An improved universal zero-moment support and adapter plate assembly is shown and described. In one embodiment, the assembly comprises an adjustable zero-moment support configured together with an off-axis adjustment. In other embodiments, an adapter and support assembly includes an external fitting, an adapter plate and an adjustable zero-moment support.

An improved universal zero-moment support and adapter plate assembly is shown and described. In one embodiment, the assembly comprises an adjustable zero-moment support configured together with an off-axis adjustment. In other embodiments, an adapter and support assembly includes an external fitting, an adapter plate and an adjustable zero-moment support.

An electronics system for an aircraft includes a mounting structure and a plate element mounted to the mounting structure with opposing face surfaces, a central region and side edge regions. A serpentine passage in the plate element contains alternating liquid slugs and vapor plugs along its length. The plate element is configured for gathering heat proximate the central region and moving the heat to the side edge regions. An electronic system is mounted on a face surface of the plate element and a heat dissipating structure is thermally coupled with the plate element and positioned along the side edge regions thereof for dissipating heat moved to the side edge regions. A cover structure covers the plate element and electronic system.

An electronics system for an aircraft includes a mounting structure and a plate element mounted to the mounting structure with opposing face surfaces, a central region and side edge regions. A serpentine passage in the plate element contains alternating liquid slugs and vapor plugs along its length. The plate element is configured for gathering heat proximate the central region and moving the heat to the side edge regions. An electronic system is mounted on a face surface of the plate element and a heat dissipating structure is thermally coupled with the plate element and positioned along the side edge regions thereof for dissipating heat moved to the side edge regions. A cover structure covers the plate element and electronic system.

An airfoil system is provided that includes an airfoil. This airfoil includes a first exterior surface, a second exterior surface, a first airfoil segment and a second airfoil segment. The airfoil extends widthwise between the first exterior surface and the second exterior surface. The first airfoil segment includes first composite material and a receptacle. A base of the receptacle is embedded within the first composite material. The second airfoil segment includes second composite material and a key. A base of the key is embedded within the second composite material. The key is mated with the receptacle thereby attaching the second airfoil segment to the first airfoil segment.

There is provided a method of mounting equipment to an aircraft having an empennage. The method comprises mounting equipment to a mounting structure for mounting to the aircraft; removing an access panel from the outer skin of the empennage of the aircraft to reveal an access panel opening into the empennage; and attaching the mounting structure to or within the access panel opening such that at least a portion of the equipment extends beyond the outer skin of the empennage. The shape of the mounting structure at least partly conforms to the shape of the access panel opening. The method also comprises covering the mounting structure and the equipment mounted thereon with a cover, and attaching the cover to the mounting structure or the empennage. An assembly, structure, tailplane and aircraft are also provided.

A laminated glazing unit includes at least one first sheet of glass and one second sheet of glass glued to one another via a first adhesive interlayer, the first sheet of glass being intended to constitute the surface of the laminated glazing unit in contact with the outside atmosphere, in which the laminated glazing unit further includes, between the first sheet of glass and the second sheet of glass, an LOC (Localizer) antenna receiving between 100 and 120 MHz and a GLIDE (Slope) antenna receiving between 320 and 340 MHz, each antenna having dimensions that are sufficiently small not to hamper the vision, even to be practically invisible through the laminated glazing unit.

A laminated glazing unit includes at least one first sheet of glass and one second sheet of glass glued to one another via a first adhesive interlayer, the first sheet of glass being intended to constitute the surface of the laminated glazing unit in contact with the outside atmosphere, in which the laminated glazing unit further includes, between the first sheet of glass and the second sheet of glass, an LOC (Localizer) antenna receiving between 100 and 120 MHz and a GLIDE (Slope) antenna receiving between 320 and 340 MHz, each antenna having dimensions that are sufficiently small not to hamper the vision, even to be practically invisible through the laminated glazing unit.

A method for arranging a set of antennas capable of transmitting or receiving in a radio frequency range in an existing aerodyne implemented either during an initial installation operation, or in a subsequent maintenance or update operation is disclosed. The method includes removing at least one component of a structural element external to the bearing surface of the existing aerodyne, the component being substantially transparent to the radio frequency range; installing the set of antennas in a zone exposed by the removal in the step; fitting an electronic and electrical harness connecting the set of antennas to a radio communications system and to a power supply inside the fuselage; re-forming the external structural element in such a way as to cover the installed set of antennas.

An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail.