A structure (10) for aircrafts, includes a part (20) including a metal leading edge (30), the leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometers and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, the coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, the layers having a thickness essentially equal to a micrometer. An aircraft including such a structure is also described.
C23C 14/06 - Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
C23C 14/16 - Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
C23C 28/02 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of metallic material
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCE (France)
EUROCOPTER (France)
Inventor
Ropars, Ludovic
Gourdet, Sophie
Lecuru, Daniel
Abstract
The invention relates to a mechanical assembly having improved behavior with respect to fatigue combined with wear due to micro-movements, wherein said assembly comprises at least two parts that are attached to one another. At least one of the at least two parts is made of a material comprising a titanium or titanium-alloy matrix and comprising titanium-carbide or titanium-boride ceramic particles which are substantially homogeneously dispersed within the matrix, wherein the particles have a minimum size of at least 0.05 μm and a maximum size not exceeding 30 μm in the area subjected to the effects of fatigue-fretting. The mass proportion of the ceramic particles in the part is preferably of 5 to 40%.
C22C 32/00 - Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
The invention relates to a structure (10) for aircrafts, characterised in that it comprises a part (20) comprising a metal leading edge (30), said leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometres and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, said coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, said layers having a thickness essentially equal to a micrometre. The invention also relates to an aircraft comprising such a structure.
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
C23C 28/02 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of metallic material
4.
Device for monitoring the integrity and soundness of a mechanical structure, and method for operating such a device
The invention relates to a device for monitoring the integrity and soundness of a mechanical structure, such as an aircraft. The device comprises a control unit, a radio frequency transmission means, and an electric battery. The control unit recovers data from a set of digital and/or analog sensors. The radio frequency transmission means enables the control unit to transmit the data received from the sensors to a man/machine interface. The electric battery powers the device and is rechargeable. The device further comprises a module for recovering electromagnetic energy capable of converting the recovered electromagnetic energy into electric power so as to recharge the battery and/or directly power the device.
G08B 21/00 - Alarms responsive to a single specified undesired or abnormal condition and not otherwise provided for
G08G 1/123 - Traffic control systems for road vehicles indicating the position of vehicles, e.g. scheduled vehicles
G08C 19/38 - Electric signal transmission systems using dynamo-electric devices
G08C 19/12 - Electric signal transmission systems in which the signal transmitted is frequency or phase of AC
G01N 19/10 - Measuring moisture content, e.g. by measuring change in length of hygroscopic filamentHygrometers
G01P 15/00 - Measuring accelerationMeasuring decelerationMeasuring shock, i.e. sudden change of acceleration
G01N 29/00 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
G01L 7/00 - Measuring the steady or quasi-steady pressure of a fluid or a fluent solid material by mechanical or fluid pressure-sensitive elements
G06F 15/02 - Digital computers in generalData processing equipment in general manually operated with input through keyboard and computation using a built-in program, e.g. pocket calculators
G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
G07C 5/00 - Registering or indicating the working of vehicles
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
G01N 37/00 - Details not covered by any other group of this subclass
5.
AIRCRAFT PROPULSION ARCHITECTURE INTEGRATING AN ENERGY RECOVERY SYSTEM
EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCE (France)
EUROCOPTER (France)
Inventor
Rechain, Bruno
Smaoui, Hichem
Joubert, Emmanuel
Bezes, Gilles
Sautreuil, Matthieu
Abstract
The object of the invention is a drive system of at least one rotor of an aircraft via electrical energy in addition to or as a replacement of a mechanical system, characterised in that the electrical energy is provided at least in part by at least one device (104) for recovering thermal energy from hot gases of an internal combustion engine (1) of the aircraft.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
B64C 27/82 - RotorcraftRotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
6.
DEVICE FOR MONITORING THE INTEGRITY AND SOUNDNESS OF A MECHANICAL STRUCTURE, AND METHOD FOR OPERATING SUCH A DEVICE
EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCE (France)
EUROCOPTER (France)
Inventor
Foucher, Bruno
Rouet, Vincent
Reynet, Rémy
Abstract
The invention relates to a device for monitoring the integrity and soundness of a mechanical structure, such as an aircraft, comprising a control unit (100) suitable for recovering data from a set of digital and/or analog sensors (110), a radiofrequency transmission means (120) enabling the control unit (100) to transmit the data received from the sensors to a man/machine interface, an electric battery (130) for powering said device, wherein said battery (130) is rechargeable, characterised in that the device comprises a module for recovering electromagnetic energy capable of converting the recovered electromagnetic energy into electric power so as to recharge said battery and/or directly power said device.
G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
The invention relates to a control system and to a method of operating such a control system, particularly to a control system for pilot command inputs for a helicopter, with a mechanical input signal (2), at least one electric position sensor (21, 21′) for said input signal (2), at least one electric power supply (25, 25′) and at least one controllable, electromechanical actuator (27, 27′) fed by the at least one electric power supply (25, 25′) and controlled by the at least one electric position sensor (21, 21′). The mechanical input signal (2) is applied mechanically to the at least one controllable electromechanical actuator (27, 27′).
The invention relates to the formulation of alerts for terrain avoidance by a rotary-wing aircraft (1), which provides for the formulation of an avoidance trajectory (TA) with a proximal section and an avoidance curve (CE). The proximal section (25) is determined as a function of a route sheet for the aircraft (1), and the avoidance curve (CE) forms a conical curve distal section (24) calculated as a function of the instantaneous manoeuvrability of the aircraft (1).
The present invention relates to a method for manufacturing a substrate (30) painted using a powder paint (21), said substrate being electrically insulated, during which the following steps are sequentially carried out: a) a treatment coating (10) is placed on a mold (1), said treatment coating (10) comprising at least one preparation layer (11, 12) made of a demolding agent (15, 15') contacting said mold (1); b) said treatment coating (10) is electrostatically coated with powder paint (21) such that said powder paint (21) is attracted to said mold (1) and maintained against the treatment coating (10); c) said powder paint (21) is at least partially transformed to obtain a powder paint (21) film (20); d) said substrate (30) is prepared on said film (20) to obtain said painted substrate.
The present invention relates to a method for manufacturing a substrate (30) painted using a powder paint (21) said substrate being electrically insulated, during which the following steps are sequentially carried out: a) a treatment coating (10) is placed on a mold (1), said treatment coating (10) comprising at least one preparation layer (11, 12) made of a demolding agent (15, 15') contacting said mold (1); b) said treatment coating (10) is electrostatically coated with powder paint (21) such that said powder paint (21) is attracted to said mold (1) and maintained against the treatment coating (10); c) said powder paint (21) is at least partially transformed to obtain a powder paint (21) film (20); d) said substrate (30) is prepared on said film (20) to obtain said painted substrate.
The invention relates to a method and a device for obtaining the predictive vertical speed of a rotorcraft, wherein said device includes a predictive vertical speed indicator (1) that comprises at least: a first means (V) for measuring the instantaneous vertical speed v of a rotorcraft; a second means (2) for measuring the instantaneous true speed (VP) of a rotorcraft; a third means (3) for calculating the predictive vertical speed (vAp) of a rotorcraft, wherein said third means is connected to the first and second means respectively by first (l1) and second (l2) links, and contains in a memory the predetermined values of the minimal power speed (Vy) and a characteristic coefficient (k) which are constants concerning said rotorcraft, for a given type of rotorcraft.
G01P 3/62 - Devices characterised by the determination of the variation of atmospheric pressure with height to measure the vertical components of speed
G01P 5/14 - Measuring speed of fluids, e.g. of air streamMeasuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
12.
METHOD AND DEVICE FOR DETECTING AND SIGNALLING THE APPROACH OF A ROTORCRAFT TO A VORTEX DOMAIN
The invention relates to a method and a device (D) for detecting and signalling the approach of a rotorcraft to a vortex domain, wherein said device comprises: a first means (1) for measuring the instantaneous vertical speed v of a rotorcraft; a second means (2) for measuring the instantaneous true speed VP of a rotorcraft; a third means (3) defining a database BDD concerning the representation of at least one instantaneous vortex domain; a fourth means (4) connected by first (l1), second (l2) and third (l3) links respectively to the first, second and third means, said fourth means being capable of detecting the approach of a rotorcraft to a vortex domain; and a fifth means (5) for signalling the approach of a rotorcraft to a vortex domain, connected to the fourth means (4) by a link (14).
The invention relates to a method for determining the angular speed of an aircraft, that comprises: measuring the angular speed using rate gyros providing measured angular speed signals ￆm; measuring the angular acceleration of the aircraft using accelerometers providing angular acceleration signals ￆm for the aircraft; and combining by additional filtration in the frequency domain the measured angular speed signals and the measured angular acceleration signals for obtaining hybrid angular speed signals ￆ.
G01C 21/16 - NavigationNavigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigatedDead reckoning by integrating acceleration or speed, i.e. inertial navigation
G01P 15/08 - Measuring accelerationMeasuring decelerationMeasuring shock, i.e. sudden change of acceleration by making use of inertia forces with conversion into electric or magnetic values
G01P 15/18 - Measuring accelerationMeasuring decelerationMeasuring shock, i.e. sudden change of acceleration in two or more dimensions
14.
TRANSMISSION SHAFT ATTACHMENT TOOLING AND BALANCING STAND COMPRISING SUCH TOOLING
The present invention relates to tooling (101, 102) for attaching a transmission shaft (1) positioned at a free end (2, 3) of said transmission shaft (1), and to the balancing stand (B) comprising said attachment tooling (101, 102). This attachment tooling is equipped with a means (110, 110') of centring the transmission shaft (1), which means can be deformed under centrifugal force so as to come into contact with said transmission shaft once said attachment tooling (101, 102) has achieved a determined rotational speed about the axis of rotation (AX) thereof.
The invention relates to a hybrid helicopter (1) including, on the one hand, an airframe with a fuselage (2) and a lift surface (3) as well as stabilising surfaces (30, 35, 40) and, on the other hand, a kinematic chain including: a mechanical interconnection system (15) between, on the one hand, a rotor (10) having a radius (R) with collective and cyclic pitch control of the blades (11) of said rotor (10) and, on the other hand, at least one propeller (6) with collective pitch control of the blades of said propeller, and at least one turboshaft engine (5) for driving the interconnection mechanical system (15). The invention is characterised in that the rotation speed (Ω) of the rotor (10) is equal to a first rotation speed (Ω1) up to a first air speed on the path (V1) of said hybrid helicopter (1), and is progressively reduced according to a linear rule based on the air speed on the path of said hybrid helicopter (1).
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
16.
LONG RANGE FAST HYBRID HELICOPTER WITH LONGITUDINAL ATTITUDE CONTROL
The invention relates to a hybrid helicopter (1) comprising on the one hand an airframe with a fuselage (2) and a lift surface (3) as well as stabilising surfaces (30, 35, 40) and, on the other hand, a kinematic chain including: a mechanical interconnection system (15) between, on the one hand, a rotor (10) having a radius (R) with a control of the collective pitch and cyclic pitch of the blades (11) of said rotor (10) and, on the other hand, at least one propeller (6) with a control of the collective pitch and cyclic pitch of the blades of said propeller (6), and at least one turboshaft engine (5) driving the mechanical interconnection system (15). The invention is characterised in that the hybrid helicopter (1) includes a first means (60, 70, 71) for controlling the rotation angle of at least one of said elevators (35) based on the flexion momentum applied on the rotor mast (12) relative to the pitch axis of said hybrid helicopter (1), and a second means (13, 14, 16, 17) for controlling the cyclic pitch of the blades (11) of the rotor (10) in order to control the longitudinal attitude of the hybrid helicopter (1) based on the flight conditions.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/82 - RotorcraftRotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
The invention relates to a hybrid helicopter (1) comprising on the one hand an airframe with a fuselage (2) and a lift surface (3) as well as stabilising surfaces (30, 35, 40) and, on the other hand, a kinematic chain including: a mechanical interconnection system (15) between, on the one hand, a rotor (10) having a radius (R) with a control of the collective pitch and cyclic pitch of the blades (11) of said rotor and, on the other hand, at least one propeller (6) with a control of the collective pitch and cyclic pitch of the blades of said propeller (6), and at least one turboshaft engine (5) driving the mechanical interconnection system (15). The invention is characterised in that the output rotation speeds of at least one of said turboshaft engines (5), of at least one of said propellers (6) of said rotor (10) and of said mechanical interconnection system (15) are proportional between them, the proportionality ratio being constant.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
The invention relates to a control system (100) for a rotorcraft (1) comprising a rotor (10), at least one variable-pitch propulsive propeller (6L, 6R), and one engine for driving the rotor and the propeller(s), characterised in that it comprises: a member (101, 101 A, 102, 103, 104) for developing a setpoint (ϑp* + ϑd*, ϑp* - ϑd*) of the propeller pitch based on a thrust variation control instruction TCL); a member (105, 105A) for developing a setpoint (RPM*) of the driving speed (RPM) of the rotor and the propeller(s) based particularly on the rotorcraft movement speed (VTAS); and a member (106) for developing a setpoint (NG*) of the engine speed based particularly on the thrust control instruction (TCL), the driving speed setpoint (RPM*) and a control instruction (ϑo) of the rotor collective pitch.
The present invention relates to an anti-slosh device (D) of a flexible tank (21), provided with an upper cushion (22) as well as a lower base (23) and a plurality of sides (24), comprises at least one first (1) and one second (2) attachments. Said first (1) and second (2) attachments are respectively attached on a first (221) and second (222) edge of the cushion, the first edge (221) being opposite the second edge (222). Said device is remarkable in that it comprises a main distributor means (10) for blocking only one of the attachments when the tension exerted on said attachment is greater than the tension exerted on the other attachment, the first (1) and second (2) attachments also being attached to the main distributor means (10).
The invention relates to a method of positioning an aircraft by combining data regarding distances separating the aircraft from satellites and inertial data, in which: a) the distance data are recorded in a FIFO memory so that delayed distance data are available as output from the memory, b) the delayed distance data are combined with the inertial data to obtain an estimate of position data of the aircraft, c) the appearance of a fault in the distance data is monitored and when such a fault is detected, at least part of the data recorded in the FIFO memory is modified so as to neutralize them.
G01C 21/00 - NavigationNavigational instruments not provided for in groups
G01S 5/14 - Determining absolute distances from a plurality of spaced points of known location
G01C 21/16 - NavigationNavigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigatedDead reckoning by integrating acceleration or speed, i.e. inertial navigation
21.
AIRLIFTABLE TANK FOR STORING A PRODUCT THAT IS TO BE JETTISONED DURING FLIGHT
The invention relates to an airliftable tank (20) for storing a product that is to be jettisoned during flight, which comprises a neck (23) ending in a product-discharge opening (24) and in which the wall (21) extending the neck is deformable enough to be partially or completely housed inside the neck.
The invention concerns a method for detecting a wire-like object suspended in a field of view of a telemeter on board an aircraft which consists in: i) calculating the ground coordinates of points corresponding to echoes delivered by the telemeter, and in selecting candidate points among said points; ii) searching in a horizontal plane for line segments to which the vertical projections of the candidate points are proximate; iii) searching in each vertical plane containing one of the line segments found in step ii), catenary portions to which the candidate points are proximate; calculating at step iii) for each vertical plane considered, for each triplet of candidate points proximate the vertical plan concerned, the value of three parameters of a catenary containing the projections on the vertical plane of the three points of the triplet concerned, then determining the presence of at least one suspended wire-like object based on the distribution of the values of the catenary parameters calculated for all the triplets of candidate points proximate the vertical plane concerned.
patents
