Abrégé

The invention relates to a system (10) for detecting the presence of and analysing particles in a lubricant flow, comprising a housing (1) having a channel (4) which conveys a lubricant flow and fluidically connects a lubricant inlet (2) and a lubricant outlet (3), further comprising a particle sensor (5), which is designed to identify and analyse particles located in the lubricant flow, and a chip warning transmitter (6), which is arranged downstream of the particle sensor (5) and is designed to locate and magnetically hold magnetisable particles located in the lubricant flow. The invention also relates to a method for detecting the presence of and analysing particles in a lubricant flow. The invention further relates to a transmission (7) comprising a system (10) of this kind.

Classes IPC  ?

• G01N 33/28 - Huiles
• G01N 15/06 - Recherche de la concentration des suspensions de particules

Abrégé

The invention relates to a drive train for a floating aircraft (100) comprising at least one drive unit (1.1, 1.2), at least one rotor shaft (2.1, 2.2) and a transmission (3) arranged in the power flow between the at least one drive unit (1.1, 1.2) and the at least one rotor shaft (2.1, 2.2), wherein the transmission (3) comprises at least one hollow shaft (4), wherein at least one supporting shaft (5) is arranged radially within the hollow shaft (4) and extends at least partially axially along an inner circumferential surface (6) of the hollow shaft (4), in order to substantially hold together fracture segments of the hollow shaft (4) in the event of a fracture of the hollow shaft (4). The invention also relates to a floating aircraft (100) comprising a drive train of this type.

Classes IPC  ?

• B64C 27/12 - Entraînements des rotors

Abrégé

The invention relates to a drive train for a floating aircraft (100), comprising at least one drive unit (1.1, 1.2), at least one rotor shaft (2.1, 2.2) and a transmission (3), arranged in the power flow between the at least one drive unit (1.1, 1.2) and the at least one rotor shaft (2.1, 2.2), wherein the transmission (3) has at least one planetary gear stage with a sun shaft (4), a hollow gear wheel shaft (5) and a planetary shaft (6), wherein at least one planetary gear wheel (7) is arranged on the planetary shaft (6) and is meshed with the sun shaft (4) and the hollow gear wheel shaft (5), wherein at least one first support ring (8.1) is arranged on an end side of the at least one planetary gear wheel (7) in such a way that the at least one support ring (8.1, 8.2) has substantially no contact with the at least one planetary gear wheel (7) in an intact state of the at least one planetary gear wheel (7), and, in the event of a fracture of the at least one planetary gear wheel (7), the at least one support ring (8.1) contacts fracture segments of the at least one planetary gear wheel (7) and holds them together substantially between the sun shaft (4) and the hollow gear wheel shaft (5). The invention also relates to a floating aircraft (100) comprising a drive train of this type.

Classes IPC  ?

• B64C 27/12 - Entraînements des rotors

Abrégé

The invention relates to a drive train for a floating aircraft (100) with a main rotor (101) and a rear rotor (102), comprising at least one drive unit (1.1, 1.2), a first rotor shaft (2.1) which is designed to be drivingly connected to the main rotor (101), and a second rotor shaft (2.2) that is designed to be drivingly connected to the rear rotor (102), as well as a main transmission (3) which is arranged in the power flow between the at least one drive unit (1.1, 1.2) and the two rotor shafts (2.1, 2.2), wherein at least one electric machine (4) is drivingly connected to a shaft (5) arranged in the power flow between the main transmission (3) and the second rotor shaft (2.2), wherein the electric machine (4) is designed to generate drive power for the second rotor shaft (2.2) in a motor operation, and to generate electrical energy for an electrical system of the aircraft (100) in a generator operation. The invention also relates to a method for operating a drive train of this type and to an aircraft (100) with a drive train of this type.

Classes IPC  ?

• B64C 27/12 - Entraînements des rotors
• B64D 27/33 - Aéronefs électriques hybrides
• B64C 27/82 - GiravionsRotors propres aux giravions caractérisés par l'existence d'un rotor auxiliaire ou d'un dispositif à jet fluide pour contrebalancer le couple du rotor de sustentation ou faire varier la direction du giravion

Abrégé

An aviation propulsion system for an aircraft with two engines, comprising respectively a connecting shaft which is rotatably drivable in rotation by one of the engines, wherein mutually facing ends of both connecting shafts are connected to each other or are connectable to each other in a rotatably drivable manner. Both connecting shafts are connected via their mutually facing ends in a rotatably drivable manner to one of the mutually facing ends of the connecting shafts via a openable coupling.

Classes IPC  ?

• B64D 35/00 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions
• F16D 9/06 - Accouplements avec organe de sécurité pour le désaccouplement par rupture due au cisaillement
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/038 - Boîtes de vitesses pour engrenages coniques

Abrégé

A method for monitoring a gearbox in an aircraft. The gearbox comprises at least one gearbox section with at least one measuring area. A first and a second electrical contact are arranged in the measuring area at a spacing from one another. A magnetic field is generated in the gearbox section. The magnetic field is adapted to move at least one ferromagnetic particle arranged in the gearbox section towards the measuring area, so that a bridge produced from one or more of the ferromagnetic particles is formed between the two electrical contacts. A measured value is generated based on an electrical parameter between the two electrical contacts. A measure of the criticality of a flight operation is determined on the basis of the measured value.

Classes IPC  ?

• F16H 57/01 - Surveillance de l'usure ou de la sollicitation des éléments de transmission, p. ex. pour déclencher les opérations de maintenance
• G01N 33/28 - Huiles

Abrégé

An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

Classes IPC  ?

• B64C 27/68 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales utilisant l'énergie électrique, p. ex. avec un amplificateur de puissance électrique
• B64C 27/04 - Hélicoptères

Abrégé

In one aspect, the present disclosure provides a system for reducing vibrations or stresses in a rotor blade system. The system may include at least three rotor blades configured to be rotated about a main rotor axis, where each of the three rotor blades may be adjusted by at least one electrically-adjustable control rod of a plurality of control rods. The plurality of control rods may include a first number of control rods forming a first group, and the plurality of control rods may include a second number of control rods forming a second group. A first circuit for may activate or deactivate the first group of control rods, and a second circuit may activate or deactivate the second group of control rods.

Classes IPC  ?

• B64C 27/00 - GiravionsRotors propres aux giravions
• B64C 27/605 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
• B64C 27/46 - Pales
• B64C 27/72 - Dispositifs d'action sur les pales

Abrégé

A torsional moment acting on a component in a drive train of an aircraft may be determined using at least one sensor, where the determined torsional moment is used for adjusting at least one adjustable damping element located in or on the component and/or for regulating a torsional stiffness in the torque-conducting component. As a result, the torsional load in the component may be reduced.

Classes IPC  ?

• F16F 15/00 - Suppression des vibrations dans les systèmesMoyens ou dispositions pour éviter ou réduire les forces de déséquilibre, p. ex. dues au mouvement
• B64D 31/00 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs
• F16F 15/10 - Suppression des vibrations dans les systèmes rotatifs par utilisation d'organes mobiles avec le système lui-même

Abrégé

A system for controlling an electromechanical actuator for setting a collective offset for a helicopter on a blade-specific basis, wherein the system comprises at least one actuator, the length and position of which can be adjusted electromechanically within a mechanically limited range, a power electronics that is configured to adjust the actuator by means of a servomotor in two directions, specifically toward a positive collective offset or toward a negative collective offset, and a first microelectronics system that is configured to control the power electronics such that positive and negative collective offsets can be set. The system also includes a second microelectronics system, which is configured to override the actuation of the first microelectronics system in order to act on the adjustment of the actuator, and by a first control line, which is configured to activate or deactivate the second microelectronics system through an external electrical signal.

Classes IPC  ?

• B64C 27/00 - GiravionsRotors propres aux giravions
• B64C 27/68 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales utilisant l'énergie électrique, p. ex. avec un amplificateur de puissance électrique
• B64C 27/72 - Dispositifs d'action sur les pales
• H02P 7/06 - Dispositions pour réguler ou commander la vitesse ou le couple de moteurs électriques à courant continu pour réguler ou commander individuellement un moteur dynamo-électrique à courant continu en faisant varier le champ ou le courant d'induit

Abrégé

A method for detecting damages to a rotor of an aircraft, where the aircraft comprises actuators for active vibration reduction, may comprising one or more of the following steps: determining actuator variables in a reference flight of the aircraft; plotting the actuator variables of respective data range tiles determined in the reference flight of the aircraft in first coordinates of a coordinate system, wherein the coordinate system contains numerous data range tiles; obtaining the number of actuator variables in the reference flight of the aircraft that are located in each data range tile; eliminating the data range tiles that have a number of actuator variables lying below a limit value for this in the reference flight of the aircraft, by means of which a reference flight signature is created; and determining actuator variables for a flight-specific signature.

Classes IPC  ?

• B64C 27/00 - GiravionsRotors propres aux giravions
• G01H 1/00 - Mesure des vibrations dans des solides en utilisant la conduction directe au détecteur

Abrégé

The invention relates to a belt drive assembly for a drive train of a helicopter, comprising a drive shaft that can be functionally connected to a crankshaft of a drive machine of the helicopter, wherein the drive shaft is functionally connected to a belt disk via a torsional vibration damper, wherein the belt disk can rotate via a bearing mechanism on a bearing shaft connected to the drive shaft for conjoint rotation therewith, wherein the belt disk can receive a belt that is functionally connected to a rotor system of the helicopter.

Classes IPC  ?

• B64C 27/12 - Entraînements des rotors
• F16H 55/36 - Poulies
• B64D 35/00 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions
• F16D 3/12 - Accouplements extensibles, c.-à-d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement adaptés à des fonctions particulières spécialement adaptés à un emmagasinage de l'énergie pour absorber les chocs ou vibrations
• F16H 7/02 - Transmissions pour transmettre un mouvement rotatif par des organes flexibles sans fin par courroiesTransmissions pour transmettre un mouvement rotatif par des organes flexibles sans fin par courroies trapézoïdales

Abrégé

An actuator for aviation may include an electromechanical drive unit connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

Classes IPC  ?

• F16H 1/32 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital dans lesquels l'axe central de la transmission est situé à l'intérieur de la périphérie d'un engrenage orbital
• B64C 27/68 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales utilisant l'énergie électrique, p. ex. avec un amplificateur de puissance électrique
• F16H 3/72 - Transmissions à engrenages pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser le mouvement rotatif utilisant des engrenages à mouvement orbital avec entraînement secondaire, p. ex. un moteur régulateur, pour faire varier la vitesse d'une manière continue
• B64C 13/28 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques
• B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
• B64C 13/42 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide comportant des dispositifs de doublement de la commande ou de mise en position de secours
• F16H 1/28 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital
• F16H 1/46 - Systèmes consistant en plusieurs trains d'engrenages, chacun comportant des engrenages orbitaux

Abrégé

A method for predicting vibrations in an aircraft comprising an active vibration reduction system includes estimating a first vibration amplitude or frequency resulting from adjustments by the active vibration reduction system and the respective sensitivities of the aircraft depending on the flying state using a statistical mathematical process, recording a second vibration amplitude or frequency by a sensor, generating a pseudo-vibration profile by combining the first and second vibration amplitudes or frequencies, comparing the pseudo-vibration profile with a predefined target vibration profile, and outputting a signal when a specific threshold value has been exceeded.

Classes IPC  ?

• B64C 27/00 - GiravionsRotors propres aux giravions
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
• G01H 1/00 - Mesure des vibrations dans des solides en utilisant la conduction directe au détecteur
• G05D 19/02 - Commande des oscillations mécaniques, p. ex. de l'amplitude, de la fréquence, de la phase caractérisée par l'utilisation de moyens électriques
• G01M 7/00 - Test de vibration des structures ou des ouvragesTest de résistance au choc des structures ou des ouvrages
• G01M 5/00 - Examen de l'élasticité des structures ou ouvrages, p. ex. fléchissement de ponts ou d'ailes d'avions

Abrégé

wherein the first control system (3) is configured to receive the first control variable via the signal-based coupling (12), to determine at least one first control value in the time domain by using the received control variable in the time domain and by using at least one first control algorithm, and to transmit this control value to the adjusting device (2) via the first signal-based coupling (11), wherein the adjusting device (2) is designed to receive this control value via the first signal-based coupling (11).

Classes IPC  ?

• B64C 27/32 - Rotors
• B64C 27/00 - GiravionsRotors propres aux giravions
• B64C 27/72 - Dispositifs d'action sur les pales
• H04B 1/3822 - Émetteurs-récepteurs, c.-à-d. dispositifs dans lesquels l'émetteur et le récepteur forment un ensemble structural et dans lesquels au moins une partie est utilisée pour des fonctions d'émission et de réception spécialement adaptés à l'utilisation dans des véhicules

Abrégé

The invention relates to a control rod for the adjusting of a helicopter rotor blade, wherein the control rod can be adjusted in longitudinal direction, comprising: at least one contact area element, at least one limit stop element, which is designed to limit the adjustability of the control rod in longitudinal direction to a specifiable adjusting range in interrelation with the at least one contact area element, wherein the limit stop element can be transferred from a first position to a second position, wherein the at least one stop element limits the adjustability of the control rod in the first position and enables the adjustability of the control rod beyond the specifiable adjusting range in the second position.

Classes IPC  ?

• F16C 7/06 - Bielles réglables
• B64C 27/68 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales utilisant l'énergie électrique, p. ex. avec un amplificateur de puissance électrique
• B64C 27/54 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p. ex. mouvement de traînée
• B64C 27/605 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
• G01D 5/04 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens mécaniques utilisant des leviersMoyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens mécaniques utilisant des camesMoyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens mécaniques utilisant des engrenages

Abrégé

The discovery concerns a rotor hub cover for a helicopter, whereby the rotor hub cover has been constructed as a rotational body with a dome-shaped cover and the rotor hub cover has performance and control electronic components, characterized by the arrangement of the performance electronic components and the control electronic components on a surface of the internal side or the dome-shaped cover.

Classes IPC  ?

• B64C 27/32 - Rotors
• B64C 11/44 - Mécanismes de changement de pas des pales électriques
• H05K 5/03 - Couvercles ou capots
• H05K 9/00 - Blindage d'appareils ou de composants contre les champs électriques ou magnétiques

Abrégé

In one aspect, the present disclosure provides a system for reducing vibrations or stresses in a rotor blade system. The system may include at least three rotor blades configured to be rotated about a main rotor axis, where each of the three rotor blades may be adjusted by at least one electrically-adjustable control rod of a plurality of control rods. The plurality of control rods may include a first number of control rods forming a first group, and the plurality of control rods may include a second number of control rods forming a second group. A first circuit for may activate or deactivate the first group of control rods, and a second circuit may activate or deactivate the second group of control rods.

Classes IPC  ?

• B64C 27/00 - GiravionsRotors propres aux giravions
• B64C 27/605 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
• B64C 27/46 - Pales
• B64C 27/72 - Dispositifs d'action sur les pales

Abrégé

An actuator for a rotor blade adjustment having an electromechanical drive unit may be connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

Classes IPC  ?

• B64C 27/68 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales utilisant l'énergie électrique, p. ex. avec un amplificateur de puissance électrique
• F16H 1/32 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital dans lesquels l'axe central de la transmission est situé à l'intérieur de la périphérie d'un engrenage orbital
• F16H 3/72 - Transmissions à engrenages pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser le mouvement rotatif utilisant des engrenages à mouvement orbital avec entraînement secondaire, p. ex. un moteur régulateur, pour faire varier la vitesse d'une manière continue
• B64C 13/42 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide comportant des dispositifs de doublement de la commande ou de mise en position de secours
• B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
• F16H 1/46 - Systèmes consistant en plusieurs trains d'engrenages, chacun comportant des engrenages orbitaux
• F16H 1/28 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital

Abrégé

The invention relates to an adjustment mechanism that includes a set ring gears which are arranged coaxially towards a central axis and which each include a cylindrical toothing system, two eccentric wheels with beveloid gears which mesh with the cylindrical toothing systems of the ring gears, eccentric axes which are inclined at an angle towards the central axis, and a central shaft that is driven by a drive shaft onto which the eccentric wheels are mounted. The set of ring gears include a center ring gear that is circulating and two outer neighboring ring gears which are solidly fixed.

Classes IPC  ?

• F16H 1/32 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital dans lesquels l'axe central de la transmission est situé à l'intérieur de la périphérie d'un engrenage orbital
• F16H 1/46 - Systèmes consistant en plusieurs trains d'engrenages, chacun comportant des engrenages orbitaux
• F16H 1/28 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital

Abrégé

A rotor blade control device for a helicopter, comprising a swash-ring, said swash-ring comprising a non-rotating component of the swash-ring, coupled in a non-rotatable manner to the helicopter, a rotating component of the swash-ring, at least three actuators disposed around a rotor shaft axis of the helicopter, a coupling means between the actuators and the non-rotating component of the swash-ring. The coupling means can be adjusted in terms of its pitch, for changing the position of a swash-ring coupling point on the non-rotating component of the swash-ring along the rotor shaft axis by the actuator, by means of a control shaft, in order to adjust the rotor blades. The coupling means has a pushing member, in addition to at least one lever non-rotatably connected to the control shaft, which is connected at a first end to the lever in a rotational joint, such that it can pivot about a pivotal axis, and is coupled at a second end to the non-rotating component of the swash-ring at a swash-ring coupling point, in a ball joint.

Classes IPC  ?

• B64C 27/605 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
• B64C 27/625 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant des masses en rotation ou des servo-rotors

Abrégé

The present disclosure provides a rotor blade control device for a helicopter. The rotor blade control device may include a swash plate disk with a non-rotating component coupled to the helicopter. At least three actuators may be arranged around a rotor shaft axis of the helicopter, and a coupling element may be located between each actuator and the non-rotating component. The coupling element can be adjusted to change the position of a crosspoint at the non-rotating component of the swash plate disk alongside the rotor shaft axis in order to adjust the rotor blades. The actuators may be arranged onto the non-rotating component and may be able to pivot around a respective swivel axis. A radial distance of the first crosspoint to the rotor shaft axis may change with the swivel movement of an actuator around the swivel axis.

Classes IPC  ?

• B64C 11/06 - Montage des pales dans le cas de pales à pas variable
• B64C 27/04 - Hélicoptères
• B64C 27/605 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came

Abrégé

A control rod configuration for adjusting a position of a rotor blade of a helicopter. The control rod configuration includes a control rod which has a bearing eye, adjacent the swash plate, which is penetrated by an axle shaft which has a bearing supported by a bearing bracket. The control rod configuration, which can be simply constructed and is less susceptible to malfunction, has an eccentric with its pivotable bearing in the bearing bracket and which is provided between the bearing bracket and the bearing eye. In addition, a method in which a rotor blade of a helicopter has an assigned control rod which is supported by an axle shaft with a bearing in the bearing bracket which is mounted to the swash plate so as to enable adjustment of the control rod by pivoting the axle shaft during flight.

Classes IPC  ?

• B64C 27/51 - Amortissement des mouvements des pales
• B64C 11/36 - Mécanismes de changement de pas des pales mécaniques non automatiques
• B64C 11/12 - Montage des pales dans le cas de pales non réglables souples
• B64C 11/28 - Pales rabattables ou repliables
• B64C 11/32 - Mécanismes de changement de pas des pales mécaniques
• B64C 27/54 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p. ex. mouvement de traînée

Produits et services

Industrial oils and greases; lubricants.

Produits et services

Industrial oils and greases; industrial lubricants

Abrégé

An electro-mechanical linear actuator unit comprising an actuator housing that accommodates at least two electric drives, each of which, when actuated by a control device, sets an associated drive of a respective spindle drive into rotation for adjusting linear movement of the associated spindle drive in order to produce relative linear adjustment of a control rod. The two electric drives are located in the actuator housing in such manner that relative adjustment can be produced by simultaneous actuation of the two electric drives, as the sum of the adjustment movements of the associated spindle drives, or by actuating a single electric drive, as the adjustment movement of the associated spindle drive. A respective brake is provided, in an area of each of the two electric drives, which can be selectively actuated by the control device to then prevent the adjustment movement of the respective associated spindle drive.

Classes IPC  ?

• H02K 41/00 - Systèmes de propulsion dans lesquels un élément rigide se déplace le long d'une piste sous l'effet de l'action dynamo-électrique s'exerçant entre cet élément et un flux magnétique se propageant le long de la piste
• F16H 25/20 - Mécanismes à vis
• H02K 7/06 - Moyens de transformation d'un mouvement alternatif en un mouvement circulaire ou vice versa
• F16H 25/24 - Éléments essentiels pour ces mécanismes, p. ex. vis, écrous
• H02K 7/102 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des freins à friction
• H02K 16/00 - Machines avec plus d'un rotor ou d'un stator

Abrégé

Controlling the pitch of individual rotor blades of a helicopter to reduce control loads, vibration and noise in or from the rotating rotor control elements. The system generates blade dynamics signals representing dynamic forces acting on either or both of the rotating and non-rotating elements of the helicopter, including rotor blades of a rotating assembly. The system extracts information representing at least one dynamic force, generates a dynamic force compensation output that represents a compensation for the dynamic force, and generates, from flight control signals and the dynamic force compensation output, a compensated pitch actuator control signal for each rotor blade wherein the compensation factor of the pitch control signal compensates for the dynamic force.

Classes IPC  ?

• B64C 27/54 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p. ex. mouvement de traînée