WO2022154684A1 - Hélice porteuse - Google Patents

Hélice porteuse Download PDF

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Publication number
WO2022154684A1
WO2022154684A1 PCT/RU2021/000007 RU2021000007W WO2022154684A1 WO 2022154684 A1 WO2022154684 A1 WO 2022154684A1 RU 2021000007 W RU2021000007 W RU 2021000007W WO 2022154684 A1 WO2022154684 A1 WO 2022154684A1
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WO
WIPO (PCT)
Prior art keywords
main rotor
blade
working fluid
hydraulic motors
helicopter
Prior art date
Application number
PCT/RU2021/000007
Other languages
English (en)
Russian (ru)
Inventor
Валерий Туркубеевич ПЧЕНТЛЕШЕВ
Original Assignee
Валерий Туркубеевич ПЧЕНТЛЕШЕВ
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Валерий Туркубеевич ПЧЕНТЛЕШЕВ filed Critical Валерий Туркубеевич ПЧЕНТЛЕШЕВ
Priority to PCT/RU2021/000007 priority Critical patent/WO2022154684A1/fr
Publication of WO2022154684A1 publication Critical patent/WO2022154684A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B64C27/64—Transmitting means, e.g. interrelated with initiating means or means acting on blades using fluid pressure, e.g. having fluid power amplification
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
    • F15B15/08—Characterised by the construction of the motor unit
    • F15B15/12—Characterised by the construction of the motor unit of the oscillating-vane or curved-cylinder type

Definitions

  • the invention relates to propellers, and relates in particular to rotors (NV) of rotary-wing aircraft (VKLA), for example, helicopters.
  • NV rotors
  • VKLA rotary-wing aircraft
  • One of the ways to improve helicopters is to increase the maximum aerodynamic quality of the HB.
  • One of the ways to increase the maximum aerodynamic quality of the NV helicopter is the individual control of the angle of installation of each NV blade (Itogi nauki i tekhniki//Ser. Aircraft building: Foreign helicopters. V.10. M.: VINITI.1989, p.18, [1]) .
  • Individual control of the installation angle of each HB blade allows, theoretically, regardless of the azimuthal position of the HB blade and the helicopter flight mode, to set the HB blade at such angles of attack, with respect to the air flow incident on the blade, at which the maximum aerodynamic quality of the HB blade is realized.
  • each HB blade is controlled by an individual hydraulic cylinder (with translational movement of the rod), which rotates together with the HB blade. That is, in essence, in this technical solution, the blade control rod is replaced by a hydraulic cylinder.
  • the working fluid from the hydraulic pumps (installed on the non-rotating part of the helicopter) is supplied under high pressure to the rotating hydraulic cylinders.
  • Another direction of improving helicopters is to increase the speed of helicopters.
  • One of the factors limiting the flight speed of helicopters is the stall on the retreating HB blades (HB blades going in the opposite direction of the helicopter flight).
  • Single-rotor helicopters have the highest payload weight return.
  • the factor limiting the further increase in the flight speed of single-rotor helicopters is the stall on the retreating HB blades.
  • This is due, among other things, to the design feature of the kinematic mechanism used on helicopters, which controls the angles of installation of the HB blades and serves to change the total and cyclic pitch of the HB blades.
  • Known helicopters use a swashplate as such a kinematic mechanism, which, in the most widely used version of its design, consists of one non-rotating ring and one rotating ring connected by a bearing. The rotating ring is attached to the levers of the HB blades with the help of rods and is attached to the HB shaft on a universal joint (cardan) or a ball bearing.
  • Rods coming from the helicopter control stick are attached to the non-rotating ring. Tilt not rotating moving and rotating rings in the longitudinal and transverse planes by means of rods (or hydraulic boosters) coming from the helicopter control stick, leads to a cyclic change in the angle of installation of the HB blades, thereby changing the magnitude and direction of the resultant aerodynamic force of the HB.
  • the installation angles of the HB blades in the sectors of the left, front, right and rear quarters of the HB disk are uniquely related to each other.
  • SAUSH reduces the angle of installation of the HB blades
  • SAUSH increases the angle of installation of the HB blades.
  • the operation of the SAUSh requires the presence of a special unit on the helicopter - a correction machine (AC).
  • the work of the AC is based on the deformation of the elastic rings of the inner and outer cages of the main bearing of the AC under the action of the diametral force from the hydraulic cylinder.
  • an ellipse is formed, the major axis of which is always located along the flight, taking into account the lead angle.
  • the difference in the sizes of the major and minor semi-axes of the ellipse will be equal in magnitude to the amplitude of the change in the HB pitch.
  • the disadvantages of the above technical solution the complexity and cumbersomeness of the kinematic mechanism for controlling the angle of installation of the HB blades; limited range, increasing the pitch of the HB blades located in the sectors of the front and rear quarters of the HB disk, and reducing the pitch of the HB blades located in the sectors of the left and right quarters of the HB disk, provided by the operation of the AC, compared with the range of change in the pitch of the HB blades provided by the known mechanical AP in well-known single-rotor helicopters.
  • the HB bush axial hinge has: hinge; axial hinge body; two radial bearings; one thrust roller bearing with turned rollers.
  • quadrants In drive technology, vane part-turn hydraulic motors (quadrants) are widely used.
  • the quadrant has a cylindrical body, in which there are at least two working chambers (into which either the working fluid is supplied under a certain excess pressure, or from which the working fluid is drained), separated by a blade.
  • the quadrant blade has an output shaft to which the driven mechanism is attached.
  • the blade At the quadrant, the blade (with its output shaft) is configured to perform reciprocating rotational movements in both directions relative to the stationary body of the quadrant. It is possible and vice versa - the body is square the welt is made with the possibility of making reciprocating rotational movements in both directions relative to the fixed blade of the quadrant.
  • quadrants make it possible to simplify the kinematics of the drive, in comparison with the drive, where hydraulic cylinders with a progressive movement of the rod are used.
  • the quadrants have the following specifications: developed torque - 17.2 + 440,000 kilograms of force per meter (kgf * m); working fluid pressure - 17.5- ⁇ -210 kilograms of force per square centimeter (kgf / cm 2 ); the maximum angle of rotation of the output shaft of the blade, for single-bladed quadrants - 280 + 300 °, for two-bladed quadrants - 120-440 °, for three-bladed quadrants - 40 + 55 ° (Petrov E.M., Yuzefovich Yu.I. Blade part-turn hydraulic motors in shipbuilding L.: Shipbuilding, 1972, p.8+9, [7])
  • cam drive mechanisms are widely used.
  • the cam drive mechanism has a spring-loaded plunger, a pusher, with a roller installed at one end on the axis, and a cam shaft.
  • a spring-loaded plunger acts on the pusher, pressing the roller of the latter against the cam of the camshaft. This design works stably at several thousand revolutions per minute of the camshaft.
  • the objective of the claimed invention is to simplify the design, reduce the weight and overall dimensions of both the HB sleeve itself and the system for individual control of the installation angle of each HB blade, as well as increase reliability and service life, compared with the prototype.
  • a propeller for example, a rotor of a helicopter, has a HB sleeve, HB blades, each HB blade is configured to individually control its installation angle, the HB sleeve has bushing body.
  • each HB blade is controlled by means of its own blade part-turn hydraulic motor for each HB blade, mounted on the HB bushing and configured to interact with the HB bushing body and with the HB blade controlled by it, on the HB bushing are also located, a container with a working fluid configured to power the above part-turn hydraulic motors, spools configured to control the supply of the above working fluid to the working chambers of the above vane part-turn hydraulic motors, while each vane part-turn hydraulic motor has its own spool, at least one hydraulic pump, made with the possibility of supplying the working fluid to the working chambers of the above bladed part-turn hydraulic motors, at least one filter made with the possibility of cleaning the above working fluid.
  • HB bushing is an integral unit, which includes, in addition to the HB bushing body and HB blades, also vane part-turn hydraulic motors with individual control of the installation angle of each HB blade, a reservoir with working fluid, a hydraulic pump, spools, filter.
  • mechanical energy is supplied to the HB bushing by means of a rotating shaft located inside the HB shaft to drive the hydraulic pump.
  • FIG.1- ⁇ 8 shows one of the possible embodiments of the claimed invention in the version of the HB sleeve of a helicopter of a single-rotor scheme, where the numbers indicate (the designations are identical for all figures of the drawings): 1 - body of the HB sleeve; 2 - top cover of the sleeve housing HB; 3 and 4 - housings of the axial hinges of the HB bushing; 5 and 6 - HB blades; 7 - HB shaft; 8 - slider; 9 - swivel body; 9vp - the position of the rotary body 9 when it is tilted forward; 9nz - the position of the rotary body 9 when it is tilted back; 10 - control washer; Yuvh - the position of the control washer 10 when it deviates upward; Yuvn - the position of the control washer 10 when it deviates down; 11 - hydraulic pump drive shaft; 12 - hydraulic block; 13 - the central body of the bladed part-
  • FIG.1 shows a view of the HB against the flight. The location of detail views A and B is shown, and the side view of NV is C.
  • FIG.2 shows a detail view A. Shows the location of the section GG.
  • FIG.Z shows the section ⁇ - ⁇ in the neutral position of the spool 31.
  • FIG.4 shows a cross-section G-D when the spool 31 deviates down.
  • FIG.5 shows a section GG when the blade HB 5 is deflected down.
  • FIG.6 shows a section G-D when the spool 31 deviates upwards.
  • FIG.7 shows a detail view B.
  • FIG. 8 shows view B.
  • the claimed invention in the HB version of a single-rotor helicopter (single-rotor helicopter), is as follows.
  • the NV is made of two-bladed, right-handed rotation (when viewed from above), the hub of which has only axial hinges, and the blades are made “rigid”, for example, as in the well-known helicopter Bo-105 from Messerschmitt-Bolkow-Blohm (Germany).
  • the inventive HB (FIG.1- ⁇ 8) has a HB sleeve housing 1, consisting (conditionally) of, made as a single unit, the central part of the HB sleeve housing and two sleeves of the HB sleeve housing. From above, the upper cover of the HB 2 bushing body is attached (in any acceptable way, for example, by bolting) to the central part of the HB 1 bushing housing, and the HB 7 shaft is attached to the central part of the HB 1 bushing housing from below (in any acceptable way, for example, by means of a bolted flange connection).
  • hydraulic block 12 which includes: two gear-type hydraulic pumps (not shown in FIG. 1- ⁇ 8), driven by the main gearbox ( FIG.1 ⁇ -8 not shown) of the helicopter through the drive shaft of the hydraulic pumps 11, located laid, inside the shaft HB 7 (the drive shaft of the hydraulic pumps 11 has a different (higher or lower) angular velocity, compared with the angular velocity of the shaft HB 7 - in order to be able to drive the above hydraulic pumps into action); filters (not shown in FIG. 1- ⁇ 8) used to clean (filter) the working fluid; check and safety valves (not shown in FIG.
  • the reservoir 51 with the working fluid is the internal cavity of the body of the HB sleeve 1, consisting of two interconnected halves located to the left and right of the central part of the HB sleeve. It is possible that the above hydraulic pumps are driven by the hydraulic pump drive shaft 11, which is driven not from the main gearbox, but from another source of mechanical energy, for example, from an electric motor (or electric motors) installed on a non-rotating part of the helicopter (for example, on the body main gearbox or helicopter fuselage).
  • the above hydraulic pumps are driven not from the main gearbox (not from the hydraulic pump drive shaft 11, which is not available in this version), but by an electric motor (or electric motors) mounted directly on the HB bushing, the electric power to which is supplied from the non-rotating part of the helicopter (from the helicopter fuselage), for example, by means of a current collector of a known design (for example, as in known electric motors).
  • the HB sleeve of the claimed invention has only axial hinges.
  • the axial hinge of the HB 5 blade has: the body of the axial hinge of the HB 3 bushing, installed in the sleeve of the HB 1 bushing body (which is the axis of the axial hinge of the HB 5 blade); two radial (for example, needle) bearings 41 and 42; one thrust bearing with rotation rollers 43: front ring 44; back ring 45; nuts 46 and 47; seal 48; thrust ring 49; retaining ring 50.
  • the body of the axial hinge of the HB sleeve 3 is fixed with nuts 46 and 47.
  • the axial hinge of the HB 5 blade (and the HB 6 blade) in the claimed invention is similar in design axial hinges of three-hinged bushings NV of known helicopters, for example, as in the famous Mi-8 helicopter of the Moscow Helicopter Plant. M.L. Mile ( Russian).
  • Two blades HB 5 and 6 are rigidly attached to the body of the axial hinge of the HB 3 bushing (for example, using bolts with an ear-fork connection - like the above-mentioned VO-105 helicopter), which are made "rigid” (similar to the HB blades of the above-mentioned VO-105 helicopter ).
  • the centrifugal load from the HB blade 5 is transferred to the body of the axial hinge of the HB sleeve 3, and then through the nut 47, through the outer race of the bearing 42, through the front ring 44, through the bearing 43, through the rear ring 45 , through the inner race of the bearing 41, through the nut 46, then onto the sleeve of the HB sleeve housing, and then to the central part of the HB sleeve body, where it is balanced by the same centrifugal force of the second HB blade 6.
  • the axial hinge of the HB 6 blade is arranged in exactly the same way as the axial hinge of the above HB 5 blade.
  • the blade HB 5 has its own individual drive angle control, made in the form of a blade part-turn hydraulic motor (FIG.1- ⁇ -8 shows only an individual drive angle control blade HB 5 - an individual drive angle control of the second opposite blade HB 6 has similar design).
  • the vane semi-rotary hydraulic motor is located inside the sleeve of the sleeve HB 1 body (inside the axis of the axial hinge of the HB blade 5), and consists of: the central body 13; front 14 and rear 15 side covers; shaft 16; vanes 17 and 18 (i.e., a cap type quarter turn vane motor is used - but any other suitable type of vane quarter turn motor, such as spool type, may be used).
  • the blades 17 and 18 are rigidly fixed on a single shaft 16 and are located in the housing 13 diametrically relative to each other (the blades 17 and 18 and the shaft 16 are a single part - as one of the possible versions).
  • the blades 17 and 18 and the shaft 16 are a single part - as one of the possible versions.
  • In front of the front side cover 14 has a groove for the spool 31 and stop 36 for the compression spring 33.
  • the central body of the semi-rotary hydraulic motor 13 is fixedly attached to the hydroblock 12 (by any acceptable method, for example, by means of a bolted connection), and, therefore, the central body of the vane semi-rotary hydraulic motor 13 is made stationary relative to the central part of the housing of the HB sleeve 1.
  • the shaft 16 of the semi-rotary hydraulic motor is attached (by any in an acceptable way, for example, by spline connection) to the body of the axial hinge of the HB 3 bushing, and, therefore, the shaft 16 is rigidly connected to the butt of the HB 5 blade (to transmit torque from the blades 17 and 18 of the non-rotary hydraulic motor to the HB 5 blade).
  • each bladed part-turn hydraulic motor (for driving both blades HB 5 and 6) is made of two blades.
  • the blade 17 is placed in its working cylinder with two working chambers 27 and 28, each of which is powered by its own (first) hydraulic pump.
  • the blade 18 is placed in its working cylinder with two working chambers 29 and 30, each of which is powered by its own (second) hydraulic pump.
  • the supply of the working fluid to the working chambers 27, 28, 29 and 30 of the part-turn hydraulic motor is controlled by the spool 31, for example, a flat end valve.
  • the spool 31 is installed on the end part of the shaft 16 of the part-turn hydraulic motor and is located between the end part of the shaft 16 and the valve body 12 (as one of the possible locations).
  • the spool 31 has a lever 32 interacting with the compression spring 33 and inlet windows 34 and 35.
  • the spool 31 interacts with the stop 36 of the front side cover 14 by means of a compression spring 33 (as one of the possible embodiments, there can be more compression springs, for example, two compression springs located coaxially to each other).
  • the spool 31 interacts with the control washer 10 by means of a pusher, consisting of a rod 37, a roller 39 mounted on an axis 40 (the pusher is structurally similar to the pushers used in the above-mentioned famous THB D).
  • the control washer 10 is made flexible (from any acceptable material, for example, from a thin sheet of steel).
  • the aforementioned compression spring 33 rests with one end against the stop 36 of the front side cover 14, and with its other end acts on the lever 32 of the spool 31.
  • the spool 31 acts on the upper end (having the shape of a fragment of a spherical surface) of the pusher rod 37.
  • Pusher rod 37 its upper end passes through the hole in the body of the HB bushing into the body of the HB bushing 1, and is sealed in any acceptable way, for example, as the rods of the known hydraulic cylinders of the drives of the control surfaces of aircraft and helicopters are sealed.
  • the pusher rod 37 through the axis 40 acts on the roller 39.
  • the roller 39 acts on the control washer 10, which is fixedly attached (in any acceptable way, for example, by bolting) to the rotary housing 9.
  • the rotary housing 9 is hinged, for example, by means of a cardan (or spherical hinge) to the slider 8.
  • the slider 8 is configured to move along its guide (FIG.1 ⁇ -8 not shown), in the direction of the axis of rotation of the shaft HB 7 up and down, but is not able to rotate in the direction of the axis of rotation of the shaft HB 7.
  • Rotary housing 9 (and control washer 10) cannot rotate in the direction of the axis of rotation of the shaft HB 7, but can only change its installation angle relative to the axis of rotation of the shaft HB 7 only in the longitudinal (forward-backward direction) plane (as one of the possible versions), and move (without inclination) together with the slider 8 in the up and down direction along the axis of rotation of the HB shaft.
  • the rotary housing 9 can change its installation angle relative to the axis of rotation of the shaft HB 7 also in the transverse (in left-right direction) plane.
  • the rotary housing 9 on the advancing side of the HB has a cut, beyond which the free edge of the control washer 10 protrudes.
  • control rod - FIG.1 ⁇ -8 not shown
  • the individual drive for controlling the pitch angle of the HB 6 blade is designed in exactly the same way as the individual drive for controlling the pitch angle of the above blade HB 5.
  • the sealing of the container with the working fluid 51 which is the inner cavity of the axial hinge of the HB bushing, can be carried out in any acceptable way, for example, as the axial hinges are sealed in the known HB bushings of helicopters.
  • the claimed invention works as follows.
  • the operation of the blade HB 5 is considered (the operation of the blade HB 6 occurs in a similar way).
  • HB helicopter shaft HB 7 (and, consequently, the body of the sleeve HB 1 with blades HB 5 and 6 attached to it) rotates with a certain angular velocity.
  • bushings HB The inlet port 35 of the spool 31, connected (always) to the outlet of the second hydraulic pump, is not connected to the inlet (and outlet) ports 21 and 22 at the end of the shaft 16 (the inlet port 35 is at an equal distance from the inlet ports 21 and 22). Consequently, the working chambers 29 and 30 are isolated from the outlet of the second hydraulic pump and from the reservoir with the working fluid 51 (i.e., the working fluid is locked in the working chambers 29 and 30), and therefore the blade HB 5 is motionless relative to the body of the sleeve HB 1 (relative to its body sleeve). bushings HB).
  • the inlet window 19 and the channel 23 in the blade 17, connected to the working chamber 28, is connected to the container with the working fluid 51 (that is, it is connected to the drain, since the container 51 is not completely filled with the working fluid and the pressure in it is less (approximately equal to atmospheric pressure) than the pressure of the working fluid at the outlet of the first hydraulic pump).
  • the inlet 35 of the spool 31, connected (always) to the outlet of the second hydraulic pump, is connected to the inlet 21 and to the channel 26 in the blade 18, and, therefore, the working chamber 30 communicates with the outlet of the second hydraulic pump.
  • the inlet window 22 and the channel 25 in the blade 18, connected to the working chamber 29, is connected to the reservoir with the working fluid 51 (that is, connected to the drain).
  • the working fluid under excess pressure begins to flow into the working chambers 27 and 30, and from the working chambers 28 and 29, the working fluid begins to merge into a container with the working fluid 51 (and then again enters the first and second hydraulic pumps, and then everything repeats ).
  • a torque is generated on the vanes 17 and 18, turning them and the shaft 16 in the direction of rotation of the spool 31 (the vanes 17 and 18 follow the spool 31).
  • the rotating shaft 16 turns the blade HB 5 behind it (since the shaft 16 and the blade HB 5 are rigidly connected to each other by means of a spline connection).
  • the HB blade 5 rotates relative to the HB sleeve housing 1 (relative to the sleeve of the HB sleeve body), reducing its installation angle (the HB blade 5 follows the spool 31).
  • the inlet port 35 of the spool 31, connected (always) to the outlet of the second hydraulic pump, is not connected to the inlet (and outlet) ports 21 and 22 at the end of the shaft 16 (the inlet port 35 is at an equal distance from the inlet ports 21 and 22). Consequently, the working chambers 29 and 30 are isolated from the outlet of the second hydraulic pump and from the reservoir with the working fluid 51 (i.e., the working fluid is locked in the working chambers 29 and 30), and therefore the blade HB 5 is motionless relative to the body of the sleeve HB 1 (relative to its body sleeve). bushings HB).
  • the inlet port 35 of the spool 31, connected (always) to the outlet of the second hydraulic pump, is connected to the inlet port 22 and to the channel 25 in the blade 18, and, therefore, the working chamber 29 communicates with the outlet of the second hydraulic pump.
  • Entrance window 21 and channel 26 in the blade 18, connected to the working chamber 30, is connected to the container with the working fluid 51 (that is, connected to the drain).
  • the working fluid under excess pressure begins to flow into the working chambers 28 and 29, and from the working chambers 27 and 30, the working fluid begins to merge into a container with working fluid 51 (and then again enters the first and second hydraulic pumps, and then everything repeats ).
  • a torque is generated on the vanes 17 and 18, turning them and the shaft 16 in the direction of rotation of the spool 31 (the vanes 17 and 18 follow the spool 31).
  • the rotating shaft 16 rotates the HB blade 5 behind it.
  • the HB blade 5 rotates relative to the HB bushing body 1 (relative to the sleeve of the HB bushing body), increasing its installation angle (HB blade 5 follows the spool 31).
  • bladed part-turn hydraulic motors (quadrants) have a speed (maximum rotation speed of the output shaft of the quadrant blade) - 20CH240 °/sec.
  • vane part-turn hydraulic motors develop a torque of up to 17.2- ⁇ 440,000 kgf * m.
  • Such a speed and such a torque value is more than enough to individually control the angle of installation of each HB blade in the claimed invention.
  • the control washer 10 in the claimed invention can be made (or all or only part of it) flexible (from any acceptable material, for example, from a thin sheet of steel). This will allow you to arbitrarily control the installation angle of each blade HB 5 and 6.
  • the surface of the control washer 10, along the trajectory of the pusher roller 39 along it, in the claimed invention can have any acceptable shape (flat (as shown in FIG. 1 ⁇ 8 and described above ), wavy (like a washboard), and more).
  • a control washer 10 along the trajectory of the pusher roller 39 along it
  • a wavy shape like a washboard
  • the HB blade will change its installation angle several times (and not once, as in known helicopters with mechanical AP), which will reduce the amount of vibration generated by the HB blades.
  • the use in the claimed invention as an individual drive for controlling the angle of installation of the HB blades of bladed part-turn hydraulic motors, and small forces acting on the above pusher, will allow the inventive individual drive for controlling the angles of installation of the HB blades to have several times more resource (service life), compared with mechanical AP in known helicopters. This will reduce the operating costs of the helicopter.
  • the control of the helicopter, when using the claimed invention on it, in pitch can be carried out by tilting the rotary body 9 (and the control washer 10) in the longitudinal plane in the forward-backward direction (carried out, for example, by the control rod - not shown in FIG. 1- ⁇ 8) , and in roll - by bending (up or down) the control washer 10 (carried out, for example, by a control rod - not shown in FIG. 1- ⁇ 8) in the left (advancing) quarter of its disk (taking into account the advance angle of the HB blades control).
  • the rotary body 9 on the advancing side of the HB has a cut, beyond which the free edge of the control washer 10 protrudes, and that the sector of the control washer 10 of the left (advancing) quarter of the disk is made flexible.
  • the HB blades 5 and 6 in the sectors of the front, right (retreating) and rear quarters of the HB disk will be set to the maximum possible installation angles (larger than those of known helicopters with known mechanical AP, but smaller critical angles of attack - so that there is no stall flow from the retreating HB blades). This will allow the claimed NV to create a greater thrust in level flight than the known single-rotor helicopters.
  • the main part of the HB thrust force will be created by the sectors of the front and rear quarters of the HB disk.
  • the HB blades will be set to the maximum possible angles of attack, which, however, are less than the critical ones (with the necessary margin).
  • the HB blades will be set at such angles of attack to only balance the HB blades located in the sector of the right (retreating) quarter of the HB disk (so that there is no unbalanced roll moment).
  • the claimed invention will make it possible to have: greater aerodynamic quality of the HB and the helicopter as a whole; high speed helicopter flight; lower level of vibrations generated by HB blades; several times longer resource (service life) of an individual drive for controlling the angles of installation of the HB blades, compared with mechanical AP for known helicopters, which will reduce the operating costs of the helicopter.
  • spools that control the supply of working fluid to the working chambers of rotary vane hydraulic motors can be mechanically controlled in any suitable way: as shown in FIG. 1 ⁇ -8 and described above; the push rod can slide directly on the control washer 10; and other.
  • a variant of the claimed invention is possible when it has spools that control the supply of working fluid to the working chambers of rotary vane hydraulic motors are not controlled by the control washer 10 (as shown in FIG. 1- ⁇ 8 and described above), that is, not mechanically, but in any other acceptable way, for example, by acting on the spools electromagnets (depending on the azimuth position of the HB blade), as is implemented in the fly-by-wire control system of an aircraft or helicopter.
  • the electrical signal to the electromagnet comes from a master device, for example, located on a non-rotating part of the helicopter, for example, on the fuselage of the helicopter.
  • the master device receives signals from feedback sensors of the azimuth position of the HB blades and the angle of installation of the HB blades (angle of attack of the HB blades).
  • each azimuthal position of the HB blade corresponds to a specific position of the HB blade installation angle (depending on the helicopter flight mode).
  • electrical signals from the driver to the electromagnets (and from feedback sensors to the driver) can be transmitted, for example, through a rotating current collector of known designs (for example, as in known electric motors), or in any other acceptable way.
  • any type of it can be used: a spool of any type (flat end (as shown in FIG. 1 ⁇ 8 and described above); cylindrical; and more.); valve; and other.
  • a bladed part-turn hydraulic motor which performs the function of an individual drive for controlling the angle of installation of the HB blade, can have any acceptable muyu design: cap type (as shown in FIG.1 ⁇ -8 and described above); reel type; etc.
  • a bladed part-turn hydraulic motor can have any acceptable number of blades (and the corresponding number of working chambers): one; two (as shown in FIG. 1- ⁇ -8 and described above); more than two.
  • the claimed invention may have any acceptable number of hydraulic pumps; one; two (as shown in FIG. 1 ⁇ -8 and described above); more than two.
  • the claimed invention may have any acceptable number of filters for cleaning the working fluid; one; two; more than two.
  • the claimed invention may have any acceptable number of HB blades: one (for example, with a counterweight, as in known helicopters with a single-bladed main rotor); two (as shown in FIG. 1- ⁇ 8 and described above); more than two.
  • the claimed invention may have a HB sleeve. having either only axial hinges (as shown in FIG. 1- ⁇ -8 and described above), or a three-hinged HB sleeve.
  • the location of the hinges on the HB hub should be as follows (starting from the axis of rotation of the HB): axial hinge (in which the above-mentioned individual drive for controlling the angle of installation of the HB blade) - horizontal hinge - vertical hinge.
  • the claimed invention can be used on HB: helicopters of all schemes (single-rotor (as shown in FIG.1 ⁇ -8 and described above); coaxial; synchropters (with crossed rotors); transverse scheme; longitudinal scheme; multi-rotor; and more); gyroplanes; rotorcraft; and other.
  • the claimed invention can also be used on: aircraft propellers; ship propellers; wind turbine screws lei; and other.
  • valve body in which hydraulic pumps, filters, check and safety valves, a hydraulic accumulator, and other necessary hydraulic equipment are located
  • the valve body can be attached to the HB sleeve body in any acceptable way: by bolting (as shown in FIG.1- ⁇ 8 and described above) ; by pressing the valve body into the body of the HB bushing and additional bolting to the body of the HB bushing; and other.
  • a variant of the claimed invention is possible, which differs from that shown in FIG. above option) are located on the HB sleeve. And all the rest of the above hydraulic equipment (two hydraulic pumps, filters, check and safety valves, a hydraulic accumulator, a container with a working fluid, etc.) are located outside the HB sleeve - on a non-rotating part of the helicopter, for example, on the main gearbox housing or on the helicopter fuselage. In this embodiment of the claimed invention, there are two pipelines arranged in a pipe-in-pipe pattern.
  • One of the pipelines located inside the HB shaft, serves to supply the working fluid under excess pressure from the source (from the above hydraulic pumps located on the non-rotating part of the helicopter) to the above spools, and further into the working chambers of the above rotary vane hydraulic motors.
  • the second pipeline drain channel formed by the outer surface of the above first pipeline and the inner surface of the HB shaft (HB shaft represents is a pipe, the inner diameter of which is larger than the outer diameter of the above first pipeline - between them there is a well-defined gap necessary for the passage of the required amount of working fluid), serves to drain the spent (in the working chambers of rotary vane hydraulic motors) working fluid into a container with working liquid (located on the non-rotating part of the helicopter).
  • a variant of execution is possible, which differs from that described above in that there are more than two pipelines (made according to the pipe-in-pipe scheme) (for example, there are two supply pipelines, and two (or one) drain pipelines).
  • the above first pipeline can be made. Or rotating together with the HB shaft (that is, it is made stationary relative to the HB shaft and the HB bushing), while the lower end of this pipeline is connected to a fixed (relative to the main gearbox housing and the helicopter fuselage) pipeline (connected to a source of working fluid - to the outlet of hydraulic pump), for example, by means of a mechanical seal of known designs.
  • a variant of the claimed invention is possible, which differs from that shown in FIG. At the same time, it can have any acceptable shape (along the trajectory of the pusher rollers along it): flat (as shown - but in FIG.1 ⁇ 8 and described above); wavy (like a washboard); and other.
  • a possible embodiment of the claimed invention differs from that shown in FIG. side of the left (advancing) quarter of the HB disk).
  • the mechanism that controls the spools can be of any acceptable design: as shown in FIG. l 8 and described above; and other.
  • the channels connecting the working chambers of the rotary vane hydraulic motors with spools can be laid in any acceptable place in the design of the rotary vane hydraulic motors: as shown in FIG.1- ⁇ -8 and described above; and other.
  • the spool can be pressed against the pusher, and the pusher against the control washer, in any suitable way: by means of a compression spring (as shown in FIG. 1- ⁇ 8 and described above); by means of a torsion spring; hydraulic cylinder; and other.
  • the claimed invention bladed semi-rotary hydraulic motors can be mounted on the main rotor hub in any suitable place: built into the axial hinges of the main rotor hub (as shown in FIG.1- ⁇ 8 and described above); and other.
  • FIG.1- ⁇ 8 shows a schematic diagram of the implementation of the claimed invention, and the above describes some of the possible options for its specific design. Other embodiments of the claimed invention are also possible.
  • the main thing in the claimed invention is that as an individual drive for controlling the angles of installation of the HB blades, it is used, its own for each blade HB, part-turn vane hydraulic motor built into the design of the axial hinge of the HB bushing (as one of the possible versions).
  • the claimed invention can be used on rotors: helicopters of all schemes (single-rotor; coaxial; synchropters (with crossed rotors); transverse scheme; longitudinal scheme; multi-rotor; and more); gyroplanes; rotorcraft; and other.
  • the claimed invention can also be used on: aircraft propellers; ship propellers; wind turbine screws; and other.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention se rapporte au domaine de l'aviation et notamment à des structures d'hélices porteuses pour hélicoptères. Cette hélice porteuse d'hélicoptère comprend un insert d'hélice porteuse et des pales d'hélice porteuse. L'insert d'hélice porteuse comprend un corps et des articulations axiales, une pour chaque pale de l'hélice porteuse. Chaque pale de l'hélice porteuse est réalisée de manière à ce que son angle de fixation puisse être commandé individuellement via son moteur hydraulique à rotation incomplète de la pale. Chacun des moteurs hydrauliques à rotation incomplète est disposé sur l'insert de l'hélice porteuse, intégré dans l'articulation axiale de sa pale de l'hélice porteuse, et peut interagir avec ledit corps d'insert de l'hélice porteuse et avec sa pale de l'hélice porteuse. L'insert de l'hélice porteuse comprend également un récipient avec un liquide de travail, un clapet à tiroir, une pompe hydraulique, un filtre, lesquels assurent le fonctionnement desdits moteurs hydrauliques à rotation incomplète de la pale.
PCT/RU2021/000007 2021-01-12 2021-01-12 Hélice porteuse WO2022154684A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/RU2021/000007 WO2022154684A1 (fr) 2021-01-12 2021-01-12 Hélice porteuse

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Application Number Priority Date Filing Date Title
PCT/RU2021/000007 WO2022154684A1 (fr) 2021-01-12 2021-01-12 Hélice porteuse

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WO2022154684A1 true WO2022154684A1 (fr) 2022-07-21

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0911994A (ja) * 1995-06-30 1997-01-14 Mitsubishi Heavy Ind Ltd ヘリコプタロータのピッチ制御装置
EP1262403A2 (fr) * 2001-05-23 2002-12-04 ZF Luftfahrttechnik GmbH Dispositif de commande individuelle des pales d'un rotor
RU2305648C2 (ru) * 2005-05-23 2007-09-10 Иван Никифорович Хамин Движитель
RU2375612C1 (ru) * 2008-04-21 2009-12-10 Открытое акционерное общество "Павловский машиностроительный завод ВОСХОД" - ОАО "ПМЗ ВОСХОД" Лопастной неполноповоротный гидродвигатель
US20160340034A1 (en) * 2013-03-14 2016-11-24 Bell Helicopter Textron Inc. Jam-Tolerant Rotary Control Motor for Hydraulic Actuator Valve
RU2740717C1 (ru) * 2020-07-24 2021-01-20 Валерий Туркубеевич Пчентлешев Винт, например несущий винт вертолета

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0911994A (ja) * 1995-06-30 1997-01-14 Mitsubishi Heavy Ind Ltd ヘリコプタロータのピッチ制御装置
EP1262403A2 (fr) * 2001-05-23 2002-12-04 ZF Luftfahrttechnik GmbH Dispositif de commande individuelle des pales d'un rotor
RU2305648C2 (ru) * 2005-05-23 2007-09-10 Иван Никифорович Хамин Движитель
RU2375612C1 (ru) * 2008-04-21 2009-12-10 Открытое акционерное общество "Павловский машиностроительный завод ВОСХОД" - ОАО "ПМЗ ВОСХОД" Лопастной неполноповоротный гидродвигатель
US20160340034A1 (en) * 2013-03-14 2016-11-24 Bell Helicopter Textron Inc. Jam-Tolerant Rotary Control Motor for Hydraulic Actuator Valve
RU2740717C1 (ru) * 2020-07-24 2021-01-20 Валерий Туркубеевич Пчентлешев Винт, например несущий винт вертолета

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