Abstract: A modular power plant for a rotorcraft comprising at least one lift rotor, the power plant comprising: at least one combustion or electric engine; a main gearbox, comprising a gearbox housing and a toothed wheel arranged in an internal space at least partially delimited by the gearbox housing, the toothed wheel having a degree of rotational freedom about a primary axis of rotation relative to the gearbox housing, the toothed wheel mechanically transmitting an engine torque generated by the at least one engine to the at least one lift rotor; and at least two mechanical connection interfaces, a first mechanical connection interface mechanically connecting the main gearbox to a first engine, and a second mechanical connection interface being left free or mechanically connecting the main gearbox to a second engine.

Abstract: An aircraft comprising two half-wings extending to either side of an airframe. The aircraft comprises at least one propeller arranged in the rear part of the airframe. The aircraft comprises a rotary wing provided with two synchronized counter-rotating rotors carried respectively by the half-wings. The aircraft comprises a power plant comprising at least one engine and a mechanical interconnection system connecting the power plant permanently to the rotors except in the event of failure and during training, and to the at least one propeller.

Abstract: The measuring device includes a substrate intended to be arranged on an aerodynamic surface; a profiled element connected at one of its ends to the substrate, and configured to be oriented, under the effect of the fluid flow; a magnet that is secured to the profiled element and is configured to generate a magnetic field; and a measuring element that is configured to measure a value of the magnetic field and to convert this measured value of the magnetic field into an angle value indicating the direction of the fluid flow; the measuring device thus making it possible to measure and provide, in real-time, a numerical angle value with which it is possible to define with high precision the direction of the fluid flow relative to the aerodynamic surface.

Abstract: A method for assisting the piloting of a rotorcraft including at least two engines capable of transmitting engine torque to at least one main rotor, the assistance method comprising the following steps: periodically determining a current position of the rotorcraft; making a first periodic comparison between the current position and a decision point; identifying an engine failure; making a second periodic comparison between the current position of the rotorcraft and a touchdown point; periodically determining an emergency landing profile, the emergency landing profile being generated at least depending on a result of the second periodic comparison; and periodically generating control orders to pilot the rotorcraft according to the emergency landing profile.

Abstract: An antenna arrangement for an aircraftincludes an antenna unit, a radome structure covering the antenna unit, and a mounting device for mounting the antenna arrangement to an outer surface of an aircraft component. The antenna unit is mounted to or integrally formed with the radome structure and the radome structure is mounted to or integrally formed with the mounting device.

Abstract: A method for assisting piloting beyond an altitude that can be reached with only the capabilities of a thermal power plant of a rotorcraft, by supplying power from an electrical power plant. After defining a take-off point of the rotorcraft and a target point, and their respective altitudes, a determination of a first maximum altitude that can be reached by the rotorcraft using only the thermal power plant is carried out according to a first altitude law. Then, an estimate of a second maximum altitude that can be reached by the rotorcraft using the thermal power plant and the electrical power plant jointly driving each rotor of the rotorcraft is made according to a second altitude law. If the second maximum altitude is higher than the altitude of the target point, the rotorcraft can fly to the target point.

Abstract: An apparatus for sensing an elastic deformation of a hollow element, wherein the apparatus comprises at least one sensor that is arranged in a watertight capsule which is connected in a watertight manner to a connector device comprising at least one watertight electrical connector that is electrically connected to the at least one sensor, the at least one watertight electrical connector forming a first waterproof barrier of the connector device between an outside of the watertight capsule and the at least one sensor, and wherein the connector device comprises at least one further waterproof barrier that is formed between the first waterproof barrier and the at least one sensor.

Abstract: Seal member arrangements having at least one seal plate are disposed over stringer receiving recesses in ribs of an aircraft. A tool for locating a seal member arrangement over a stringer-receiving recess in a rib of an aircraft assembly. The tool system has a holder configured to hold the seal member arrangement over the recess. A biasing arrangement is configured to act on the holder to bias the seal member arrangement into an aligned position with a stringer received in the recess. A fixing arrangement is configured to act on the seal member arrangement to fix the seal member arrangement in the aligned position. A sealing kit, an aircraft assembly, a method of fixing a seal member arrangement over a stringer-receiving recess in a rib of an aircraft are also disclosed.

Abstract: A drive system 20, 20? for rotating a wheel 11, 11? of an aircraft landing gear 10, 10?, is disclosed having a drive element 24, 24?, a motor 21, 21? operable to rotate the drive element, and a driven gear 25, 25? adapted to be attached to the wheel. The drive system has a drive configuration in which the drive element is capable of meshing with the driven gear to drive the driven gear, wherein the drive system further comprises a transmission error measurement apparatus 30, 40, the apparatus configured to obtain, over time, measurement data of one or more characteristics of the drive system when in the drive configuration, the measurement data providing an indication of a transmission error between a torque commanded by the motor and a resulting torque at the driven gear. An aircraft 100 and a method of providing an indication of a transmission error in a drive system is disclosed.

Abstract: A rotorcraft having an aerodynamic device arranged below a rotor, which rotor participates at least in providing lift for the rotorcraft in the air, the rotor being mounted to rotate about a first axis of rotation, the aerodynamic device having a fairing provided with at least one air inlet for enabling a stream of cool air to flow from a region that is situated outside the rotorcraft to another region that is situated inside the rotorcraft; at least at a mouth of the at least one air inlet in the fairing, the aerodynamic device has at least one moving flap that is mounted to move in rotation, the at least one moving flap having at least one degree of freedom of movement in rotation about a second axis of rotation relative to the fairing, and the at least one moving flap orienting itself automatically and passively.

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a pylon configured to be fastened beneath a wing of the aircraft, a turbomachine having a longitudinal direction, a median plane and a transverse plane, and a nacelle surrounding the turbomachine and having a load support disposed in the top part of the nacelle. The load support has a structural part fastened to the pylon and an aerodynamic part capping the structural part. The aerodynamic part has, at the front, a front part fastened to the structural part and, at the rear, a rear part fastened to the pylon. Separating the load support into two parts makes it possible to reduce the movements of the aerodynamic part capping the structural part of the load support.

Abstract: A method of facilitating the piloting of a hybrid rotorcraft that comprises a lift rotor and at least one propulsion rotor together with at least one engine operating in compliance with at least one rating. For at least one rating, onboard calculator determines a first power margin of the power plant that is available for the lift rotor and at least one second power margin that is available for said at least one propulsion rotor. A single indicator displays a line together with a first index pointing to said line to illustrate a current operating point of the lift rotor, and a second index pointing to said line to illustrate a current operating point of said at least one propulsion rotor. For each monitored rating, a first symbol is spaced apart from the first index by a first distance illustrating the first power margin. A second symbol is spaced apart from the second index by a second distance illustrating the second power margin.

Abstract: A method and system of preparing a drone for takeoff are disclosed. The drone has at least one first control member and at least one second control member that are suitable for being actuated manually by at least one person in charge of preparing the drone for takeoff. The drone also includes a navigation light and at least one anticollision light for generating various mutually different light signals in a predetermined switch-on sequence.

Abstract: A device for lacquer transfer is disclosed having a frame, a nozzle with a dispensing end for dispensing lacquer, and a transfer roller with a circumferential lateral wall, a circumferential outer contact surface of the lateral wall comprises several depressions, wherein the nozzle and the transfer roller are arranged such that lacquer is dispensable from the dispensing end onto the outer contact surface and into the depressions, wherein the transfer roller is configured to roll with the outer contact surface on a work surface of a workpiece for transferring the lacquer from the outer contact surface and from the depressions to the work surface of the workpiece. A first hardening unit is formed as a UV-light unit configured for partially hardening the lacquer in a contactless way by emitting UV-light, the first hardening unit is arranged within an interior space defined by the transfer roller.

Abstract: The method and system for merging information aimed at merging the instances of individuals, a data-processing system performs the following steps: generating the instances of individuals using an ontology which defines, for each property of each instance of an individual, an evolution model to be applied to the property, evolution model representing the evolution of reliability of the property over time in relation to variability of the property over time; preforming the merging of information by comparing, two-by-two, the generated instances of individuals with instances of individuals stored in a knowledge base, performing, for each shared property, a calculation of similarity distance by applying at least evolution model defined for the property, so as to define a coefficient of confidence for each property in order to decide whether or not to merge the instances of individuals; and updating the knowledge base with the instances of individuals resulting from information merging.

Abstract: A linear electromechanical servocontrol comprising a power rod that is able to move in translation. The servocontrol comprises a single linear electrical actuator provided with at least one electric motor connected by a mechanical link to the power rod, the servocontrol comprising an anchor secured to the electrical actuator, the at least one electric motor being controlled by a computer, the anchor having an anchoring rod that is able to move in translation, the anchor having an anchoring brake that is configured to immobilize the anchoring rod with respect to the electrical actuator in a normal operating mode or to allow the electrical actuator to move in relation to the anchoring rod in a safe operating mode at the request of the computer.

Abstract: A planet gear assembly comprising a planet carrier provided with at least one crankpin carrying a planet gear, the planet gear comprising a toothing provided with teeth, the toothing being situated around the crankpin and outside the crankpin. A planet gear bearing is arranged at least partially inside the crankpin, the planet gear comprising a foot that extends along an elevation axis at least partially into the crankpin, the planet gear comprising a rim connecting the foot and the toothing, outside the crankpin, the planet gear bearing extending radially from the foot to the internal face of the crankpin.

Abstract: A flow body for a vehicle having a flow surface, as well as a skin system attached to the flow surface is proposed. The skin system has a top layer and a foam arrangement positioned between the flow surface and the top layer, wherein the top layer includes an elastic, surface-like material, wherein the foam arrangement includes a first layer of an elastic, compressible open cell foam, wherein the foam arrangement is bonded to the top layer. The skin system has a static shape in an unloaded state, in which the shape defines an outer surface geometry that directly follows the geometry of the respective flow surface, and the skin system has a deflected shape when the flow body is subjected to turbulent air flow. The deflected shape at least temporarily compresses the foam arrangement.

Abstract: A device and method for lacquer transfer includes a lacquer application unit and at least one of a masking application unit and a masking removal unit, the application unit for applying lacquer to a work surface, wherein the masking application unit is configured to apply a masking to the work surface and is attached to the lacquer application unit so the masking application unit is moved in the application direction ahead of the lacquer application unit across the work surface when the lacquer application unit is moved across the work surface in the application direction. The masking removal unit can remove a previously applied masking from the work surface and is attached to the lacquer application unit such that the masking removal unit is moved in the application direction behind the lacquer application unit across the work surface when the lacquer application unit is moved across the work surface in the application direction.

Abstract: A component which is configured to be joined to a further component in a preselected relative orientation is disclosed. The further component has an interface surface and the component is configured to contact the interface surface when joined to the further component. The component includes a surface disposed on a side of the component intended to face the interface surface when the components are joined, a plurality of recesses formed in the surface, and a plurality of spacer elements. Each recess has a preselected orientation relative to the component, the preselected orientation being selected in dependence on the preselected relative orientation. Each spacer element comprises a contact surface configured to contact the interface surface when the components are joined. Each spacer element is disposed in one of the recesses such that the orientation of a given contact surface is defined by the orientation of the corresponding recess.