Abstract: A method and apparatus for carrying out a symmetric deflection of the spoilers so as to reduce the lift of the aircraft during a takeoff roll thereby improving lateral and directional control on the ground.

Abstract: A method of fitting a fuselage shell of an aircraft with at least one window frame of a cabin window includes positioning an uncured laminate including a fiber-reinforced plastic-based composite material configured to form a fuselage shell on a mold surface. A window aperture is introduced into the laminate. A window frame including a fiber-reinforced plastic-based composite material is positioned on the laminate in a region of the window aperture. The laminate is cured under the action of pressure and temperature so as to connect the window frame with the laminate by a material bond.

Abstract: A vacuum-operated sanitary device, in particular a vacuum toilet, comprising a bowl and a flushing device, with the flushing device comprising a nozzle arrangement with a nozzle inlet of a first cross section, a nozzle outlet of a second cross section, which nozzle outlet is directed onto an interior wall of the bowl, and a nozzle duct of a third cross section, which nozzle duct connects the nozzle inlet with the nozzle outlet, wherein the third cross section is smaller than both the first cross section and the second cross section; a first delivery device connected to the nozzle inlet, wherein the first delivery device is designed to deliver a first flushing medium; and a second delivery device that opens into the nozzle duct, wherein the second delivery device is designed to deliver a second flushing medium.

Abstract: A protection device includes a flexible laminar body resistant to impacts, arranged separately from the body to be protected and put in the way of the beam of possible trajectories with which a foreign object could impact on the object to be protected, and it includes a plurality of energy absorption elements, provided with device clamping elements over a support structure positioned outside of the beam of possible trajectories, in order for the flexible laminar body to intercept an impact trajectory by the foreign object, resulting in its deformation and the subsequent progressive extension of the energy absorption elements reducing the loads to be supported by the support structure. The protection device is applied to prevent birds or other objects from impacting on sensitive areas of aircraft. The protection device is of a textile nature of reduced weight.

Abstract: A connecting arrangement for connecting two reinforcing elements of an aircraft or spacecraft, wherein the reinforcing elements have different cross-sectional profiles with at least one foot portion and at least one comb portion, at least one foot portion connecting element which on one side can be adapted to the geometric shape of the foot portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the foot portion of the second reinforcing element and can be connected rigidly thereto; and at least one comb portion connecting element which on one side can be adapted to the geometric shape of the comb portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the comb portion of the second reinforcing element and can be connected rigidly thereto.

Abstract: This invention relates to a device for controlling the switching of a user interface (100) to a plurality of computers (120, 130, 150), said user interface including display means (111) and at least one input peripheral (112), and being interconnected with said plurality of computers via a switch (165). The device includes a memory (225) for storing a list of identifiers, each identifier identifying an application available on one of said computers; a graphical interface (220) for generating a window including a menu, said menu containing the list of applications the identifiers of which are stored in said memory; control means (250) adapted to receiving a selection command identifying an application selected from said list by at least said input peripheral and to transmitting to said switch an order for switching said interface to the corresponding inputs/outputs of the computer hosting said selected application.

Abstract: High-pressure water jet cutting techniques generate numerous handling problems both for the plates being cut and for cut parts. These problems can be resolved by the device according to the disclosed embodiments. This device includes a plurality of wires held under stress at a predetermined stress level above a plate being cut. These wires intercept a jet cutting the plate. This interception results in the creation of a micro-fastener holding the cut part to the plate. This micro-fastener can be easily broken. The plurality of wires also prevents the boiling effect of water in a cutting pool, this boiling resulting from the impact of the water jet in the pool.

Abstract: An exemplary embodiment of the present invention indicates an installation system for an airplane for securing interior equipment, which exhibits longitudinal and transverse rails. The transverse rails are designed as peripheral rails, and exhibit perforations to which the interior equipment can be secured.

Abstract: An aerodynamic body, with at least one ancillary flap arranged such that it can be moved on the aerodynamic body with the aid of a guide mechanism, and with a drive device for purposes of actuating the ancillary flap, the guide mechanism having a pivotal articulation, by which the ancillary flap is articulated on the aerodynamic body such that it can be extended, and which is arranged in a rear region of the ancillary flap as viewed in the flow direction.

Abstract: A cooling system, in particular for use on board an aircraft, includes a cooling circuit allowing circulation of a two-phase refrigerant therethrough, an evaporator disposed in the cooling circuit, and a condenser disposed in the cooling circuit. A plurality of subcoolers is arranged in series in the cooling circuit downstream of the condenser.

Abstract: An accumulator arrangement for use in a cooling system suitable for operation with two-phase refrigerant includes a condenser having a refrigerant inlet and a refrigerant outlet. The accumulator arrangement further includes an accumulator for receiving the two-phase refrigerant therein, the accumulator having a refrigerant inlet connected to the refrigerant outlet of the condenser and a refrigerant outlet. Finally, the accumulator arrangement includes a subcooler having a refrigerant inlet and a refrigerant outlet, the refrigerant inlet of the subcooler being connected to the refrigerant outlet of the accumulators, and the subcooler being arranged at least partially within the interior of the accumulator.

Abstract: A holding device for in particular panel-shaped interior lining parts of a fuselage, has a configuration that is easy and simple to mount, each holding device includes a supporting device, which is used to anchor the holding device on a primary structure of the fuselage and comprises a joint; a connecting tube, which extends out of the supporting device and one end of which is attached to the joint; a mounting for an interior lining part, to which mounting the other, opposite end of the connecting tube to the one end is attached; and a lanyard, which is fastened to the supporting device is and the mounting and extends through the connecting tube and the length of which is greater than the length of the connecting tube.

Abstract: Methods for transferring a payload such as passengers and/or luggage and/or freight between an airport and a cabin of an aircraft are provided. Air terminals, aircraft and removable cabin modules suitable for implementing these methods are also provided. An aircraft is provided which includes a removable cabin module. A docking module is also provided for transferring a removable cabin module between an aircraft and an airport. A method for modifying the internal configuration of the cabin of such an aircraft by replacing a removable cabin module of the aircraft is also provided.

Abstract: A method of manufacturing a structure, the method comprising: forming a panel assembly by bonding a stack of thickness control plies of composite material to a laminar composite panel, the stack of thickness control plies having a first edge proximate an edge of the laminar composite panel, a second edge opposite the first edge, and a ramp where the thickness of the stack of thickness control plies decreases towards the first or second edge; measuring the thickness of the laminate composite panel or the panel assembly; controlling the number of thickness control plies in accordance with the measured thickness; attaching a first component to the panel assembly, the first component having a surface which engages the laminar composite panel and a ramp which engages the ramp in the stack of thickness control plies; and attaching the laminar composite panel at or near its edge to a further component.

Abstract: A method of stiffening a rib (19, 20) during the assembly of an aircraft wing is described. A stiffener panel (40, 41) is attached to a face of the rib (19, 20). The rib is aligned with one or more wing components with the stiffener panel (40, 41) attached. An assembly operation such as drilling (16) is performed with the rib aligned and the stiffener panel attached. The stiffener panel (40, 41) is removed from the rib after the assembly operation. The stiffener panel has a resilient external sealing ring which is mounted on a face of the panel and forms an external perimeter of a vacuum cavity; and at least one resilient internal sealing ring which is mounted on the panel (20, 21) within the perimeter defined by the external sealing ring and forms an internal perimeter of the vacuum cavity. The stiffener can be attached to the rib by a vacuum clamping force, the vacuum being sealed by the external and internal sealing rings. The internal sealing ring(s) seal any holes which are present in the rib.

Abstract: A line system for an aircraft cabin has a line channel with a first surface and a second surface facing in an opposite direction with respect to the first surface. The line system also includes at least one conductor running in the line channel a plurality of first plug channels which enable contacting of the at least one conductor through the first surface, and at least one second plug channel which enables contacting of the at least one conductor through the second surface. At and at least one connector plug with an elongated contact pin which contacts the at least one conductor through the second plug channel, the contact pin having a first section situated in the second plug channel and a second section situated outside the second plug channel.

Abstract: The present invention relates to a circuit for detecting a functional status of an electro-motor. Typical electro-motors need additional components to identify the functional status of the motor. This means additional weight for such motors determining the functional status. According to the present invention, a circuit is provided using a part of a motor as a sensor for detecting the functional status of the electro-motor.

Abstract: The invention relates to an airframe having a substantially circular cross section in a lateral direction (Y) and which extends in the longitudinal direction (X). The airframe comprises, a plurality of rails for supporting seats, each rail being parallel to the longitudinal direction (X) of the airframe, a plurality of beams parallel to the rails; and a plurality of crossmembers aligned, in use, in the lateral direction (Y) of the airframe. Each crossmember supports only some of the successive rails, each crossmember being supported by only some of the successive beams in the lateral direction (Y) of the airframe with the beams forming part of a wing box and/or a main landing gear well of the airframe. Each crossmember comprises at least one connection to each of the beams that support it where each connection comprises at least one articulation about at least one axis.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: Disclosed herein is a folding transport cart which in a parking configuration has a minimum extension and in an operative configuration has a maximum extension in a transverse direction. A folding transport cart can comprise: two side parts which extend substantially perpendicular to the transverse direction of the transport cart, and a folding base part which comprises two flat base segments which are each connected on one base side axis for articulated movement to one side part and are connected on a common base central axis for articulated movement to one another. In order to ensure reliable folding and unfolding the transport cart can comprise a base locking mechanism for locking the folding base part in the operative configuration and a cover part which is connected for articulated movement to one of the side parts.