Abstract: A method and device for automatically estimating a degradation in fuel consumption and in drag of an aircraft. The device comprises a device for calculating a numerical value of the effect of a degradation in performance on the fuel consumption and/or the drag of the aircraft, and an arrangement for displaying this numerical value on a screen in the cockpit of the aircraft.

Abstract: An apparatus for recovering kinetic energy released during and aircraft landing after ground contact, for ground and/or flight operation, comprising at least one energy converter for conversion of the kinetic energy into another energy form, where the energy converter is located in the area of the nose landing gear and/or in the area of the main landing gear of the aircraft. At least one energy storage system is provided for receiving and releasing at least a part of the converted kinetic energy. The apparatus has a high degree of multiple utilization and enables, for example, maneuvering of a landed aircraft on the taxiway independently of the engines, where the aircraft is substantially moved with the braking energy recovered during the landing process. Since the main engines are no longer required for maneuvering, there is a considerable potential for saving energy and the use of motor-operated tow vehicles is eliminated.

Abstract: A method and device for displaying the performance of an aircraft when climbing and/or descending. The device includes devices for data capture, calculation and generating images for a display screen. The calculation device is configured to calculate a maximum slope that the aircraft can adopt depending on current data received from a data capture device. A display device presents images of the maximum slope superimposed with altitudes of a projected flight plan.

Abstract: The invention provides a test apparatus for providing axial stresses in a structure, comprising a first set of formations for abutting a first surface of the structure at a first plurality of locations, a second set of formations for abutting a second surface of the structure at a second plurality of locations, and a force actuator, and wherein each set of formations comprises at least three formations and wherein at least two formations in each set of formations are aligned with a notional alignment line along the structure and at least one formation in each set of formations is out of alignment along the structure with said notional alignment line, such that when the force actuator applies a force, loads are applied at different locations, causing the structure to bend biaxially and thereby providing biaxial stresses in the structure.

Abstract: A computing unit allocates boarding paths, available for boarding a transport unit, in particular an aircraft, to passengers of the transport unit. An associated method allocates boarding paths, available for boarding the transport unit to passengers of the transport unit. A computer program carries out the method, and a directing system directs passengers of the transport unit along boarding paths available for boarding the transport unit. The computing unit is configured to form two or more changeable seat groups from a plurality of seats provided in the transport unit and to allocate the boarding paths, available for boarding the transport unit, to the two or more seat groups formed.

Abstract: The aim of the invention is to allow the set of doors to be adjusted without increasing the number of landing gear retraction/extension maneuvers, by incorporating a specific entrance in the fairing (2) of the landing gear bay (4) that provides access to the different accessories (14, 17a, 17b) used to adjust the doors (21-25). The method of the invention consists in: providing a removable bodywork element (5) which is inserted into the fairing (2) of a landing gear bay, surrounded by a stiffening structure (7) and of sufficient dimension such that the adjustment levers (14, 17a, 17b) can be reached from the outside; accessing the inside of the bay (4) by retracting the removable bodywork element (5); and using the levers (14, 17a, 17b) to adjust the different doors (21 to 25) in a flush aerodynamic position, as well as the clearances between said doors. In one embodiment of the invention, one door (25) comprises a central bodywork portion (5) and a peripheral portion (7) including stiffening means (70).

Abstract: A display device for a vehicle includes a housing, a display screen, and at least one functional unit, including an operating element, each being a switch unit or a communication unit, adapted to be releasably coupled to the housing and includes an insertion portion and an operating element support portion supporting the respective operating element, and a first contact arrangement provided on the insertion portion and electrically coupled to the operating element. The housing includes at least one functional unit coupling arrangement, each adapted to be selectively and releasably coupled to at least one of the at least one functional unit and including a cavity inside the housing for receiving the insertion portion of the at least one functional unit, a second contact arrangement in the cavity, a retaining means, and an opening in an exterior wall of the housing communicating the cavity with the exterior of the housing.

Abstract: A high lift system with a main wing and control flaps, wherein the respective guiding device are at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least two inlet ducts running along the main wing chordwise direction with in each case at least one inlet, which device is located on or underneath the lower surface of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet ducts in a fluid-communicating manner, and has at least one outlet, which is located on the upper surface of at least one regulating flap and/or with respect to the main wing chordwise direction in the rear third of the main wing of the high lift system.

Abstract: An intermediate support structure for the cockpit of an aircraft is provided. The intermediate support structure includes a raised floor and at least one structural element extending as an arch above the raised floor, the arched structure being adapted to hold in position at least one item of equipment in the upper part of the cockpit. The intermediate support structure also includes a fastener for mounting the intermediate support structure onto a fuselage primary structure, where the fuselage primary structure defines a portion of the cockpit of the aircraft.

Abstract: A wing tip device has a lighting device arranged to project from a spanwise portion onto a substantially vertical portion of the wing tip device.

Abstract: A support strut designed as a passive safety strut for the support of a floor structure of an aircraft including a local instability formed by a strut section. For example, for purposes of defining a design fracture point in the event of unusual compressive loading to improve the safety of the occupants of the aircraft.

Abstract: A system for cooling an aircraft region includes an air-conditioning unit for providing cool air, a circulating air conveying device, and a mixing chamber which is connected to the air conditioning unit via an air distribution line and to which circulating air can be fed by the circulating air conveying device. An inlet line which is connected to an aircraft-side connection for an aircraft-external air unit opens into the air distribution line connecting the air conditioning unit to the mixing chamber. Therefore, air flows from the aircraft-external air unit and air flow from the air-conditioning unit are simultaneously provided to the mixing unit and then to the aircraft region.

Abstract: The present invention describes composite rods keeping two elements apart a determined distance carrying the loads between them, such as railways, industrial premises, etc. Besides, the manufacturing method thereof and the tool involved in this process are also described.

Abstract: The invention relates to a protection panel (115) for a vehicle that comprises an outer surface (140) including at least one composite material, and is mounted via deformable parts on a mounting (135) attached to the vehicle structure. The deformable parts are attached to several stiffening parts (145) of the mounting. In some embodiments, the deformable parts are perpendicular to the outer surface of the panel and are capable of buckling under the effect of impacts. In some embodiments, the deformable parts are in the form of clips, the composite material consists of CFRP and the mounting is rigid.

Abstract: An aircraft noise-reduction apparatus comprise a flow-facing element (1) and a flow control device (2) positioned downstream of the flow-facing element (1). The flow control device (2) is arranged, in use, to reduce noise induced by unsteady flow downstream of the flow-facing element (1).

Abstract: Provided is a fuselage segment that extends in a longitudinal fuselage segment axis and is closed in a circumferential direction around this longitudinal fuselage segment axis. The fuselage segment features a plurality of shell components for forming a skin of the fuselage segment that respectively feature two first shell component edges extending along a longitudinal shell component direction and two second shell component edges extending along a lateral shell component direction. The shell components are respectively connected to at least one adjacent shell component along at least one first shell component edge and along at least one second shell component edge. Methods for manufacturing such a fuselage segment are also provided.

Abstract: The invention relates to a bearing application for staircases in an aircraft with at least two decks. According to the invention at least two bearings, each with at least partially different possibilities of movement about and along or parallel to the x-axis, y-axis and z-axis of a system of coordinates, are arranged on each staircase at the lower and upper staircase end (rotatory and/or translational movements). Due to the presence of at least four bearings on each staircase, the relative movements between decks can be compensated for. Consequently the static design of the staircases can be limited to the intrinsic weight and operation-related loads by the mass of the users, thereby providing weight savings.

Abstract: According to the invention, a terrain avoidance maneuver is engaged when the alerts of a given pair of alerts are emitted simultaneously, the triggering of one of the alerts depending on the information provided by a first measurement chain and the triggering of the other alert of the pair relying on information provided by a second measurement chain, distinct from and independent of the first chain.

Abstract: A system for automatically modifying a lateral flight plan of an aircraft includes modifying means adapted to modify the flight plan by an action to chosen among the following actions: deleting, adding and moving at least one waypoint of an initial flight plan (T1). The modified flight plan (T3) includes one downstream waypoint (P6) defined as the waypoint on which the aircraft gets back to the initial flight plan (T1), and one upstream waypoint (P4) preceding the downstream waypoint (P6). By defining an intermediate point (P5?) between the upstream (P4) and downstream (P6) waypoints, the coordinates are calculated in order to allow the aircraft to reach the downstream waypoint (P6) with the same course as the initial flight plan (T1).

Abstract: A voltage supply unit for providing an adaptive voltage supply to a consumer in a means of transport, wherein the voltage supply unit comprises a voltage output device and an output control device. The output control device and the voltage output device are designed to set an output voltage of the voltage supply unit adaptively in a consumer-dependent manner.