Abstract: A device for providing radiofrequency signal connections for users comprises a plurality of access points which transmit or receive radiofrequency signals in different predetermined radiofrequency bands and are each connected via a transmission and reception signal path to at least one shared transmitting and receiving antenna, a filter being provided in the transmission and reception signal paths respectively and isolating the radiofrequency bands sufficiently from one another and from predetermined mobile radio frequency bands.

Abstract: An ultrasonic scanner has an encoder contacting a drum containing an array. The scanning assembly can be replaced via a snap fit formation. The encoder and drum are resiliently biased and movable relative to the chassis. The array can also be movable relative to the chassis.

Abstract: A guiding mechanism is disclosed for moving a cargo door into extended cargo door positions to open and into a retracted cargo door position to close at least one section of an opening of a loading hatch on a fuselage of an aircraft. A first structural component in the form of the cargo door is pivotably supported on a second structural component on a front lateral edge by a pivot joint arranged in a pivoting axis in order to assume the extended cargo door positions on the loading hatch. The guiding mechanism features at least one actuator for moving the cargo door, a supporting device arranged on an actuating element, and a spring mechanism on the actuator for exerting a compressive force.

Abstract: A device aiding the flight management of an aircraft during a phase of landing on an airport includes means for automatically determining an adaptive aiming point that is shifted along the runway in the downstream direction and which can be used by different usual landing aid means of the aircraft.

Abstract: A system for ventilating an explosion hazard region of an aircraft includes a ram-air channel, which has an air inlet for feeding ambient air into the ram-air channel as well as an air outlet. The ram-air channel is devised to feed air to a device that is to be cooled on board the aircraft. A ventilation line has an air inlet for feeding air flowing through the ram-air channel into the ventilation line as well as an air outlet. The ventilation line is devised to feed air to a region of the aircraft that is to be ventilated. An accumulator is disposed between the ram-air channel and the air inlet of the ventilation line and is devised to convert the dynamic pressure of the air flow conveyed through the ram-air channel at least partially into static pressure for regulating flow through the explosion hazard region.

Abstract: An assembly comprising at least two non-metal components which are fixed to each other using at least one fixing system. The fixing system includes a fixing device with a fixing element which is provided with a head and a rod, and a crimping ring which is in contact with one of the components. A protection device is a part of the fixing system which delimits a cavity for confining gas around a portion of the device comprising the crimping ring. In order to improve the repeatability of the operation for positioning the protection device, a guiding device is provided which includes an assembly element on the portion of the fixing device, and an element for guiding the protection device.

Abstract: A propeller for an aircraft turbine engine comprising a plurality of vanes as well as a hub having a plurality of accommodating ports receiving the bases of said vanes, each vane base being rotatably mounted in its associated accommodating port. The propeller also has at least one vane retaining ring structure in the radial direction outwardly from the hub, being cladded around the latter.

Abstract: A device for laying up a dry preform having an elongated shape includes a punch that reproduces the elongated shape of the dry preform, a depositing assembly, and a mobile carrier that moves at least one of the punch and the depositing assembly. The depositing assembly deposits, onto the punch, a fibrous band including a small amount of binding agent to make up the dry preform having a cross-section with at least two non-coplanar wings. The depositing assembly also includes pressing devices that press the fibrous band, a channel that pre-shapes the fibrous band to have the cross-section, and a calibration device that applies a normal pressure to all surfaces of the dry preform that are opposite from the punch while cooling the pressed portion of the fibrous band to control a thickness of the dry preform having the cross-section.

Abstract: An air guide element (10) for an aircraft air conditioning system comprises a housing (12), which has an air inlet opening (14) and an air outlet opening (16). The air inlet opening (14) and the air outlet opening (16) are disposed in such a way and the housing (12) is shaped in such a way that air that is fed to the air guide element (10) through the air inlet opening (14), as it flows through the air guide element (10), is deflected at an angle of ca. 45° to 135° relative to the direction of the air flow through the air inlet opening (14). A cross-sectional area of flow of the housing (12) that is disposed at right angles to the direction of the air flow through the air outlet opening (16) is subdivided into at least two regions (18a, 18b, 18c).

Abstract: A system for air-conditioning an aircraft cabin includes an air conditioning unit connected to a central mixer, a first recirculation system designed to remove exhaust air from a first aircraft cabin region and connected to the central mixer, and a second recirculation system designed to remove exhaust air from a second aircraft cabin region and connected to a local mixer. A control device is designed to control the second recirculation system to reduce an air volume flow being removed from the second aircraft cabin region when shifting from a first operating state (e.g., normal operation) to a second operating state (e.g., defined operating situations such as when quick cooling is desired). The air volume being removed from the first aircraft cabin region may be increased accordingly in the second operating state.

Abstract: A cargo loading system for a cargo compartment of a means of transport, for example a cargo aircraft or a passenger aircraft, is provided. The system includes at least one power drive unit for transporting cargo of the means of transport. The power drive unit and a control module are coupled to a BUS system. The control module generates control signals for the power drive unit and maintenance data of the power drive unit for the control and maintenance of the power drive unit. The BUS system transmits the control signals and maintenance data of the power drive unit between the control module and the power drive unit. In this manner an existing hardware platform of the means of transport can be used, and weight and cabling as well as the number of control boxes of the means of transport can be reduced.

Abstract: This invention proposes an insulation blanket for an aircraft, the said blanket coming in the form of a strip of insulation material of elongated shape having two more or less parallel longitudinal edges (12). This blanket comprises: at least one bar (14) extending over one face of the insulation blanket (6), from one longitudinal edge (12) to the other thereof, as well as means for holding (18) the said bar (14), and the bar (14) bears at least one system support intended to receive a system (30, 32).

Abstract: A method for the computer-aided design of an aeronautic system forming all or part of an aircraft, using a criterion of maintenance time cost over a given period of use. The cost is computed as the weighted sum of a first component representing the mean flight time lost during this period, a second component representing the mean unscheduled maintenance time for this system during said period, and a third component representing the scheduled maintenance time for this system throughout said period. The configuration corresponding to the lowest time cost is then selected.

Abstract: A method for adhesive application in vehicle construction during joining of joining partners which are subject to tolerances comprises the following steps: detecting the geometric data of the joining partners in an automated manner, detecting the joint gap dimensions of the joining partners from the detected geometric data, joining the joining partners in the joining position thereof, and applying the adhesive in the joint gap.

Abstract: An aircraft with aerofoils including a main wing and a control flap that includes an adjustment flap. The aircraft includes an actuator for the control flap, as well as a sensor device for acquiring the position of the control flap, an arrangement of flow-influencing devices for influencing the fluid that flows over a segment of the main wing, and flow-state sensor devices for measuring the flow state. The aircraft includes a flight control device connected to the sensor device for acquiring the position of the control flap and to the flow-state sensor devices, and connected to the actuator and flow-influencing devices for transmitting actuating commands, and a flight-state sensor device connected to the flight control device for transmitting flight states. The flight control device includes a function that selects the flow-influencing devices that are operated for optimizing local lift coefficients on the aerofoil, depending on the flight state.

Abstract: An aircraft nacelle including a pipe (32), a peripheral wall (34), a lip (36), and a front frame (38) connecting the peripheral wall (34) and the pipe (32) and forming with the lip (36) a space (50) in which the hot air that is provided for frost treatment can circulate, with the pipe (32) including a coating (44) for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element (52) made of a heat-conducting material inserted between the lip (36) and the pipe (32) ensuring the continuity of the aerodynamic surfaces of the lip (36) and the pipe (32) and the propagation of heat from the space (50) toward the rear of the nacelle, whereby the at least one element (52) includes a coating (54) for acoustic treatment that is made of a heat-resistant material.

Abstract: A method and device for aiding the navigation of an aircraft flying at low altitude as described. The device (1) includes positioning means (2) generating the current position of the aircraft, and calculation means (4) for detecting when the budgets allocated to a position error of the aircraft are exceeded by protection ranges.

Abstract: A method and apparatus is disclosed for measuring the volume of fluid in a variable volume vessel.

Abstract: A mounting system includes a first and second mounting part having a first and second base part with a first and second plurality of first and second locking means respectively, for mounting two components to each other. Each of the locking means is attached to the respective base part and is provided with an attachment part extending from the base part, and a distal part provided as a head portion with at least one engaging section protruding sidewards over the attachment part. The locking means are laterally displaceable in relation to the base part to allow sidewards displacement of the engaging sections for engagement and disengagement of the locking means and thus the first and the second base. In the engaged state, latching means are provided blocking the sidewards displacement of the engaging sections to an extent that a disengagement of the locking means is prevented.

Abstract: An aircraft air conditioning system has a fresh air line connected to a fresh air inlet for supplying fresh air to the air conditioning system and a sorption device disposed in the fresh air line which contains a sorbent for taking up moisture from the fresh air flowing through the fresh air line. The sorption device is adapted to expose the sorbent contained in the sorption device to ambient pressure surrounding an aircraft carrying the aircraft air conditioning system when the aircraft is flying for the purpose of regeneration of the sorbent. The sorption device is thermally connectable to a heat source that is adapted, when the aircraft is flying and while the sorbent contained in the sorption device is exposed to the ambient pressure, to supply thermal energy from the heat source to the sorbent contained in the sorption device for the purpose of assisting the regeneration.