Abstract: Disclosed is a method and a system for pretensioning fiber-reinforced plastic (FRP) sleeves surrounding an assembly of parts. The method includes application of pretensioning FRP sleeves surrounding a permanent magnet rotor with surface magnets.

Abstract: The present invention concerns a rod end that has a locking mechanism where the locking mechanism has an insert, a fork end, a female torque locking element, and a male torque locking element. Upon activation of the locking mechanism, the female torque locking element engages with the male torque locking element in a form-fitting connection. The locking mechanism of the present invention can easily be activated and is capable of withstanding a torque.

Abstract: Disclosed are methods and related compositions for producing a positive-locking load application for rod-shaped fiber composite structures, and the design thereof. The present invention concerns a method for producing a positive-locking load application for tension-compression rods from a fiber plastic hollow structure by means of an outer sleeve. In this process, a force pushes the fiber plastic hollow structure at least partially over at least one force application element, which is provided with at least one undercut to create a positive-locking connection. An object of the present invention is attained through local heating of the fiber plastic hollow structure to the point of plasticity of the fiber plastic hollow structure, at least in the region of the undercut(s) of the force application element, and application of at least one outer sleeve to the fiber plastic hollow structure in the region of the force application element.

Abstract: Disclosed are reinforced structures. The structures are comprised of reinforced elements that have continuous fibers embedded in a matrix material. The reinforced elements are combined in a matrix material to form a desired shape of reinforced structure.

Abstract: Disclosed are reinforced structures. The structures are comprised of reinforced elements that have continuous fibers embedded in a matrix material. The reinforced elements are combined in a matrix material to form a desired shape of reinforced structure.

Abstract: The invention relates to a strut, such as fiber composite struts used in aircraft or spacecraft, which has a largest possible outer diameter within a cylindrical installation space of the strut. The invention concerns an insert connected to a fiber composite hollow structure, such as a fiber plastic composite hollow structure, where the hollow structure engages an undercut of the insert, wherein the outer region of the fiber composite hollow structure likewise has an undercut and this undercut is filled with a fiber composite jacket, such as a fiber plastic composite jacket, and the inner region of the fiber composite hollow structure has, at least in one subregion, a core connected thereto.

Abstract: Disclosed is an apparatus and method for forming three-dimensional woven preforms that can be curved and have continuous fibers in the direction of curvature. Also disclosed are woven preforms formed thereby.

Abstract: The present invention achieves a high mechanical load capacity of a rod end by means of a component loop that passes around a bearing, where the component may be made of continuous-fiber reinforced composite material with thermoplastic matrix and where the continuous-fiber reinforced composite material with thermoplastic matrix may extend into a threaded stem of the rod end, and the component made of continuous-fiber reinforced composite material with thermoplastic matrix may be enclosed by short-fiber reinforced, long-fiber reinforced, or unreinforced thermoplastic. The threaded stem can be implemented with an external or an internal thread.

Abstract: Embodiments for clamps and shaping clamp systems are disclosed herein and drawn to such applications as, including but not limited to, an apparatus and method for forming three-dimensional woven preforms that can be curved and have continuous fibers in the direction of curvature. Embodiments of the clamps may include an upper clamp, and a lower clamp of complementary shape and mateable with the upper clamp, with the clamp being configured to receive a fabric therebetween.

Abstract: Woven preforms, for example those used for jet aircraft engine fancases, may need additional stiffeners to improve the strength and/or dynamic performance of the preform assembly, as well as to serve as attachment points. The present invention describes several improved woven preforms that include circumferential or axial stiffeners, as well as methods of manufacturing the same. One embodiment includes circumferential stiffeners added to a woven preform. Another embodiment includes sub-preforms with integral flanges that combine to make integral stiffeners. A further embodiment includes an intermediate stiffener wrapped onto a base sub-preform wrap, wherein the intermediate stiffener wrap incorporates intermediate stiffeners. Another embodiment incorporates bifurcations in one or more layers of an outermost wrap of a multi-layer fabric composite that forms a preform, wherein the bifurcated outer wrap is folded to form stiffeners that may be oriented circumferentially or axially.

Abstract: Disclosed is a method of forming a 3D woven omega-shaped stiffener by flat weaving a plurality of layers of interwoven warp and weft fibers to form a flat woven fabric having a cap portion, a first and a second web portion, a first and second foot portion, and an inner wrap portion. The 3D woven fabric is woven so that least some of the weft fibers are continuous across a juncture between the web portion and the foot portions. The flat woven fabric is then formed into the omega shape.

Abstract: Disclosed is an apparatus and method for forming three-dimensional woven preforms that can be curved and have continuous fibers in the direction of curvature. Also disclosed are woven preforms formed thereby.

Abstract: Disclosed is an apparatus and method for forming three-dimensional woven preforms that can be curved and have continuous fibers in the direction of curvature. Also disclosed are woven preforms formed thereby.

Abstract: Disclosed is an apparatus and method for forming three-dimensional woven preforms that can be curved and have continuous fibers in the direction of curvature. Also disclosed are woven preforms formed thereby.

Abstract: Preforms for use in fiber-reinforced composites, fiber-reinforced composites, and methods for making thereof are disclosed. One method includes interweaving a plurality of warp yarns with a single weft yarn so as to form a tubular woven structure with a central axis. The preform can be woven using an endless or tubular weaving technique, and can be woven so as to have two or more diameters along a length thereof. The preform can include one or more layers of a fabric formed on or attached to one or both surfaces of the tubular woven structure. The end structure can be a part of a window frame, a wheel rim, or a combustor in a jet engine.

Abstract: A three dimensional woven preform, a fiber reinforced composite incorporating the preform, and methods of making thereof are disclosed. The woven preform includes one or more layers of a warp steered fabric. A portion of the warp steered fabric is compressed into a mold to form an upstanding leg. The preform includes the upstanding leg and a joggle in a body portion. The body portion and upstanding leg are integrally woven so there is continuous fiber across the preform. A portion of the warp steered fabric includes stretch broken carbon fibers in the warp direction, and another portion includes conventional carbon fibers. The warp steered fabric can be woven on a loom equipped with a differential take-up mechanism. The warp steered fabric can be a single or multilayer fabric. The preform or the composite can be a portion of an aircraft window frame.

Abstract: Woven preforms, for example those used for jet aircraft engine fancases, may need additional stiffeners to improve the strength and/or dynamic performance of the preform assembly, as well as to serve as attachment points. The present invention describes several improved woven preforms that include circumferential or axial stiffeners, as well as methods of manufacturing the same. One embodiment includes circumferential stiffeners added to a woven preform. Another embodiment includes sub-preforms with integral flanges that combine to make integral stiffeners. A further embodiment includes an intermediate stiffener wrapped onto a base sub-preform wrap, wherein the intermediate stiffener wrap incorporates intermediate stiffeners. Another embodiment incorporates bifurcations in one or more layers of an outermost wrap of a multi-layer fabric composite that forms a preform, wherein the bifurcated outer wrap is folded to form stiffeners that may be oriented circumferentially or axially.

Abstract: Woven preforms, for example those used for jet aircraft engine fancases, may need additional stiffeners to improve the strength and/or dynamic performance of the preform assembly, as well as to serve as attachment points. The present invention describes several improved woven preforms that include circumferential or axial stiffeners, as well as methods of manufacturing the same. One embodiment includes circumferential stiffeners added to a woven preform. Another embodiment includes sub-preforms with integral flanges that combine to make integral stiffeners. A further embodiment includes an intermediate stiffener wrapped onto a base sub-preform wrap, wherein the intermediate stiffener wrap incorporates intermediate stiffeners. Another embodiment incorporates bifurcations in one or more layers of an outermost wrap of a multi-layer fabric composite that forms a preform, wherein the bifurcated outer wrap is folded to form stiffeners that may be oriented circumferentially or axially.

Abstract: A three-dimensional (3D) woven preform with channels in the through thickness direction developed for applications such as forming light weight preforms with an increased thickness.

Abstract: Woven preforms, for example those used for jet aircraft engine fancases, may need additional stiffeners to improve the strength and/or dynamic performance of the preform assembly, as well as to serve as attachment points. The present invention describes several improved woven preforms that include circumferential or axial stiffeners, as well as methods of manufacturing the same. One embodiment includes circumferential stiffeners added to a woven preform. Another embodiment includes sub-preforms with integral flanges that combine to make integral stiffeners. A further embodiment includes an intermediate stiffener wrapped onto a base sub-preform wrap, wherein the intermediate stiffener wrap incorporates intermediate stiffeners. Another embodiment incorporates bifurcations in one or more layers of an outermost wrap of a multi-layer fabric composite that forms a preform, wherein the bifurcated outer wrap is folded to form stiffeners that may be oriented circumferentially or axially.