Abstract: The invention relates to a vibrating rivet tool for pressing and fixing rivets in component holes in component of aircraft. The vibrating rivet tool comprises a rivet receptacle and a drive unit for producing a high static pressing force. According to the invention, the static pressing force is superimposed by a mechanical vibration, of which the amplitude acts substantially in the direction of a longitudinal axis of the rivet. As a result, the force necessary to press and fix the rivet in a component hole is reduced in such a way that the overall size and mass of the vibrating rivet tool according to the invention are smaller/lower in comparison with conventional rivet tools. Due to the small overall size and low weight, the vibrating rivet tool can more easily be integrated in automated riveting processes.

Abstract: The invention relates to a device for reducing latch loads during the process of loading and flying air cargo containers inside cargo holds of aircraft. The device exhibits a floor plate of a cargo unit of a transport means, an edge profile, a rail bumper as well as a first damping unit. The first damping unit is situated between the edge profile and the floor plate, or between the edge profile and the rail bumper of the cargo unit. The first damping unit is designed for damping a movement by the cargo unit in a direction of movement of the cargo unit so as to reduce the loads placed on the cargo unit.

Abstract: A device for manufacturing a composite material part that includes a resin matrix reinforced by fibers and having a recessed shape with a small opening, whereby the device includes a mold whose shapes are adapted to those of the part to be produced, a compacting membrane and at least one shim that is placed in the recessed zone between the part and the compacting membrane whose function is to transmit the pressure exerted by the compacting membrane to the surfaces of the part that is in contact with the shim. The shim can be expanded and is able to occupy a first state before polymerization in which it occupies a low volume so as to allow its insertion into the recessed zone, and a second state, in particular during polymerization, in which it occupies a larger volume so as to exert pressure on the surfaces of the recessed zone.

Abstract: A method and device for aiding the piloting of an aircraft during a landing phase enables an appropriate braking mode to be selected for use with an automatic braking system. The device includes a minimum braking distance estimation device that determines a minimum braking distance required using a currently selected braking mode, and also includes an alarm device for alerting the crew, during a landing, of the selecting of an insufficient braking mode on an automatic braking system. The crew may then take an appropriate action at a mode selection input device.

Abstract: A fiber placement tool comprising a plurality of tool segments, each tool segment having an outer surface defining a predetermined profile, each tool segment being removably mounted on at least one elongate shaft.

Abstract: The disclosed embodiments relate to a method for manufacturing an aircraft fuselage section of composite material that comprises the following operations manufacturing a one-piece section; cutting the section longitudinally; spreading apart two edges located on the two sides of the cut; reassembling the section and making a longitudinal joint with the two edges overlapping. The disclosed embodiments also relate to a section made in accordance with this method.

Abstract: An aircraft versatile power system (1) comprises an air breathing engine (2), a power converter (6), and a motor (4). The power converter (6) transforms shaft motion provided by the air breathing engine (2) into another type of energy. The motor (4) uses the energy provided by the power converter (6) to move a motor shaft (14), and the motor shaft (14) turns the landing gear wheels (3), generating aircraft movement. The air breathing engine (2) also produces thrust, enabling an aircraft dual propulsive operation either by the landing gear wheels (3) movement, or by direct thrust through the nozzle (25).

Abstract: The invention provides a self-stiffened composite panel including an external skin, an internal skin superposed on the external skin, which covers an internal face of the external skin and at least one stiffener protruding inwards relatively to the internal skin which extends along a longitudinal direction, characterised in that the stiffener is made as one piece with the internal skin and consists of a portion of the internal skin which is located at distance from the external skin. The invention also provides a process for making such a self-stiffened panel.

Abstract: The invention relates to a coupling device for a duct (201) in piping, comprising: a duct (201); a coupling (231) comprising means (255) for realizing a hermetic longitudinal sliding connection with an extremity of the duct (201) along a total distance d parallel to the axis (210), referred to as longitudinal, of said duct (201); means (265) of stopping the translational movement of the first extremity of the duct (201) in the coupling (231) for a travel d1 less than d. The translational movement stopper means (265) are withdrawable for defined compression conditions of the duct.

Abstract: A display mount is provided for a vehicle, such an aircraft. The display mount includes, but is not limited to a support frame and a display accommodation device. The support frame is designed for incorporation in a supply channel, and the display accommodation device is designed to receive a display. The display accommodation device is connected to the support frame such that the display accommodation device is movable with a combined rotational movement and translational movement relative to the support frame between a first operating position and a second operating position.

Abstract: The invention relates to a method for actuating an adjusting drive for adjusting an elevator (12) and an adjusting drive for adjusting a moveable tail (23) provided with the steps: Generation of an elevator command to actuate the elevator adjusting drive; Calculating a moveable tail command (IHC1) for actuating the moveable tail adjusting drive in such a manner that the moveable tail (23) is tracked to the elevator input signal (10); Depending on the adjusting states of the elevator (12) and/or the moveable tail (23) or flight states, retaining the adjusting state of the moveable tail adjusting drive or actuating the moveable tail adjusting drive with a moveable tail command (IHCMD) for changing the adjusting state of the moveable tail (23), during actuation of the elevator adjusting drive with an elevator command for changing the adjusting state of the elevator (23) and in the event of a deviation from the calculated moveable tail command (IHC1) and the commanded moveable tail command (IHCMD), acting upon th

Abstract: A device for aiding the piloting of an aircraft during a final approach phase includes a flight management system and an approach selecting device for automatically selecting an approach to be used during landing of the aircraft. A method for aiding the piloting of an aircraft includes automatically selecting an approach to be used during landing of an aircraft by selecting an approach with the smallest decision height that can also be technically implemented by the aircraft.

Abstract: A method and a device are described for compensation of mechanical stresses in an aircraft structure. The method comprises the steps of producing signals that represent mechanical stresses occurring in the aircraft structure, and operating actuators, which absorb at least some of the mechanical stresses and are arranged in the aircraft structure, such that the mechanical stresses are compensated.

Abstract: Commercial aircraft (11) having a black box (41) comprising a flight data recorder (49) connected to suitable acquisition units (13, 14, 15) for recording information required for crash investigation purposes inside a container (43), wherein the aircraft (11) comprises a crash detection device (17); the black box (41) is installed in a suitable location for being ejected outside the aircraft in a crash event through a duct (21, 31) having its exit in a fuselage area where the ejected black box (41) would not impact on the aircraft; the aircraft (11) also comprises ejection means (23, 33), controlled by a black box ejection control unit (19) connected to said crash detection device (17), for ejecting the black box (41) through said duct (21, 31), when an impending crash is detected by said crash detection device (17).

Abstract: An apparatus (10) for testing an aircraft pedal system (12) comprises a pedal actuation device (14) for actuating an aircraft pedal (12?, 12?), a force sensor (26) for sensing an actuation force applied to the aircraft pedal (12?, 12?) upon actuation of the aircraft pedal (12?, 12?) and for providing a signal indicative of the actuation force, a deflection sensing device (28, 30) for sensing an angular deflection of a device (12?, 12?; 13) deflected in response to the actuation of the aircraft pedal (12?, 12?), and a control unit (32) adapted to process the signals of the force sensor (26) and the deflection sensing device (28, 30) so as to generate an output indicating the angular deflection of the device (12?, 12?; 13) deflected in response to the actuation of the aircraft pedal (12?, 12?) in dependence on the actuation force applied to the aircraft pedal (12?, 12?).

Abstract: The invention relates to a system for regulating a temperature of hydraulic fluid in at least one hydraulic circuit of an aircraft, wherein, in a periphery of the aircraft, additional hydraulic consumption units are each provided with at least one controllable valve for heating the hydraulic fluid above an adjustable minimum temperature limit value (Tmin), wherein the controllable valve is closed during a maneuver of the aircraft, wherein the controllable valves of the additional hydraulic consumption units are closed when the temperature of the hydraulic fluid exceeds an adjustable theoretical temperature value (Tsoll), and wherein a temperature control system is connected to a temperature sensor for adjusting the controllable valve on the basis of a local temperature of the hydraulic fluid, the temperature sensor being near the hydraulic consumption units which are arranged in wings and tail of the aircraft.

Abstract: A method of computer simulation of an aerodynamic behavior of an aircraft in flight close to the ground includes generating a volume mesh of a three-dimensional geometric domain. The volume mesh is at least partly delimited by a three-dimensional geometric model of the aircraft and by a plane modelling the ground. The volume mesh defines a computational domain. The method also includes imposing a uniform boundary condition on the plane comprising a predetermined speed vector with a non-zero tangential component and a non-zero normal component, and solving a discrete numerical model of the Navier-Stokes equations by computer on the volume mesh with the uniform boundary condition imposed on the plane to obtain a numerical solution of a fluid flow inside said computational domain.

Abstract: A method for assembling two structural elements, at least one of the two structural elements being tube-shaped and including a skin made of a fiber-reinforced composite material. The ability of the element to adapt to the shape and perimeter of a junction interface is improved by providing longitudinal grooves distributed on the circumference of the junction interface. The grooves are of a sufficient length to provide the junction interface with the flexibility to accommodate, through relative radial movement of each portion located between two grooves, differences in shape and perimeter among the junction interfaces of the two structural elements.

Abstract: A water scavenging system (1) for removing water from an aircraft fuel tank (2), the water scavenging system comprising: a water line (10); and a valve (20) which is configured to control the flow of water in the water line in response to a change in an effective angle of the valve. In use, the valve opens automatically in response to an increase in the effective pitch of the aircraft during take off and climb. The valve comprises: a pendulum (40); and a valve closure member (46) which is coupled to the pendulum such that a change in the angular position of the pendulum relative to the water line causes the valve closure member to move from a closed position in which the valve closure member impedes the flow of water in the water line to an open position in which water can flow through the valve.

Abstract: A structural element of an aircraft includes a hollow part. An indicator provides a visual indication, for example by moving, if ice forms in a given region of the hollow part.