A composite part is provided and includes a component, a first set of first composite plies with finite lengths and a second set of second composite plies with finite lengths. A respective end of each of the first composite plies is wrapped around the component in a clockwise wrapping direction and includes first fibers. A respective end of each of the second composite plies is wrapped around the component in a counter-clockwise wrapping direction and includes second fibers.

A composite metallic joint assembly may include a composite metal rod having a metal liner and a composite material disposed around the metal liner. A first portion of the composite metal rod may comprise the composite material and the metal liner and a second portion of the composite metal rod may comprise the metal liner exposed at a radially outer surface of the composite metal rod. The metal liner may have a first radial thickness at a first axial position corresponding to the first portion of the composite metal rod and a second radial thickness at a second axial position corresponding to the second portion of the composite metal rod. The second thickness may be greater than the first thickness.

Systems and methods for landing gear arrangements are provided. In various embodiments, a landing gear arrangement may comprise a first composite layer, the first composite layer having a cylindrical geometry, a metallic ring comprising an inner surface and an outer surface, the metallic ring perimetrically surrounding at least a portion of the first composite layer, the inner surface being in contact with the first composite layer, a metallic connecting tab extending away from the outer surface, and a second composite layer at least partially perimetrically surrounding the metallic ring and at least partially perimetrically surrounding the first composite layer, the outer surface being in contact with the second composite layer.

A collar for having in cross-section a generally triangular filler section and a generally rectangular outer section over the filler section. The collar may be part of a tube assembly where the collar serves to couple a fitting to tube. A method of installing the collar includes pressing the collar over the outer surface of the tubing until the strain on the collar in the hoop direction is at a predetermined level.

The method includes producing an initial preform on a mandrel by filament winding without generating shrinking, cutting the initial preform to the correct length, placing the assembly provided beforehand with internal drainage device and pressurization device into a female mold, and bringing the preform assembly to a softening temperature and pressurizing the assembly at both ends until it is deformed by a diametrical increase in its dimensions. The method further includes bringing the impregnation resin to polymerization temperature and pressure in order to allow the workpiece to consolidate, its external shape becoming consistent with the internal shape of the mold, opening the mold and removing the workpiece from the mold, and machining the final shapes of the composite workpiece.

A joining structure according to one embodiment of the present invention includes a first member and a second member, the first member having a hole extending along an axis direction, the second member including a shaft member, the shaft member being formed of a fiber-containing composite material and having a shape to fit in the hole, the second member being joined to the first member via the shaft member so that movement thereof in the axis direction is restricted.

A link arm member of the present invention is used in a vehicle for connecting a suspension and a stabilizer, and includes: a support bar that is sealed by plastically deforming a hollow metal pipe at both ends thereof; and a housing part made of resin that is arranged at each end of the support bar and has a receiving hole for receiving a ball part of a ball stud to which the suspension or the stabilizer is fixed, wherein the housing part is formed by insert molding with the support bar.

The manufacture of structural elements for aircraft requires the use of complex and costly methods, particularly in the case of parts of elongate overall shape and variable thickness or cross section made of composite material. The disclosure herein proposes to overcome this problem by a method that allows the manufacture of a structural part from a preform made of composite material of simple shape obtained by pultrusion and of one or more reinforcing elements made of composite material and secured by cocuring with the preform to a region of this preform which region is to be reinforced.

A chassis link for a motor vehicle having load introduction elements connected by a straight profile portion of fiber-reinforced plastic. The profile portion and load introduction elements are connected via an adhesive connection in a common connection portion in which an end portion of the load introduction element and an end portion engage another in positive engagement. On both sides of a profile portion neutral fiber plane, the adhesive connection has longitudinal adhesive layers extending in a longitudinal direction of the profile portion and parallel to one another in a vertical. In vertical direction of the profile portion the longitudinal adhesive layers have a cross-sectional area becoming larger with increasing distance from the neutral fiber plane so that a relief is brought about in regions of the adhesive connection which have a relatively large distance from the neutral fiber plane in vertical direction of the profile portion.

A composite shaft with an end fitting mounted on an interface region on at least one end of said shaft, wherein in said interface region the shaft is tapered; and wherein said end fitting comprises a surface with matching taper, the surface engaging with said interface region.