Abstract: A control system for an aircraft allowing a pilot of the aircraft to control aerodynamic means, the control system comprising a processing unit for generating control commands, the control commands being transmitted to control devices to modify a position of the aerodynamic means and to pilot the aircraft according to four control axes having a pitch control axis, a roll control axis, a yaw movement control axis and a lift control axis, the control system comprising a control member generating control setpoints, the control setpoints being transmitted to the processing unit generating the control commands under the dependency of the control setpoints, the control member being mechanically disconnected from the control devices.

Abstract: A test bench configured to test a drag damper. The test bench comprises a first support that can be rotated about a first axis by a motor, the test bench comprising a second support that can rotate about a second axis, the second axis being axially offset from the first axis, the test bench comprising a first connector secured to the first support and a second connector secured to the second support, the first connector and the second connector being offset from the first axis and the second axis, the first connector and the second connector being opposite each other along an arrangement axis and being configured to carry the damper in line with the arrangement axis.

Abstract: A communication system for an aircraft, comprising a plurality of radios including at least a first radio that is operable in an encrypted mode for transmitting/receiving encrypted audio signals, and a second radio that is operable in a clear mode for transmitting/receiving unencrypted audio signals; an intercom system that interconnects the plurality of radios, wherein the plurality of radios is connected to the intercom system via a plurality of communication lines; and a security module that is configured to connect or disconnect selected ones of the plurality of communication lines for inhibiting simultaneous transmission of an encrypted audio signal via the first radio and an unencrypted audio signal via the second radio.

Abstract: A method for testing a portable electronic device. The method comprises the following steps: acquiring at least one set of parameters; storing the at least one set of parameters in a first area of a storage unit of the portable electronic device; storing the at least one set of parameters in a second area of the storage unit; generating at least a first image by means of a first processing operation; in a first displaying step, displaying the at least one first image for a predetermined time period; in a first erasing step, erasing first intermediate results corresponding to calculation steps carried out during the first processing operation; generating at least one second image by means of a second processing operation; and in a second displaying step, displaying the at least one second image for a predetermined time period.

Abstract: An electromechanical actuator for electrical flight controls of an aircraft, the actuator comprising a transmission shaft, four electromechanical conversion members, each having a respective stator and rotor secured to the transmission shaft, and four control systems, each dedicated to respective ones of the electromechanical conversion members. The stator has teeth and windings surrounding at least one tooth, whereas the rotor is provided with permanent magnets. Each electromechanical conversion member is a flux-concentrating member and each winding is concentric and has a single layer. The electromechanical actuator is intended in particularly for controlling a hydraulic actuator via a mechanical transmission within an electrical flight control device of an aircraft.

Abstract: An arrangement provided with a partition at least partially delimiting an emergency exit, the arrangement having a movable panel that closes the emergency exit in an inactive operating mode, the arrangement comprising an evacuation system provided with a lifeline. The lifeline comprises a deployment section passing through a passage in the partition and secured to a handle, the panel together with the partition delimiting a recess in which the handle is arranged in the inactive operating mode.

Abstract: A gearbox including an angular contact ball bearing comprising a first row of balls provided with a plurality of balls, a second row of balls provided with another plurality of balls, at least one inner ring and at least one outer ring. According to the invention, in a degraded operating mode of the bearing, the first row of balls is configured to transmit at least one first axial force oriented along a first axis and at least one second axial force oriented along a second axis opposite the first axis, the second row of balls transmitting no axial force.

Abstract: An angular orientation tool for manufacturing and checking a harness, the harness comprising at least one connection member and at least one elongate element. According to the disclosure, the tool comprises: a fixed plate; at least one immobilization device for immobilizing the elongate element; a movable part having a degree of rotational mobility in relation to the fixed plate; at least one immobilization support configured to immobilize the connection member relative to the movable part; and a graduated angular scale for reading a relative angular orientation between the elongate element and the connection member.

Abstract: A method for helping to keep a drone within an authorized airspace. This method involves displaying several symbols on a display of a path estimator comprising: i) displaying an aircraft symbol showing a current position of the drone in relation to the authorized airspace; ii) displaying a boundary symbol showing a boundary of the authorized airspace in a position in relation to the aircraft symbol representative of a position of the boundary in relation to the current position of the drone; and iii) determining a geometry and displaying a path symbol showing a predicted path of the drone without changing values of an item of speed data and an item of navigation data, the geometry of the path symbol being based at least on the value of the item of speed data and the value of the item of navigation data.

Abstract: An actuating system for an actuatable door and to an actuatable door having such an actuating system. The actuating system comprises first and second rotatable latching shafts, a coupling link, first and second pivotable mechanical transmission elements that are mounted onto first and second rotatable latching shafts, respectively, and first and second latching members. First and second latching members are non-rotatably mounted to the second rotatable latching shaft and adapted for latching the actuatable door in a closed position. A first rotation of the first rotatable latching shaft results in pivoting of the first and second mechanical transmission elements and a second rotation of the second rotatable latching shaft, which causes a third rotation of first and second latching members.

Abstract: An assembly comprising a first part and a second part, the assembly comprising a disconnectable coupling system provided with a mechanical fuse for securing the first part and the second part according to an axis of movement up to a breaking threshold. The assembly comprises at least one single-use friction brake interposed between the first part and the second part, the friction brake braking a movement of the first part with respect to the second part after the mechanical fuse has broken.

Abstract: A method and apparatus for estimating an airspeed of a rotorcraft by analyzing its rotor. The rotorcraft includes a fuselage and a main rotor that is equipped with a plurality of blades and that rotates about an axis of a hub of the rotor, and in which the free end or “tip” of each blade describes a path in the vicinity of a tip-path plane. The method makes it possible to determine said airspeed of the rotorcraft in a frame of reference united with the tip-path plane by solving a model of the rotor that puts a pitch angle of at least one blade relative to the tip-path plane into relation with the airspeed of the rotorcraft and with an auxiliary speed. The auxiliary speed may be an induced velocity of the air flowing through the rotor or else an axial airspeed at the upstream infinity of the rotorcraft.

Abstract: A vibration damping device equipped with a resonator mechanism comprising at least one resonator, the at least one resonator having a first beater extending from an embedded end to a free beating end. The resonator consists of an elastically deformable base equipped with a first branch and a second branch connected by a central section, the embedded end being embedded at the first branch, the first branch extending from a first end to a second end each rigidly fastened to a mount, the second branch extending from a first end section to a second end section each rigidly fastened to a vibration source.

Abstract: A rotorcraft including a first power plant, at least one main rotor participating at least in providing lift for the rotorcraft in the air, and at least one tail rotor carried by a tail boom, the first power plant including at least one engine. In accordance with the invention, the rotorcraft includes: at least one pusher or puller propeller independent from the at least one main rotor, the at least one pusher or puller propeller participating at least in providing propulsion or traction for the rotorcraft; a second power plant including at least one electric motor; and at least one control member configured to generate a control setpoint or instruction for controlling the at least one electric motor.

Abstract: The present disclosure relates to a system and a method for assisting the piloting of an aircraft, said method comprising, during a flight phase of said aircraft, at least two steps of measuring at least two current values of at least two respective operating parameters of said aircraft. The method comprises, for each of said at least two operating parameters, the following steps: generating an item of digital data representative of a current value of this operating parameter; identifying a current range within which an index lies, each range from said at least two ranges of indices being associated with a specific display configuration of said item of digital data; and displaying said item of digital data on at least one page of symbologies according to said specific display configuration corresponding to said current range.

Abstract: A modular load carrying apparatus for a rotary wing aircraft and to a rotary wing aircraft with such a modular load carrying apparatus. The modular load carrying apparatus may include a tube, first and second caps at first and second axial ends of the tube, a carrier star with docking devices that are adapted for rotatably receiving a seat or a carrier beam that may be folded against the tube in a stowed position or unfolded from the tube in a deployed position. A tension rod may be spanned between the first and second caps and transfer tension loads from the carrier star via the second cap towards the first cap.

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: A mechanical system comprising a sump and at least one component to be lubricated or cooled arranged in the sump, the mechanical system comprising a lubricating fluid system provided with a lubricating fluid and a tank arranged in the sump. The tank is a leaking tank and is situated above said at least one component to be lubricated or cooled, the lubricating fluid flowing out of the tank by force of gravity, so as to reach said at least one component to be lubricated or cooled. The lubricating fluid system has at least one lift flow generator connected by at least one filling line to the tank and to at least one suction point present in a bottom of the sump. The lift flow generator fills the tank with the lubricating fluid present in said bottom at least during a starting phase.

Abstract: A method of managing risks and alerts for a system. The system includes source modules and auxiliary modules for identifying actual or potential risks of failures or of malfunctions of the system. A central module of the system serves to determine actual or potential risks of failures or of malfunctions of the system and actual or potential risks associated with parameters external to the system and that might have impacts on operation of the system. Then, an overall risk level is determined by combining the various actual or potential risks and their effects on the system, and then an action and information interface may be controlled as a function of the overall risk level, e.g. for modifying a display of information relating to the system and/or to its environment, or indeed for automatically performing an action on the system.

Abstract: A guided missile with a sleeve-shaped missile body, at least one engine for producing forward thrust, at least one flight direction control device, and at least one aerodynamic extension. The least one flight direction control device is rotatably mounted to a top area and/or a bottom area of the sleeve-shaped missile body for adjusting a flight direction of the guided missile. The least one aerodynamic extension comprises an aerodynamic cross-sectional shape that is arranged on a left-hand side and/or a right-hand side of the sleeve-shaped missile body.