Abstract: The invention relates to a method for assisting the piloting of an aircraft in the vicinity of a landing or takeoff point, by: determining the locus of entry and/or exit points for a given approach and/or departure altitude that are not safe for reaching the landing and/or takeoff point; and presenting a diagram including said locus on a display device.

Abstract: A method for doing an optimization of the performance envelope initially authorized for an existing rotorcraft engine (M) to enable the engine (M), to be used in an optimized performance envelope that is different from the performance envelope initially authorized for the engine, is remarquable in that this optimization is compensated by modifying the total service life of the engine (M).

Abstract: This invention relates quite in general to production of fiber composite components by infiltration of a fiber material with a synthetic resin and subsequent curing. In order to improve the required preparation of a liquid or viscous resin system, as claimed in the invention especially a synthetic resin granulate (10, 12) and a process for its production are provided, encompassing the step of stabilization of the synthetic resin granulate (10?) by adding nanoparticles (12?) which attach on the surface of the granulate particles (10). The granulate (10, 12) which is thus free of blocks can be easily handled, for example bagged, flow-conveyed and metered. Advantageously the nanoparticles do not have an adverse effect on the infiltration properties of the resin and on the component properties.

Abstract: The present invention relates to a preimpregnated main fabric (1?) provided with reinforcement (2) having a bottom face (F?) impregnated with a first thermosetting matrix (5) and a top face (F) impregnated with a second thermosetting matrix (6). The invention is remarkable in that the first and second thermosetting matrices (5, 6) have different physico-chemical and rheological properties.

Abstract: A diagnostic method for locating a failure in a complex system that includes the steps of detecting operating information using a detector device; verifying a performance of the system based on the operating information; determining an operating status of the system to be one of “operational,” “non-operational” and “degraded” based on the operating information; comparing the operating information with predetermined data when the operation status is one of “operational,” “non-operational” and “degraded;” and generating at least one hypothesis as to a location of the failure of the system.

Abstract: A door arrangement for an aircraft that has a fuselage with a fuselage structure includes a door to be arranged inside a door frame of the fuselage structure and a door joint mechanism attached to the door of the door frame and to the fuselage structure. The door joint mechanism has a seven-joint linkage provided with first to seventh joints by means of which the door, guided exclusively in a rotationally articulated manner, is moveable over a predefined pivoting angle range from a closed position inside the door frame to an open position outside of the door frame and fuselage, and back again. In addition, an aircraft, especially a fixed-wing aircraft, encompassing at least one aircraft door arrangement is provided.

Abstract: A method of managing maintenance of an aircraft. The method includes defining a recommended maintenance program for the aircraft. Maintenance deadlines for the recommended maintenance program are determined by using primary data from a testing of at least one of pieces of equipment and elements of the aircraft. Utilization data for the aircraft is used and stored. A calculation device is used to implement at least one algorithm to recalculate the maintenance deadlines as a function of the actual utilization data. The recommended maintenance program is updated.

Abstract: A hybrid engine installation (200) includes drive element (204) suitable for driving a mechanical element (BTP, BTA) in rotation. In addition, the hybrid engine installation is remarkable in that it includes at least one gas turbine (253, 254) and at least one electric motor (201) mechanically linked to the drive element (204) to drive it in rotation.

Abstract: A method of fabricating components (23) based on fiber-reinforced plastics material, in particular with the help of a wrapped mold core (10), includes the following steps: a) fabricating the mold core (10); b) wrapping the mold core (10) with a wrapper (14) that withstands resin; c) applying fiber semi-finished products (16) and introducing resin to create the plastics component (23); and d) hardening the plastics component (23) under the effect of temperature; which method is improved by the fact that, under all circumstances, and during hardening in step d), substantial pressure equilibrium is established across the fiber semi-finished product (16, 20) between ambient pressure (pu) and the pressure (pk) inside the core. A device is also described.

Abstract: An intermediate product for the manufacture of a hollow fiber-composite component having a shape and dimensions, includes a three-dimensional, hollow preform of reinforcing fiber material corresponding to the shape and the dimensions with a three-dimensional reinforcing fiber structure which is formed from at least one planar, single- or multi-layer blank of two-dimensional, web-like reinforcing fiber material matching the dimensions, and a closable total cross-sectional profile with at least two hollow chambers located adjacent to each other and separated from each other by a rib-like partition. The partition is formed by an overlap region of the at least one blank which is stitched in two dimensions by a compacting seam which fixes the shape and dimensions of the rib-like partition as well as its position relative to adjacent regions of the blank and prefixes, precompacts and reinforces the reinforcing fiber material in the region of the partition.

Abstract: The present invention relates to a support (20, 24, 26) for a stationary article surmounting a helicopter rotor (11), which support comprises a hollow structure presenting a longitudinal axis (25); the hollow structure comprises two hollow parts (20, 24) of elongate shape along said longitudinal axis that are designed to be engaged one in the other and to be mutually stressed in twisting along said common longitudinal axis.

Abstract: Described is a blade (10) extending longitudinally from a root (11) of the blade (10) to a free end (12) of the blade (10), the blade (10) being provided with an incorporated resonator (20) for reducing the drag movements (F1, F2) of the blade (10), the resonator (20) being provided with a closed tank (30) that is partially filled with a liquid (50). Furthermore, the resonator (20) includes a central tube (40) immersed inside the tank (30), the tank (30) and the central tube (40) being arranged in a longitudinal direction (Y) of the blade (10), the central tube (40) having first and second ends (41, 42) that communicate with the tank (30) so that the liquid (50) can move from the tank (30) into the central tube (40), and vice versa.

Abstract: A blade (10) extending longitudinally from a root (11) of the blade (10) to a free end (12) of the blade (10), the blade (10) having a resonator (13) incorporated therein to reduce the drag movements (F1, F2) of the blade (10), the resonator (13) being provided with a solid and movable heavy element (30) and with resilient retaining element (20) secured to the heavy element (30) and to the blade (10). Furthermore, the resonator (13) includes guide element (40) in which the heavy element (30) is capable of oscillating (F1?, F2?) longitudinally, the guide element (40) being arranged in a longitudinal direction (D1) of the blade.

Abstract: A hybrid helicopter (1) includes firstly an airframe provided with a fuselage (2) and a lift-producing surface (3), together with stabilizer surfaces (30, 35, 40), and secondly with a drive system constituted by: a mechanical interconnection system (15) between firstly a rotor (10) of radius (R) with collective pitch and cyclic pitch control of the blades (11) of the rotor (10), and secondly at least one propeller (6) with collective pitch control of the blades of the propeller (6); and at least one turbine engine (5) driving the mechanical interconnection system (15). The device is remarkable in that the outlet speeds of rotation of the at least one turbine engine (5), of the at least one propeller (6), of the rotor (10), and of the mechanical interconnection system (15) are mutually proportional, the proportionality ratio being constant.

Abstract: An assisted control system for controlling the attitude of a rotorcraft comprises a flight control device; at least one control member configured to act on an aerodynamic element of the rotorcraft; a mechanical connection connecting the flight control device to the at least one control member, the mechanical connection including at least one connecting rod moveable in translation, a crank device pivotably disposed about a stationary support shaft passing through the crank device, and a motor including a drive rotor and a stator configured to facilitate a pivoting movement of the crank device about the stationary support; a motor control device configured to control a rotation of the drive rotor relative to the stator; and at least one sensor configured to measure information representative of an operation performed by the flight control device under pilot control and to deliver a signal to the motor control device.

Abstract: A device (D) for opposing sloshing in a flexible tank (21) provided with a top cushion (22) and having a bottom (23) and a plurality of sides (24), the device includes at least first and second ties (1 and 2). The first and second ties (1 and 2) are secured respectively to first and second edges (221 and 222) of the cushion, with the first edge (221) being opposite from the second edge (222). The device is remarkable in that it includes main distributor elements (10) for blocking only one of the ties when the tension exerted on that tie is greater than the tension exerted on the other tie, the first and second ties (1 and 2) also being secured to the main distributor unit (10).

Abstract: Solidborne noise and vibration is decoupled in a rotary wing aircraft by a laminated ball joint (15) for a suspension bar (13) of a transmission gearbox, the ball joint including at least two damper layers (19) dedicated to a frequency band for decoupling in the range 0 to 7000 Hz. For this purpose, the damper layers (19) and possibly also likewise dedicated interleaved layers (20) are given shape and/or dimension and/or physical-property parameters as a function of the frequency for decoupling in the determined frequency band.

Abstract: To achieve automatic setting into coincidence, the following are provided: a mechanical tension elements arranged to act on an upstream member (9) substantially along the axis (X) along which approach elements (13) act, but in the opposite direction; elements (37) for constraining the member (9) in rotation with a mechanical angular guide element; and phase-shifter elements (47) for shifting the phase of the upstream member (9) relative to the downstream member (10) by sliding against a reference that is stationary in rotation relative to the downstream member (10).

Abstract: An aircraft includes a pressurised cabin with a lockable door, an electrical energy supply network, and a cabin differential pressure warning system provided with an autonomous waning system energy supply device, which is independent of the electrical energy supply network.

Abstract: A breakable coupling device for coupling together first and second main transmission shafts stationary in translation along a longitudinal axis of rotation of the device comprises a blocking device having a discontinuous first housing and a continuous second housing forming a closed loop; a compression device; at least one drive device connecting the blocking device and the compression device together in rotation about the longitudinal axis below a predetermined torque, wherein the discontinuous first housing is configured to receive the at least one drive device below the predetermined torque; and a shifting device configured to shift the at least one drive device non-reversibly from the discontinuous first housing towards the continuous second housing when the torque exerted on the at least one drive device is greater than the predetermined torque.