Abstract: An aircraft antenna (101) including a radome (102) wherein the radome (102) has a main body (105) shaped to enclose one or more antennae (107) when the antenna (101) is attached to a fuselage skin portion (103), wherein the main body (105) includes a front surface portion (203), a rear surface portion (401), adjacent side surface portions (205,207), and an upper surface portion (209) that form a smooth outer aerodynamic surface (211) of the antenna (101), and wherein the upper surface (209) is substantially planar in shape along a length of 60% to 80% of a length (L) of the of the radome (102).

Abstract: An illumination system for illuminating outer aircraft components of an airborne vehicle, such as an aircraft, includes a light projection system configured to project visual imagery to an outer surface of the airborne vehicle, and a projection controller having a light control processor configured to control the operation of the light projection system on the basis of at least one of operational flight status of the airborne vehicle, geographical location of the airborne vehicle and configuration data of movable surfaces of the airborne vehicle or on ambient light measurement.

Abstract: An aircraft antenna assembly has a structural section of an aircraft, an antenna element, a cover transparent to radio waves, and a structural element. The structural section has an assembly of interconnected elongate longitudinal and transverse reinforcing elements and an outer skin arranged on one side of the assembly and secured on the reinforcing elements. A surface of the outer skin facing away from the elements forms an outer surface of the structural section. An opening closed by the cover, is formed in the outer skin. In the region of the opening, at least one of the reinforcing elements has a gap, in which the structural element is arranged and which divides the respective reinforcing element into two sections on opposite sides of the gap. The antenna element is arranged in the region of the opening on the opposite side of the outer skin from the outer surface.

Abstract: An aircraft including a primary-structure connection element for attaching the aircraft skin to the primary structure of the aircraft is provided. The primary-structure connection element is designed as a shearweb, a clip and/or as a frame stabilization element or as a rib stabilization element and is manufactured from a fiber-reinforced thermoplastic material with the use of injection molding. Likewise, an injection molding method for the manufacture of such a primary-structure connection element is provided, in which method the fiber-reinforced thermoplastic material is injected in its melted state into an injection molding device. The manufactured shearweb etc. is removed from the injection molding device. In this method, in particular, chopped carbon fibers and/or glass fibers in combination with polyphenylene sulfide (PPS) and/or polyetherether ketone (PEEK) are used, for example also in pellet form.

Abstract: A method for producing a connector, in particular for repair, in particular in the field of aviation and aerospace, including the steps of: providing a base layer; attaching a first layer of fiber composite material having a first rigidity to the base layer; attaching a second layer of fiber composite material having a second rigidity to the first layer, offset therefrom, the second rigidity being greater than the first rigidity; and riveting the first layer to the base layer and riveting the second layer to the first layer and to the base layer.

Abstract: An aircraft including a primary-structure connection element for attaching the aircraft skin to the primary structure of the aircraft is provided. The primary-structure connection element is designed as a shearweb, a clip and/or as a frame stabilization element or as a rib stabilization element and is manufactured from a fiber-reinforced thermoplastic material with the use of injection molding. Likewise, an injection molding method for the manufacture of such a primary-structure connection element is provided, in which method the fiber-reinforced thermoplastic material is injected in its melted state into an injection molding device. The manufactured shearweb etc. is removed from the injection molding device. In this method, in particular, chopped carbon fibers and/or glass fibers in combination with polyphenylene sulfide (PPS) and/or polyetherether ketone (PEEK) are used, for example also in pellet form.

Abstract: A structural element for reinforcing a fuselage cell of an aircraft is provided. The structural element comprises a reinforcement profile which is made in one piece from a metallic material. The profile is provided with a strap at least in regions. As a result of the strap which is made of a fiber-reinforced layer material or fiber metal laminate and is adhesively bonded, at least in regions, to a flange of the reinforcement profile the structural element has high damage tolerance and advantageous fatigue properties. The fiber metal laminate or layer material is made of a plurality of metal layers and fiber-reinforced plastics material layers which are stacked in alternating fashion and adhesively bonded to one another over the entire surface. The reinforcement profile and the strap are joined by means of a joining layer. Said joining layer is preferably constructed from two prepreg layers and a non-fiber-reinforced adhesive layer.

Abstract: The present invention provides a door frame construction in particular for an aircraft or spacecraft, including a former; a fibre metal laminate which is connected to the former; and an outer skin which is connected to the fibre metal laminate.

Abstract: A method for producing a connector, in particular for repair, in particular in the field of aviation and aerospace, including the steps of: providing a base layer; attaching a first layer of fibre composite material having a first rigidity to the base layer; attaching a second layer of fibre composite material having a second rigidity to the first layer, offset therefrom, the second rigidity being greater than the first rigidity; and riveting the first layer to the base layer and riveting the second layer to the first layer and to the base layer.

Abstract: A structural element for reinforcing a fuselage cell of an aircraft is provided. The structural element comprises a reinforcement profile which is made in one piece from a metallic material. The profile is provided with a strap at least in regions. As a result of the strap which is made of a fibre-reinforced layer material or fibre metal laminate and is adhesively bonded, at least in regions, to a flange of the reinforcement profile the structural element has high damage tolerance and advantageous fatigue properties. The fibre metal laminate or layer material is made of a plurality of metal layers and fibre-reinforced plastics material layers which are stacked in alternating fashion and adhesively bonded to one another over the entire surface. The reinforcement profile and the strap are joined by means of a joining layer. Said joining layer is preferably constructed from two prepreg layers and a non-fibre-reinforced adhesive layer.