Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

A blade made of layered material, such as composite material, configured for exposure to a fluid flow, comprises skins (1, 2) defined between a leading edge (3) and a trailing edge (4) which skins in cross-section form a flow profile. The layered material may consist of several layers of fiber material (5, 5′, . . . ) impregnated with a matrix material, wherein layers of fiber material each comprise a respective body portion (6, 6′, . . . , 13) between and transverse to the skins and each at least a respective skin portion (7, 7′, . . . ; 8, 8′, . . . ) that forms part of the skins. The said skin portions all extend from the related body portion in the direction of the trailing edge. Of said skin portions at least two consecutive skin portions of the one skin overlap and/or two consecutive skin portions of the other skin overlap each other.

A method of manufacturing a cured composite structure includes placing a radius filler element into a radius cavity extending along a length of a composite base member formed of dry fiber material comprised of reinforcing fibers. The radius filler element is formed of a radius filler material. The method also includes infusing resin into the dry fiber material, and chemically reacting the resin with the radius filler material to create a mixture of resin and radius filler material along side surface interfaces between the radius filler element and the composite base member. The method additionally includes curing or solidifying the resin, and allowing solvent in the resin to evaporate causing hardening of the mixture and bonding of the radius filler element to the composite base member, and resulting in a cured composite structure.

A method of manufacturing stiffened structural panel for an aircraft including a main sheet made of composite material with unidirectional fibers, and a stiffening structure secured to the main sheet and made of a composite material comprising a resin and chopped fibers, the stiffening structure including on the one hand a base adhering to one of the two lateral faces of the main sheet, and a network of stiffeners in the form of a grid projecting from the base. The method includes a step of compression molding the stiffening structure from a block formed of a prepolymer reinforced with chopped fibers.

[Problem]

To increase rigidity.

[Solution]

Provided is a structure including a main body portion, a plurality of reinforcement members arranged on the main body portion, each of the reinforcement members including a base material formed of resin or metal. Provided is a manufacturing method of a structure which includes a main body portion having a hollow configuration surrounding an internal space thereof. The manufacturing method includes a preparation step of preparing a plurality of reinforcement members each including at least a base material formed of resin or metal, a carrying-in step of carrying the plurality of reinforcement members into the internal space from an opening arranged at the main body portion, and a step of arranging a fixing portion which fixes the plurality of reinforcement members into the main body portion.

[Problem]

To increase rigidity.

[Solution]

Provided is a structure including a main body portion, a plurality of reinforcement members arranged on the main body portion, each of the reinforcement members including a base material formed of resin or metal. Provided is a manufacturing method of a structure which includes a main body portion having a hollow configuration surrounding an internal space thereof. The manufacturing method includes a preparation step of preparing a plurality of reinforcement members each including at least a base material formed of resin or metal, a carrying-in step of carrying the plurality of reinforcement members into the internal space from an opening arranged at the main body portion, and a step of arranging a fixing portion which fixes the plurality of reinforcement members into the main body portion.

A rib foot cleat for sealing around a stringer passing through a rib mouse hole in an aircraft assembly. The rib foot cleat has a body for attaching to a rib at a rib mouse hole and defines a cleat channel configured to be arranged over the stringer. The rib foot cleat also has an injection hole through the cleat body which is in fluid communication with the cleat channel, to allow sealant material to be injected through the injection hole in to the cleat channel for sealing around the stringer.

A rib foot cleat for sealing around a stringer passing through a rib mouse hole in an aircraft assembly. The rib foot cleat has a body for attaching to a rib at a rib mouse hole and defines a cleat channel configured to be arranged over the stringer. The rib foot cleat also has an injection hole through the cleat body which is in fluid communication with the cleat channel, to allow sealant material to be injected through the injection hole in to the cleat channel for sealing around the stringer.

Methods of manufacturing of aerospace structures are disclosed. More specifically, methods of manufacturing relatively lightweight yet strong aerospace structures. In one embodiment, the method includes the addition of a volume of a rigid and flexible polyurethane mixture into a mold to create a composite structure. In one aspect, the method includes the integration of special structures within a larger structure to remove traditionally structurally weak or vulnerable areas.