Abstract: A window mounting structure that has a mounting support interface which is installed on an aircraft fuselage. The window pane assembly is inserted in the window opening and a mounting frame is pressed onto the mounting support interface. The mounting frame may be locked in place with a locking member.

Abstract: A movable cargo support for an aircraft cargo hold or passenger cabin includes a base. The base has a bottom surface with support(s) to support the base member on a floor surface of the cargo hold or passenger cabin. The base has wheel assemblies, each wheel assembly having at least one wheel rotatable about a rotation axis and movably mounted on the base to pivot about a steering axis of the wheel assembly. The at least one wheel of each wheel assembly is movable between an extended position, in which the at least one wheel protrudes beyond the support plane, and a retracted position, in which the at least one wheel does not extend beyond the support plane. Each wheel assembly has a biasing member for biasing the at least one wheel towards the extended position.

Abstract: A fuselage for an aircraft or spacecraft includes a first fuselage section having a support structure with a load bearing outer skin, and a second fuselage section having a non-load bearing outer skin and a space frame structure for supporting the non-load bearing outer skin, wherein the non-load bearing outer skin includes at least one skin area, which is configured to be openable for venting a compartment, which is at least sectionwise enclosed by the at least one skin area. An aircraft or spacecraft is disclosed including the a fuselage.

Abstract: An aircraft fuselage for releasing a fuel tank from inside the aircraft fuselage in case of emergency includes an outer structure, a mounting device to releasably secure a sled device for carrying a fuel tank in an inside of the outer structure, and a first openable release door separating the inside from an outside of the outer structure, wherein the first release door is positioned in relation to the mounting device such that the fuel tank is released through the first release door when the mounting device releases the sled device. A method is disclosed for releasing a fuel tank from inside the aircraft fuselage in case of emergency as well as an aircraft including such an aircraft fuselage.

Abstract: A connecting rod coupling device for attaching a component to an aircraft fuselage and/or stiffening the fuselage has a first coupler, and a second coupler couplable to the first coupler. The first coupler has an elongate body with a first channel on a lateral surface along a first longitudinal axis. The second coupler has a hollow-cylindrical portion, which, on an inner face along a second longitudinal axis, has a second channel complementing the first channel. The hollow-cylindrical portion has a radial cutout through which the elongate body is radially insertable into the second channel from outside the hollow-cylindrical portion. The second coupler has a closure body, which closes the radial cutout, and can be positioned removably in the cutout to complete the second channel on a radially internal face. The second coupler also has an element, pushable onto the hollow-cylindrical portion to secure the closure body on the hollow-cylindrical portion.

Abstract: An aircraft cabin floor arrangement includes two floor support part-structures, each having vertical support members, a beam member, cantilevering members and a seat rail. The beam member and the seat rail extend in a first direction with the seat rail being carried by the beam member. The cantilevering members cantilever in a second direction transverse to the first direction. The vertical support members extend in a third direction transverse to the first and second directions. The two floor support part-structures are each configured to be arranged along opposing side portions within an aircraft fuselage structure and are configured to transfer load from the cantilevering members and the beam member to the fuselage structure. The cantilevering members and the beam member are configured to carry a cabin floor configured to provide a load transfer in a plane direction of the floor and to contribute to a stiffening of the fuselage structure.

Abstract: A locking arrangement for connecting and interlocking rods at a node within a framework includes connection rods and a central node bearing to be engaged from different directions by each of the connection rods at respective mounting ports through plugging each connection rod onto a respective mounting port. The central node bearing is configured with at least one locking element at each mounting port to be actuated between a locked state, in which the at least one locking element resides in an outward position and the respective connection rod plugged onto the respective mounting port is clutched to the central node bearing by the at least one locking element, and an unlocked locked state, in which the at least one locking element resides in an inward position and the respective connection rod is released from the central node bearing.

Abstract: A freight carrier configured to be received in an aircraft cargo hold, a system of one or more such freight carriers and a receiving platform, and a platform, are each provided. The freight carrier includes a floor element having a resting surface configured to lie on a floor surface of a cargo hold of an aircraft. The freight carrier is configured such that its resting surface can be moved over a floor surface in a floor plane. The floor element has a base element having a base surface. The base surface is situated on the base element such that the base surface faces away from the resting surface. The resting surface is provided with an arrangement to allow the freight carrier to be slid over the floor surface. The floor element has a cavity which extends toward the base surface between the front portion and the rear portion.

Abstract: A blocking mechanism which is integrated with a threaded fastener is proposed for improving the reusability and handling of locking devices for threaded fasteners, such as threaded bolts or nuts. The blocking mechanism can be switched to and from between a blocked state, in which the threaded fastener is gripped in a positively locking manner, and an unblocked state, in which the threaded fastener can be rotated. The blocking mechanism can have a blocking element which can engage into a blocking groove of the threaded fastener in a positively locking manner in the blocked state, and thus prevents rotation. For example, a nut which is provided with the blocking mechanism can be used to pivotably fasten a fastening rod to a fastening rail.

Abstract: A connection assembly for connecting a first element to a second element is provided. The connection assembly has a male element and a female element. The female element has a barrel nut. The barrel nut has a conical inner portion positioned at a first longitudinal region and a cylindrical inner portion positioned at a second longitudinal region. The barrel nut has a first engaging element portion and a first plain portion arranged alternatingly around a circumferential direction of the barrel nut. The male element has a cylindrical bolt-like shape and has a second engaging element portion and a second plain portion arranged alternatingly around a circumferential direction of the male element. The male element further has flattened sides at the second plain portion. The second engaging element portion of the male element is configured to engage with a respective one of the first engaging element portion of the barrel nut.

Abstract: A system includes a freight carrier, front catch element and rear catch element, the front edge of the base element of the freight carrier having front engagement elements, and the rear edge has rear engagement elements. The front catch element has front floor engagement devices to engage locking elements so movement of the front catch element in the floor surface plane and perpendicular thereto is prevented. The front catch element has front engagement devices to engage the front engagement elements. The rear catch element has rear floor engagement devices to engage locking elements in rails so movement of the rear catch element in the floor surface plane and perpendicularly thereto is prevented. The rear catch element has rear engagement devices to engage the rear engagement elements so movement of the rear catch element relative to the base element parallel to the plane of the supporting surface and perpendicular to the plane towards the supporting surface is prevented.

Abstract: In a method of making a composite panel for an aircraft, such as formed as a belly fairing, a plurality of layers are arranged on top of each other to form a layer arrangement. Each layer is formed by a number of mats made of a textile, which are laterally adjacent to each other and overlap each other to form one or more overlapping areas in each layer of the layer arrangement. The mats are impregnated with a matrix material. Sewing is performed across all layers of the layer arrangement at least at an edge thereof, and/or in the overlapping areas of at least one of the outer layers of the layer arrangement. One or more seams are created. The matrix material is cured after sewing the layer arrangement.

Abstract: A freight carrier for a freight region of an aircraft, having a base element with a support side and roller elements. Each of the roller elements is retained on a retention member to be rotatable about a rotation axis, wherein each of the retention members is displaceable between a deployed position and a retracted position, wherein the spacing of the roller elements from the base face is greater in the deployed position. The rotation axes of the roller elements are in a common rotation axis plane when the retention members are in the deployed position, the roller elements retained on the base element so the rotation axis of each of the roller elements is rotatable about a vertical axis, wherein the vertical axis extends parallel with and with spacing from an axis which extends through the rotation axis of the roller element and perpendicularly to the rotation axis plane.

Abstract: A coupling kit-of-parts is provided for mounting an interior substructure to a primary structure of an aircraft. The kit includes a locking member and a mounting member. When the locking member is inserted into the mounting member, a first member part and a second member part are pushed radially outward to engage the primary structure in a form-fitting manner. When the locking member is removed, the first and second member parts are urged radially inward thereby disengaging from the primary structure.

Abstract: A manufacturing tool with an adaptable form for winding applications of fiber-matrix composites to generate duct components from fiber-matrix composites includes a support structure, outer deposit surface and adjustable manipulators. The support structure has at least two support connectors and is configured to be mounted to bearings of a winding manufacturing system by the support connectors. The outer deposit surface is configured for material deposit support and to provide a variable circumferential contour for laying down fiber material in a winding process. The adjustable manipulators are between the outer deposit surface and the support structure to adjustably support the outer deposit surface on the support structure. The adjustable manipulators are configured to adjust a distance between the outer deposit surface and the support structure to provide different adjustable outer shapes of the manufacturing tool.

Abstract: A fastening element for fastening a first component to a second component. The fastening element includes an elastically deformable body and an elongated actuating member. The actuating member is movably guided relative to the body to be selectively movable further into or further out of the body. The body is configured to be elongated by moving the actuating member further into the body and applying a corresponding load onto the body and to elastically deform back by moving the actuating member further out of the body and releasing the load applied thereto. Further, the body is configured to have a smaller outer diameter when correspondingly elongated than when non-elongated and/or deformed back.

Abstract: Methods for fastening two fiber composite parts to each other with a fastener that includes electroactive polymer material. The parts have an opening within an inner circumferential surface. Fibers protrude from the inner circumferential surface into the opening and interlock with chains of micrograins of the electroactive polymer material. The fastener may switch between an activated state and a deactivated state and in the deactivated state, the fastener engages the exposed fibers.

Abstract: A method and a repair kit for repairing a sandwich structure, in particular a floor panel in a vehicle, such as an aircraft, the sandwich structure having a top layer and a bottom layer defining an intermediate space between them which is at least partially filled out with a core material, the method comprising the steps of localizing a damaged section of the sandwich structure, such as a hole in the top layer and the underlying core material; removing the damaged section to create a repair cavity while preserving the bottom layer; filling up the repair cavity with a filling material; covering the filled-up repair cavity with a cover layer; and fixing the cover layer with at least one fixing element extending through the cover layer and the filling material and/or the core material next to the filling material.

Abstract: A fuselage for an aircraft or spacecraft includes a first fuselage section having a support structure with a load bearing outer skin, and a second fuselage section having a non-load bearing outer skin and a space frame structure for supporting the non-load bearing outer skin, wherein the non-load bearing outer skin includes at least one skin area, which is configured to be openable for venting a compartment, which is at least sectionwise enclosed by the at least one skin area. An aircraft or spacecraft is disclosed including the a fuselage.

Abstract: A system for installing a self-supporting truss structure having interconnected truss elements on an aircraft fuselage. The truss structure has radially outer closed truss nodes and radially inner releasable connecting nodes. The installation system has a carrying device, movable on a fuselage floor and with an upper receptacle, a stand for temporarily holding truss elements in predetermined relative positions, and a movement device, on the upper receptacle, and holding the stand in a settable position relative to the support surface. The stand is further away from the support in installation positions than in a transport position. The installation system is configured, with the stand in the transport position, to move the carrying device into a predetermined internal fuselage position and to lock it there, to move the stand into a suitable installation position via the movement device, and to lock the at least one lockable connecting node via a drive.