in a staggered and stacking manner. The machining method comprises the following steps: A. cutting and prefabricating each manual paving layer, with the sizes of prefabricated holes in the manual paving layers changing layer by layer to form the slope surface; B. paving one automatic paving layer on one side of an appearance mould as the first layer, stacking the manual paving layers and the automatic paving layers alternately, and sequentially stacking the manual paving layers to corresponding positions from big to small according to the sizes of the prefabricated holes; C. curing the wing cover; and D. machining the access hole. According to the machining method and the structure disclosed by the invention, a concave type composite material cover structure is formed by alternately stacking and paving the manual paving layers and the automatic paving layers, so that the fiber delamination damage of the wing cover caused by conventional machining is avoided, the overall force-transfer characteristic of the access hole of the cover is ensured, and the structural strength of the access hole is improved.

Description

technical field [0001] The invention relates to the technical field of aircraft skins, in particular to a processing method and structure of composite material wing skins. Background technique [0002] In order to meet the needs of daily maintenance, the lower surface of the wing of the aircraft is provided with an inspection opening, so that the skin of the wing is provided with an opening, and an inspection cover is provided at the opening to cover the opening. [0003] In order to make the outer surface of the wing maintain a flat aerodynamic shape after the inspection cover is embedded in the wing, the traditional method is to add a slope to the opening edge of the wing skin, and the slope matches the edge of the inspection cover. [0004] Since mechanical processing will cause delamination damage to the wing skin fibers of composite materials, it will have an adverse effect on the mechanical properties of the aircraft. For small and medium-sized aircraft, the method of ...

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Problems solved by technology

[0004] Since mechanical processing will cause delamination damage to the wing skin fibers of composite materials, it will have an adverse effect on the mechanical properties of the aircraft. For small and medium-sized aircraft, the method of cutting composite materials layer by layer and manually laying them down, but this The method is limited in molding quality and production efficiency, and it is difficult to apply to the wing skin structure of large aircraft

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