Abstract: An anti-impact shield (50) for a mechanical part (22) of a rotorcraft, the mechanical part (22) having a central portion (221) together with first and second U-shaped ends (EX1, EX2) each having a bottom wall (225) and two side branches (224), the bottom walls (225) of the ends (EX1, EX2) of the mechanical part (22) being parallel to each other and secured to the central portion (221). Furthermore, the shield (50) is provided with first and second U-shaped ends (51, 52) respectively held inside the first and second ends (EX1, EX2) of the mechanical part (22) by interference of shapes, the first and second ends (51, 52) of the shield (50) each having a respective bottom wall (53) and two side branches (54).

Abstract: A device for indicating at least a first vibration level VIB1 derived from a first acceleration signal ?1 includes: first analysis element FT1 for resolving the first acceleration signal ?1 into a plurality of axial analysis signals ?1i each occupying an identified frequency band Bi; a first memory RM1 having recorded therein a plurality of axial weighting coefficients KAi, each corresponding to one of the identified frequency bands Bi; and a first control circuit CC for summing the pth powers of the axial analysis signals ?1i weighted by the axial weighting coefficients KAi, thereby producing the first vibration level VIB1.

Abstract: The present invention provides a device enabling the collective pitch of the blades of the main rotor of a single-engined rotorcraft to be reduced automatically in the event of an engine failure. The device comprises an actuator which increases the collective pitch of the blades above a predefined threshold, and which decreases the collective pitch below the predefined threshold. The actuator is arranged on a bell crank of the mixing unit of the rotorcraft.

Abstract: The invention relates to an aircraft door arrangement, especially for an aeroplane, said arrangement comprising a door, a doorframe, a supporting section with a pivotal axis (AD) on the door side, along which the door is pivotably positioned, and a pivotal axis (AF) on the frame side, along which the supporting section (8) is pivotably positioned on the door frame. At least the pivotal axis (AD) on the door side is defined by two articulations (G1, G2) which are interspaced in the vertical direction (Y) of the supporting section (8), at least one (G1; G2) of said articulations comprising two vertically (Y) interspaced bearings (L1a, L1b). The inventive door arrangement also comprises a pivotal drive (10) which is arranged on the door side of the supporting section (8) and is used to pivot the door, and an output element (12; 14, 16) which is coupled to the pivotal drive (10) and the door and transfers an actuating movement of the pivotal drive (10) to the door.

Abstract: A rotor, especially for a rotary-wing aircraft, with a rotor mast and one or more adjustable rotor blades includes a rotor blade adjustment device without a swash plate and arranged on a carrier device that automatically rotates synchronously with the rotor blades, the rotor blade adjustment device rotating along with the carrier device in a manner that is free of relative movement with respect to the carrier device as well as with respect to the rotor mast and the rotor blades. The rotor blade adjustment device includes all of the blade actuators and kinematic elements required for a synchronized, cyclic and collective rotor blade adjustment as well as a control signal interface via which the control signals for the blade actuators can be transmitted from a stationary rotor section to the rotor blade adjustment device that is rotating along. Also, a rotary-wing aircraft, especially a helicopter, including at least one such rotor.

Abstract: A connection arrangement for detachably connecting a first flexible tank and a second flexible tank in an aircraft includes a latching device, a first tubular connecting element attached to the first tank, and a second tubular connecting element attached to the second tank. The first and the second connecting elements are detachably connected to each other using the latching device. In a connected state of the connecting elements, fluid exchange can take place between the first and the second tanks via the first and the second connecting elements, the latching device is disposed inside one of the first and second flexible tanks and is actuatable from outside the respective flexible tank.

Abstract: An equipment-fastening device EFD to enhance the crash safety of aircraft, for fastening a piece of equipment to a support structure of an airframe, includes a load-limiting release mechanism and a load-peak transformer connected to the release mechanism and having a load-limiting, impact-energy-absorbing deformation element. Load peaks that occur in case of a crash and that stem from equipment fastened to the support structure by means of the equipment-fastening device are first reduced to a residual load peak by the EFD after the release, thereby relieving the stress on the support structure. Only then is any residual load peak that might still remain introduced via a first fastening section of the EFD into the support structure with a time delay vis-à-vis the load peaks that occurred originally.

Abstract: The rotary flap (1) is liable to turn about a longitudinal axis of rotation (4) defined according to the first span (5) of said flap (1), said flap (1) having a profile (6) extending along the chord (CO) and comprising a first leading edge (7), a first trailing edge (8), an inner surface (9) and an outer surface (10), The inner surface (9) and outer surface (10) have non-concave shapes, first leading edge (7) having a rounded shape provided with a curve radius (R) more or less constant or elliptical in shape whose first major axis to minor axis quotient is less than or equal to 1.5, with first trailing edge (8) having a main angle (?) that is included between 10° and 30°, and axis of rotation (4) is situated at a first distance (C1) from first leading edge (7), that is included between 15% and 35% of the chord (CO) of flap (1).

Abstract: The system is of a type including a flange (5) and a set of conical internal rings (9) and external rings (8) combined to link by friction the flange to the shaft through the relative axial movement of the rings. Advantageously, the flange includes a rigid housing (7) with a cylindrical axial passage (7A) to receive coaxially the set of conical rings (8,9) and define between the inner surface of the passage (7A) and the outer surface of the external ring (8) an annular space (10) in which can be engaged the end (2A) of the shaft and of which the external ring (8) is elastically and radially deformable.

Abstract: A rotorcraft rotor with hinged blades, includes: a hub; a plurality of blades hinged to flap relative to the hub; bottom abutments of the hub, and bottom abutments of the blades suitable for co-operating with the bottom abutments of the hub; and top abutments of the hub, and top abutments of the blades suitable for co-operating with the top abutments of the hub; the top abutments of the hub being movable between a deployed position in which they extend facing the top abutments of the blades, and a retracted position in which they are offset angularly away from the top abutments of the blades. The rotor also includes elements for locking the top abutments of the hub in the deployed position, and inertial means for releasing the top abutments of the hub and for deactivating the locking means.

Abstract: The present invention relates to a convertible aircraft provided with first and second tilt fans disposed on either side of the fuselage a little forward of the center of gravity of the convertible aircraft. In addition, the convertible aircraft includes, in remarkable manner, a non-tilting fan that is permanently in a vertical position and that is contained inside the fuselage.

Abstract: In a method of the invention for assisting the piloting of an aircraft, a guard curve (CGS) is determined as a function of the resources of the aircraft, the position of an obstacle (O) or a terrain point situated in front of the aircraft is measured by telemetry, the distance D between the guard curve and the obstacle (O) or the terrain point is calculated, and a pull-down order or a pull-up order is produced as a function of the distance D.

Abstract: A rotor brake includes a braking force absorption element non-rotatably connected to a rotor shaft; a stationary brake actuator for actuating a braking force transmission element that is functionally coupled to the braking force absorption element so as to exert a braking effect; and at least one rotor speed-controlled, centrifugal force-actuated rotor brake deactivation device. In addition, a rotor having at least one such rotor brake, as well as rotary-wing aircraft, especially a helicopter, having at least one rotor as well as at least one such rotor brake.

Abstract: A process and device for estimating the vertical speed of a rotary wing aircraft may include integrating the sum of: (1) a first component corresponding to a vertical acceleration measurement and (2) a second component obtained from the difference between: (a) a first value incorporating a barometric measurement and (b) a second value incorporating a previous estimation of the vertical speed. The second component is derived from the difference between the first and second values by clipping this difference to eliminate, as appropriate, the part of the difference which is greater, in absolute value, than a predetermined value.

Abstract: A method for producing a component made of fiber composite material includes sewing a plurality of reinforcing-fiber layers together using a thread to create a seam and to form at least one reinforcing-fiber preform, wherein the seam has a predetermined thread tension and the sewing pre-compacts the reinforcing-fiber preform to a pre-compacting size. The at least one reinforcing-fiber preform is placed into an injection mold. A final compacting of the reinforcing-fiber preform to a final compacting size is performed by closing the injection mold, wherein the final compacting includes relaxing the thread tension of the seam. A resin is injected into the injection mold and the resin is cured. In addition, an intermediate product includes at least one reinforcing-fiber perform.

Abstract: A method for damping vibrations in a tail boom of a rotary-wing aircraft includes the steps of detecting tail boom vibrations induced by external vibration excitation, and generating and introducing strains into the tail boom based on the detected tail boom vibrations. The strains are applied over a surface area and are out-of-phase with respect to the detected tail boom vibrations so as to damp the externally excited induced tail boom vibrations. In addition, a rotary-wing aircraft, includes a fuselage, a cockpit area integrated into the fuselage, a tail boom arranged on the fuselage and a tail boom vibration-damping device.

Abstract: The present invention relates to a pilot indicator for a rotorcraft provided with a main rotor and at least one gas turbine engine. The indicator has first and second sensors delivering information relating respectively to a first speed of rotation Nr corresponding to said main rotor, and a second speed of rotation NTL corresponding to the free turbine of said engine. The indicator is also provided with display means provided with a display screen for displaying the first and second present values respectively for the first and second speeds of rotation Nr and NTL. In addition, said processor means determines an estimated value for the first speed of rotation Nr.

Abstract: A device for contactless electrical power transmission in a system including at least one stationary and one moving part, power being transmitted between the at least one stationary part and the at least one moving part includes an inductive transformer including a primary winding disposed on the stationary part and a secondary winding disposed on the moving part, the inductive transformer bridging an isolating point between the stationary part and the moving part. The device also includes a frequency generator having a series-resonant circuit capacitor connected to the primary winding and at least one actuator control element connected to the secondary winding and including a matrix arrangement of a plurality of switchable power semiconductors. At least portions of the inductive transformer, frequency generator and at least one actuator control element are disposed in an area of a rotor shaft and a rotor head of a rotary-wing aircraft.

Abstract: A pilot indicator is provided for an aircraft provided with at least one gas turbine engine. The indicator includes a set of sensors delivering information relating to different monitoring parameters of the engine, namely: the speed of rotation Ng of the gas generator, the temperature T4 of the gas at the inlet of the free turbine, and the torque Cm. The indicator is also provided with a processor for processing information from the sensors, and a display provided with a display screen. In addition, the processor determines an estimated value of a limiting parameter, where the limiting parameter is that one of the monitoring parameters that is closest to its limit.

Abstract: An installation includes at least a pressurized lubricating circuit for elements housed in the rocking crankcase, each circuit including a radial transfer bearing between two opposite cylindrical journals coaxial about the rocking axis, one fixed journal on a fixed part and one pivoting journal on a pivoting part integral with the pivoting crankcase. Each transfer bearing has two U-shaped annular gaskets facing each other and spaced apart along the rocking axis so as to define between them an annular pressurized liquid lubricant chamber. The annular chamber is supplied with pressurized liquid lubricant by at least a supply duct integrated in the fixed part and whose upstream part is connected to a pressurized lubricant source, and feeds the rocking crankcase with pressurized lubricant through a dispensing duct emerging into the rocking crankcase. The invention is useful for lubricating rocking power transmission boxes for convertible aircraft tilt rotors.