Abstract: In the retracted position, aircraft landing gear of an aircraft is supported by an uplock hook. The deployment of the aircraft landing gear includes the steps of supporting at least part of the weight of the landing gear by a releasable catch in the form of an uplock hook, applying a lifting force to the landing gear to remove at least part of the load sustained by the releasable catch, releasing the catch and effecting the downward movement of the landing gear to the deployed position.

Abstract: The invention relates to a passenger seat, in particular an aircraft passenger seat, comprising seating components such as a seat section (3) and a backrest (1), which is located on a backrest frame (7) and has at least one support section (15) that supports the relevant part of the body of the seat occupant, said section being displaceable in relation to the backrest frame (7) by means of an adjusting device (25). Said seat is characterized in that a web (15) constitutes the displaceable support section, said web extending between the lateral edges (5) of the backrest frame (7) and being suspended by its upper edge (17) from the backrest frame (7) and engaging at its lower end (23) that adjoins the seat section (3) with the adjusting device that is configured as a tensile device (25). The tensile device is used to exert a tensile force on the lower end of the web (15), in order to pull the web (15) forwards by said lower end (23) from a position in which it lies longitudinally against the backrest (1).

Abstract: Systems and methods for aerial refueling are disclosed. In one embodiment, an aerial refueling system includes a first conduit portion moveably coupled to a second conduit portion and moveable relative to the second conduit portion along a longitudinal axis, and a force absorbing assembly operatively coupled to the first and second conduit portions. The force absorbing assembly includes a first absorber portion and a second absorber portion engaged with the first absorber portion. The first absorber portion is configured to compress when subject to a compression force having a longitudinal component at least approximately aligned with the longitudinal axis, the longitudinal component tending to urge the first conduit portion toward the second conduit portion and causing absorption of at least a portion of the longitudinal component by the first absorber portion until the longitudinal component reaches a first limit.

Abstract: An engine mount structure is provided with active vibration mechanisms which are attached in the vicinity of the engine mount to prevent engine vibrations from propagating into the engine mounting structure, for example, the wing or fuselage structure of an aircraft. Additionally, sensors are provided on the engine and/or wing/fuselage structure to provide control signals to the active vibration mechanisms so that the active vibration mechanism react to the sensed data to minimize the vibration transmissibility from the engine into the wing/fuselage.

Abstract: An exoatmospheric device comprises an inertial measurement unit comprising a spin axis gyroscope adapted to obtain data regarding angular rotation of the exoatmospheric device about a spin axis, and at least one off-spin axis gyroscope adapted to obtain data regarding angular oscillation of the spin axis. The exoatmospheric device further comprises a processing unit coupled to the inertial measurement unit and adapted to detect attitude error by analyzing correlations between the measured rotation about the spin axis and the measured angular oscillation of the spin axis.