Abstract: The invention relates to a method of detecting and identifying a defect or an adjustment error of a rotorcraft rotor using an artificial neural network (ANN), the rotor having a plurality of blades and a plurality of adjustment members associated with each blade; the network (ANN) is a supervised competitive learning network (SSON, SCLN, SSOM) having an input to which vibration spectral data measured on the rotorcraft is applied, the network outputting data representative of which rotor blade presents a defect or an adjustment error or data representative of no defect, and where appropriate data representative of the type of defect that has been detected.

Abstract: Device assisting with interception by an aircraft of a flight path segment located in a horizontal plane and a system of assistance with interception and follow-up of such a segment. The device includes means of determining a ground speed vector and means of displaying to present, on a screen, a means of indication (10) of the ground speed corresponding to a first rectilinear section (10) in the horizontal plane, connected to a symbol (7) whose angular orientation corresponds to the direction of said ground speed vector and whose length is variable, a means of interception approach indication (12) corresponding to a second recipient section (3) in the horizontal plane of variable width and provided for as an extension of first rectilinear section (11) and a means of indication (14) of the interception turn corresponding to at least one circle arc (15) in the horizontal plane, provided to extend second rectilinear section (13).

Abstract: The present invention relates to problems of maintenance of elastomeric members. According to the invention, the elastomeric member is provided with at least one elastomeric layer 1 disposed between two rigid strength members 2. In addition, the elastomeric member is provided with graduations 5 located on its visible surface 7, presenting an angle of inclination relative to the rigid strength members 2, thus making it possible to evaluate and monitor propagation of a crack 6 merely by inspecting it visually.

Abstract: The present invention relates to a method of controlling a drag damper for a helicopter blade under all operating configurations of the helicopter, the method consisting in: a) measuring the elongation of the damper; b) amplifying the measured signal and filtering out noise; c) isolating the natural response of the blade corresponding to the drag movement of the blade from the forced response imposed by a rotor driving the blades; and d) analyzing in real time the natural response and adjusting the damping as a function of the analysis.

Abstract: The present invention relates to a method of adjusting at least one defective, main or anti-torque rotor of a particular rotorcraft. The method uses a neural network representing the relationships between firstly accelerations representative of vibration generated on at least a portion of a reference rotorcraft, and secondly defects and adjustment parameters. After determining the defects, if any, of a defective rotor, an adjustment value ? is defined for at least one of the adjustment parameters, advantageously by minimizing the following relationship: ? c ? ? ? c ? ? a ? ? ? a ? ? ? ( ? h = 1 B - 2 ? ? ( ? h ? ? R c , a , h ? ( ? ) + ? c , a , h ? 2 ) + ? ? B - 1 ( ? R c , a , B - 1 ? ( ? ) + ? c , a , B - 1 ? 2 ? ? c , a , B ? ) 2 ) .

Abstract: The system for stretch-forming composite material bands (3) includes, in addition to an unrolling head (20), an original assembly composed of a light source (4) for heating the band (3) and hardening the composite and a pair of rollers (6a and 6b) applying the desired pressure to assemble the band to a laminated composite (2) already deposited or applying it to the support (1). As the application of heat is concentrated at a distance from the rollers (6a and 6b) and with a perpendicular incidence, the rollers can be conveniently made of an elastic material, which enables them to adapt to the transverse curvature of the support equipment (1) and to apply a uniform pressure.

Abstract: A device for aiding the location of a failure within a complex system may include a database that stores diagnostic aid rules; a detector that detects a failure, if any, of the complex system and provides, upon a failure, information relating to the origin of this failure; and a central unit that determines, for any failure detected, on the basis of the diagnostic aid rules and the failure origination information, the element or elements of the complex system that may have caused the failure. Additionally, the central unit determines the corresponding probability that each element caused the failure for presentation to a user.

Abstract: An antivibration device for reducing the vibration of a structure, includes a stationary casing, mounted on the structure, and first and second sets each including two contra-rotary rotors having eccentric flyweights, the flyweights and the rotors being disposed respectively in first and second mutually parallel planes, the centers of rotation of the contra-rotary rotors representing the corners of a rectangular parallelogram in the second plane, and the axes of rotation of the contra-rotary rotors being mutually parallel and orthogonal to the first plane. In addition, it includes a stationary main motor secured to the casing with a through shaft having a first end driving the contra-rotary rotors of the first set and a second end driving the contra-rotary rotors of the second set.

Abstract: A safe interactive navigation apparatus and method allows the crew of an aircraft to prepare and follow a safe flight plan without relying on instrument flying infrastructure. An aircraft navigation assistance method calculates a continuous, three-dimensional projected path on board the aircraft as a function of data related to the route and characteristics of the aircraft.

Abstract: A method of diagnosing an aircraft by analyzing at least one spectrum obtained from measurements taken on the aircraft, in particular from vibration measurements, in which the spectrum (spectra) to be analyzed is/are input to a calculation module (23) together with at least one first reference spectrum, the calculation module determining a diagnosis value (Diag) as a function of the spectrum (spectra) to be analyzed, of the reference spectrum (spectra), and of parameters determined from at least two reference spectra including the first reference spectrum.

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 warning system energy supply device, which is independent of the electrical energy supply network.

Abstract: A rotary wing blade of limited taper ratio, comprising in succession along a reference radius: an inner zone; a forward-swept zone; and a back-swept zone. In addition, the beginning of the forward-swept zone lies in the range 0.47 to 0.65 times the reference radius R of the rotary wing. Furthermore, the leading edge of the blade at the reference radius presents an angle ? lying in the range ?40° and ?65° relative to the general axis of the blade.

Abstract: A device (20) for interconnecting electrical bundles, includes a plurality of pluggable connection and cross-connect cards (34 to 38) for the electrical bundles. The device further includes a “main” printed circuit (28, 28b) fitted with connectors or slots (29 to 33) designed and arranged to receive the pluggable cards, the printed circuit having a plurality of parallel tracks (46), each enabling two tracks (61 to 63, 68) or tracks starters (70 to 72) provided respectively on two distinct pluggable cards plugged in the connectors of the main printed circuit to be put to the same potential, each of the parallel tracks (46) being in contact with a respective pin (50, 150) of a plurality of connectors of the main printed circuit.

Abstract: A device for indicating a beat level L, the device including an analyzer which responds to a reference frequency ? and a harmonic coefficient B to extract from an evaluation signal E a first acceleration signal ?B at a frequency equal to the product of reference frequency ? multiplied by harmonic coefficient B; and a second acceleration signal ?B-1 at a frequency equal to the product of reference frequency ? multiplied by the harmonic coefficient minus one; and it further includes a control circuit CC which receives acceleration signal ?B, ?B-1 to produce beat level L.

Abstract: A method and a device for obtaining the three components (u,v,w) of the air speed (TA) of an aircraft along its flight path, the device including an arm (2) provided with two pressure probes disposed at each of its ends, each probe having two pressure intakes.

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: The invention relates to a device for treating noise in the cabin (20) of an aircraft, the device comprising: a plurality of microphones (22 to 24) fastened to respective seats (35) of the cabin; a plurality of loudspeakers (26, 27); at least one treatment unit (28) arranged to receive noise measurement signals delivered by the microphones, and to deliver control signals to the loudspeakers for the purpose of attenuating the noise in the cabin, the treatment unit comprising a plurality of treatment modules associated with respective ones of the microphones and/or of the loudspeakers; and at least one acoustic resonator (29 to 32) including a vent (29 to 31) coupled to a cavity (32) and connecting a loudspeaker to the cabin; the acoustic resonator including a vent (29 to 31) coupled to a cavity (32), the loudspeaker and its associated resonator presenting a frequency (33 or 34) of maximum sound level (50, 500) that is less than 1000 Hz.

Abstract: A method of detecting the presence of a suspended filamentary object in view of a telemeter on an aircraft includes: i) calculating terrestrial coordinates of points corresponding to telemeter echoes, and selecting candidates; ii) searching a horizontal plane for straight line segments close to vertical projections of candidate points; and iii) searching each vertical plane containing one of the straight line segments for portions of catenaries close to candidate points. In step iii), for each considered vertical plane and each triplet of candidate points close to the considered vertical plane, calculating values of three parameters of a catenary containing the projections on the vertical plane of the three points of the considered triplet, and determining presence of at least one suspended filamentary object as a function of the distribution of values of catenary parameters calculated for all of the triplets of candidate points close to the vertical plane under consideration.

Abstract: A device (1) for fastening elongate elements (2) such as cables or bundles of cables or the like to a structure (S) includes at least a first flexible self-gripping strip (3) having a loop-closure system on a first face (30) and a second flexible selfgripping strip (4) with a hookclosure system on a first face (40) The first and second flexible strips (3 and 4) adhere at least in par.t one against the other via their second faces (35 and 45) that are self-adhesive, so as to form a flexible collar (C) by uniting at least their facing free end zones (51 and 52) The device further includes a rigid plate (10) for constituting a support for fastening the device (1) to the structure (S).

Abstract: A heater and/or demister device D for installing in a heater and/or demister circuit of a vehicle. The device D is provided with a fan 7 for producing a flow of warm air from a flow of ambient air and a flow of compressed hot air taken from an engine of the vehicle. The device comprises a cylindrical outer body 9 surrounding the fan 7 and an impeller 3, the impeller 3 being fed with the flow of compressed hot air and driving the fan 7.