• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a device for adjusting the inclination of rotor blades (9) of a rotor, in particular rotors, propellers or turbines of land, air or water vehicles as well as stationary turbine or fan arrangements, comprising - a main drive (2) with a main rotor (3 ) which is arranged rotatably driven about a main axis (1) of the main rotor (3), a bearing (6) are rotatably mounted about their respective blade axis (7), the blade axis (7) being arranged at right angles to the main axis (1), - a control drive (4) with which the inclination of at least one of the rotor blades (9) in the respective blade axis (7) can be adjusted via a control element (5), wherein in particular the control drive (4) is arranged coaxially to the main axis (1) and / or to the main drive (2), the control element (5) is rotatable with the main rotor (3) about the main axis (1), that the control element (5) is designed and arranged in such a way that the control drive (4) between the main rotor (3) and the control element (5) applied differential torque around the main axis (1) can be applied, so that the blade inclination of at least one of the rotor blades (9) in the blade axis (7) can be adjusted via the control element (5) when a differential torque is applied between the main drive (1) and the control drive (4) is, and that the device has a control and regulation unit (10) with which the control drive (4) can be controlled and by means of which a positive or negative differential torque between the main drive (1) and the control drive (4) on the control drive (4 ) can be specified.
    公开号:AT523262A4
    申请号:T50067/2020
    申请日:2020-01-29
    公开日:2021-07-15
    发明作者:
    申请人:Manuel Schleiffelder Mag；
    IPC主号:
    专利说明:

    The blade pitch of a propeller is usually designed and optimized for a certain speed and a certain air flow speed. In addition, due to the relative speed to the surrounding air masses, which changes with the radius of the propeller, both the blade inclination and the blade profile of a propeller become continuously flatter from the inside to the outside. However, the efficiency drops outside the optimal speed and rotational speed range of the rotor blades or rotor configuration. Variable-pitch propellers are known from the prior art which allow the pitch of the rotor blades to be changed collectively either once before operation or continuously during operation and thus enable more efficient operation of the propeller over a larger speed and rotational speed range. Depending on the design of the blade pitch range, a variable pitch propeller can also be used to generate reverse thrust and in some cases, for example in a glider with an auxiliary engine or multi-engine propeller machines, the rotor blades can be adjusted so that they can assume a so-called "sail position" to reduce air resistance For example, EP 3305657 A1 discloses an electric variable-pitch propeller with a rotating servomotor and sliding contacts.
    Furthermore, so-called adjustment rotors are known from the prior art, which are used, for example, in helicopters. The so-called swash plate, which enables a mechanical arrangement for the cyclical adjustment of the blade inclination of rotors, is widely used in variable-displacement rotors. This change in the blade inclination during a rotor revolution enables, for example in helicopters, pitch and roll moments to be induced and a direction of flight to be initiated. In recent times, developments have been promoting the individual control of individual rotor blades by means of hydraulic or electrical actuators that rotate with them. A swash plate mechanism known from the prior art is disclosed in US Pat. No. 1,828,783, for example. Furthermore, EP 2692635 A1 discloses a device with which the rotor blades can be adjusted independently of one another by means of hydraulically operated control rods.
    have highly stressed mechanical elements and are therefore maintenance-intensive.
    The object of the present invention is therefore to provide a device for adjusting the inclination of the rotor blades of a rotor which enables a simple and space-saving construction and with a small number of components
    gets by.
    This object is achieved by the characterizing features of claim 1. It is provided that the control element can be rotated with the main rotor about the main axis, that the control element is designed and arranged such that a differential torque applied around the main axis can be applied by the control drive between the main rotor and the control element, so that the blade inclination at least one of the Rotor blades in the blade axis can be adjusted via the control element when a differential torque is applied between the main drive and the control drive, and that the device has a control and regulating unit with which the control drive can be controlled and by means of which a positive or negative differential torque between the main drive and the Control drive can be specified on the control drive.
    The features according to the invention make it possible to apply a differential torque between the main rotor and the control element via the control drive, so that the control element is rotated relative to the main rotor by this differential torque. The rotation is then transmitted to the rotor blades via the control element, so that their inclination or the inclination of an individual rotor blade is adjusted in the blade axis. The adjustment of the inclination in the blade axis causes different flow conditions along the rotor blade and can thus be optimized depending on flight operations. Furthermore, the design according to the invention achieves a simple structure which can be easily maintained and which enables broad use. Furthermore, the mechanical control forces, the hydraulic pilot pressure or the electrical control current do not have to be transmitted via an interface with high relative speed, and this enables contactless, efficient, fast and also individual articulation of the rotor blades and, so far, very complex double rotor configurations
    simplified.
    Further advantages and advantageous embodiments are defined by the features of the dependent claims:
    In order to be able to easily transmit the differential torque to the rotor blades via the control element, it can be provided that the control element has a lever mechanism, a gear or deflection gear, in particular a bevel gear, via which the differential torque between the control drive and the main drive acts as a torque on the rotor blades can be applied to adjust the inclination of the rotor blades in the blade axis. By transmitting the differential torque by means of a gear or deflection gear, the deflection of the differential torque from the main axis into the blade axis of the rotor blades can be achieved in a simple manner.
    A particularly simple embodiment of the control drive provides that the control drive is designed as an electric motor, the stator of which is arranged on the main axis, in particular coaxially to the main drive, the rotor of the control drive being connected to the control element in a torque-transmitting manner and an adjustment torque by means of the rotor of the control drive can be applied to the rotor blades via the control element. Advantageously, the control drive can be designed as a DC motor with a control unit as a four-quadrant controller, so that, particularly when a negative torque difference is commanded, energy is transferred through recuperation
    System can be fed back.
    In order to be able to easily detect the position of the main rotor and the control element or the control drive and to regulate it particularly precisely, the device can have at least two angle sensors, the angle sensors being arranged in such a way that the angular position of the main rotor and the control element each have one Angle sensor can be detected and transmitted to the control and regulating unit, so that the angular position between the main rotor and the control element can be specified by means of the control and regulating unit by regulating the torque difference between the main rotor and the control element.
    Reduce flight behavior.
    A simple possibility for adjusting several rotor blades via the control element is provided by the control drive having at least one lever mechanism, the lever mechanism comprising a lever element which is arranged between the control element and the respective rotor blade, the lever element being connected to the respective rotor blade via a blade adjustment rod , wherein the lever element is designed and arranged in such a way that the blade inclination of the rotor blades in the blade axis is adjustable when a differential torque is applied between the main drive and the control drive via the control element and the lever mechanism.
    Particularly in the case of helicopters or airplanes, it is required that most systems are provided twice. This is provided by an embodiment in that the control drive is embodied multiple times, in particular doubly, redundantly, preferably mirrored with respect to the blade axis, in the device.
    An optional design of the control drive provides that the control drive is arranged offset, in particular parallel, to the main axis, the rotation being transferable to the control element via a gear stage which is arranged between the control drive and the control element for deflecting and transmitting the torque.
    An optional embodiment of the device is provided in that the control drive is designed as an electric motor, the stator of the control drive being arranged in particular coaxially to the main axis of the main rotor, the control drive having a number of independently controllable windings, a number corresponding to the number of rotor blades of control elements are arranged over the circumference of the stator of the control drive, the control elements each having a segmented rotor that is movable along the circumference of the control drive and each extending along a circumferential section of the control drive, the respective rotors being designed to be movable relative to one another along the circumference of the control drive are, wherein each control element is connected to the respective rotor blade via a gear or deflection gear, in particular a bevel gear, that the inclination of the rotor blades in the respective en blade axis can be adjusted independently of one another, and the control and regulating unit is designed in such a way that the individual coils of the control drive can be controlled differently by the control and regulating unit, so that a different torque difference between the respective control element along the circumference of the control drive for each control element and can be applied to the main rotor, so that the inclination of the rotor blades can be adjusted in any circumferential section of the control drive independently of the respective other rotor blades. The control elements that can be moved relative to one another make it possible to adjust the individual control elements and thus the rotor blades independently of the other rotor blades. In this way, the respective control elements can be adjusted independently of one another at the same time via the controls for the individual windings. Furthermore, the design of the control drive as an electric motor enables a very compact and energy-saving design of the adjustment for individual rotor blades, which also works particularly effectively.
    In order to be able to adjust several rotor blades differently or to be able to set the inclination of the rotor blades differently along one revolution of the main rotor, it can be provided that the device corresponds to one of the rotor blades
    Number of control drives, with one control drive each via one,
    Another aspect of the invention provides that a device according to the invention is used in vehicles, in particular land vehicles, aircraft or watercraft. For this purpose, the corresponding vehicle includes at least one
    device according to the invention.
    An optional embodiment of the vehicle according to the invention is provided in that the vehicle comprises at least two devices according to the invention, the devices being arranged coaxially on a common rotor axis one behind the other and in particular being designed as counter-rotating propellers or counter-rotating dual-rotor configuration.
    Further advantages and embodiments of the invention emerge from the description and the accompanying drawings.
    The invention is shown schematically in the following on the basis of particularly advantageous but not restrictive exemplary embodiments in the drawings and is described by way of example with reference to the drawings:
    1 shows a first embodiment of the device according to the invention in an isometric view, FIG. 2 shows a simplified schematic view of the embodiment according to FIG. 1, FIG. 3 shows an embodiment for the individual adjustment of the blade inclination for two or more rotor blades, FIG. 4 shows a device for adjusting the pitch of the rotor blades by means of a lever element, FIG. 5 shows a further embodiment of the device according to the invention with an offset control drive, FIG. 6 shows an embodiment of the device according to the invention with redundant control elements and control drives, FIG. 7 shows an embodiment of the device as Double rotor configurations, Fig.8 shows an embodiment of the device as a ring propeller configuration and Fig.9 and Fig.10 a
    Another embodiment of the device for individual blade adjustment.
    1 shows a first embodiment of the device according to the invention for adjusting the inclination of rotor blades 9 of a rotor. The device
    7732
    As shown in FIG. 2, the control drive 4 is designed as an electric motor, the stator 41 of which is arranged on the main axis 1 of the main drive 2. The rotor 42 of the control drive 4 is connected to the rotor blades 9 via the control element 5, the control element 5 having a bevel gear 8. The bevel gear 8 consists of a ring gear 81 and three segmented bevel gears 82. The segmented bevel gears 82 are each rotatably connected in the blade axis 7 to one of the rotor blades 9, so that the relative rotation of the ring gear 81 to the main rotor 3 results in an adjustment of the blade inclination of the rotor blades 9 leads in the blade axis 7 and so the so-called pitch can be adjusted.
    As shown in FIGS. 1 and 2, the control element 5 rotates with the main rotor 3 about its main axis 1, so that the inclination of the rotor blades 9 remains constant. If a differential torque is now applied between the main drive 2 and the control drive 4, this causes a relative adjustment of the control element 5 to the main rotor 3 in the main axis 1, so that the ring gear 81 is rotated relative to the main rotor 3 and the segmented bevel gears 82 rotated about the blade axis 7 and thus rotate or adjust the rotor blades 9 in each case in the blade axis 7. The control drive 4 also has a control and regulating unit 10 which controls the control drive 4 and
    by means of which a positive or a negative differential torque between the
    The device also has two rotary encoders 13, 14, which are connected to the control element 10 and, according to internal parameters of the control element 10, for example via an instantaneous current or phase offset control, a defined torque difference between the main rotor 3 and the control element 5 is introduced or a desired one Angular offset regulated with respect to the main rotor 3 out
    can be.
    In Fig. 3, a further embodiment of the device according to the invention is shown in a schematic representation. The device according to the invention has two control drives 4a and 4b, one of the control drives 4a and 4b being connected to one of the rotor blades 9 via a respective control element 5a, 5b. As described in connection with FIGS. 1 and 2, the control drives 4a, 4b are each designed as electric motors, their rotors 42a, 42b being connected to the respective rotor blade 9 by means of a mutually decoupled bevel gear 8. Thus, the rotor blades 9 or the bevel gears 8 can be controlled independently of one another via the control drives 4a, 4b, so that the individual rotor blades 9 can be adjusted individually and independently of one another in the blade axis 7. In a helicopter, for example, the blade inclination of the rotor blades 9 can be set differently for each rotor blade 9 and an advantageous flight behavior can be achieved in this way. A rotary encoder 13 is provided for each of the control drives 4a, 4b, the measured values of which are transmitted to the control and regulation unit 10 and the control drives 4a, 4b designed as electric motors can be regulated or set in this way by the control and regulation unit 10. For example, the control element 10 on the control drive 4a can apply a different torque difference to the main rotor 3 than on the control drive 4b, as a result of which, via the bevel gear 8a, a different blade inclination of the rotor blade connected to the control drive 4a in contrast to the rotor blade 9 connected to the control drive 4b can be adjusted. Thus, for example, the rotor blades 9 can be adjusted independently of one another in the blade axis 7 over one revolution of the main rotor 3, thereby achieving advantageous flow conditions on the rotor blades 9 in different circumferential sections of the main rotor 3. The respective control drives 4a, 4b or their control elements 5a, 5b with the bevel gears 8a, 8b each rotate with the main drive 2 and only take effect when applied
    the pitch of the rotor blades 9.
    In Fig. 4, a further embodiment of the device according to the invention is shown. The control elements 5a, 5b each have, in addition to the bevel gear 8a, 8b, a lever mechanism which connects the bevel gear 8a, 8b to the rotor blades. The lever mechanism in each case has a lever element 21 which adjusts a blade adjustment rod 22 in the direction of the main axis 1 of the main rotor 3 and can adjust the blade inclination of the rotor blades 9 in this way. The height difference can thus advantageously be compensated for by the stacked control drives 4a, 4b and a compact and simple structure can be provided in this way. If a differential torque is applied between the main drive 2 and the control drive 4a, 4b, the respective lever elements 21 are rotated via the bevel gears 8a, 8b in the respective bearings 23a, 23b and the respective blade adjustment rod 22 is shifted in the direction of the main axis 1 so that the Blade adjustment rods 22 connected to the rotor blades 9 each cause an adjustment of the blade inclination of the rotor blades 9. If the same differential torque is applied to the main rotor 3 at the respective control drives 4a, 4b, the blade inclination of the rotor blades 9 is adjusted jointly or equally. Furthermore, when a different torque is applied between the main drive 2 and the respective control drive 4a, 4b, a different adjustment of the blade inclination of the rotor blades 9
    be achieved.
    In Fig. 5, an alternative embodiment of the control drive 4 is shown. The control drive 4 is in turn designed as an electric or hydraulic motor, which is arranged parallel to the main axis 1 of the main drive 2 next to the main axis 1. A further gear stage 23 is arranged between the control drive 4 and the bevel gear 8, which can be designed, for example, as a gear drive or toothed belt drive. The differential torque between the control drive 4 and the main drive 2 is then output via the gear stage 23 to the bevel gear 8 or the control element 5, thus achieving an alternative adjustment of the blade inclination of the rotor blades 9 in the blade axis 7.
    As shown in FIG. 6, the control drive 4, the control element 5, the gearbox and other parts can also be designed twice or redundantly, so that two control drives 4a, 4b each adjust the blade inclination of the rotor blades 9 together via the respective control elements 5a, 5b or the control drive 4b, for example
    if the control drive 4a fails, its task can take over. The identically designed control drives 4a, 4b are, as shown in FIG device according to the invention.
    In Fig. 7, an embodiment of the device according to the invention is shown as a so-called double rotor. The embodiment comprises two main drives 2a, 2b which are arranged on a common main axis 1. Each main drive 2a, 2b has a number of rotor blades 9a, 9b which can each be rotated in the blade axis 7a, 7b via a control element 5a, 5b. The structure of the device designed as a double rotor can be designed for each main drive 1 and the associated control drive or the associated control element 5a, 5b in accordance with the embodiments of FIGS. The differential torque between the main rotor 3 and the control elements 5a, 5b is transmitted via a bevel gear 8a, 8b to the rotor blades 9a, 9b so that their inclination can be adjusted in the respective blade axis 7a, 7b. The individual control drives 4a, 4b are each activated by a control and regulating unit 10a, 10b and the differential torque for the respective control element 5a, 5b is thus applied.
    8 shows a further optional embodiment of the device according to the invention. The device is designed as a so-called ring propeller, in which the rotor blades 9 extend inwards in the direction of the main axis 1. The device has a cylindrical ring 30 on which the stator 24 of the main drive is arranged. The control drive 4 is also arranged on the ring 30, so that the stator 41 of the control drive 4 is also arranged on the ring 30 with respect to the main axis 1 further down to the stator 24 of the main drive 2. The control element 9 is designed according to the embodiments in FIGS. 1 to 6, whereby in the embodiment shown in FIG. 8 the control element 5 transfers the differential torque applied between the control element 5 and the main rotor 3 to the rotor blades 9 via a deflection gear or a bevel gear 8 transmits. The embodiment shown in FIG. 8 is usually also referred to as a ring propeller or ring turbine, with other arrangements of the rotor blades 9 known from the prior art with inwardly pointing or pointing rotor blades 9, corresponding to the embodiment shown in FIG
    a device according to the invention can be realized.
    Optionally, as shown in FIGS. 1 to 6, the deflection of the control element 5 is limited by means of an inclination limiting unit 12 so that the inclination of the rotor blades 9 in the blade axis 7 can only be adjusted to a limited extent. For example, the inclination limiting unit 12 can be designed by means of a stop shown in FIG. 1, which limits the rotation of the ring gear 81 relative to the main rotor 3. Alternatively, the inclination limiting unit 12 can also be designed by means of a coupling element and, for example, as shown in FIGS. 2 to 6, be designed as a spring element which is arranged between the main rotor 3 and the control element 5. As shown in FIGS. 3 to 6, the inclination limiting unit 12 can be provided for each control drive 4, 4a, 4b or the rotor blades 9 can be jointly connected to the main rotor 3 via the inclination limiting unit 12, so that in each case a minimum or maximum adjustment of the
    Blade tilt can be limited.
    As an alternative to the embodiment of the control drives 4, 4a, 4b,... As electric motors shown in FIGS. 1 to 6, the control drives 4, 4a, 4b, Drives be designed. The regulation of the blade inclination via the control and regulation unit 10 can be carried out as a constant position or constant torque regulation, as a torque regulation, (angle) position regulation, in particular with a FOC regulator or a vector regulation for brushless DC motors, so that depending on the operation or flight operation, an optimal adjustment of the rotor blades 9 can be brought about.
    9 and 10 show a further embodiment of the device according to the invention. The device comprises a control drive 4 designed as an electric motor, the stator 41 of which is arranged coaxially to the main axis 1 of the main rotor 3. The device comprises three rotor blades 9, each of which is rotatably connected to the control drive via a control element 5. The rotor blades 9 are distributed evenly over the circumference of the main rotor 3 at a distance of 120 ° from one another. The control drive 4 has a number of independently controllable windings 43 in which a mutually independent electrical field can be applied. The control elements 5 are designed as rotor segments and are each adjustable in relation to one another in the main axis 1. Between the control elements 5 and the rotor blades 9, a bevel gear 8 is arranged in each case, which comprises both a part of a ring gear 81 and a segmented bevel gear 82 (FIG. 10). The control elements 5 each have a rotor 42 which extends along a circumferential section of the control drive 4 and on which the
    segmented ring gear 81 of the bevel gear 8 is arranged. The rotors 42 each extend over a circumferential section of the control drive 4 and can be adjusted relative to one another along the circumference of the control drive 4. A part of the rotor magnets of the control drive 4, which is designed as an electric motor, are arranged in each of the segmented rotors 42. A corresponding free space is arranged between the individual control elements 5, so that they can assume a position relative to one another in relation to the main rotor 3. In order to be able to control the individual control elements individually via the control and regulation unit 10, it is necessary for the individual stator coils or windings 43 to be able to be controlled individually. For example, a separate control circuit, which is controlled or centrally controlled by the control and regulation unit 10, can be provided for each individual control element 5. If, for example, the individual windings 43 or coils are controlled in accordance with a circumferential segment, a differential torque can be applied between this and the main rotor 3 for an individual, segmented control element 5, so that the respective control element 5 relative to the main rotor along the circumference (FIG. 9). is adjusted. By adjusting the control element 5 relative to the main rotor 3 or the rotor blades 9 or the blade axis 7, the ring gear 81 is adjusted with the control element 5 and the segmented bevel gear 82 rotates the rotor blades 9 in the blade axis 7, whereby the inclination of the rotor blades 9 is adjusted. The windings 43 can thus be controlled differently over the circumference of the control drive 4, so that the inclination of the rotor blades 9 can be adjusted together for each individual control element 5 or for each circumferential section in any circumferential section consisting of a certain number of stator coils. In the case of helicopters, for example, a different pitch of the rotor blades 9 can be set depending on the rotation of the main rotor 3 in the different circumferential sections of the main rotor 3, so that the helicopter has a positive flight behavior.
    Optionally, a negative differential torque between the main rotor 3 and the control element 5 can also be applied by a braking torque that is generated, for example, in an electric motor in generator mode. For example, the negative torque can also be used to generate energy and the system
    fed back or stored.
    The device according to the invention can be used, for example, in helicopters or in other propeller-driven aircraft or in propeller drives from
    Land vehicles or watercraft as well as stationary turbine or fan applications are used.
    权利要求:
    Claims (1)
    [1]
    Device for adjusting the inclination of rotor blades (9) of a rotor, in particular rotors, propellers or turbines of land, air or water vehicles as well as stationary turbine or fan arrangements, comprising
    - A main drive (2) with a main rotor (3) which is arranged to be driven and rotatable about a main axis (1) of the main rotor (3),
    - A number of rotor blades (9) arranged on the main rotor (3) at right angles to the main axis (1), in particular evenly distributed, which are each rotatably mounted in a bearing (6) about their respective blade axis (7), the Blade axis (7) is arranged at right angles to the main axis (1),
    - A control drive (4) with which the inclination of at least one of the rotor blades (9) in the respective blade axis (7) can be adjusted via a control element (5), in particular the control drive (4) being coaxial to the main axis (1) and / or to the Main drive (2) is arranged,
    characterized in that the control element (5) can be rotated with the main rotor (3) about the main axis (1),
    that the control element (5) is designed and arranged in such a way that an applied differential torque about the main axis (1) can be applied by the control drive (4) between the main rotor (3) and the control element (5), so that the blade inclination of at least one of the rotor blades (9) is adjustable in the blade axis (7) when a differential torque is applied between the main drive (1) and the control drive (4) via the control element (5), and that the device has a control and regulating unit (10) with which the control drive (4) can be controlled and by means of which a positive or negative differential torque between the
    Main drive (1) and the control drive (4) on the control drive (4) can be specified.
    Device according to claim 1, characterized in that the control element (5) has a gear or deflection gear, in particular a bevel gear (8), via which the differential torque between the control drive (4) and the main drive (1) acts as a torque on the rotor blades ( 9) can be applied to adjust the inclination of the rotor blades (9) in the blade axis (7).
    Device according to one of the preceding claims, characterized in that
    that the control drive (4) is designed as an electric motor, the stator (41) of which is arranged on the main axis (1), in particular coaxially to the main drive (2), the
    Device according to one of the preceding claims, characterized in that the device has at least two angle sensors (13, 14), the angle sensors (13, 14) being arranged in such a way that the angular position of the main rotor (3) and the control element (5) each with an angle encoder (13, 14) can be detected and transmitted to the control and regulating unit (10), so that by means of the control and regulating unit (10) the angular position between the main rotor (3) and the control element (5) via the regulation of the torque difference between Main rotor (3) and control element (5) can be predetermined.
    Device according to one of the preceding claims, characterized in that the device has an inclination limiting unit (12) arranged between the main rotor (3) and the control element (5), the inclination of the rotor blades (9) in the blade axis (7) by means of the inclination limiting unit (12) can be limited, the inclination limiting unit (12) being designed in particular as a stop or coupling element or spring, in particular a return spring.
    Device according to one of the preceding claims, characterized in that the control drive (4) has at least one lever mechanism, wherein the lever mechanism comprises a lever element (21) which is arranged between the control element (5) and the respective rotor blade (9), wherein the Lever element (21) is connected to the respective rotor blade (9) via a blade adjustment rod (22), the lever element (21) being designed and arranged in such a way that the blade inclination of the rotor blades (9) in the blade axis (7) when a differential torque is applied is adjustable between the main drive (1) and the control drive (4) via the control element (5) and the lever mechanism.
    Device according to one of the preceding claims, characterized in that the control drive (4) is designed multiple, in particular doubly, redundantly, preferably mirrored with respect to the blade axis (7), in the device.
    Device according to one of the preceding claims, characterized in that the control drive (4) is offset, in particular parallel, to the main axis (1)
    11.
    is arranged, the rotation being transmitted to the control element (5) via a gear stage (23) which is arranged between the control drive (4) and the control element (5) for deflecting and transmitting the torque.
    Device according to one of the preceding claims, characterized in that the main rotor (3) is arranged in a cylindrical ring (30) and the rotor blades (9) extend towards the center of the ring (30) towards the main axis (1), wherein the device is designed in particular as a ring propeller or ring turbine.
    Device according to one of the preceding claims, characterized in that the control drive (4) is designed as an electric motor, the stator (41) of the control drive (4) being arranged in particular coaxially to the main axis (1) of the main rotor (3), the control drive (4) has a number of independently controllable windings (43),
    - A number of control elements (5) corresponding to the number of rotor blades (9) being arranged over the circumference of the stator (41) of the control drive (4), the control elements (5) each being movable along the circumference of the control drive (4) , segmented rotor (42) each extending along a circumferential section of the control drive (4), the respective rotors (42) being designed to be movable relative to one another along the circumference of the control drive (4),
    - each control element (5) being connected to the respective rotor blade (9) via a lever mechanism, a gear or deflection gear, in particular a bevel gear (8), in such a way that the inclination of the rotor blades (9) in the respective blade axis (7) is independently adjustable, and
    - The control and regulating unit (10) is designed such that the individual coils (43) of the control drive (4) can be controlled differently by the control and regulating unit (10), so that along the circumference of the control drive (4) for each Control element (5) a different torque difference between the respective control element (5) and the main rotor (3) can be applied, so that the inclination of the rotor blades (9) can be set independently of the other rotor blades (9) in any circumferential section of the control drive (4) is.
    Device according to one of the preceding claims, characterized in that
    that the device has a number of control drives (4a, 4b, ...) corresponding to the rotor blades (9), with one control drive (4a, 4b, ...) in each case.
    13th
    is each connected via a control element (5a, 5b, ...) of the same design to a respective A-rotor blade (9), with the presence of a differential torque between the main drive (2) and the respective control drive (4a, 4b, ..) .) the inclination of the respective rotor blade (9) connected to this control drive (4a, 4b, ...) is adjustable.
    Vehicle, in particular land vehicle, aircraft or watercraft, comprising at least one main rotor (3), characterized in that the vehicle comprises at least one device according to one of Claims 1 to 11,
    Vehicle according to claim 12, characterized in that the vehicle comprises at least two devices according to one of claims 1 to 11, the devices being arranged coaxially on a common rotor axis (3) one behind the other and in particular being designed as counter-rotating propellers or counter-rotating dual-rotor configurations.
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    同族专利:
    公开号 | 公开日
    WO2021151129A1|2021-08-05|
    AT523262B1|2021-07-15|
    引用文献:
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    GB627010A|1945-09-25|1949-07-26|Power Jets Res & Dev Ltd|Improvements relating to gearing for imparting relative angular movement between rotating shafts|
    US4591313A|1983-12-30|1986-05-27|The Boeing Company|Propeller pitch control system and apparatus|
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    EP2328261B1|2009-11-26|2020-01-08|Krebs & Aulich GmbH|Electric actuator|
    US20140322017A1|2011-11-24|2014-10-30|Hispano Suiza|Rotary mechanical system with contactless actuation|
    US1828783A|1926-06-18|1931-10-27|Oehmichen Etienne|Lifting device|
    US4556366A|1983-10-17|1985-12-03|General Electric Company|Propeller actuation system|
    JPS621690A|1985-06-27|1987-01-07|Fukashi Uragami|Variable pitch propeller|
    US5282719A|1991-05-13|1994-02-01|Alliedsignal Inc.|Quad mode fan pitch actuation system for a gas turbine engine|
    FR2951696B1|2009-10-22|2011-12-23|Snecma|SYSTEM FOR VARYING THE IMPACT OF THE BLADES OF AN AIRCRAFT TURBOMACHINE PROPELLER USING A BRUSHLESS ELECTRIC MOTOR|
    US8496436B2|2010-01-11|2013-07-30|Hamilton Sundstrand Corporation|Torque compensation for propeller pitch change mechanism|
    US8857757B2|2012-08-02|2014-10-14|Bell Helicopter Textron Inc.|Independent blade control system with hydraulic pitch link|
    NO342415B1|2016-08-31|2018-05-22|FLIR Unmanned Aerial Systems AS|Controlling blade pitch by a plurality of electric motors|
    EP3305657B1|2016-10-05|2019-01-23|MT-Propeller Entwicklung GmbH|Electrical adjustment propeller arrangement|
    US10988247B2|2017-10-19|2021-04-27|Uvionix Aerospace Corporation|Unmanned aerial vehicle and propulsion system for an unmanned aerial vehicle|CN113955084A|2021-12-22|2022-01-21|四川承天翼航空科技有限公司|Rotor wing variable-pitch control system and method and synchronous/asynchronous variable-pitch control method|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    ATA50067/2020A|AT523262B1|2020-01-29|2020-01-29|Device for adjusting the inclination of the rotor blades of a rotor|ATA50067/2020A| AT523262B1|2020-01-29|2020-01-29|Device for adjusting the inclination of the rotor blades of a rotor|
    PCT/AT2020/060459| WO2021151129A1|2020-01-29|2020-12-14|Device for adjusting the inclination of rotor blades of a rotor|
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