Abstract: A transmission gearbox (1) has a casing (2) that tilts around a tilting axis (B—B) via two bearings (19). Each of the bearings includes: a fixed part (20) having a sleeve (20a); and a trunnion (21a) which belongs to a pivoting part (21) and which pivots around the sleeve, the pivoting part being solidly connected to the casing (2). A shouldered wear ring (22) is disposed between the sleeve (20a) and the trunnion (21a) of each bearing (19). The invention is suitable for use in the pivot mounting of a power transmission gearbox (1) that is used to rotate the tilting rotor (14) of a convertible aircraft.

Abstract: The present invention relates to a device for lashing down a rotorcraft wing, said wing being provided with at least first and second adjacent blades P and P?, the ends of said blades being provides with respective endpieces. In addition, the device comprises a main cord CP having a first end CPE1 fastened to first fastener means 5? arranged on a second end CPE2 secured to a second blade P? and having a second end CPE2 secured to a second fastener means M1 arranged on a first endpiece of the first blade P. The lashing-down endpiece includes first fastener means 5 for fastening to a first main cord CP and second fastener means M1 for fastening to a second main cord CP.

Abstract: The present invention relates to an absorbent covering having high damping power, the covering being secured to a structure (20) and being provided with an absorbent layer (10) of elastic material (4). Remarkably, said absorbent layer (10) comprises a dissipater mesh arranged in the elastic material (4) and constituted by a plurality of nodes (2) and of dissipater elements (1), which dissipater elements are advantageously elliptical in shape.

Abstract: A rotor, comprising at least one rotor blade (B1, B2, B3, B4; B5) connectable to a rotor head (2), which rotor blade possesses a blade neck (8) having a virtual flapping hinge in the form of a flexurally soft, flexurally elastic blade-neck portion, there being provided, in a blade-connector region (12, 14; 16; 30, 32) of the blade neck (8), two auxiliary flapping hinges (H1, H2), spaced apart from one another in the radial longitudinal direction of the rotor blade (B1, B2, B3, B4; B5) with reference to a rotor radius (R), between which the virtual flapping hinge is substantially disposed and between which the blade neck (8) is deformable in flexurally elastic and curved fashion in the context of a flapwise motion. A rotorcraft, in particular a helicopter, in particular a tiltrotor helicopter, having at least one such rotor.

Abstract: The invention relates to a rotor comprising a rotor shaft, a rotation torque transmission element which is mounted thereon and at least one element of the plate-shaped rotor head whose axis of rotation extends therethrough. Said rotor is provided with two groups of different arms. The first group consists of the flexible rotor blade connection arms which remove centrifugal forces and to which a respective blade can be fixed. The second group consists of flexible connection rotor arms which are devoid of centrifugal force to which the elements of the plate-shape rotor head can be rotationally fixed by means of the rotation torque transmission element.

Abstract: The present invention relates to torque limiter (L) provided with a first plate (10) that rotates a second plate (20) via a plurality of balls (60), said second plate (20) sharing the same axis as the first plate (10), each ball (60) being suitable for escaping from a respective housing in order to cease driving the second plate when the torque exceeds a predetermined threshold. Each housing comprises a first orifice and a second orifice facing each other and formed respectively in the first plate and in the second plate. The torque limiter (L) is remarkable in that it includes first and second distinct inlets for causing said first plate (10) to turn about its axis (AX).

Abstract: A fuel level gauge includes a measuring pipe configured as a riser pipe that has a fuel inlet opening at one end region defines a measuring distance. The fuel level gauge also includes a fuel level sensor associated with the measuring pipe and disposed the vicinity of the fuel inlet opening and having a measurement-sensitive sensor area for purposes of measuring the fuel filling height in the measuring pipe. A fuel-permeable, thin-walled enveloping element surrounding the measuring pipe tightly so as to seal it in a first area of the measuring pipe and enclosing a second area of the measuring pipe at a predefined distance over a large surface. The second area encompasses at least the fuel inlet opening and the measurement-sensitive area of the fuel level sensor, and forms a large-volume antechamber upstream from the fuel inlet opening in the second area between an inside of the enveloping element and an outside of the measuring pipe.

Abstract: A damping structure includes a member defining an internal cavity; an aggregate which includes at least solid bodies in contact and which completely fills the internal cavity; a rigid plate for closing off the internal cavity; and an elastic element which exerts elastic pressure on the rigid plate so as to constrain the aggregate. The member defining the cavity may be elongate with the internal cavity being formed longitudinally inside the member. At least some of said solid bodies may be hollow or solid, compact, made of different materials, of different shapes, and/or of different sizes.

Abstract: A hingeless rotor, in particular for a rotorcraft, comprising: a rotor head, a rotor mast having a rotor axis, a torque-transmission element nonrotatably joined to the rotor mast, at least one rotor blade, and a rotor-head-side rotor-blade connector having a centrifugal-force-discharging blade connector loop, which loop encircles the rotor axis or the rotor mast and is nonrotatably joined to the torque-transmission element.

Abstract: A device for locking a holding structure for securing a foldable blade of a rotorcraft rotor to the hub of the rotor. The holding structure is hinged in pitch and in drag relative to the hub and the rotor includes, for the purpose of folding the blade, elements for locking the blade-holding structure in pitch and in drag, which device is remarkable in that the associated drive elements includes brake elements preventing it from turning in flight, in particular under the effect of vibration from the rotor.

Abstract: A twist element for a bearingless rotor is made mostly of composite fiber material and has a cross section with a substantially symmetric, flattened shape that has approximately the contour of a horizontal, central section of a double cone. In addition, a bearingless rotor having at least one such twist element. and a rotorcraft, particularly a helicopter, having at least one rotor with at least one such twist element are provided.

Abstract: A rotor, in particular for a rotorcraft, encompassing: a rotor head, at least one rotor blade, and a rotor-head-end rotor-blade connector having an integral, bearingless, centrifugal-force-controlled blade angle adjustment device. A rotorcraft, in particular a helicopter, in particular a tiltrotor helicopter, encompassing at least one such rotor. A method for adjusting the blade angle of a rotor blade of a rotor, in particular of a bearingless rotor that possesses a rotor head and a rotor-head-end rotor-blade connector, encompassing the following steps: rotating the rotor blade; and automatically adjusting the blade angle by twisting the rotor-head-end rotor-blade connector, and thus the rotor blade, about its longitudinal axis by means of centrifugal forces acting on the rotor blade.

Abstract: A method and apparatus for detecting the defects of at least one rotor of a rotary wing aircraft, in particular a helicopter, in order to adjust the rotor. In the method, in a preliminary step, a reference aircraft is used corresponding to a particular type of aircraft and having a rotor (6, 10) without defect and adjusted so that the level of vibration is at a minimum, a series of measurements are taken on the aircraft (1), and a neural network is deduced therefrom illustrating the relationships between accelerations representative of vibration, and defects, and adjustment parameters. Thereafter, in a later step, for a particular aircraft (1) of the same type, measurements are taken on the particular aircraft (1) and on the basis of said measurements and on the basis of the neural network, the defects, if any, are detected and values for the adjustment parameters are determined that will enable the level of vibration of the aircraft (1) to be minimized, which parameters are applied to the rotor (6, 10).

Abstract: A heater mat for using the Joule effect to heat an aerodynamic surface. The heater mat is provided with a resistor element including at least two substantially parallel segments of electrically-conductive fibers disposed on the aerodynamic surface. The segments come from a single strip of electrically-conductive fibers, with two adjacent segments being obtained by folding a portion of the single strip at least twice.

Abstract: A connection endpiece placed on a resistor element provided with at least one layer of electrically-conductive fibers, the endpiece serving to connect a power supply wire electrically to the resistor element. The endpiece includes at least one metal plate having a top face for connection to the power supply wire, and provided with at least one rigid metal connector member of substantially flat shape arranged at a first end of the metal plate and connected to at least one layer of electrically-conductive fibers of the resistor element, the top face of the metal plate being covered in a removable anti-adhesive covering.

Abstract: The blade includes a current part (1) having an aerodynamic profile enclosing a spar (7) and extending from blade tip (4) to a blade root (3) provided with a pitch sleeve (21), through which twisting arm (6) passes and protrudes beyond blade root (3), and having a first part of a bundle (5) of superimposed and elongated metal strips, current part (1) including a block (13) based on synthetic material molded in form in a single piece around spar (7), and a second part of bundle (5) extending in line with the first part forming the twisting arm (6) and cooperating with the anchoring devices (14, 17) of the block (13) based on synthetic material around the spar (7).

Abstract: A cyclic swashplate device for controlling rotorcraft blade pitch is disclosed for application to rotorcraft swashplates, in particular, in helicopters. A cyclic swashplate device controls the rotorcraft blade pitch. The device (10?), with rotating (10?) and non-rotating (14?) cyclic swashplates is designed in such a way that at least one of the two disks includes a modular link fitting assembly (46, 42) ensuring the links with the disk (12?, 14?) and the pitch connecting rods (6) and/or at least one driving device or with the pilot control devices (17) and/or at least one retaining device. Interconnecting fittings are attached rigidly and separately to an annular device, such as one of the rings (31?, 30?) of a bearing (21?) on the corresponding disk (14?, 12?).

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: The present invention relates to a device for indicating a beat level L, the device comprising analyzer means which respond to a reference frequency ? and a harmonic coefficient B to extract the following from an evaluation signal E: a first acceleration signal ?B at a frequency equal to the product of said reference frequency ? multiplied by said harmonic coefficient B; and a second acceleration signal ?B -1 at a frequency equal to the product of said reference frequency ? multiplied by said harmonic coefficient minus one; and it further comprises a control circuit CC which receives said acceleration signal ?B??B-1 to produce said beat level L.

Abstract: A brake device for the rotor of a helicopter, the device associating a mechanism having a disk and a manual control for main braking of the rotor, and a mechanism for secondary braking of the rotor under strong wind. The secondary braking device includes a secondary lever hinged to the body and capable of being actuated against secondary return elements to drive a bearing finger against a main lever of the main brake mechanism and cause the jaws of the mechanism to move correspondingly towards each other so that the secondary lever actuates the main lever in order to amplify the clamping forces applied to the disk by the jaws in comparison with the forces they exert when driven by the main lever alone.