Abstract: A method and a device (1) for bonding a metal fairing (6) to protect a leading edge of an aircraft airfoil (7), the metal fairing (6) is designed to be bonded against the airfoil (7) with the help of an adhesive (9). The bonding device (1) is remarkable in that it includes a rigid yoke (2) having inserted therein induction heater elements (30) for heating the metal fairing (6).

Abstract: An emergency opening system (1) of an aircraft cabin door (3) mounted in an aircraft fuselage structure (4) by means of a hinge arm (2). An actuator (7), designed to assist the opening of the aircraft cabin door (3) against the force of gravity by means of a gas operated actuating rod (8) is mounted with its fix end (9) to said hinge arm (2) and said actuating rod (8) is connected to an actuator joint (10). A fork lever (24) is linked to said actuator joint (10). A bell crank (13) is respectively pivotable mounted to said hinge arm (2) and to said actuator joint (10) for the fork lever (24). At least one coupling lever (12) is pivotable joint to said fork lever (24) at at least one coupling joint (14). Said at least one coupling lever (12) is mounted in at least one hinge (18) of the hinge arm (2) by means of a respective bolt (26), said bolt (26) being drivingly connected to said aircraft cabin door (3) for rotation of said aircraft cabin door (3).

Abstract: A method of generating a terrain avoidance warning for a rotary wing aircraft including generating an avoidance trajectory including a proximal segment representative of a transfer time and an avoidance curve including at least one distal segment of a conic section curve following on from the proximal segment, wherein the proximal segment extends in continuation from a predicted trajectory over a distance representing an applicable reaction time, the applicable reaction time being minimized as a function of a route sheet for the aircraft, and wherein the generating includes calculating the at least one distal segment as a function of an instantaneous maneuverability of the aircraft.

Abstract: A helicopter with a fuselage and a skid-type landing gear mounted to said fuselage. Said landing gear comprises pivotable cross beams and skids, said skids being each disposed in an essentially longitudinal direction laterally on a respective side of the helicopter's landing gear. At least one discrete damper is provided for at least one pivotable cross beam, said discrete damper being connected with one end to the pivotable cross beam and with another end to the fuselage. The pivotable cross beam are of the cantilever type. Fixed bearings and floating bearings are provided at the fuselage. Torsion bar springs are mounted to said fixed bearings and said floating bearings, said respective inner end of at least one pivotable cantilever cross beam being attached to said torsion bar spring at the floating bearing in such a manner that moments are transferred from the respective inner end of each pivotable cantilever cross beam via said torsion bar spring to the fuselage at said fixed bearing.

Abstract: A control method for controlling an overspeed safety system (5) of an aircraft (1) having at least a first engine (10) and a second engine (20), during which method an engine is shut down when a monitoring parameter of that engine exceeds a first threshold, and another engine distinct from this engine is shut down when the monitoring parameter for said other engine exceeds a second threshold, said second threshold being greater than said first threshold.

Abstract: A method of determining an angular velocity of an aircraft includes measuring the angular velocity using at least one gyro delivering a measured angular velocity signal affected by stochastic noise; measuring the angular acceleration of the aircraft using at least one accelerometer delivering a signal representing the angular acceleration of the aircraft; and using a filtering complementary in a frequency domain to combine a sum of the measured angular velocity signal and the angular acceleration signal so as to obtain a hybrid estimated angular velocity signal with reduced stochastic noise.

Abstract: The present invention relates to an aircraft (1) comprising an airframe (2) provided with a fuselage (10) and fixed wings (20), a rotary wing (30), at least two propellers (41, 42), and a power plant suitable for driving said rotary wing (30) and said propellers (41, 42) into rotation.

Abstract: The present invention relates to a rotorcraft rotor (1) having a plurality of blades (3) movably mounted on a hub (2) via blade roots (4) that are respectively associated therewith. The rotor (1) is fitted with an information capture appliance having at least one measurement assembly (E1) comprising a flexible bar (11) interposed in engagement at its respective ends between the hub (2) and a blade root (4) that is allocated thereto. A strain gauge (7, 8) formed of a SAW transducer is implanted on the bar (11) and generates information relative to the bending of the bar (11) following tilting orientations of the blade root (4) in flapping (B) and/or in lag (T).

Abstract: A crashworthy bench (1) for an aircraft having a cabin that includes a floor (51), a ceiling (52), and substantially vertical partitions. Said bench (1) comprises a frame (2), at least one seat for a passenger, with each seat comprising a seat, a back, a retaining system (7) for retaining said passenger, and at least one energy absorber device (20). Said frame (2) is fastened to the inside of said cabin via one low connection point (8) for each seat and via at least one high connection point (9) for said bench (1). Two low connecting rods (11) and one leg (12) connect the frame (2) to each low connection point (8) on said floor (51). Two high connecting rods (15) connect the frame (2) to the high connection points (9) on said ceiling (52) or on a vertical partition of the cabin of the aircraft.

Abstract: A coupling means (10) extending along a longitudinal axis of symmetry (100) from a first plate (11) towards a second plate (12), which plates are connected together by a link member (20). Said link member (20) is provided with a first hub (21) secured to said first plate (11) and with a second hub (22) secured to said second plate (12), a first end section (21?) of the first hub (21) being connected to a second end section (22?) of the second hub (22) by link means (30), said link means (30) comprising a first web (31) connecting said first end section (21?) to a maximum section (33) of said link means (30), said link means (30) having a second web (32) connecting a second end section (22?) of said second hub (22) to said maximum section (33).

Abstract: A method of minimizing the consequences for the occupants of a rotary wing aircraft (1, 10) of an off-specification landing with forward and/or downward acceleration vectors. The aircraft (1, 10) extends along an anteroposterior longitudinal plane of symmetry (4) in elevation separating a first side (5) of said aircraft (1) from a second side (6) thereof. Said rotary wing (10) comprises at least one rotor (11) driven in rotation by a main gearbox (20) and being provided with a plurality of blades (12). Said main gearbox (20) being fastened to a structure (30) of said aircraft (1) by a plurality of fastener elements (40) comprising at least one first fastener element (51, 52) disposed on said first side (5) and at least one second fastener element (61, 62) disposed on said second side (6).

Abstract: A method of detecting at least one suspended threadlike object by telemetry, the object lying in the detection field of a telemeter on board a vehicle. The method wherein in step iii), for each vertical plane taken into consideration, and for each set of at least four candidate points close to the vertical plane in question, using the least squares method to calculate the values of three parameters a, b, and c of a catenary having an equation of the form: y=a cos h[(x?b)/a]+c the catenary containing the projections on the vertical plane of the points in the set under consideration; and determining that at least one suspended threadlike object is present as a function of the value of the correlation coefficient associated with said least squares method for all of the sets of at least four candidate points close to the vertical plane under consideration.

Abstract: A device (10) for reducing vibration of a main rotor (1) having a support (20) and a plurality of heavy elements (30) and of rollers (50). Each heavy element (30) includes two first openings (31) respectively at least partially in registration with two second openings (22) of the support (20. Each roller (50) passes through a first opening (31) and a second opening (22). The device (10) has link means (60) for connecting the support (20) to the hub (2). A drive shaft (70) and a drive means (80) rotate at a first speed of rotation (V1) greater than a second speed of rotation (V2) of the hub (2). The drive shaft (70) rotates about an axis of rotation (AX1) of the support (20). The link means (60) is connected to the support (20) by a link member (90) enabling the support (20) to rotate about the axis of rotation (AX1) relative to the link means (60).

Abstract: A device for fastening a nut (4) on the surface of a body (2) by means of a plate (5) that holds the nut (4) captive. The plate (5) has both a centering member (14) and a lug (15) projecting from its seat (6) against the body (2), which centering member and lug are housed in corresponding orifices (16, 17) in the body (2). Means for bonding by cementing or by riveting prevent the plate (5) fitted against the body (2) from moving axially. The cementing means involve melting the lug (15) inside the orifice (17) that receives it, the lug being heating to form cementing material. The plate (5) includes a cell (19) in register with the lug (15) for guiding tooling.

Abstract: An architecture for feeding fuel to a power plant (1) of a rotorcraft, which power plant comprises a plurality of engines (2, 3) individually fed with fuel by respective assemblies (4, 5). Each assembly (4, 5) comprises a fuel feed circuit (9, 10) for feeding a safe tank (6, 7) from a fuel tank (8) that is common to the assemblies (4, 5). Together the feed circuits (9, 10) form a circuit for forced both-way transfer of fuel from either one of the assemblies to the other via the common tank (8) and an intercommunication (21) interposed between the safe tanks (6, 7), which safe tanks are fitted with respective spillage devices (17, 18, 19, 20) for transferring excess fuel to the common tank (8).

Abstract: A method of providing a volume-mass law for determination of a fuel flow rate of an engine, particularly providing a fuel flow rate to a helicopter turbine, comprising the steps of: determining a sample type of fuel and a start density ?0 of said sample type of fuel in said fuel tank using an equation ?0=aT+b0, with a and b0 being known for said sample type of fuel and calculating real time offset parameters bn from an algorithm to determine real time densities ? of the fuel.

Abstract: The invention relates to a force generator (10a) for mounting on a structure (12) in order to introduce vibrational forces in a controlled manner into said structure for affecting vibrations, comprising at least one spring arm (14) on which a flexural arm (22) having an inertial mass (24) and extending in the direction toward the attaching point is fastened, and having at least one piezo transducer (26) at both ends (16, 18) of the spring arm (14), wherein the center of gravity of the inertial mass (24) is disposed in the region of the center of the spring arm (14). Alternatively, two guide springs are disposed on both sides of the spring arm (14) parallel thereto, in order to generate a vibrational motion, wherein the fastening point of the flexural arm (22) comprises an unchanged orientation during the vibrational motion.

Abstract: The invention relates to a drainage circuit (4) for a flow of a liquid (5), the circuit being fitted with a monitoring appliance (13) for monitoring an excess flow rate of the liquid (5). The monitoring appliance (13) comprises a monitoring duct (14) interposed between an upstream duct (7) for collecting the liquid (5) and a downstream duct (9) for discharging the liquid (5). The monitoring duct (14) has retaining means (15) for retaining part of the liquid (5) inside a chamber (16) arranged to receive a spillway (22) of the captured liquid (19) in a reserve (20) fitted with indicator means (23) with a visual scale for providing warning information relating to the quantity of liquid (24) contained in the reserve (20).

Abstract: A method of failure simulation for an aircraft (7) having a power plant (10) with at least two turbine engines (11, 12), together the two engines develop an overall power, each engine (11, 12) being capable of delivering at least one contingency power in order to compensate for a total failure of other engines (11, 12). The device serves during a failure simulation to modify the overall power delivered by the power plant, with this modification being performed with the help of first adjustment means (20). Second adjustment means (30) serve to modify also the difference between the minimum power obtained during the simulated failure and the stabilized overall power, and also the time between said failure stabilizing on said overall power.

Abstract: A method of performing a health check of at least one turbine engine (3). During a development step (STP0), the installation losses (1) are quantified for a plurality of test values for a reduced speed of rotation (Ng?) of a gas generator (4) of the engine. During an acquisition step (STP1), the speed of rotation of said gas generator (4) is increased until said engine develops a maximum power, and then the speed of rotation of the gas generator (4) is decreased until the reduced speed of rotation (Ng?) reaches a test value. The aircraft is stabilized and at least one monitoring value is acquired. During an evaluation step (STP2) of evaluating the health check, at least one operating margin is determined by using a monitoring value and the effects of mounting the engine in an airplane.