Abstract: A propulsion system for an aircraft, which has a chassis, a propeller able to move in rotation about an axis of rotation, a main gear as one with the propeller, an electric generator, at least one linear electric motor having a fixed element and a slider able to move in translation, for each linear electric motor, a secondary gear meshing with the main gear and mounted to be able to move in rotation about an axis of rotation perpendicular to the axis of rotation, and a rod of which one end is articulated on the corresponding slider and of which the other end is articulated on the corresponding secondary gear at an articulation that is offset with respect to the axis of rotation of the secondary gear.

Abstract: A line assembly for installation in an aircraft fuselage includes a first line section having a first diameter, a second line section having a second diameter, a set of first line brackets, and a set of second line brackets. The first line brackets include a first receiving space configured to hold the first line section and a first support portion for attaching the first line brackets to a fuselage structural part. The second line brackets include a second receiving space configured to hold the second line section and a second support portion for attaching the second line brackets to the first line section. The second line section includes a higher flexibility than the first line section. The second line section is attached to the first line section through a plurality of second line brackets arranged at a distance to and independent from the first line brackets.

Abstract: A device for latching a door of an oxygen mask container in an aircraft cabin includes a door for an oxygen mask container having an inner side, outer side and hinge, a first latching device attached to the inner side, and a second latching device movable relative to the first latching device to selectively engage or disengage the second latching device. A retaining element is attachable to a structural part inside the oxygen mask container. A test control device on the inner side of the door includes a movable hook element and can move the hook element to a first or second position. The hook element can engage the retaining element in the first position to restrict an opening degree of the door. The hook element is placed in the second position such that when the door is opened, the hook element is moved past the retaining element.

Abstract: An aerodynamic element includes at least one first, fixed aerodynamic part including a box section that is covered at least partly by a plate with an extreme part, and one second aerodynamic part including a peripheral surface with an end and at least one holding element provided with a shoulder which forms, with the extreme part of the plate, a groove in which the end of the peripheral surface can be housed, such that the peripheral surface and the plate form a junction having an ascending profile. The presence of the groove makes it possible to obtain a continuous ascending junction with favors a laminar airstream on the upper surface of the aerodynamic element.

Abstract: An expansion tank system for a liquid cooling system includes a first chamber for receiving a coolant, a second chamber for pressurized gas, a first gas conveying device for conveying gas from the first to the second chamber, a second gas conveying device for conveying gas from the second to the first chamber, a first pressure sensor in fluid communication with the first chamber, and a control unit connected to the first gas conveying device, the second gas conveying device and the first pressure sensor for controlling the second conveying device to selectively convey gas from the second to the first chamber if a pressure measured through the first pressure sensor is below a predefined first threshold value, and for controlling the first conveying device to convey gas from the first to the second chamber if a pressure measured through the first pressure sensor is above a second threshold value.

Abstract: In order to improve usability of hybrid or fully electric aircraft, a fuel cell having improved efficiency and increased volume/weight specific energy density is provided. The fuel cell has a self-supporting membrane structure that is formed as a triply periodic level surface, which separates a first cavity supplied with gaseous fuel from a second cavity supplied with gaseous oxidizer in a gas-sealed manner while connecting the cavities in an ion-conductive manner.

Abstract: An aircraft glazing unit including a body of transparent material and at least one subsurface thickness indicator at a predetermined depth within the material. The provision of a subsurface thickness indicator allows for the unit to be re-polished to remove erosion, whilst providing a visual indicator to ground crew of the remaining thickness of material in the unit. In this way, the service lifetime of the glazing unit can be extended.

Abstract: A system and method for controlling an actuator for a control surface of an aircraft includes a processing unit configured for acquiring a set of N values of the same parameter, N being equal to 2×p or to 2×p+1, p being an integer greater than or equal to 2, and determining a voted value of the parameter by a voter (15) with N inputs. The voter with N inputs includes a module for determining two intermediate values from among the values of a subset of 2×p values of the set of N values of the parameter, this module including at least p+1 voters with 2×p?1 inputs, receiving as input distinct subsets of 2×p?1 inputs of the subset of 2×p inputs, two sub-modules for determining a maximum value and a minimum value, respectively, each receiving as input the outputs of the various voters with 2×p?1 inputs and delivering as output the two intermediate values.

Abstract: A system includes a reception unit to receive current flight data of the aircraft and current meteorological data, a data processing unit to perform an iterative computation to determine, as a function at least of a set of predetermined rules, of a set of constraints and of current values including current meteorological data, an optimal flight trajectory making it possible to generate a dissipation of the energy of the aircraft to bring it, at a stabilized final position, into a final energy state with a minimum ground distance, the optimal flight trajectory defining positions at which actions must be implemented on the aircraft, and a data transmission unit to transmit at least the minimum distance to at least one user system.

Abstract: A method for managing access to a shared resource in an electronic system including a control unit and the shared resource. The control unit is intended to execute applications that are candidates for access to the shared resource. The method uses a calendar of periods of equal duration, each assigned to just one of the applications, to define a temporal distribution of access to the shared resource, and penalty indices associated with each of the applications. The method includes steps for conditionally processing the access requests transmitted by the applications according to their penalty indices. Thus, each application is prevented from accessing the shared resource when the quota assigned thereto is reached, which makes it possible to limit the encroachment of an application that is executed on the access quotas for accessing the resource that are assigned to the other applications.

Abstract: A movable flow body device for an aircraft including an elongated flow body having a main extension axis, a first mechanical interface in a first position along the main extension axis, a second mechanical interface in a second position and a third mechanical interface in a third position. The first mechanical interface may be a master interface arranged in a central region, while the second and third mechanical interfaces are slave interfaces. Preferably, in the outboard position, a link plate between a support lever and a support rib of the flow body is inverted compared to the further inboard mechanical interface, which allows for supporting slimmer and longer flow bodies in the outboard region and providing a rigging hinge line through the whole flow body.

Abstract: A propulsion assembly having a propulsion system including an exhaust nozzle fastened to the nozzle wall on the outside thereof so as to define between them a chamber, and a heat exchanger system ensuring an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall. The heat exchanger system has a pipe portion arranged in the chamber and the exchange of heat energy takes place at this pipe portion. With such an arrangement, the heat energy of the combustion gases is transferred to the fuel for better combustion.

Abstract: Tooling for manufacturing multi-spar torsion boxes with different web heights, the tooling includes a mandrel module having a hollow beam geometry which comprises a first base and a second base opposite to the first base, and two walls extending between said first base and said second base, and at least one spacer module configured for coupling with the mandrel module, wherein the web height of a multi-spar torsion box is defined by the coupling between the mandrel module and at least one spacer module. A method for manufacturing multi-spar torsion boxes with different web heights.

Abstract: A pump arrangement for providing a saturated or subcooled liquid includes a tank for saturated liquid, a heat exchanger for cooling the saturated liquid, a pump, an expansion valve, and an output for feeding saturated or subcooled liquid to a consumer. A tank outlet is in fluid communication with a liquid inlet of the heat exchanger, such that saturated liquid stored inside the tank can flow into the heat exchanger designed to sub-cool the saturated liquid. A liquid outlet of the heat exchanger is in fluid communication with a pump inlet. The expansion valve outlet is in fluid communication with a coolant inlet of the heat exchanger. An expansion valve inlet is arranged for receiving and expanding a fraction of liquid flowing through the pump arrangement and routing it into the coolant input to at least partially evaporate and receive evaporation enthalpy of the liquid to be subcooled.

Abstract: A semi-active noise control system includes a layer configured to be part of an interior panel of an aircraft The layer includes conductive tracks, a driver arrangement, tuned mass dampers, and sensors. Each tuned mass damper has an eigenfrequency that depends on a control signal applied to the tuned mass damper and is connected to the driver arrangement via a conductive track and configured to receive control signals from the driver arrangement. Each sensor is connected to the driver arrangement via a conductive track and is configured to sense vibrations and/or acoustic sounds and send measurement signals to the driver arrangement. The driver arrangement is configured to analyze the measurement signals and to generate and send control signals to the tuned mass dampers such that the eigenfrequency of the tuned mass dampers is matched with the frequency of the vibrations and/or acoustic sounds sensed by the sensors.

Abstract: A laser communication system for an aircraft has optical head units, separate laser transmitting unit, laser receiving unit, optical fiber for each optical head unit, optical switching device for coupling an optical head unit and a separate laser transmitting unit, and a central control unit, the optical head units connected to the optical switching device through the optical fiber, the optical head units having an optical axis, parallel to which light is emitted or received, and an optical pointing mechanism for adjusting the respective optical axis. The separate laser transmitting unit has a laser. The control unit connects to the optical switching device, laser transmitting unit, laser receiving unit and optical head unit to control a laser based data communication through coupling an optical head unit, which is in a free line of sight to a target outside the aircraft, to the laser transmitting unit and to modulate operation of the laser transmitting unit for emitting a signal.

Abstract: A pipe joint with a socket, and a pipe fitted into the socket. An annular seal is compressed between the socket and the pipe. The seal is electrically conductive and resiliently flexible. The socket or the pipe has a recess which houses the seal. The recess has a ridge in a base of the recess and the seal has a groove which extends around a radial periphery of the seal. The ridge fits into the groove to fool proof the installation, such that a standard non-conductive O-ring seal is more difficult to install in error.

Abstract: A system and a method for evaluating performance of a porous skin of an aircraft including the porous skin, and a boundary layer control system. The performance evaluation system includes a first sensor providing data related to the performance of the porous skin. The performance evaluation system is further configured to clean the porous skin based on the performance of the porous skin determined using the data received from the first sensor in order to ensure that the porous skin operates at its maximum capability.

Abstract: An apparatus for determining tire pressure of an aircraft tire. The apparatus includes a processing system configured to: obtain a first set and a second set of tire measurement data for an aircraft, wherein the first set is from a start of a flight cycle and the second set is from a time before the first set; and determine a steady state tire pressure based on the first and second sets of measurement data.

Abstract: A tire pressure sensor device (122) for a wheel (112) of an aircraft (102) including a pressure sensor (124) for measuring the internal pressure of a tire, a temperature sensor (126) for measuring a temperature local to the tire (116), a memory unit (131) local to the tire for storing data, and a control unit (128) local to the tire arranged to record in the memory unit (131) data of the readings taken at intervals of time. The data recorded for each reading includes an indication of the time of the reading, the tire pressure and the temperature local to the tire. Measurements may be taken and recorded over time, both when the aircraft is on the ground and when the aircraft is in flight. Data may be uploaded to a portable handheld device (140) for analysis when maintaining the tires in their correctly inflated state.