Abstract: The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system, the aircraft electronics cooling system providing a thermal coupling between an electronic device to be cooled and the liquid cooling system of the aircraft. A coolant delivered by the liquid cooling system may flow through a board of the electronic device, through a heat sink on which the electronic device is arranged and/or through a housing in which the electronic device is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

Abstract: Thermal test apparatus comprising a specimen supported by a fixture, a thermal shroud comprising a flexible insulating fabric forming an enclosure around at least a portion of the specimen, and a temperature controlled air supply connected to an opening formed in the enclosure for delivering a supply of temperature controlled air into the enclosure. Also, a method of conducting a thermal test.

Abstract: A mounting device for mounting a cable or a line on a structural component of an aircraft or spacecraft. The mounting device comprises at least two parts, one of these parts being configured as an attachment part and being provided to be attached to the structural component. The other part is configured as a receiving part and is provided to receive a portion of the cable or of the line. Both parts can be coupled together by means of at least a first ball-and-socket joint. This coupling is configured such that the two parts can be brought into a plurality of spatial positions relative to one another. Also provided is an aircraft or spacecraft, in particular an aircraft, which has a structural component and a cable or a line which is mounted on the structural component by a mounting device of this type.

Abstract: The present invention provides a tank vent device for venting gas from a tank 10 comprising a gas inlet 107 for receiving gas from a vent outlet of the tank, a gas outlet 109 for discharging the gas received, and a pressure valve 70 connecting the gas inlet and gas outlet, wherein the pressure valve is connected to a control pressure input 108 and is controllable by control pressure supplied at the control pressure input, whereby, in use, the pressure valve is controlled by the control pressure to open and close so as to regulate the flow of gas between the gas inlet and the gas outlet. The present invention also provides a vent tank 10, methods of venting gas and refueling an aircraft.

Abstract: The control system of an aircraft including at least two communication networks and a controlled device control unit connected to one of them. The system determines control commands for the device with a DAL-A quality assurance level requirement and includes a set of at least three physical units each including at least two computers, an electrical power supply and a network interface device. The electrical power supplies, and the network interface devices, are of at least three different types, the computers are of at least two different types and include operating systems of at least two different types; the computers each have a DAL-C, DAL-D or DAL-E hardware and/or software quality assurance level and at least six of the computers are configured to independently determine control commands for the device. A DAL-A hardware and software quality assurance level selection logic unit is configured to select valid control commands used by the control unit to control the device.

Abstract: A de-icing device includes a hot air circuit including an inlet for hot air bled from an engine, and a duct connecting the inlet to an outlet of the circuit which opens towards the leading edge. The device also includes electrical heating means associated with the duct, and control means for controlling the heating means connected to detection means that detect the temperature of the hot air downstream of the heating means and are able to activate these if the detected temperature of the bled air is below a value corresponding to a minimum temperature required for de-icing, increased by a predetermined margin. The range of temperatures of the hot air supplied to the leading edge is lowered overall, whereas the minimum de-icing temperature is assured. Composite materials can be used near the leading edge without being damaged.

Abstract: A bleeding system includes an open conduit and, upstream, a control controlling the hydraulic fluid flow, toward the open conduit. The bleeding system includes a dismountable connection device including connection mechanism adapted to be connected to the bleeding system; an outlet adapted to be connected to a pipe; a first central portion including the connection mechanism, a cylindrical bearing, and a conduit extending from the connection mechanism up to the surface of the cylindrical bearing; and an annular second portion including a bore adapted to pivot on the cylindrical bearing, at least one conduit connecting the outlet and the surface of the bore. The first portion and/or the annular portion include a groove ensuring the hydraulic fluid flows between the conduits. The central portion includes a section arranged between the connection mechanism and the cylindrical bearing to ensure the connection of the connection device to the bleeding system.

Abstract: A pinned lug joint comprising: a first part comprising two first lugs projecting from a bridge which extends between them; a second part pivotally coupled to the first part, the second part comprising a second lug positioned between the first lugs; and a sealing member, the sealing member being mounted to the first lugs and extending between them to seal an air gap between the second lug and the bridge at least when the second part is in a first position. The pinned lug joint may be used to attach a panel assembly to part of an aircraft.

Abstract: An apparatus for the forming of a lay-up of fiber composite material, in particular in the aerospace sector is provided. In this case, the apparatus has at least one forming tool, which has a surface contour corresponding to a desired geometry of the lay-up after the forming, and a tool carrier, to which the at least one forming tool is releasably fastened. From a further viewpoint, the invention makes available an apparatus with a modular structure, it then being possible for any desired forming tools to be combined with the tool carrier according to requirements. This leads in particular to less laborious handling, since it obviates the need for handling of the comparatively large tool carrier.

Abstract: An apparatus and a method for transferring data and energy over network units of a defined network. The apparatus has at least two units, a bus coupling the units with a receive line and a transmit line and a bus control device coupled with the bus, the bus control device having first means for controlling the transfer of data defined by the defined network as data voltage signals over the transmit line and over the receive line, second means for charging the data voltage signals on the transmit line with first supply voltage signals adapted for voltage supply of units of a first plane system, and third means for charging the data voltage signals on the receive line with second supply voltage signals adapted for voltage supply of units of a second plane system.

Abstract: The present invention provides a method for preventing the forming of cracks and slowing the crack propagation in metallic airplane structural parts by laser shock peening with the following steps: Providing an airplane structural part having a crack; irradiating a first surface area of the airplane structural part close to the crack with a first pulsed laser beam having a first wavelength and a first pulsation frequency, wherein energy of the first laser beam is absorbed by the airplane structural part and a shock wave runs through the airplane structural part, which creates compressive prestressings in the airplane structural part.

Abstract: The invention aims to produce an instrumentation making it possible to measure the loadings which pass through mechanical joins between two mechanical structures, so as to best evaluate the dimensions and masses without impairing their mechanical properties of a secure transfer of load. To this end, the invention proposes introducing into the zones of transit of the loadings an instrumented component of the form that favors the measurement of shear and its installation. In one embodiment, a zone of transit of loadings consists of an instrumentalized hollow shaft which takes the form of a cylinder (1) able to be introduced into collinear openings (30) in the fittings (20, 25, 26). It comprises a longitudinal housing (10) into which is introduced an insert (2) composed of a central prop (21) in tight contact with the internal wall (1i) of the shaft (1) and connected, on each side, to a flyweight (31, 32) also in tight contact, by way of multiple tabs (41 to 44) away from contact with said internal wall (1i).

Abstract: A shell component for an aircraft or spacecraft. The shell component includes a skin panel, a plurality of stringers which are arranged on the skin panel, a former which includes a fiber composite material and is arranged over the stringers so as to cross the stringers, and a former connection structure which includes a ductile material and a plurality of foot portions fixed to the skin panel. The foot portions each transition integrally into a shoulder portion fixed to the former over an associated fixing span, the fixing spans associated with the foot portions extending along the former substantially continuously over the stringers.

Abstract: An aircraft fuselage includes at least one opening that can be closed by a flap or door, which comes to abut against at least one door stopper that is arranged on a fuselage-side door frame bulkhead and transfers the impact forces into an intermediate costal for diversion into an aircraft structure that encompasses bulkheads, wherein the door frame bulkhead exhibits an opening, through which an impact section of the door stopper extends, wherein a fastening plate section adjoining the latter comes to abut the rear side of the door frame bulkhead, which interacts with means for directly introducing the impact forces from the door stopper into the intermediate costal.

Abstract: The support (1) comprises a main body (3) which has a convex shape comprising facets which are planar and curved and free of edges, and it is provided with main contact surfaces (5) each of which is able to accept an electric cable, and with openings (6) surrounding each of the main contact surfaces (5).

Abstract: A high lift system for an aircraft with at least one high lift flap arranged on each of the main wings of the aircraft. The high lift system includes an input device for the generation of flight phase-related requirements for the high lift flap. The high lift system further includes a control device, with a conversion function with which the flight phase-related requirements are converted into setting commands for the actuation of a lift device for the adjustment of the high lift flap. The conversion function is configured such that from a take-off requirement, a setting command to the drive device is generated with which the leading edge flap of the high lift flap is arranged in a set state in which a gap exists between the leading edge flap and the main wing with a gap width of between 0.1% and 0.4% relative to the local wing chord.

Abstract: A molding tool for manufacturing a fiber-reinforced plastic aerodynamic aircraft component, which aircraft component, in order to form several bays arranged on the inside and delimited by an outer skin and spars arranged spaced apart from each other, in each case includes a multi-part mold core that matches the shape of the respective bay, wherein to conform to local skin reinforcements and/or spar reinforcements that extend into at least one of the bays, the multi-part mold core includes four or five core parts, of which two core parts comprising a triangular cross section are arranged along opposing edges of the bay, which edges interact with two or three core parts that fill the space between the two triangular core parts, which space extends diagonally relative to the bay.

Abstract: A method and apparatus for more easily controlling energy of an aircraft. A control interface includes a movable element configured to move along a path, where the path includes two path portions. The path portions are respectively associated with at least two combinations of actuators which affect the energy of the vehicle. At least one of the two combinations of actuators is associated with a current phase of movement of the aircraft. A control unit is configured to generate an energy instruction according to a command associated with a current position of the movable element on one of the two path portions. According to the current phase of movement of the vehicle, the energy instruction is for one of the two combinations of actuators.

Abstract: An aircraft panel assembly comprising a first panel constructed from a first sheet material having a first thermal expansion coefficient, the first panel comprising a first face, a second panel constructed from a second sheet material having a second thermal expansion coefficient different from the first thermal expansion coefficient, the second panel comprising a second face facing the first face, the first and second panels being joined at a first discrete fastening point and a second discrete fastening point, the fastening points being connected by a first notional panel join line describing the shortest distance between the fasteners along the first face, and a second notional panel join line describing the shortest distance between the fasteners along the second face, in which the first panel comprises a stress relief feature between the fastening points such that the first notional panel join line diverges from, and converges with, the second notional panel join line.

Abstract: The present invention concerns an AFDX network which is extended by a passive optical network or PON. The AFDX network comprises an AFDX switch to which are connected a plurality of equipments. The AFDX switch constitutes the optical line termination and said equipments constitute the optical network terminations of the PON. The PON broadcasts over the downlink, to all said equipments, every AFDX frame output by said AFDX switch. It also multiplexes over the uplink the AFDX frames transmitted by the same equipments. The invention also concerns an ?AFDX network using a PON.