Abstract: An aircraft with airfoils having a main wing and at least one control flap arranged such to be adjusted relative to the main wing, as well as a high-lift system with at least one regulating flap for adjusting the lift of the airfoils to adjust the state of lift of the aircraft, featuring flow control devices for influencing the fluid flowing over the surface segment; an activating unit; and a lift state specification device connected to the activating unit for adjusting the state of lift of the aircraft.

Abstract: An apparatus for holding a cabin attendant seat in a cabin of a vehicle includes a base body attachable to a wall surface in the cabin, at least one holding mechanism for holding a cabin attendant seat, at least one linear movement mechanism, and at least one arresting mechanism. The at least one linear movement mechanism is attached to the base body and supports the at least one holding mechanism. The at least one linear movement mechanism is configured for laterally moving the at least one holding mechanism between at least two laterally distanced discrete positions. The at least one arresting mechanism is coupled with the at least one linear movement mechanism and is configured for arresting the at least one linear movement mechanism in the at least two discrete positions. By this apparatus a very space effective provision of a cabin attendant seat especially on a monument is given.

Abstract: A tool-holder including: a first rail and a second rail that are parallel and each of which includes first fixing elements configured for fixing said rail to the surface, a driving slide including first guiding elements configured to slide over the first rail, a drive system configured to move the driving slide along the first rail and a first fixing system, a driven slide including second guiding elements configured to provide a sliding connection with the second rail and a second fixing system, an assembly bar carrying a first complementary fixing system cooperating with the first fixing system to form a removable fixing between them, a second complementary fixing system intended to cooperate with the second fixing system to form a removable fixing between them, and a carriage having a first assembly system, and a movement system on which the carriage is fixed and that is configured to move said carriage along the assembly bar, and a support module including second fixing elements for fixing the tool and a

Abstract: The invention concerns a device for a adjustable flap adjustably mounted on a main wing surface of an aeroplane wing, in particular, a landing flap, with at least one adjustment unit for purposes of adjustment of the adjustable flap, which has an actuator arranged, or that can be arranged, on the main wing surface, and has a kinematic adjustment mechanism running between the actuator and the adjustable flap, wherein the adjustable flap is mechanically coupled with the actuator via the kinematic adjustment mechanism. At least one damping unit for purposes of damping a dynamic loading effected by the adjustable flap on the adjustment unit, which can occur as a result of a critical malfunction event occurring in the region of the adjustable flap, is arranged, or can be arranged, between the main wing surface and the adjustable flap.

Abstract: The invention relates to fluid actuator for influencing the flow along a flow surface through ejection of a fluid. By means of a like fluid actuator, a continuous flow is distributed to at least two outlet openings in order to generate fluid pulses out of these outlet openings. Control of this distribution takes place inside an interaction chamber which is supplied with fluid flow via a feed line. Into this interaction chamber there merge at least two control lines via control openings to which a respective different pressure may be applied. Depending on the pressure difference at the control openings, the flow in the interaction chamber is distributed to the individual outlet openings.

Abstract: An aircraft including a wing (1) and a wing tip device (6). The wing tip device (6) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the ground configuration the wing tip device is folded inwardly from the flight configuration such that the span of the aircraft is reduced. The wing tip device (6) is connected to the wing along a hinge axis (14) by spar beams (10 and 12) of the wing tip device, one of the beams being mounted for pivoting about a fixed axis and the other beam being mounted on a spherical bearing (15) to provide greater freedom of movement. Various actuator arrangements may be provided to pivot the wing tip device.

Abstract: A modular lavatory assembly for a vehicle cabin includes a lavatory module having a housing and a toilet system having a toilet arranged in an inner space of the lavatory module and at least one service module having at least one service unit for personal use by a passenger. The at least one service module is attached to an outside of the housing. The housing encloses an inner space, which is free from additional service modules and includes at least one recess for accessing the at least one service unit of the at least one service module from an inside of the housing with the at least one service module being configured for providing access through the at least one recess. The at least one service module includes at least one additional access for accessing the at least one service unit from outside the housing.

Abstract: To be able to transmit higher forces when retaining movable components on board an aircraft, a retaining system includes a support structure with a first retaining area and a second retaining area having a movable locking element, and a movable component with a locking receptacle forming a locking device with the locking element, and a retaining device. The movable component is movably attached to the first retaining area with the retaining device, and the movable component can be locked on the second retaining area with the locking device. The at least one movable locking element can be moved between an open setting (SOFF) and a locked setting (SVER), wherein the at least one movable locking element engages with the locking receptacle in the locked setting, so that the movable component is temporarily immovably retained, and allows the movable component to move in the open setting.

Abstract: An aircraft auxiliary power unit (APU) flexible and fireproof drainage device including a bellows which receives leakage fluids from an APU engine; a drain pipe which transfers leakage fluids outside the aircraft from the bellows, and a support piece surrounding the drain pipe. The bellows connects the APU engine with the drain pipe. The support piece provides stability to the bellows and the drain pipe.

Abstract: A high lift component includes at least one intermediate seal on at least one lateral surface, wherein the intermediate seal includes at least one hollow body made of an elastic material, which hollow body includes a fluid inlet that is connectable to a fluid source. A gap between two high lift components, which gap is subjected to dynamic changes in geometry, can be flexibly sealed in this manner.

Abstract: An aircraft nacelle comprising a first duct secured to an air intake and a second duct secured to a powerplant, the first duct comprising an exterior surface and an end portion connected to the second duct. The nacelle includes a hollow section piece in contact with the exterior surface of the first duct which extends over at least part of the circumference of that end portion of the first duct that is connected to the second duct.

Abstract: A main landing gear for aircraft having a fuselage, a wing and a jet engine on opposite sides of the fuselage and housed in a nacelle attached to the wing. The main landing gear includes a landing gear at each side of the wing having wheels coupled to a driving device that moves the wheels between stowed and deployed positions. The engine nacelles each include a well located laterally with respect to the jet engines and configured as a housing space for stowing the wheels of the landing gears.

Abstract: A tubular element bracket comprises at least one central body elongate along a longitudinal axis, comprising a central portion elongate along the longitudinal axis and a support element configured to receive at least one tubular element, the support element being arranged at one end of the central body, referred to as the upper end, and a fixing plate configured to be fixed to a support, notably of an aircraft. The central portion and the support element are formed in one piece. The support element is in the form of an open fixing collar. The bracket comprises a fixing arrangement configured to make it possible to fix the central body manually and autonomously to the fixing plate by its other end, referred to as the lower end.

Abstract: A connecting arrangement for joining at least two components to form a structural assembly, near a wing of an aircraft, wherein at least one component is formed from a fiber composite plastic and at least one further component is formed from either a metal or a fiber composite plastic. A bushing is secured in a hole through the components. The bushing includes a first end with a collar which faces towards a lower face of the structural assembly and a second end. A zone of an upper face of the structural assembly radially surrounds the second end and includes a depression. A connecting element is installed in the bushing. This provides a smooth, aerodynamically beneficial configuration of the upper face, which can be coated, and which ensures a reliable electrical contact between the connecting element and a conductive surface of the first component.

Abstract: A rotary joint includes an outer shell segment having the outer shape of a solid of revolution, the outer shell segment having a plurality of openings arranged in the outer surface; an inner shell segment having the outer shape of the solid of revolution of the outer shell segment, the inner shell segment being aligned concentrically with the outer shell segment and spaced apart from the outer shell segment by a compensation gap; and a plurality of strut holding fixtures, the strut holding fixtures having a hollow interior and a flange portion, wherein each of the strut holding fixtures is arranged in one of the plurality of openings and the flange portion extends within the compensation gap between the inner shell segment and the outer shell segment in each case.

Abstract: A system for activating the distress beacon determines a positional difference between a theoretical position of the aircraft determined from data of the flight plan and a real position of the aircraft determined from the navigation and monitoring equipment installed in the aircraft. This system delivers an instruction to arm the distress beacon when one or more conditions are met, among which is the condition that the positional difference exceeds a predetermined value.

Abstract: A drive system for an aircraft landing gear is described. The drive system includes a drive pinion, a drive shaft arranged to rotate the drive pinion about a drive axis, and a casing which rotatably supports the drive shaft. The drive pinion is rotatably supported on the casing by a self-aligning bearing. The drive pinion is coupled to the drive shaft by a flexible coupling adapted to transfer torque between the drive pinion and the drive shaft and to permit tilting of the drive pinion relative to the drive axis.

Abstract: A heat exchanger for cooling air, with a coolant onward-flow connection for feeding liquid coolant for cooling air and a coolant return-flow connection for discharging liquid coolant. For removing ice by melting accumulated ice in the heat exchanger, a heater is provided that is associated with an electrical heating element. An operational safety device prevents overheating of the heater. The operational safety device comprises a fault-current detection device. Such a heater, with a heating element for heating air for subjecting accumulated ice to heated air, and with such an operational safety device is provided. Also, a galley for a commercial aircraft is provided with a receiving space for trolleys, and a cooling device for cooling the receiving space. The cooling device comprises such a heat exchanger for cooling air.

Abstract: The present disclosure pertains to an actuation mechanism for a flap with aileron functionality, including a crank having a crank axle, a crank arm and a crank pivot; a displacement shaft articulated to the crank pivot at an actuating end portion; and a rotatable linear-motion bearing in which the displacement shaft is slidably supported, wherein the displacement shaft is fixedly connectable to a flap body of the aircraft flap at a flap end portion of the displacement shaft opposite to the actuating end portion, and wherein the linear-motion bearing is rotatably attachable at a pivot point to an aircraft wing comprising the aircraft flap, so that the displacement shaft is able to rotate around an axis running spanwise of the aircraft wing around the pivot point. The present disclosure further pertains to an aircraft flap with such an actuation mechanism and an aircraft having an aircraft flap.

Abstract: An ultrasound inspection roller provided with a wheel, a sensing system and a support for holding the sensing system inside the wheel, a wedge connected to the ultrasound sensing system at one end and provided with a curved profile at its other end facing the wheel, adapted to the curvilinear shape of the wheel, and a liquid of a density higher than 9.9*102 kg/mm3 placed inside the wheel such that the sensory system, the wheel and the wedge are acoustically coupled. The roller allows the early detection of problems during manufacturing of composites and the performance of corrective measures in real time, and assures a good coupling between the transducers and the material to be inspected in dry conditions.