WO2018016932A1 - Mécanisme de variation de pas d'hélice cycloïde - Google Patents

Mécanisme de variation de pas d'hélice cycloïde Download PDF

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Publication number
WO2018016932A1
WO2018016932A1 PCT/KZ2017/000005 KZ2017000005W WO2018016932A1 WO 2018016932 A1 WO2018016932 A1 WO 2018016932A1 KZ 2017000005 W KZ2017000005 W KZ 2017000005W WO 2018016932 A1 WO2018016932 A1 WO 2018016932A1
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WIPO (PCT)
Prior art keywords
shaft
gear
axis
angular
changing
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PCT/KZ2017/000005
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English (en)
Russian (ru)
Inventor
Ергалий ТАСБУЛАТОВ
Ермек АШКЕНОВ
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Ергалий ТАСБУЛАТОВ
Ермек АШКЕНОВ
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Publication of WO2018016932A1 publication Critical patent/WO2018016932A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H1/00—Propulsive elements directly acting on water
    • B63H1/02—Propulsive elements directly acting on water of rotary type
    • B63H1/04—Propulsive elements directly acting on water of rotary type with rotation axis substantially at right angles to propulsive direction
    • B63H1/06—Propulsive elements directly acting on water of rotary type with rotation axis substantially at right angles to propulsive direction with adjustable vanes or blades
    • B63H1/08—Propulsive elements directly acting on water of rotary type with rotation axis substantially at right angles to propulsive direction with adjustable vanes or blades with cyclic adjustment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B64C11/04—Blade mountings
    • B64C11/06—Blade mountings for variable-pitch blades

Definitions

  • the invention relates to air and water transport, as well as to energy (wind and hydropower plants), in particular to wing propellers - cycloid propellers operating in both air and water environments.
  • the cycloid propeller consists of blades located in diameter, rotating around the axis of the rotor, creating directional motion. In order to create movement, it is necessary to change the tilt angles of the individual blades using the blade pitch control mechanism.
  • curtate movement along a shortened cycloid
  • prolate movement along an elongated cycloid
  • a number of wing propellers are known from the prior art — cycloid propellers, in particular, a ship wing propeller, also known as Voith Schneider Propeller (A.s. SU N ⁇ > 51404, B 63H 1 / 10, 01.01.1937), which is a crank mechanism with a central shaft, where the central shaft acts as an eccentric. Oscillatory movements of the rocker arm on the blade shaft bring the wing propeller into the mode of movement along a shortened cycloid (curtate).
  • the disadvantage of this technical solution is the limitation on the maximum possible speed of the vessel.
  • Cycloidal VTOL UAV Pulsoid propeller
  • Patent US N ° 6932296, B64C 27/22, 08/23/2005 patented by Glenn Martin Tierney, which is a planetary mechanism and consists of the blades located along the diameter of the rotor hub, and the shaft of each blade is kinematically connected by means of two angular gears and a shaft between them, an external satellite and spurious satellite gears with a central gear fixed to the central shaft, which performs the function of an eccentric.
  • This cycloid propeller works in two modes of cycloid movement: due to the rotation of the central gear - in the shortened cycloid mode (curtate) with the rotational speed of the hub of the rotor and due to the stationary central gear - in the mode of extended cycloid (prolate) .
  • the disadvantage of this mechanism is the impossibility of switching from one mode to another during the rotation of the rotor of the wing propeller, since the rotor must be stopped to switch modes.
  • the closest to the set of attributes to the claimed solution is technically blade pitch change mechanism cycloidal propeller (Propeller for Aircraft), Kirsten and patented Hoover (Kurt FJ KIRSTEN & Herbert M. HEUVER ) ( Patent US «2045233, B64C 1/00 1, 06/23/1936).
  • the mechanism for changing the pitch of the blades is a combination of three devices: a planetary mechanism, a crank-link mechanism that create two different types of rotation and are located one above the other, and a differential mechanism that converts and provides rotation of the blade shaft along an elongated cycloid.
  • This mechanism has a central gear located in the hub of the rotor, rigidly fixed to the axis of the rotor, engaged with a satellite gear, which is freely fixed on the axis of the bevel gear, containing two bevel gears.
  • the second tier on the axis of the bevel gear is the differential, consisting of bevel gears.
  • the link On the central shaft, the device for changing the eccentricity and direction of the thrust vector, the link is freely fixed, on which the rocker is located, freely fixed by the third tier on the axis of the angular gear.
  • the axis of the angular gearbox through the intermediate shaft is kinematically connected with the angular gearbox of the shaft of the blade of the cycloid propeller.
  • the rotation of the hub of the rotor leads to the rotation of the satellite gears and to the oscillatory movements of the rocker, and the differential summarizes the uniform rotation of the satellite and the oscillatory movements of the rocker to the uneven rotation transmitted through the axis of the angular gear to the angular gear of the blade shaft.
  • the disadvantage of this mechanism is irrationality: the crank-link mechanism creates oscillatory movements similar to the movements characteristic of the mechanisms of changing the step of the cycle.
  • the planetary mechanism creates rotational motions similar to the step change mechanism of the cycloid propeller of the elongated cycloid (prolate) with zero eccentricity, while the differential mechanism summarizes and provides motions characteristic only of the step change mechanism of the cycloid propeller along the elongated cycloid .
  • the technical result consists in the development and creation of four variants of the mechanism for changing the pitch of a cycloid propeller, namely:
  • the specified technical result in the proposed mechanism for changing the pitch of the blades of a cycloid propeller of a shortened cycloid (curtate) in the first embodiment is achieved by the fact that in the device containing in the hub of the rotor a device for changing the eccentricity and direction of the thrust vector, a central shaft, an axis with an angular gear comprising two bevel gears and an intermediate shaft connecting the axis of the angular gearbox to the angular gearbox of the shaft of the cycloid propeller blade, according to the invention, a slider is additionally introduced with the possibility of sliding along the hub of the rotor along the radial guides. An angular gearbox is located on the slider.
  • a connecting rod was introduced, freely fixed on the central shaft and rigidly fixed on the axis of the bevel gear.
  • the axis of the bevel gear is the axis of the slider and is parallel to the central shaft and the shaft of the blade, and the top of the cone of the driving bevel gear on the axis of the bevel gear on the slider and the top of the cone of the driven bevel gear of the bevel gear on the shaft of the blade are oppositely directed, which ensures rotation of the shaft of the blade and the axis of the bevel gear on the slider in one direction.
  • the technical result is achieved by the fact that the intermediate shaft is made telescopic.
  • the device for changing the eccentricity and direction of the thrust vector contains a helical shaft located perpendicular to the axis of the rotor hub, which moves the central shaft with the central gear through a screw connection.
  • the helical shaft changes the position of the central shaft radially from the axis of the hub of the rotor and, accordingly, changes the pitch of the blades.
  • a change in the direction of the thrust vector is made by turning the casing of the device for changing the centricity and direction of the thrust vector on the axis of the rotor hub. It is also possible to use other, already known versions of the device for changing the eccentricity and direction of the thrust vector, similar to the Voigt-Schneider mover and devices using servo drives.
  • the device includes a central gear in the rotor hub that engages with a satellite gear, which is freely fixed on the axis an angular gearbox containing two bevel gears, an intermediate shaft connecting the axis of the angular gearbox to the angular gearbox of the shaft of the cycloid propeller blade, and an eccentric change device and a thrust direction of the vector of the invention further introduced slider koto- ing is slidable along a radial guide on stu- pitse rotor.
  • the axis of the bevel gear is the axis of the slider and is parallel to the central shaft and the shaft of the blade, and the top of the cone of the driving bevel gear on the axis of the bevel gear on the slider and the top of the cone of the bevel gear of the bevel gear on the shaft of the blade are equally oriented, which ensures rotation the shaft of the blade and the satellite gear in opposite directions.
  • a connecting rod was additionally introduced, freely fixed on the central shaft and rigidly fixed on the axis of the angular gearbox.
  • the satellite gear and bevel gear of the bevel gear are freely fixed on the axis of the bevel gear and are rigidly fixed to each other.
  • the central gear is rigidly mounted on the central shaft of the eccentricity device.
  • the intermediate shaft is made telescopic.
  • the device for changing the eccentricity and direction of the thrust vector contains a helical shaft located perpendicular to the axis of the rotor hub, which moves the central shaft with the central gear through a screw connection.
  • the helical shaft changes the position of the central shaft radially from the axis of the hub of the rotor and, accordingly, changes the pitch of the blades.
  • the direction of the thrust vector is changed by turning the body of the device to change the eccentricity and the direction of the thrust vector on the axis of the rotor hub. It is also possible to use other, already known versions of the device for changing the eccentricity and direction of the thrust vector, similar to the Voigt-Schneider propulsion device and devices using servo drives.
  • the specified technical result in the proposed mechanism for changing the pitch of the blades of the multicycloid propeller in the third embodiment is achieved by the fact that the device containing the central gear in the hub of the rotor engages with the satellite gear, which is freely fixed on the axis of the angular gearbox, containing two bevel gears, the central shaft of the device for changing the eccentricity and direction of the thrust vector and the intermediate shaft connected to the angular gear of the shaft of the blade of the cycloid propeller, ccording to the invention additionally introduced a slider which is slidable on the hub of the rotor along radial guides. On the slider is located an angular gearbox and a satellite gear.
  • an additional connecting rod is introduced, freely fixed on the central shaft and rigidly fixed on the axis of the angular gear, in addition, a second angular gear located on the slider and a second intermediate shaft, as well as a gear shift box, are additionally introduced .
  • the satellite gear and bevel gear of the angular gearbox are freely fixed on the axis of the angular gearbox and rigidly fixed to each other.
  • the axis of the angular gearbox is the axis of the slider and is parallel to the central shaft and the shaft of the blade, and the vertices of the cone of both bevel gears located on the axis of the angular gearbox are directed towards the center.
  • the central gear is rigidly fixed to the central Mr. shaft of the device changes eccentricity.
  • the gearbox of the multicycloid propeller contains two parallel-located leading hollow shafts with internal splines of the shaft fixed in the housing of the rotor hub and one coaxially arranged driven hollow shaft.
  • a crank is rigidly fixed on one drive shaft, transmitting oscillatory movements of the mechanism for changing the cycloid propeller pitch of a shortened cycloid.
  • Another drive shaft with internal splines, transmitting rotational movements of the step change mechanism of the cycloid propeller of the elongated cycloid, is made in the form of a coupling hub.
  • a driven shaft is coaxially located on the side of the coupling half, while a crank and a splined double-sided coupling are freely fixed on the driven shaft, which ensures the engagement of the driven shaft with the crank or coupling of the drive shaft of rotational movements.
  • the crank on the driven shaft through the connecting rod is connected to the crank on the drive shaft of the oscillatory movements.
  • the driven shaft of the cycloid propeller gearbox is connected to the angular gear of the shaft of the blade of the cycloid propeller.
  • Other variants of the gearbox are also possible, for example, replacing cranks and connecting rods with gears and the location of the driven shaft not aligned with the drive shaft.
  • the device for changing the eccentricity and direction of the thrust vector contains a helical shaft located perpendicular to the axis of the hub of the rotor, which moves the central shaft with the central gear through a screw connection.
  • the helical shaft changes the position of the central shaft radially from the axis of the rotor hub, and, accordingly, changes the pitch of the blades.
  • the direction of the thrust vector is changed by turning the eccentricity device and the direction of the thrust vector on the axis of the rotor hub. It is also possible to use others already of known embodiments of a device for changing the eccentricity and direction of the thrust vector, similar to the Voigt-Schneider mover and devices using servo drives
  • the specified technical result in the proposed mechanism for changing the pitch of the blades of the multicycloid propeller in the fourth embodiment is achieved by the fact that the device containing the central gear in the rotor hub engages with the satellite gear, which is freely fixed on the axis of the bevel gear, containing two bevel gears , the central shaft of the device for changing the eccentricity and direction of the thrust vector and the intermediate shaft connected to the angular gear of the shaft of the blade of the cycloid propeller, according to the invention, a slider is additionally introduced, which has the ability to slide along the rotor hub along radial guides. On the slider is located an angular gearbox and a satellite gear.
  • a connecting rod was additionally introduced, freely fixed on the central shaft and rigidly fixed on the axis of the bevel gear.
  • the axis of the angular gearbox is also the axis of the slider; in addition, a one-way splined cam clutch and a conical gear wheel having reciprocal cams on the clutch side are additionally introduced.
  • the bevel gear is freely fixed on the axis of the bevel gear and engages with the bevel gear of the bevel gear mounted on the countershaft.
  • the coupling is located on the splines of the axis of the bevel gear.
  • sleeve having slots on the outer surface, which is freely fixed on the axis of the angular gear.
  • the satellite gear is rigidly fixed to the hub.
  • a second one-way splined cam clutch located on the sleeve has been introduced.
  • the bevel gear of the angular gearbox is freely fixed, which has reciprocal cams on the coupling side.
  • plugs are located on both couplings, which are connected to the servo drive.
  • the central gear is rigidly fixed to the central shaft of the ex centricity. The specified technical result is also achieved by the fact that the intermediate shaft is made telescopic.
  • the device for changing the eccentricity and direction of the thrust vector contains a helical shaft located perpendicular to the axis of the hub of the rotor, which moves the central shaft with the central gear through a screw connection.
  • the helical shaft changes the position of the central shaft radially from the axis of the hub of the rotor, and, accordingly, changes the pitch of the blades.
  • the direction of the thrust vector is changed by turning the body of the device for changing the eccentricity and the direction of the thrust vector on the axis of the rotor hub. It is also possible to use other, already known versions of the device for changing the eccentricity and direction of the thrust vector, similar to the Voigt-Schneider mover and devices using servo drives.
  • the angular gearbox is located on the slider, and the axis of the angular gearbox is the axis of the slider and is parallel to the central shaft and the shaft of the blade, while the top of the cone of the pinion gear on the axis of the angular gearbox and the top of of the driven bevel gear of the bevel gear on the blade shaft are equally directed, providing rotation of the blade shaft and the satellite gear in opposite directions, and the satellite gear and the bevel gear of the bevel gear are freely fixed on the axis of the bevel gear and rigidly fixed to each other, the central gear is rigidly strengthened on the central shaft of the device for changing the eccentricity and direction of the thrust vector,
  • the mechanism for changing the step of the multicycloid propeller of the slider which has the ability to slide along the rotor hub along radial guides; a connecting rod, freely fixed on the central shaft and rigidly fixed on the axis of the angle gear, while the angle gear is located on the slider; the second bevel gear, also located on the slider and having one common axis with the first bevel gear, while the driving bevel gear of the second bevel gear is rigidly fixed to the common axis, and the second intermediate shaft, and the pinion gear and bevel gear of the first bevel gear freely fixed on the axis of the angular gear and rigidly fixed to each other.
  • the axis of the bevel gear is is parallel to the central shaft and the blade shaft, the tops of the cone of both bevel gears located on the axis of the angular gearbox are directed to the center, and the central gear is rigidly fixed to the central shaft of the device for changing the eccentricity, while both intermediate shafts are made telescopic, which generally creates conditions for synchronizing the rotation of the intermediate shafts.
  • the introduction of the gearbox which is functionally transmitting rotational movements from telescopic intermediate shafts to the angular gear of the blade shaft, while the solid shafts of the telescopic shafts mesh with the driving hollow shafts of the gearbox, makes it possible to switch from work in the accelerated mode - a cycloid (curtate) to the operation mode according to an extended cycloid (prolate) without stopping the rotation of the rotor and vice versa, while switching modes occurs due to the movement of the coupling COROLLARY servo controller a controllable coordinated with the sensors and the values of the eccentricity of the rotor hub position relative to the housing unit and the eccentricity changes the direction of the thrust vector.
  • the mechanism for changing the pitch of the multicycloid propeller of the slider which has the ability to slide on the rotor hub along radial guides, of a sleeve having slots on the outer surface and freely fixed on the axis of the angular gearbox, while the angular gearbox is located on the slider, and ca - the tellite gear is rigidly fixed to the sleeve, the introduction of a connecting rod, rigidly fixed to the axis of the angular gear and freely mounted on the central shaft of the device for changing the eccentricity, the central gear is rigidly fixed on the central shaft and engages with the satellite gear, as well as the introduction of the bevel gear freely fixed on the axis of the bevel gear and engaged with the bevel gear of the bevel gear mounted on the intermediate shaft, while the axis of the bevel gear is the axis of the slider and is located parallel to the central shaft and the blade shaft, and the tops of the cone of both bevel gears located on the axis
  • the mode switching device consisting of two one-sided spline cam couplings, a screw and a servo drive, with the first clutch located on the splines of the sleeve between the pinion gear and the bevel gear having reciprocal cams on the clutch side, and the second clutch is located on the splines of the angle axis - a gearbox on the back of the introduced bevel gear, the bevel gear having reciprocal cams on the clutch side, and on both couplings there are forks connected to one common servo drive, which is functionally Provides the ability to switch from operation in a short cycloid mode (curtate) to an extended proxy cycloid mode without stopping the rotation of the rotor and vice versa.
  • Fig. 1 shows a cycloid propeller with a mechanism for moving along a shortened cycloid (curtate) in the first embodiment in a section (for convenience, a two-bladed rotor is shown).
  • Figure 2 shows a diagram of the movement of the blades of the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along a shortened cycloid (curtate).
  • Fig. 1 shows a cycloid propeller with a mechanism for moving along a shortened cycloid (curtate) in the first embodiment in a section (for convenience, a two-bladed rotor is shown).
  • Figure 2 shows a diagram of the movement of the blades of the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along a shortened cycloid (curtate).
  • Fig. 1 shows a cycloid propeller with a mechanism for moving along a shortened
  • FIG. 3 is a diagram of a change in the position of the blades of the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along a shortened cycloid (curtate) at zero eccentricity
  • Fig. 4 is a diagram of a mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along a shortened cycloid ( curtate) with an eccentricity greater than zero.
  • Figure 5 - presents a graph of the dependence of the angles of rotation of the blades relative to the angles of rotation of the hub of the rotor of the mechanism for changing the pitch of the blades of the cycloid propeller, creating a movement on a shortened cycloid (curtate).
  • Fig.6 shows a cycloid propeller with a mechanism of movement along an elongated cycloid (prolate) in the second embodiment in section (for convenience of perception, a two-bladed rotor is shown)
  • Fig.7 is a diagram of the movement of the blades of the mechanism for changing the pitch of the blades of the cycloid propeller RA, creating movement along an elongated cycloid (prolate).
  • Fig. 8 is a diagram of the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along an elongated cycloid (prolate) at zero eccentricity; Fig.
  • FIG. 9 is a diagram of a mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along an elongated cycloid (prolate) during eccentricity Above zero.
  • Figure 10 is a graph of the angle of rotation of the blade relative to the angle of rotation of the hub of the rotor of an elongated cycloid (prolate).
  • 11 shows a mechanism for changing the pitch of a multicycloid propeller in the third embodiment in the context (for ease of perception, a two-blade rotor is shown), the clutch servo is not shown.
  • FIG. 12 shows graphs of the dependence of the rotation angles of the blade relative to the rotation angles of the hub of the rotor when operating in the mode of shortened cycloid (curtate) - C and elongated cycloid (prolate) - P with the eccentricity necessary for synchronizing and shifting gears.
  • 13 shows a mechanism for changing the pitch of a multicycloid propeller in the fourth embodiment in a section (for convenience of perception, a two-blade rotor is shown), the clutch servo is not shown.
  • the mechanism for changing the pitch of the blades of a cycloid propeller in the first embodiment, creating movement along a shortened cycloid (curtate), is a synthesis of a crank-slide, crank-beam mechanism and a device for changing the eccentricity and direction of the thrust vector.
  • the mechanism comprises (Fig. 1) a central shaft 1 that performs the function of an eccentric, on which the connecting rod 2 is freely fixed at one end and rigidly connected to the axis of the bevel gear 3, the other tsom. On the axis of the bevel gear 3, the sector gear 4 of the bevel gear is rigidly fixed.
  • the second sector gear 5 of the angular gearbox is located on the body of the slider 6.
  • the connecting rod 2 performs two functions at once: in fact, as a connecting rod for the slider 6 and as a lever that performs rocker function for sector gear 4 angular gear.
  • the connecting rod heads 2 on the central shaft 1 are arranged coaxially in one another, providing independent rotation on the axis of the central shaft 1.
  • the axis of the angular gear 3 is parallel to the central shaft 1 and the shaft 10 of the blade 9, and the top of the cone of the driving bevel gear 4, located on the axis 3 of the angular gear, which is located on the slider 6, is directed opposite to the top of the cone driven conical bevel gear pinion 12, which is located on the shaft 9 of the blade that provides the blade shaft rotation axis 9 and the bevel gear 3 on the slider 6 in the same direction.
  • the connection of the angular gearbox consisting of bevel gears 11 and 12 of the shaft 10 of the blade 9 and the mechanism for changing the pitch of the blades of the shortened cycloid occurs through an intermediate telescopic shaft 13 with a spline connection for the possibility of changing the length of the shaft.
  • the device for changing the eccentricity and direction of the thrust vector consists of a central shaft 1, a helical shaft 14, which changes the position of the central shaft 1 along the housing 15 through the rotation of the bevel gear 16 and the bevel gear 17 of the shaft 18.
  • the change in the eccentricity and accordingly the pitch of the blades is carried out by rotation shaft 18 with a worm gear drive 19 or another type of drive (gear, chain, etc.).
  • the change in the direction of the thrust vector is provided by turning the housing 15, which rotates freely inside the hub of the rotor 7 through a worm drive 20 or another type of drive (gear, chain, etc.).
  • the rotation of the hub of the rotor 7 from the engine is carried out through the shaft 21 and bevel gears Nos. 22 and 23, while it is also possible to use other types of drives.
  • Oscillatory movements of the axis of the angular gear 3 are transmitted to the shaft of the blade 10 through the angular gears, in particular, bevel gears 4, 5, 11 and 12 with a general gear ratio K> 1, i.e. the angle of rotation of the shaft of the blade 10 corresponds to or more than the angle of rotation of the axis of the angular gear 3. Accordingly, with an increase in the overall gear ratio, an increase in the maximum pitch of the blade is achieved with a simultaneous decrease in the necessary displacement of the central shaft 1, which performs the function of an eccentric and, accordingly, is achieved decrease in linear movement of the slider 6 along the guides 8.
  • the rotation angle ⁇ of the blade 9 has a relation with respect to the rotation angles of the hub of the rotor 7 (FIG. 4) and the change in the eccentricity ⁇ according to the graph shown in FIG. 5, providing the oscillatory movement of the blade 9 along a shortened cycloid (curtate) according to the formula:
  • ⁇ arcsin (£ * sin ⁇ / L) * K1 (3)
  • ⁇ the angle of rotation of the blade 9
  • ⁇ the angle of rotation of the hub of the rotor 7
  • L is the length of the connecting rod 2 between the axis of the central shaft 1 and the axis of the bevel gear 3.
  • the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along an elongated cycloid (prolate) in the second embodiment is a synthesis of a crank-slide and planetary mechanisms and a device for changing the eccentricity and direction of the thrust vector.
  • the mechanism contains (Fig.6) a Central non-rotating gear 24, which is mounted on the Central shaft 1, which performs the function of an eccentric.
  • the slider 6 slides radially from the central axis along the hub of the rotor 7 along the guides 8.
  • An angular gearbox is located on the slider 6, the bevel gear 25 of which is freely mounted on the axis 3 of the angular gearbox.
  • a connecting rod 2 is loosely connected to the axis 3 of the angular gearbox and is connected freely to the central shaft 1.
  • a satellite gear 26 is freely fixed to the axis 3 of the angular gearbox and engages with the central gear 24 rigidly fixed to the central shaft 1.
  • the satellite gear 26 and bevel gears 27 are rigidly interconnected.
  • the connecting rod 2 performs two functions at once: in fact, as a connecting rod for the slider 6 and as a planetary gear for the satellite gear 26.
  • the connecting rod heads 2 on the central shaft 1 are arranged coaxially in each other, providing independent rotation on the axis of the central shaft 1.
  • the angular gearbox consists of bevel gears 11 and 12, the shaft 10 of the blade 9 and the mechanism for changing the pitch of the blades Orochony cyclin alkaloids takes place via a telescopic intermediate shaft 13 with shlitse- vym compound for the possibility of changing the length of the shaft.
  • the device for changing the eccentricity and direction of the thrust vector consists of a central shaft 1 with a fixed central gear 25 fixed on it, a commercial shaft 14, which changes the position of the central shaft 1 along the housing 15 through the rotation of the bevel gear 16 and the bevel gear 17 of the shaft 18.
  • the eccentricity and, accordingly, the pitch of the blades is changed by rotating the shaft 18 with a worm gear 19 or another type of drive (gear, chain, etc.).
  • a change in the direction of the thrust vector is provided by turning the housing 15, which rotates freely inside the hub of the rotor 7 through a worm drive 20 or another type of drive (gear, chain, etc.).
  • the rotation of the hub of the rotor 7 from the engine is carried out through the shaft 21 and bevel gears 22 and 23, it is also possible to use other types of drives.
  • the mechanism for changing the pitch of the blades of a cycloid propeller allows the cycloid propeller to move along the path in FIG. 7.
  • the satellite gear 26 rotates around the central gear 25 and around its own axis.
  • the connection of the angular gear with bevel gears 11 and 12 of the shaft of the blade 10 and the angular gear with bevel gears 25 and 27 of the mechanism for changing the pitch of the blades occurs through a telescopic shaft 13 with spline connection for the possibility of changing the length of the shaft.
  • the gear ratio between the bevel gear 25 mounted on the intermediate telescopic shaft 13 and the bevel gear 27 on the axis 3 of the angular gearbox is equal to the gear ratio between the central 24 and the satellite gear 26, and the gear ratio of the angular gear with bevel gears 11 and 12 of the shaft 10 of the blade 9 equal to one.
  • the axis of the bevel gear 3 is parallel to the central shaft 1 and the shaft 10 of the blade 9, and the top of the cone of the drive bevel gear 27 on the axis of the bevel gear and the top of the cone of the bevel gear 12 of the bevel gear on the shaft of the blade are equally oriented, which ensures rotation of the shaft 10 blades 9 and satellite gear 26 in opposite directions.
  • the gear ratio of the gears is
  • the rotation of the driven telescopic shaft 13 is uneven, that is, alternately decreasing and increasing its angular rotation speed, which, in turn, ensures the circular motion of the blade 9 along an elongated cycloid (prolate) according to the graph shown in FIG. 10 according to the formula:
  • L is the length of the connecting rod 2 between the axis of the central shaft 1 and the axis of the bevel gear 3.
  • a second price is set the swivel gear onto the central shaft over the first central gear. Accordingly, all subsequent satellite gears of the second tier (4th, 5th and 6th blades) are engaged with the second central gear.
  • the mechanism for changing the pitch of the blades of the multicycloid propeller in the third embodiment (Fig. 11) consists of four devices that perform functions according to their purposes:
  • the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along a shortened cycloid, and the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along an elongated cycloid, are located on one slider 6 and have a common axis 3 of the angular gearbox, connecting rod 2, guides 8, and also a central shaft 1 with the central gear 24 located on a common device for changing the eccentricity and the thrust vector, which gives an optimization of the number of moving parts.
  • the angular gear of the mechanism for changing the pitch of the blades of the cycloid propeller, creating movement along the shortened cycloid, consisting of two sector gears 4 and 5, the angular gear with the bevel gears 25 and 27, the satellite gear 26 of the mechanism of changing the pitch of the blades of the cycloid propeller, creating movement along the elongated cycloid are located on slider 6 in two tiers one above the other and on the same axis 3 of the angular gear.
  • the axis 3 of the angular gearbox is parallel to the central shaft 1 and the shaft 10 of the blade 9, and the tops of the cone of bevel gears 4 and 27 located on the axis 3 of the angular gearbox are directed towards the center.
  • Solid shafts 28 and 29 telescopic shafts of the pitch change mechanism of the blades the cycloid propeller, creating a movement along a shortened cycloid, and the mechanism for changing the pitch of the blades of a cycloid propeller, creating a movement along an elongated cycloid, mesh with the hollow shafts 30 and 31 of the drive shaft of the gearbox.
  • the gearbox consists of three parallel shafts fixed in the rotor hub housing, namely:
  • the driven shaft 33 is located at one end in the housing of the hub 7 of the rotor, and at the other end abuts through the bearing into a rotational motion drive shaft 31 coaxial with it, which ensures independent rotation of both shafts.
  • a coupling half 34 is rigidly fixed on the driving shaft 31 from the driven shaft 33.
  • a crank 35 is freely fixed on the driven shaft 33.
  • a two-way clutch 36 is located on the driven shaft 33, which engages the driven shaft 33 with the crank 35 or a coupling half 34 on a drive shaft 31 of rotational movements.
  • a crank 35 having reciprocal cams on the clutch side 36 is connected to a crank 32 through a connecting rod 37.
  • the output shaft 33 of the gearshift gear transmits rotation to the angular gearbox consisting of gears 11 and 12 of the shaft 10 of the blade 9 of the cycloid propeller.
  • the device for changing the eccentricity and direction of the thrust vector consists of a central shaft 1 with a fixed central gear 25 fixed to it, a helical shaft 14, which changes the position of the central shaft 1 along the housing 15 through the rotation of the bevel gear 16 and a bevel gear 17 of the shaft 18.
  • the eccentricity and accordingly the pitch of the blades are changed due to the rotation of the shaft 18 with a worm gear 19 or another type of drive (gear, chain, etc.).
  • Changing the direction of the thrust vector is provided by turning the housing 15, which rotates freely inside the hub of the rotor 7 through a worm gear 20 or another type of drive (gear, chain, etc.).
  • the rotation of the hub of the rotor 7 from the engine is carried out through the shaft 21 and bevel gears 22 and 23, other types of drives can also be used.
  • the mechanism for changing the pitch of the blades of the multicycloid propeller in the third embodiment provides the movement of the cycloid propeller along the trajectory in Fig. 2 and Fig. 7.
  • the connection of the coupling 36 with the crank 35 of the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along a shortened cycloid (curtate) or with the coupling half 34 of the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along an elongated cycloid (prolate) leads to rotation of the driven shaft 33
  • the necessary conditions for switching modes are provided by synchronizing the rotation of the drive shaft 30 of the mechanism for changing the pitch of the blades of the cycloid propeller, which creates movement along the shortened cycloid and the drive shaft 31 the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along an elongated cycloid in a certain sector of rotation
  • the mechanism for changing the pitch of a multi-cycloid propeller in the fourth embodiment consists of four devices that perform functions according to their purposes: (Fig. 13):
  • the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along a shortened cycloid, and the mechanism for changing the pitch of the blades of a cycloid propeller, creating movement along an elongated cycloid, are located on one slider 6 and have a common axis 3 of the angular gearbox, an intermediate telescopic shaft 13 with a conical rigidly fixed to it gear 25, connecting rod 2, guides 8, and central shaft 1 with central gear 24 located on a common device for changing the eccentricity and thrust vector, which gives optimization to lichestva moving parts.
  • the axis 3 of the angular gearbox is the axis of the slider 6 and is parallel to the central shaft 1 and the shaft of the blade 9, and the tops of the cone of the bevel gear 4 of the blade pitch change mechanism of the cycloid propeller, creating a movement along the shortened cycloid, and the bevel gear 27 of the blade pitch change mechanism
  • the cycloid propeller which creates motion along an elongated cycloid, is directed toward the center and freely fixed on axis 3 of the angular gearbox.
  • a hub 38 having slots on the outer surface is freely fixed on the axis 3, while the satellite gear 26 meshed with the central gear 24 is rigidly fixed to the hub 38.
  • bevel gears 4 and 27 are meshed with a bevel gear 25 fixed to intermediate telescopic shaft 13.
  • bevel gear 25 can be made in the form of a twin gear having two gear conical surfaces to obtain minimum eccentricity when moving along a shortened cycloid (curtate).
  • the connecting rod 2 is rigidly fixed on the axis of the bevel gear 3 and freely fixed on the central shaft 1 of the device for changing the eccentricity.
  • the mode switching device consists (Fig.
  • the device for changing the eccentricity and direction of the thrust vector consists of a central shaft 1 with a fixed central gear 25 fixed thereon, a screw shaft 14, which changes the position of the central shaft 1 along the housing 15 through rotation of the bevel gear 16 and the bevel gear 17 of the shaft 18.
  • the eccentricity and accordingly the pitch of the blades are changed due to the rotation of the shaft 18 by the worm gear 19 or another type of drive (gear, chain, etc.).
  • Changing the direction of the thrust vector is provided by turning the housing 15, which rotates freely inside the hub of the rotor 7 through a worm gear 20 or another type of drive (gear, chain, etc.).
  • the rotation of the hub of the rotor 7 from the engine is carried out through the shaft 21 and bevel gears 22 and 23, it is also possible to use other types of drives.
  • the mechanism for changing the pitch of the blades of the multicycloid propeller in the fourth embodiment ensures the movement of the cycloid propeller along the paths shown in FIG. 2 and FIG. 7.
  • the servo drive simultaneously moves the one-way clutches 39 and 40, which leads to the connection of one and the disconnection of the other clutch with bevel gears 4 and 27 and, accordingly, the subsequent transmission of torque to bevel gear 25 located on the intermediate telescopic shaft 13.
  • Necessary conditions for switching modes are ensured by synchronizing the rotation of the bevel gear 4 of the mechanism for changing the pitch of the blades of the cycloid propeller, which creates movement according to the shortened cycloid, and the bevel gear 27 of the mechanism for changing the pitch of the blades of the cycloid propeller, creating movement along the elongated cycloid, in a certain sector of rotation of the hub 7 of the rotor with certain gear ratios of the bevel gear 4 of the mechanism for changing the pitch of the blades of the cycloid propeller, creating movement along the shortened cycloid and bevel gear 25, as well as the position of the eccentricity of the central shaft 1 with the central gear 24 relative to the axis of the hub of the rotor 7.
  • Clutch 40 has four cams. The number of cams in the coupling 40, with K5> 1 (13) must meet the condition
  • ⁇ is an integer.
  • Voight-Schneider movers used on ships have good traction and maneuverability, but are limited in speed of movement, because have only one mode of movement along a shortened cycloid (curtate).
  • the use of a cycloid propeller in water transport with the blade pitch control mechanism of the present invention which can alternately operate both in the short cycloid (curtate) mode and in the extended cycloid (prolate) mode, will reduce fuel consumption, increase speed and expand the range of capabilities of ships with a cycloid propeller.
  • Cycloid propellers can also be used in water transport with a horizontal axis located in the stern of the ship’s hull over most of its width.
  • a cycloid propeller with the blade pitch control mechanism proposed in the present invention, possibly in air transport, primarily on cyclocopters.
  • Vertical take-off, initial speed gain, hovering and vertical landing can be carried out in the mode of shortened cycloid (curtate), and flight, presumably at speeds higher than the helicopter, may occur in prolate mode.
  • the autorotation mode is provided.
  • a cycloid propeller with the blade pitch control mechanism of the present invention is possible on modern aircraft lighter than air, including on airships.
  • the use, in particular, on airships of cycloid propeller (s) with the ability to work both on shortened (curtate) and elongated (prolate) cycloids as a propulsion device will improve the airships' ability to maneuver and stabilize due to the possibility of cycloid the propeller almost instantly change the direction of thrust.
  • the cycloid propeller with the blade pitch control mechanism of the present invention with the ability to operate both on shortened (prolate) and elongated (prolate) cycloids can be used in wind and hydropower as a generator drive.
  • the cycloid propeller provides self-starting of the rotor rotation at the minimum air or water flow rate, while it is assumed that the main mode for the cycloid propeller to work is to use the shortened cycloid (curtate) mode, and for operation in extreme conditions, for example, in hurricane winds, as well as when it is necessary to stop the rotor, use the prolate mode.
  • the cycloid propeller also enables more rapid orientation in the direction of the wind than other systems of wind generators, for example, horizontal-axis units.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Retarders (AREA)
  • Gear Transmission (AREA)

Abstract

L'invention concerne le domaine de la conception de propulseurs à aubes ou propulseurs cycloïdes fonctionnant dans un milieu aqueux ou aérien. Le mécanisme de variation de pas d'hélice cycloïde comprend un coulisseau ayant la possibilité de glisser le long du moyeu du rotor en suivant les guides radiaux et une bielle fixée librement sur l'arbre central et fixée rigidement sur l'axe du réducteur d'angle. Le réducteur d'angle est disposé sur le coulisseau. Les engrenages satellite et d'entraînement conique sont fixés librement sur l'axe du réducteur d'angle et fixés entre eux. L'axe du réducteur d'angle est en même temps l'axe du coulisseau et est disposé en parallèle à l'arbre central et à l'arbre de la pale. Le dispositif de changement de régimes est constitué de cames biseautées de manchons à roue libre. Deux arbres intermédiaires sont télescopiques et s'engrènent avec les arbres d'entraînement creux de la boîte de vitesses. L'invention permet un fonctionnement alterné du propulseur multi-cycloïde en modes de fonctionnement suivant des cycloïdes raccourci ou allongé et un transfert d'un mode en un autre sans arrêter la rotation.
PCT/KZ2017/000005 2016-07-18 2017-03-29 Mécanisme de variation de pas d'hélice cycloïde WO2018016932A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KZ20160643 2016-07-18
KZ2016/0643.1 2016-07-18

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WO2018016932A1 true WO2018016932A1 (fr) 2018-01-25

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109204755A (zh) * 2018-11-13 2019-01-15 公培明 一种新型活动桨叶式轮桨
CN112550646A (zh) * 2020-11-27 2021-03-26 东南大学 一种采用控制轴平面位置解耦机构的多叶片摆线推进器
CN113665810A (zh) * 2021-08-26 2021-11-19 大连理工大学 一种转动圆盘式摆线桨偏心机构
CN115258109A (zh) * 2022-08-05 2022-11-01 江苏科技大学 一种全向调节的摆线推进器

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2045233A (en) * 1934-08-17 1936-06-23 Kurt F J Kirsten Propeller for aircraft
RU2060203C1 (ru) * 1992-03-17 1996-05-20 Виталий Григорьевич Федчишин Циклоидный движитель федчишина в.г.
US6109875A (en) * 1998-03-14 2000-08-29 Voith Hydro Gmbh & Co., Kg Cycloidal propeller
US6932296B2 (en) * 2003-10-21 2005-08-23 Information Systems Laboratories, Inc. Cycloidal VTOL UAV

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2045233A (en) * 1934-08-17 1936-06-23 Kurt F J Kirsten Propeller for aircraft
RU2060203C1 (ru) * 1992-03-17 1996-05-20 Виталий Григорьевич Федчишин Циклоидный движитель федчишина в.г.
US6109875A (en) * 1998-03-14 2000-08-29 Voith Hydro Gmbh & Co., Kg Cycloidal propeller
US6932296B2 (en) * 2003-10-21 2005-08-23 Information Systems Laboratories, Inc. Cycloidal VTOL UAV

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109204755A (zh) * 2018-11-13 2019-01-15 公培明 一种新型活动桨叶式轮桨
CN109204755B (zh) * 2018-11-13 2024-02-06 公培明 一种活动桨叶式轮桨
CN112550646A (zh) * 2020-11-27 2021-03-26 东南大学 一种采用控制轴平面位置解耦机构的多叶片摆线推进器
CN112550646B (zh) * 2020-11-27 2021-09-07 东南大学 一种采用控制轴平面位置解耦机构的多叶片摆线推进器
CN113665810A (zh) * 2021-08-26 2021-11-19 大连理工大学 一种转动圆盘式摆线桨偏心机构
CN113665810B (zh) * 2021-08-26 2024-04-26 大连理工大学 一种转动圆盘式摆线桨偏心机构
CN115258109A (zh) * 2022-08-05 2022-11-01 江苏科技大学 一种全向调节的摆线推进器

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