The invention discloses an aircraft skin small damage positioning method based on a honeycomb model. The method comprises the following steps: establishing an aircraft skin small damage positioning system; calibrating cameras; arranging honeycomb model mark points at a damage part on the surface of the aircraft skin; shooting the damage part by utilizing the cameras; performing sub-pixel level processing on shot original images to obtain pixel edges of the mark points; extracting hexagon boundary points from the pixel edges; computing the straight lines passing through the centers of the markpoints and intersection coordinates of the straight lines according to the hexagon boundary points; and computing the actual center locations of the mark points according to intersection coordinates of the mark points. The feature contrast and matching between the mark points on the aircraft skin surface can be realized, and then the precise detection on the aircraft skin damage part can be realized; the method has the significance that the positioning design is performed by utilizing the infinity and seamless external expansion of the inscribed regular hexagon honeycomb model of a circle, thereby reaching high-matching efficiency and high-detection precision of the aircraft skin damage detection.

Aircraft skin small damage positioning method based on honeycomb model

An aircraft flap is constructed of nested layers of composite material in the aircraft flap that include an inner layer, a middle layer and an outer layer. The aircraft flap is constructed with the inner layer laid up around a central mandrel, the middle layer laid up around the middle layer and the outer layer laid up around the middle layer. The inner layer, the middle layer and the outer layer are co-cured on the mandrel, removed from the mandrel and then assembled together with the inner layer formed in a folded over configuration around a hollow interior volume of the aircraft flap, the middle layer formed in a folded over configuration over the inner layer, and the outer layer formed in a folded over configuration around the middle layer.

Trailing edge flap having a waffle grid interior structure

Aircraft components and aircraft are provided. An aircraft includes the aircraft component. The aircraft component includes an outer skin portion, a plurality of major stiffeners, and a plurality of minor stiffeners. The outer skin portion has an interior side and an exterior side configured to define an exterior boundary of the aircraft. The major stiffeners are integral with the outer skin portion and extend out from the interior side. The major stiffeners are configured to resist global deflection of the aircraft component in response to a bird strike on the aircraft component. The minor stiffeners are disposed between the major stiffeners, are integral with the outer skin portion, and extend out from the interior side. The minor stiffeners are configured to resist perforation of the aircraft component in response to the bird strike on the aircraft component.

Unified canopies for aircraft

A composite reinforcement structure including a first skin having a first end and a second end and a second skin having a first end and a second end. The first end of the first skin and the first end of the second skin are coupled. A corrugated spar is disposed between the first skin and the second skin and is bonded to the first skin and the second skin.

Composite reinforcement structures and aircraft assemblies comprising composite reinforcement structures

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Unified canopies for aircraft

Composite reinforcement structures and aircraft assemblies comprising composite reinforcement structures