Blade variable pitch driving mechanism for coaxial reverse propeller rotor

Abstract

The invention relates to a blade variable pitch driving mechanism for a coaxial reverse propeller rotor. The control host independently controls the corresponding synchronous speed reduction motors of the positive and negative layers of variable pitch propeller groups to rotate forwards / backwards through a conductive slip ring and slip group contact connection type electrical loop to drive the corresponding worm gears / worms to drive the corresponding movable blades to synchronously adjust the pitch angle and lock the pitch angle; according to the coaxial reverse-pitch variable-pitch driving mechanism, in a fly-by-wire flight control mode that variable-pitch driving is carried out on movable blades by a worm gear / worm integrated in a propeller hub through a touch connection type electrical loop and a synchronous gear motor, the axial occupied size of the coaxial reverse-pitch variable-pitch driving mechanism is greatly reduced, meanwhile, the blade variable-pitch effect is achieved, and the coaxial reverse-pitch variable-pitch driving mechanism is simple in structure, compact in layout, high in reliability and low in maintenance cost; meanwhile, under the condition that mechanical performance strength redundancy is guaranteed, the shaft diameter of the overhanging type main shaft and related matched assemblies can be optimized and reduced, the weight of the whole driving unit assembly is further reduced, and the energy efficiency ratio of the aircraft is increased.

Description

Technical Field

[0001] 1. This invention belongs to the field of aerospace technology and relates to a blade pitch-changing drive mechanism for a coaxial counter-rotating rotor. Background Technology

[0002] 2. Coaxial counter-rotating propellers refer to power transmission devices that use a shared drive shaft to drive two layers of rotors rotating in opposite directions. Because the torques generated by the two sets of rotors can cancel each other out under coaxial conditions, the stability is high. Since the first-layer rotor can provide aerodynamic pre-compression for the second-layer rotor, the coaxial counter-rotating drive form has better aerodynamic performance. At the same time, the distance between the two layers of rotors will affect the overall aerodynamic efficiency. Variable pitch propellers usually use variable pitch actuators to adjust the pitch angle of the movable blades within a certain range through external mechanical drive components, so that the propeller and the power unit (engine / motor) can operate under high-efficiency conditions. Specifically: ① The variable pitch propeller uses an external pitch actuator to drive and adjust the pitch angle of the movable blades. The external pitch actuator uses a coaxial rotating mechanical component set outside the hub to implement the pitch drive, which requires a large axial dimension, resulting in a large distance between the two rotor layers, thus reducing the overall aerodynamic efficiency; ② The variable pitch propeller uses an external pitch actuator to drive and adjust the pitch angle of the movable blades. The coaxial rotating drive mechanism set outside the hub is an exposed and unprotected rotating pure mechanical structure, which is easily damaged and requires high maintenance; ③ The two rotor layers adopt a cantilevered main shaft structure, that is, the hubs of the two rotor layers are fixedly installed at the shaft ends of the forward and reverse rotation output shafts of the coaxial counter-rotating propeller actuator. Since the mechanical component of the external coaxial rotating mechanism of the pitch actuator occupies a large axial space dimension, the coaxial counter-rotating propeller actuator needs to use a larger diameter output shaft and larger related transmission components, thus increasing the unit weight of the entire variable pitch drive unit.

[0003] 3. In summary, the existing method for coaxial counter-rotating rotors to implement blade pitch control using an external pitch actuator suffers from significant drawbacks: large axial dimensions, low overall aerodynamic efficiency, high maintenance requirements, and a heavy overall weight of the pitch actuator unit. Therefore, addressing these issues—large axial dimensions, low overall aerodynamic efficiency, high maintenance requirements, and a heavy overall weight of the pitch actuator unit—is a crucial technical challenge that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0004] 4. To solve the above technical problems, the present invention provides a blade pitch-changing drive mechanism for a coaxial counter-rotating rotor.

[0005] 5. To achieve the above objectives, the present invention provides the following solution: 6. Specifically, the first-stage variable-pitch propeller assembly and the second-stage variable-pitch propeller assembly are fixedly connected to the front ends of the main shaft and hollow shaft of the coaxial reverse propeller actuator, respectively; one end of conductive slip ring I is fixedly connected to the top of the housing of the coaxial reverse propeller actuator, and the other end of conductive slip ring I is fixedly connected to the rear end of the second-stage variable-pitch propeller assembly; one end of conductive slip ring II is fixedly connected to the front end of the second-stage variable-pitch propeller assembly, and the other end of conductive slip ring II is fixedly connected to the rear end of the first-stage variable-pitch propeller assembly. 7. The conductive slip ring I, the second layer of variable pitch propeller assembly, the conductive slip ring II, and the first layer of variable pitch propeller assembly are coaxial with the main shaft; 8. The variable pitch propeller assembly is composed of an outer tube, an inner tube, a base plate, a top plate, blades, a shaft, a worm gear, a worm, and a synchronous geared motor. 9. More specifically, the impeller hub is a rigid body composed of an outer tube, an inner tube, a base plate, and a top plate, which are fixedly connected at corresponding positions. The outer tube and the inner tube are coaxial. The root of the impeller blade is fixedly connected to one end of the shaft to form a movable impeller blade. The corresponding shaft is rotatably connected to the shaft holes at corresponding positions of the outer tube and the inner tube. The inner hole of the turbine is fixedly connected to the corresponding position of the shaft. The corresponding positions at both ends of the worm gear are rotatably connected to the corresponding bearing inner holes of the base plate and the top plate, respectively. A synchronous reduction motor is fixedly installed at a corresponding position on the base plate corresponding to the worm gear. The output shaft of the corresponding synchronous reduction motor is fixedly connected coaxially to the shaft end of its corresponding worm gear. The corresponding worm gear meshes with its corresponding turbine. 10. Connecting cable I has its two ends electrically connected to the input terminal of conductive slip ring I and the output terminal of the control host, respectively; connecting cable II has its two ends electrically connected to the corresponding output terminal of conductive slip ring I and the corresponding input terminal of the synchronous geared motor, respectively; connecting cable III passes through the corresponding through hole of the second layer variable pitch propeller assembly, and its two ends are electrically connected to the corresponding output terminal of conductive slip ring I and the input terminal of conductive slip ring II, respectively; connecting cable IV has its two ends electrically connected to the output terminal of conductive slip ring II and the corresponding input terminal of the synchronous geared motor, respectively. 11. When the control host needs to adjust the pitch angle of the movable blades of the first-stage variable-pitch propeller assembly, the control host controls the corresponding synchronous geared motor to perform forward / reverse rotation via connecting cable I, conductive slip ring I, connecting cable III, conductive slip ring II, and connecting cable IV. The corresponding synchronous geared motor drives the corresponding worm gear and worm wheel to rotate the corresponding shaft and blades, and locks the motor after the pitch angle of the corresponding movable blade is adjusted to the correct position. When the control host needs to adjust the pitch angle of the movable blades of the second-stage variable-pitch propeller assembly, the control host controls the corresponding synchronous geared motor to perform forward / reverse rotation via connecting cable I, conductive slip ring I, and connecting cable II. The corresponding synchronous geared motor drives the corresponding worm gear and worm wheel to rotate the corresponding shaft and blades, and locks the motor after the pitch angle of the corresponding movable blade is adjusted to the correct position.

[0006] 12. The shaft and blades of the corresponding movable blades are driven independently by their corresponding synchronous geared motors, turbines, and worm gears with variable pitch. 13. The present invention achieves the following technical effects compared to the prior art: 14. A coaxial counter-rotating rotor blade pitch-changing drive mechanism of the present invention, wherein the main control unit independently controls the forward / reverse rotation of the corresponding synchronous reduction motors of the two layers of variable pitch propellers through a conductive sliding ring contact-type electrical circuit, thereby driving the corresponding worm gear / worm to drive the corresponding movable blades to synchronously adjust the blade pitch angle and lock them. That is, the fly-by-wire flight control mode of using a contact-type electrical circuit + synchronous reduction motor to drive the movable blades through the worm gear / worm integrated in the rotor hub, which greatly reduces the axial size occupied by the coaxial counter-rotating rotor pitch-changing drive mechanism.

[0007] 15. Compared to the existing technology of using an external pitch actuator to implement blade pitch change in coaxial counter-rotating rotors, this invention provides a blade pitch change drive mechanism for coaxial counter-rotating rotors. The control host independently controls the forward / reverse rotation of the corresponding synchronous geared motors of the two layers of variable pitch propellers through a conductive slip ring contact-type electrical circuit, driving the corresponding worm gear / worm to drive the corresponding movable blades to synchronously adjust the blade pitch angle and lock them. That is, the fly-by-wire flight control mode uses a contact-type electrical circuit + synchronous geared motor to drive the worm gear / worm integrated in the rotor hub to drive the movable blades for pitch change. It achieves the effect of blade pitch change while significantly reducing the axial size of the coaxial counter-rotating pitch change drive mechanism. Its structure is simple, compact, reliable, and has low maintenance costs. At the same time, while ensuring mechanical performance strength redundancy, the shaft diameter of the cantilevered main shaft and related components can be optimized and reduced to further reduce the weight of the entire drive unit assembly and improve the energy efficiency ratio of the aircraft. Attached Figure Description

[0008] 16. The accompanying drawings illustrate exemplary embodiments of the invention and, together with the description thereof, serve to explain the principles of the invention. These drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification.

[0009] 17. Figure 1 This is a top view of the overall structure of an embodiment of the present invention; 18. Figure 2 This is a frontal view of the overall structure of an embodiment of the present invention; 19. Figure 3 Embodiments of the present invention Figure 1 Enlarged structural diagram of region A in the middle; 20. Figure 4 This is an electrical schematic diagram of an embodiment of the present invention; 21. Explanation of reference numerals in the attached drawings: 22.1-Coaxial counter-rotating propeller drive; 2-Main control unit; 3-Conductive slip ring I; 4-Variable pitch propeller assembly; 5-Conductive slip ring II; 6-Synchronous geared motor; 7-Main shaft; 8-Hollow shaft; 9-Rotating shaft; 10-Propeller blade; 11-Base plate; 12-Outer tube; 13-Inner tube; 14-Top plate; 15-Worm gear; 16-Connecting cable I; 17-Connecting cable II; 18-Connecting cable III; 19-Connecting cable IV; 20-Worm gear; Detailed Implementation

[0010] 23. The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by other people skilled in the art without creative effort are within the scope of protection of the present invention.

[0011] 24. To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0012] 25.Reference Figures 1-4 As shown, the arrow points forward, illustrating a coaxial counter-rotating rotor blade pitch-changing drive mechanism provided in this embodiment of the invention.

[0013] 26. Specifically, the first-stage variable-pitch propeller assembly 4 and the second-stage variable-pitch propeller assembly 4 are fixedly connected to the front ends of the main shaft 7 and the hollow shaft 8 of the coaxial counter-rotating propeller actuator 1, respectively; one end of the conductive slip ring I3 is fixedly connected to the top of the housing of the coaxial counter-rotating propeller actuator 2, and the other end of the conductive slip ring I3 is fixedly connected to the rear end of the second-stage variable-pitch propeller assembly 4; one end of the conductive slip ring II5 is fixedly connected to the front end of the second-stage variable-pitch propeller assembly 4, and the other end of the conductive slip ring II5 is fixedly connected to the rear end of the first-stage variable-pitch propeller assembly 4. 27. The conductive slip ring I3, the second layer variable pitch propeller assembly 4, the conductive slip ring II5, and the first layer variable pitch propeller assembly 4 are coaxial with the main shaft 7; 28. The variable pitch propeller assembly 4 is composed of an outer tube 12, an inner tube 13, a base plate 11, a top plate 14, a blade 10, a rotating shaft 9, a worm gear 15, a worm 20, and a synchronous geared motor 6. 29. More specifically, a rigid hub is formed by the fixed connection and assembly of the outer tube 12, inner tube 13, base plate 11, and top plate 14 at corresponding positions. The outer tube 12 and inner tube 13 are coaxial. The root of the blade 10 is fixedly connected to one end of the rotating shaft 9 to form a movable blade. The corresponding rotating shaft 9 is rotatably connected to the shaft holes at corresponding positions of the outer tube 12 and inner tube 13. The inner hole of the turbine 15 is fixedly connected to the corresponding position of the rotating shaft 9. The corresponding positions at both ends of the worm gear 20 are rotatably connected to the corresponding bearing inner holes of the base plate 11 and top plate 14, respectively. A synchronous reduction motor 6 is fixedly installed at the corresponding position of the base plate 11 corresponding to the worm gear 20. The output shaft of the corresponding synchronous reduction motor 6 is fixedly connected coaxially to the shaft end of its corresponding worm gear 20. The corresponding worm gear 20 meshes with its corresponding turbine 15. 30. The two ends of connecting cable I16 are electrically connected to the input terminal of conductive slip ring I3 and the output terminal of control host 2, respectively; the two ends of connecting cable II17 are electrically connected to the corresponding output terminal of conductive slip ring I3 and the corresponding input terminal of synchronous geared motor 6, respectively; connecting cable III18 passes through the corresponding through hole of the second layer variable pitch propeller assembly 4, and the two ends of connecting cable III18 are electrically connected to the corresponding output terminal of conductive slip ring I3 and the input terminal of conductive slip ring II5, respectively; the two ends of connecting cable IV19 are electrically connected to the output terminal of conductive slip ring II5 and the corresponding input terminal of synchronous geared motor 6, respectively. 31. When the control host 2 needs to adjust the pitch angle of the movable blades of the first-level variable-pitch propeller assembly 4, the control host 2 controls the corresponding synchronous geared motor 6 to perform forward / reverse rotation driving action through connecting cable I 16, conductive slip ring I 3, connecting cable III 18, conductive slip ring II 5, and connecting cable IV 19. The corresponding synchronous geared motor 6 drives the corresponding worm 20 and worm wheel 15 to drive the corresponding shaft 9 and blade 10 to perform rotational action, and locks it after the pitch angle of the corresponding movable blade is adjusted to the correct position. When the control host 2 needs to adjust the pitch angle of the movable blades of the second-level variable-pitch propeller assembly 4, the control host 2 controls the corresponding synchronous geared motor 6 to perform forward / reverse rotation driving action through connecting cable I 16, conductive slip ring I 3, and connecting cable II 17. The corresponding synchronous geared motor 6 drives the corresponding worm 20 and worm wheel 15 to drive the corresponding shaft 9 and blade 10 to perform rotational action, and locks it after the pitch angle of the corresponding movable blade is adjusted to the correct position.

[0014] 32. The shaft 9 and blade 10 of the corresponding movable blades are driven independently by their corresponding synchronous geared motors 6, turbines 15 and worm gears 20 with variable pitch. 33. This specification uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. Furthermore, those skilled in the art will recognize that, based on the ideas of the present invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of the present invention.

[0015] 34. Those skilled in the art should understand that the above embodiments are merely for clearly illustrating the present invention and are not intended to limit the scope of the invention. Those skilled in the art can make other changes or modifications based on the above disclosure, and these changes or modifications still fall within the scope of the present invention.

Claims

1. A variable-pitch drive mechanism for a coaxial counter-rotating rotor, characterized in that: The first-stage variable-pitch propeller assembly (4) and the second-stage variable-pitch propeller assembly (4) are fixedly connected to the front ends of the main shaft (7) and hollow shaft (8) of the coaxial reverse propeller driver (1), respectively; one end of the conductive slip ring I (3) is fixedly connected to the top of the housing of the coaxial reverse propeller driver (2), and the other end of the conductive slip ring I (3) is fixedly connected to the rear end of the second-stage variable-pitch propeller assembly (4); one end of the conductive slip ring II (5) is fixedly connected to the front end of the second-stage variable-pitch propeller assembly (4), and the other end of the conductive slip ring II (5) is fixedly connected to the rear end of the first-stage variable-pitch propeller assembly (4); the variable-pitch propeller assembly (4) is composed of an outer tube (12), an inner tube (13), a bottom plate (11), a top plate (14), a blade (10), a rotating shaft (9), a worm gear (15), a worm (20), and a synchronous geared motor (6).

2. The coaxial counter-rotating rotor blade pitch-changing drive mechanism according to claim 1, characterized in that: The impeller hub is a rigid body composed of an outer tube (12), an inner tube (13), a bottom plate (11), and a top plate (14) fixedly connected at corresponding positions. The outer tube (12) and the inner tube (13) are coaxial. The root of the impeller blade (10) is fixedly connected to one end of the rotating shaft (9) to form a movable impeller blade. The corresponding rotating shaft (9) is rotatably connected to the shaft holes at corresponding positions of the outer tube (12) and the inner tube (13). The inner hole of the turbine (15) is fixedly connected to the corresponding position of the rotating shaft (9). The corresponding positions at both ends of the worm gear (20) are rotatably connected to the corresponding bearing inner holes of the bottom plate (11) and the top plate (14). A synchronous reduction motor (6) is fixedly installed at the corresponding position of the bottom plate (11) corresponding to the worm gear (20). The output shaft of the corresponding synchronous reduction motor (6) is fixedly connected coaxially to the shaft end of its corresponding worm gear (20). The corresponding worm gear (20) meshes with its corresponding turbine (15).

3. The coaxial counter-rotating rotor blade pitch-changing drive mechanism according to claim 2, characterized in that: The shaft (9) and blade (10) of the corresponding movable blade are driven independently by their corresponding synchronous geared motor (6), turbine (15) and worm gear (20).

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