Abstract: A method for controlling a hybrid helicopter having at least one lifting rotor, at least one forward-movement propeller and an empennage provided with at least one moveable empennage surface. The method includes the following steps: using a main sensor to determine a current value of a rotor parameter conditioning a current power drawn by the lifting rotor, using an estimator to determine a current setpoint of the rotor parameter, adjusting a position of the moveable empennage surface using a deflection controller as a function of the current value and of current setpoint.

Abstract: An aircraft with a fuselage and at least one emergency exit system, the at least one emergency exit system including a jettisonable component that is accommodated and locked in an associated frame structure of the aircraft in normal operation mode to form a portion of the fuselage and that is releasable from the associated frame structure for being jettisoned from the aircraft in an emergency mode; and further including an emergency evacuation assistance device that is adapted to assist in an emergency evacuation of the aircraft via the associated frame structure in the emergency mode; wherein the emergency evacuation assistance device is attached to the jettisonable component such that the emergency evacuation assistance device is deployed by means of the jettisonable component when the jettisonable component is jettisoned from the aircraft in the emergency mode.

Abstract: Atest 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 method for detecting wear before failure of a free-wheel, the free-wheel comprising a driving part integrated into an upstream mechanical power transmission system and a driven part integrated into a downstream mechanical power transmission system. The method comprises determining an oscillation measurement of a monitoring parameter within the upstream or downstream mechanical power transmission system, determining a value of at least one dynamic parameter characteristic of the oscillation measurement or of a transform of the oscillation measurement in a frequency reference frame, and generating an alarm when the value of the dynamic parameter reaches at least one wear threshold.

Abstract: A boom for an aircraft, and, more particularly, to a tail boom for a helicopter, whereby the tail boom may comprise a watertight compartment and watertight bulkheads. The watertight bulkheads may close at least one end of watertight compartment. Watertight bulkhead may include attachment device, frame, and watertight fabric.

Abstract: A life raft system for an aircraft, comprising a storage container; an inflatable life raft that is stored in the storage container in normal operation mode, an inflation device for inflating the inflatable life raft in an emergency mode, and a control unit for activating the inflation device in the emergency mode; wherein the control unit comprises a floatable control buoy with an activation member that is operable for activating the inflation device, wherein the floatable control buoy is provided for operation at a predetermined distance remote from an associated aircraft in an emergency mode.

Abstract: A buoyancy method for deploying a plurality of floats of a buoyancy system of an aircraft. The plurality of floats comprises a plurality of main floats and a plurality of secondary floats that are folded in flight. The method comprises a step of deploying the main floats in flight prior to ditching, and a step of deploying the secondary floats after ditching.

Abstract: A flight control handle suitable for being operated by a pilot, the flight control handle including a stick-forming grip carrying an end box that is provided with a hollow shell provided with a top face, at least one control projecting towards an external environment of the top face. The flight control handle has a controllable member suitable for being actuated by a person, the end box including at least one electronic wall incorporating an electronic circuit, the electronic circuit including at least one sensor that co-operates with the controllable member.

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: A method and a system for identifying tools intended for tools comprising a marking provided with at least one optically readable symbol. The system comprises, in particular, one or more image capture devices covering a checking area and a calculator. Several tools are positioned by an operator in the checking area, then an image of the checking area is captured by each image capture device. Next, at least one complete symbol is detected in at least one image by an image processing operation carried out by the calculator, and one or more detected tools corresponding respectively to a detected complete symbol are identified. Finally, a list comprising each detected tool is determined.

Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a propeller that is at least configured to propel the rotary wing aircraft in forward flight condition, wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and a shrouded duct that is arranged in the aft region and that forms an inner air duct which accommodates at least partly the propeller, wherein the shrouded duct comprises a yaw and pitch stability enhancement unit for improving yaw and pitch stability of the rotary wing aircraft in the forward flight condition.

Abstract: An assistance method for assisting a pilot of a single-engined rotary-wing aircraft during a flight phase in autorotation, the aircraft including a hybrid power plant provided with a main engine, with an electric machine, with a main gearbox, and with an electrical energy storage device. The aircraft also includes a main rotor driven by the hybrid power plant. In the method, during a flight, operation of the main engine is monitored in order to detect a failure, in particular by means of a drop in power on the main rotor, then, when a failure of the main engine is detected, the electric machine is controlled to deliver auxiliary power We to the main rotor, making it possible to assist a pilot of the aircraft in performing the flight phase in autorotation following the failure.

Abstract: A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight trust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.

Abstract: A torque transmission system having multiple torque transmission pathways from a driving shaft to a driven shaft. The driving shaft extends from a lower segment to an upper segment via an intermediate segment, the driven shaft extending from a first segment to a second segment. The transmission system includes a nominal spline coupling that is operational in a nominal operating mode, a backup spline coupling between the driving shaft and the driven shaft that is inactive in the nominal operating mode, and a backup radial guide device between the driving shaft and the driven shaft that is inactive in the nominal operating mode.

Abstract: A rotorcraft having an aerodynamic device arranged below a rotor, which rotor participates at least in providing lift for the rotorcraft, the rotor being mounted to rotate about an 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 air inlet being delimited by an outer peripheral portion of the fairing. In accordance with the invention, the aerodynamic device has a perforated plate provided with at least one perforation, the perforation being suitable for allowing the stream of cool air to pass through it, the perforated plate having at least one main portion shaped to match an outer shape of the outer peripheral portion of said fairing.

Abstract: A method of electrically powering a non-voltage-regulated electricity network, and also to an electrical architecture. The electrical architecture comprises: a plurality of sources of electrical energy including both at least one rechargeable electrical energy storage device and also an electrical power generation device a main electricity network electrically connected directly to the sources of electrical energy; and pieces of electrical equipment electrically powered by the main electricity network. The method comprises both a first powering step for electrically powering the main electricity network by the rechargeable electrical energy storage device and also a second powering step for electrically powering the main electricity network by the electrical power generation device, followed by a regulating step for regulating an internal voltage of the electrical power generation device as a function of the first power delivered by the rechargeable electrical energy storage device.

Abstract: A device for releasing a panel of an aircraft, the device being configured to be secured to a support, the support having an opening and the device being attached to cover a periphery of the opening, the device comprising a panel configured to be arranged at least opposite the opening. Such a device comprises: at least two ejector members, each of the at least two ejector members comprising at least one link; and at least one control member for applying a pulling force to the at least one link.

Abstract: A rope ladder comprising: a first ladder step connecting element that is mounted to a first braided rope, a second ladder step connecting element that is mounted to a second braided rope, and a ladder step that couples the first ladder step connecting element with the second ladder step connecting element; wherein the first ladder step connecting element is braided into the first braided rope and the second ladder step connecting element is braided into the second braided rope, and wherein the ladder step fixes the first ladder step connecting element in the first braided rope and the second ladder step connecting element in the second braided rope.

Abstract: A method for controlling a thermal and electrical power plant for setting in motion at least one rotary member of a rotorcraft, the power plant comprising at least one heat engine and an electrical system provided with at least one electric machine. The method comprises: selecting, with a selector, an operating mode chosen from several operating modes; determining a density altitude and comparing, with a controller, the current density altitude and a threshold density altitude; and controlling, with the controller, the at least one electric machine depending on at least the chosen operating mode as well as the comparison and a necessary power to be supplied to the power transmission system.

Abstract: A measurement apparatus for determining a bending moment acting on a hollow cylindrical body in a current state as well as to a method of operating such a measurement apparatus. The measurement apparatus may include a sensor support structure, a sensor arrangement with sensors, and a processing system. The processing system may determine displacements of the inner surface of the hollow cylindrical body relative to the sensors based on the distances measured in the current state compared to the distances measured during an initial undeformed state, and determine the bending moment acting on the hollow cylindrical body based on the displacements.