Abstract: An air directing arrangement for controlling flow of air at a compartment outlet of a fuselage of a rotorcraft. The air directing arrangement comprises a continuous surface that covers the compartment outlet outside the fuselage and forms a flow channel for directing an air flow at the compartment outlet; a first flow-through opening that is formed at a first position of the flow channel, wherein the first flow-through opening forms an air inlet area; and a second flow-through opening that is formed at a second position of the flow channel, wherein the second flow-through opening is arranged downstream of the first flow-through opening in the predetermined flow direction, and wherein the second flow-through opening forms an air outlet area; wherein the air inlet area is smaller than the air outlet area.

Abstract: A method for controlling a rotorcraft, the rotorcraft comprising at least two combustion engines, at least one regulation system and one transmission system, the at least two engines being mechanically connected to the transmission system respectively by at least two couplings. Such a control method comprises at least identifying an N2-regulated engine, identifying a non-N2?-regulated engine and generating a control setpoint limit for at least one first regulation system of the N2-regulated engine and depending on the speed of rotation N2 of at least one first output shaft of the N2-regulated engine.

Abstract: A measurement system for measuring a dynamic deformation of an object, the measurement system comprising an optical fiber, the optical fiber extending at least partially into a tube that is configured to be secured to the object, the optical fiber having a measurement sector that is able to move inside the tube, the measurement sector comprising at least one Bragg grating. The measurement system comprises a non-Newtonian fluid filling at least one chamber delimited by the tube, the measurement sector extending into the at least one chamber, the non-Newtonian fluid being in contact with the tube and the measurement sector.

Abstract: A ground service system that includes a ground service device and a connecting interface. The ground service device secures rotor blades of a multi-blade rotor of a rotary-wing aircraft in a non-operational mode of the rotary-wing aircraft, when the ground service device is attached to the connecting interface on the rotary-wing aircraft. The ground service device includes a rack with three struts and an attachment device that are releasably attachable to four receiver mounts of the connecting interface. The ground service device further includes clamps for releasably connecting the rotor blades with the four receiver mounts to secure the rotor blades in the non-operational mode of the rotary-wing aircraft.

Abstract: A human and/or non-human cargo attachment device for a rotorcraft. The device comprises a mounting interface with a carrier device and an attachment that is rigidly mounted to the carrier device for attachment to a rotorcraft rope or cable. A device body is mounted to the carrier device. The device body has a stationary body section and a movable body section. The stationary body section is stationarily arranged on the carrier device and comprises a plurality of rotatable attachment hooks for attachment of human or non-human external cargo. The movable body section is movably arranged on the carrier device for enabling movements of the movable body section relative to the stationary body section between a locking position and a release position.

Abstract: A system comprising a connection device having a first shaft and a second shaft, the connection device comprising a free-wheel interposed between the first shaft and the second shaft that can only transmit engine torque from the first shaft to the second shaft when a motor mode is activated. The connection device comprises a coupler, the coupler being provided with a fusible section, the connection device comprising a dog clutch connection that can only transmit engine torque from the coupler to the first shaft when an electrical power generation mode is activated.

Abstract: The transmission system, including a drive shaft, a driven shaft and a connecting device enabling the drive shaft to transmit mechanical torque to the driven shaft, and guide devices guiding the drive shaft in rotation about a drive axis and guiding the driven shaft in rotation about a driven axis. When the transmission system is at a standstill, the drive axis and the driven axis are misaligned, and they move closer to one another when the transmission system transmits torque from the drive shaft to the driven shaft.

Abstract: A method for testing a hybrid power plant equipping a rotary-wing aircraft comprising at least one lift rotor, the hybrid power plant being configured to rotate the at least one lift rotor, the hybrid power plant comprising at least one heat engine configured to rotate the at least one lift rotor; and at least one electric motor supplied with electrical energy by at least one electrical power source, the at least one electric motor being configured to rotate the at least one lift rotor at least when at least one of the at least one heat engine fails.

Abstract: A rotary wing aircraft with a fuselage that forms an aircraft interior region, the fuselage comprising an upper primary skin that separates the aircraft interior region from an aircraft upper deck arranged above the fuselage, the upper primary skin being mounted on top of a predetermined number of supporting beams; wherein the aircraft upper deck comprises an engine accommodating region with a firewall arrangement, the engine accommodating region accommodating at least one aircraft engine within the firewall arrangement such that the firewall arrangement defines a fire proof separation at least between the at least one aircraft engine and the aircraft interior region; and wherein the firewall arrangement comprises at least a funnel-shaped lower firewall arranged between the at least one aircraft engine and the upper primary skin of the fuselage.

Abstract: A ball lock pin comprising a pin body with an inner accommodation and at least one locking ball accommodation; a blocking pin at least partly arranged in the inner accommodation and movable between a blocking position and a releasing position; at least one locking ball movably arranged in the at least one locking ball accommodation and biased into a locking position by the blocking pin, if the blocking pin is in the blocking position, wherein the at least one locking ball is released for moving into an unlocking position if the blocking pin is in the releasing position; a primary spring element arranged in the inner accommodation and biasing the blocking pin into the blocking position; and a redundant spring element arranged in the inner accommodation and biasing the blocking pin into the blocking position.

Abstract: An apparatus for connection to an anchor track or an anchor point in an aircraft, comprising a main body, a quick fastening device that is attached to the main body and configured for being removably fastened to the anchor track or the anchor point, and at least a first connecting element and a second connecting element which are attached to the main body and configured for being connected to external load connecting devices.

Abstract: A method for checking a level of damage of at least one part of an aircraft. According to the disclosure, such a method comprises at least: a collection step for receiving data representative of measurements of at least one flight parameter, the data being generated during a mission of the aircraft by at least one embedded sensor; a projection step for projecting points onto a map in order to form an image point; an identification step for identifying, for each image point, an image zone in which the image point is located; and an analysis step for statistically analyzing the identified image zones and determining the level of damage of the at least one aircraft part.

Abstract: A blade comprising a blade root extended by an aerodynamic intermediate part that extends up to a free end. The blade root comprises a one-piece attachment body made from composite materials, that is hollow and has a casing that defines an empty internal space, the attachment body incorporating: a pitch attachment configured to be traversed by a pitch link rod connected to a pitch lever, the attachment body incorporating a leading edge attachment configured to be traversed by a leading edge link rod connected to a first drag damper, a trailing edge attachment configured to be traversed by a trailing edge link rod configured to be connected to a second drag damper, and a connection attachment configured to be traversed by at least one connecting rod connected to a first reinforcement of a stratified spherical stop.

Abstract: A method of determining a remaining operating time of an electrical energy storage unit in an aircraft, comprising: using a first sensor arrangement for measuring first performance parameters of the electrical energy storage unit; determining first performance indicators based on the first performance parameters; using at least one second sensor arrangement for measuring second performance parameters of the electrical energy storage unit; determining second performance indicators based on the second performance parameters; comparing the first performance indicators with the second performance indicators to determine consolidated performance indicators; and determining predictive remaining operating times of the electrical energy storage unit based on the consolidated performance indicators, wherein the predictive remaining operating times comprise at least a predictive nominal remaining operating time and a predictive emergency remaining operating time.

Abstract: A rotary wing aircraft that extends along a roll axis between a nose region and an aft region, comprising: at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; and a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition.

Abstract: A rotorcraft provided with a rotary wing and a skid landing gear, the landing gear being provided with a first skid and a second skid and with a first cross-member and a second cross-member. The first cross-member is connected to an airframe of the rotorcraft only by two fastenings. The second cross-member is only carried during flight by two supports fastened to the airframe and traversed by the second cross-member. Each support comprises a hole delimited by a stop surface, the second cross-member always being separated from each stop surface by a clearance. A median supporting member is arranged transversely between the two supports and above the second cross-member.

Abstract: A retractable landing gear for an aircraft. The landing gear comprises a rocker arm hinged to a structure of the aircraft and carrying at least one wheel that is able to move between a deployed position and a retracted position, a shock-absorber hinged to the structure, a connecting rod connecting the rocker arm and the shock-absorber, a strut provided with two connecting links that are hinged to each other and respectively hinged to shock-absorber and connected to an actuator fastened to the structure. The connecting rod is out of alignment with the shock-absorber when a force applied to the shock-absorber is less than a predetermined force, and the landing gear comprises a locking device provided with an elastic return member and a stop device for locking the strut when the wheel is in the deployed position, and then for securing the wheel in the deployed position.

Abstract: A modular attachment device for insertion into a plurality of strands of a braided rope, comprising: at least one braiding segment that is braidable into the plurality of strands; at least one first lateral fixation segment that is mountable to the at least one braiding segment at a first lateral attachment interface; and at least one second lateral fixation segment that is mountable to the at least one braiding segment at a second lateral attachment interface, wherein at least one of the first and second lateral fixation segments comprises at least one anchor point for attachment of an external component, and wherein the first and second lateral fixation segments are mountable to the at least one braiding segment for securing the plurality of strands on the at least one braiding segment.

Abstract: An external cargo adapter for use with a rotorcraft that comprises at least one carrier station, in particular at least one weapon station, comprising: at least one mounting lug for attachment to the at least one carrier station; at least one cargo carrying ring for connection to a connecting rope adapted for transport of an external cargo; and a connecting member that connects the at least one mounting lug with the at least one cargo carrying ring.

Abstract: A landing gear provided with a stand and a pivoting assembly carrying a contact member and able to rotate about a pivot axis in relation to the stand. An immobilization system comprises a movable pin and a passage provided in a base secured to the pivoting assembly. An elastic locking system tends to push the pin into the passage in a locked mode. An elastic unlocking system is configured to move the pin out of the passage when activation of an unlocked mode is commanded by a control, the elastic unlocking system being calibrated to allow the pin to be extracted from the passage only when there is a shearing force less than a threshold between the base and the pin.