Joints for joining panels together, such as for joining honeycomb sandwich panels used in aerospace applications, and methods of joining said panels are disclosed. In some examples of disclosed joints, a first panel and a second panel can be joined together to form a joint. The first panel can be a flat panel that includes a rabbet formed along a first longitudinal edge, and the second panel can be a curved panel that includes a notch formed along a second longitudinal edge. In forming the joint, a portion of the rabbet can be positioned within the notch, and the flat panel and curved panel can be oriented at a non-parallel and non-perpendicular angle to one another. Adhesive can be applied along the rabbet and/or the notch in order to secure the joint.

Joints for joining panels together, such as for joining honeycomb sandwich panels used in aerospace applications, and methods of joining said panels are disclosed. In some examples of disclosed joints, a first panel and a second panel can be joined together to form a joint. The first panel can be a flat panel that includes a rabbet formed along a first longitudinal edge, and the second panel can be a curved panel that includes a notch formed along a second longitudinal edge. In forming the joint, a portion of the rabbet can be positioned within the notch, and the flat panel and curved panel can be oriented at a non-parallel and non-perpendicular angle to one another. Adhesive can be applied along the rabbet and/or the notch in order to secure the joint.

The invention relates to methods of bonding and a conductively bonded joint, provided by high loadings of conductively coated nano scale particulate fillers in a conductive adhesive in combination with a conductive intermediary structure, more particularly to a lightning strike resilient bonded joint between fibre reinforced polymer composites. A method of joining a first fibre reinforced polymer composite surface and a second fibre reinforced polymer composite surface, comprising the steps of providing a conductive intermediary structure between said first and second surfaces, filling the void between said surfaces and enveloping said intermediary structure with a conductive adhesive, curing the conductive adhesive to form a bonded first and second surface. A conductive adhesive comprising a curable binder and a high aspect ratio nanoscale carbon particulate filler present in the range of from 0.1 to 40% wt, wherein said particulate filler comprises a metal coating.

The invention relates to methods of bonding and a conductively bonded joint, provided by high loadings of conductively coated nano scale particulate fillers in a conductive adhesive in combination with a conductive intermediary structure, more particularly to a lightning strike resilient bonded joint between fibre reinforced polymer composites. A method of joining a first fibre reinforced polymer composite surface and a second fibre reinforced polymer composite surface, comprising the steps of providing a conductive intermediary structure between said first and second surfaces, filling the void between said surfaces and enveloping said intermediary structure with a conductive adhesive, curing the conductive adhesive to form a bonded first and second surface. A conductive adhesive comprising a curable binder and a high aspect ratio nanoscale carbon particulate filler present in the range of from 0.1 to 40% wt, wherein said particulate filler comprises a metal coating.

A flexible elastomeric grip for the shaft of a golf club having an end cap with a cavity for receiving a sensor and/or counterweight. The cap has a durometer hardness equal to or greater than the tubular body portion of the grip and a flange sized to match the larger diameter of the body, with a sleeve engaging the inner periphery of the larger end of the tubular body. In one version of the cap, the sleeve portion is extended in length and has stiffening ribs on the outer surface of the sleeve; and, in another version, the sleeve is shorter and may also have stiffening ribs on the outer surface of the sleeve. In another version of the cap, fibrous material is disposed in the flange and sleeve to increase lateral stiffness without increasing durometer.

Crown reinforcement of an aircraft tire comprises a working reinforcement (2) radially inside of tread (3) and radially outside of carcass reinforcement (4). Working reinforcement (2) comprises two working bi-plies (21, 22) radially superposed with respective axial widths (L.sub.1, L.sub.2), from first axial end (I.sub.1, I.sub.2) to second axial end (I.sub.1, I.sub.2). Each working bi-ply (21, 22) comprises two working layers (211, 212; 221, 222) radially superposed and respectively made up of axially juxtaposed portions of strip (5) of axial width W extending circumferentially in periodic curve (6) that forms, in the equatorial plane (XZ) of the tire and with the circumferential direction (XX) of the tire, a non-zero angle A and has a radius of curvature R at its extrema (7). The difference DL between the respective axial widths (L.sub.1, L.sub.2) of the radially superposed working bi-plies (21, 22) is at least equal to 2(W+(RW/2)(1cos A)).

A welded joint between at least one metal material element and at least one thermoplastic material element is obtained by pressing the elements against each other while applying heat. Contact surfaces of the metal material, which are in contact with the thermoplastic material, are provided with uneven surface portions having a distribution of asperities. With heat applied, the thermoplastic material fills spaces between these asperities and maintains this configuration after subsequent cooling, thereby improving strength of the joint. The uneven surface portions are obtained in a preliminary forming step of the metal material in a press mold, which is configured with a forming surface for generating the uneven surface portions by mechanical deformation and/or with a device for guiding a laser or electron beam. By this technique, hybrid components are obtained made of one or more elements of metal material between which a shaped component of thermoplastic material is interposed.

A welded joint between at least one metal material element and at least one thermoplastic material element is obtained by pressing the elements against each other while applying heat. Contact surfaces of the metal material, which are in contact with the thermoplastic material, are provided with uneven surface portions having a distribution of asperities. With heat applied, the thermoplastic material fills spaces between these asperities and maintains this configuration after subsequent cooling, thereby improving strength of the joint. The uneven surface portions are obtained in a preliminary forming step of the metal material in a press mold, which is configured with a forming surface for generating the uneven surface portions by mechanical deformation and/or with a device for guiding a laser or electron beam. By this technique, hybrid components are obtained made of one or more elements of metal material between which a shaped component of thermoplastic material is interposed.

Blower vane for an aircraft turbine engine, the vane comprising a blade connected to a root, the vane being made of a woven fibre-based composite material embedded in a polymeric resin, the vane further comprising a medium for identifying the vane, which is a radio-identification medium, the blower vane being characterised in that it comprises at least a first portion the fibres of which are only electrically conductive fibres, and at least a second portion the fibres of which are formed by a mixture of electrically conductive fibres and non-electrically conductive fibres, and in that the identification medium is located in or on the second portion.

A fiber composite component having a first and a second fiber composite element each bent along a transverse axis opf the fiber composite component to have, respectively, in succession, a first and second base flange, a first and second web section, a first and second top flange and a first and second stiffening web. Respectively, the first and second base flanges are parallel to the first and second top flanges, the first and second web sections are angled with respect to each of the first and second base flanges and the first and second top flanges, the first and second stiffening webs are at right angles with respect to the first and second top flanges, and the first stiffening web and the second stiffening web are congruent with respect to one another, and are connected to one another, along a longitudinal axis of the fiber composite component.