Abstract: A device for exciting a landing gear of an aircraft while it is on the ground. The device includes an oblong bracing foot, a movable support on which the oblong foot is mounted and an arrangement for setting the gear into vibration.

Abstract: A high lift system with a main wing and regulating flaps, also bearing devices for the mounting of the regulating flaps, and positioning devices for the positioning of the regulating flaps, wherein the respective bearing device and/or positioning device is 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 one inlet duct with at least one inlet, which device is located on or underneath the lower face of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet duct in a fluid-communicating manner, and has at least one outlet, which is located on the upper face in the region of at least one regulating flap of the high lift system.

Abstract: An equipment burn-in method, which includes the equipment undergoing treatment in an oven, the oven undergoing cycles including at least one temperature-rise and/or temperature-fall transition, for which ventilation of the equipment is cut off during at least part of a temperature transition of the oven.

Abstract: A seat rail cover for a seat rail includes a first longitudinal section and a second longitudinal section. The first longitudinal section includes a first cover element and a first support element. The first support element extends in a longitudinal direction of the seat rail cover and protrudes from the first cover element transversely to the longitudinal direction. The second longitudinal section includes a second cover element and a second support element. The second support element extends in longitudinal direction and protrudes from the second cover element transversely to the longitudinal direction. The first longitudinal section is movable in longitudinal direction of the seat rail cover with respect to the second longitudinal direction from a non extended state to an extended state. Such a seat rail cover provides a variable length and may improve the dispersion of loads applied to the cover elements of the seat rail cover.

Abstract: A cargo container for accommodating transport goods and for being arranged in a cargo compartment of a means of transport is provided. The cargo container includes a housing that can be closed so that it is airtight, and an internal coating. The internal coating is incombustible and is arranged on an inner surface of the housing. Thus, the cargo container makes it possible to limit propagation of a fire to the internal space of the housing.

Abstract: A power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, a power management device coupled to the first power supply bus bar, at least one primary electrical equipment including a primary load being coupled in parallel to the power management device, and at least one secondary electrical equipment including a secondary load being coupled in parallel to the power management device. The power manager device is configured to supply electrical power to the at least one secondary electrical equipment, to supply electrical power to the at least one primary electrical equipment, and to deactivate the power supply to the at least one secondary electrical equipment, as long as the at least one primary electrical equipment is supplied with electrical power.

Abstract: An aircraft power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load coupled in parallel to the first power supply bus bar, a bus bar switch configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar, if the monitored power demand of the primary load exceeds a primary threshold, and at least one tertiary electrical equipment including a tertiary load coupled to the first power supply bus bar downstream of the at least one primary electrical equipment.

Abstract: A warning light circuitry includes a first logic gate adapted for receiving a first, a second, a third, and a fourth input signal; a second logic gate adapted for receiving a fifth, a sixth, and a seventh input signal; a third logic gate electrically connected to the first and second logic gate; and a warning light electrically connected to the third logic gate. The first logic gate is adapted for providing a first output signal to the third logic gate upon receiving the first, the second, the third, and the fourth input signals. The second logic gate is adapted for providing a second output signal to the third logic gate upon receiving the fifth, the sixth, and the seventh input signals. Therein the third logic gate is adapted for triggering the warning light upon receiving the first or the second output signal.

Abstract: An aircraft is equipped with engines, each engine having at least one pod and one compressor/turbine hitch. The aircraft has at least one data processing unit and at least one system at the engine level. At least one engine is equipped with at least one static pressure probe for measuring the ambient air under the pod. Also, air static pressure probes are arranged at the engine levels, with one pressure probe at the output of the compressor, at least one rotation speed sensor, for example of a blower, and ambient air temperature probes at the air input or in any compression point. The processing unit is able, from measurements performed by such probes at the engine level, to supply to at least one of the systems at the engine level, determination data for the air speed of the aircraft.

Abstract: The invention relates to method for obtaining a part made of a composite of fibers embedded in a resin matrix which comprises a body and an edge. The method comprises a first step of stacking plies of fibers and further comprises a step of curing the plies. The method further comprises prior to the curing step, the step of covering the edge with at least one additional ply, in order to compensate for the migration of the resin during curing.

Abstract: A harness is provided comprising a body having a series of electrical conductors embedded therein and substantially running along the length thereof. The body may be part of a structural component such as stringer.

Abstract: An air guiding element (10) for an aircraft air conditioning system comprises a housing base body (12), in which an air inlet opening (14) and an air outlet opening (16) are constructed. A first flow control element (28) is arranged in the housing base body (12), relative to the direction of the air flow through the air guiding element (10), upstream of the air outlet opening (16). The first flow control element (28) comprises a plurality of air guiding channels (30) which are surrounded by a noise-absorbing material (32).

Abstract: The invention in particular has as an object detecting incompatibility between equipment items of a on-board system. A logic interface associated with one equipment item comprises at least one input while a logic interface associated with another equipment item comprises at least one output. The input and the output are connected. After a minimal data definition level associated with the input and a data definition level associated with the output have been obtained (505), the said minimal data definition level associated with the input is compared (515) with the said data definition level associated with the output. Following this comparison, if the said minimal data definition level associated with the input is lower than the said data definition level associated with the output, an alarm indicating an incompatibility of these two equipment items is generated (545).

Abstract: An aerodynamic control surface assembly comprising: an aerodynamic control surface (4); an actuator (10) for controlling deployment of the control surface; and a locking mechanism (30) moveable from a locked to an unlocked position. When the locking mechanism is set to the locked position, the actuator is operatively coupled to the control surface and the control surface can move in dependently of the actuator when the locking mechanism is set to the unlocked position. Such an assembly may be used in an aircraft to prevent clashing between a deployed flap (16) and a drooped spoiler (4) in the event of an actuator control systems failure.

Abstract: An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.

Abstract: A coupling assembly for joining a first component to a second component, the assembly comprising a shaft for connecting to a first component, and a bracket including a mounting plate for connecting to a second component. The bracket has a bracket arm extending from the mounting plate, and a head having a through-bore on the bracket arm. The shaft is received in the through-bore. A setting device acts between the head and the shaft for setting of the position of the shaft with respect to the head in the axial direction of the shaft. The assembly further includes one or more spherical bearing surfaces, which permit self-alignment of the setting device to accommodate tilting of the shaft with respect to the head about a central point in two orthogonal directions. Also, a joint comprising a first component joined to a second component by one or more of the coupling assemblies. Also, a method of forming a joint using one or more of the coupling assemblies.

Abstract: Disclosed is a method for the monitoring of a cabin region of a transport system located outside a field of view, wherein at least one light beam is emitted, passing through the cabin region in the longitudinal direction, and in the event of a disturbance of the at least one light beam path a message is generated. A monitoring device is also provided, with at least one emitter unit for purposes of emitting at least one light beam, with at least one receiver unit for purposes of receiving the emitted light beam, and with at least one messaging unit for purposes of generating a message in the event of a disturbance of the at least one light beam path; also disclosed is an aircraft cabin with at least one such monitoring system.

Abstract: The invention relates to a monitoring system for monitoring a state of a door lock mechanism of a door or of a closure of a storage space of a means of transportation, comprising a generator and a sensor/actuator. The generator produces electrical energy from vibration energy, and the sensor detects the state of the door lock mechanism. The sensor uses the kinetic energy that is produced by the actuation of the door lock to generate an electrical signal, which is then transmitted to a microcontroller.

Abstract: A method of controlling an elastomeric damper. The damper is heated by passing an electric current through the damper or through a heating element in contact with the damper said heating causing a decrease in stiffness of the damper. The elastomeric damper may comprise an elastomeric material filled with electrically conductive particles, and the damper may be heated by passing an electric current through the elastomeric material. Alternatively the damper may be heated using a discrete resistive heating element, such as a coil embedded within the elastomeric damper or wound around it.

Abstract: A manufacturing method for passenger door corner components of aircraft or spacecraft includes using additive layer manufacturing, ALM, to form an integral passenger door corner component. The integral passenger door corner component includes a substantially cruciform shape having a frame coupling member with two frame couplings as end pieces. The frame coupling member intersect with a beam coupling member with two beam couplings as end pieces.