Electrically-controlled variable-pitch aircraft propeller

Abstract

According to the electrically-controlled variable-pitch aircraft propeller, when the propeller pitch angle of the movable propeller blade needs to be adjusted, a control host is communicated with an electrical loop through a conductive slip ring to control the forward / reverse rotation action of a speed reducing motor so as to drive a driving gear, a driven gear, a worm and gear set and a rotating shaft to achieve controllable rotation of the movable propeller blade; therefore, the synchronous adjustment of the pitch angles of the movable paddles is completed. The device is simple in structure, high in reliability and low in maintenance cost. The problems that a variable pitch propeller is easy to damage, difficult to maintain and high in cost in a high-pressure lubricating oil driving mode can be better solved, meanwhile, the rotating shafts of the movable blades are of a two-end shaft hole distributed stress structure, and under the condition that mechanical performance strength redundancy is guaranteed, the diameter of the rotating shafts can be reduced, and the purpose of reducing the weight of a propeller hub unit assembly can be achieved.

Description

Technical Field

[0001] 1. The utility model belongs to the field of aerospace technology and relates to a variable pitch aircraft propeller, more specifically an electrically controlled variable pitch aircraft propeller. Background Art

[0002] 2. Variable pitch propellers, a variable pitch drive driven by high-pressure lubricating oil is installed inside the hub. The control system can adjust the pitch angle of the blade within a certain range through the high-pressure lubricating oil variable pitch drive, so that the propeller and the engine can operate under high-efficiency conditions. At the same time, when the aircraft needs to brake for landing, the high-pressure lubricating oil variable pitch drive can control the propeller to form a reverse propeller to quickly reduce the aircraft speed. In the windmill state, the high-pressure lubricating oil variable pitch drive can also make the propeller feather to reduce the flight resistance caused by the windmill state. Through the action of the high-pressure lubricating oil variable pitch drive, the sealing surface at the hub and the blade mounting hole will have a low-speed rotation swing to cooperate with the pitch adjustment. The sealing surface is installed with a sealing ring to achieve the sealing of the variable pitch drive return oil chamber inside the hub. During use, foreign objects such as sand and dust often invade the sealing ring position, causing wear on the hub sealing surface. The wear at this position often causes the oil leakage to accelerate, and then the oil leakage will cause dry friction at this position, resulting in a vicious cycle.

[0003] 3. In summary, the prior art method of using high-pressure lubricating oil to drive a variable pitch propeller is vulnerable, difficult to maintain and expensive. Therefore, how to solve the problem of the prior art of using high-pressure lubricating oil to drive a variable pitch propeller being vulnerable, difficult to maintain and expensive is a technical problem that those skilled in the art need to solve urgently. Summary of the invention

[0004] 4. In order to solve the above technical problems, the utility model provides an electrically controlled variable pitch aircraft propeller.

[0005] 5. To achieve the above purpose, the utility model provides the following solutions:

[0006] 6. The utility model provides an electrically controlled variable pitch aircraft propeller, comprising: an outer tube, an inner tube, a bottom plate, a flange plate, a top plate, an axis hole, a rotating shaft, a worm gear set, a driven gear, a driving gear, a reduction motor, a blade, a driving shaft, a conductive slip ring, a mounting plate, a control host, a connecting cable, and a power device;

[0007] 7. The outer tube, the inner tube and the bottom plate are fixedly connected at the corresponding positions to form a rigid main structure of the hub. The outer tube and the inner tube are coaxial. Coaxial and through-type shaft holes are evenly arranged at the corresponding positions of the outer tube and the inner tube. The axis of the shaft hole is 90 degrees perpendicular to the axis of the inner tube. The root of the blade is fixedly connected to one end of the rotating shaft to form a movable blade. The movable blade is rotatably connected to the shaft hole through the rotating shaft. The flange plate is fixedly connected to the corresponding position of the inner tube. The worm wheel of the worm gear group is fixedly connected to the corresponding position of the rotating shaft. The worm of the worm gear group is respectively connected to the flange plate and the bottom plate. The corresponding bearing inner holes of the plate are movably connected, and the driven gears are fixedly connected to the corresponding shaft heads of the worms of the worm gear set respectively; the top plate is fixedly connected to the corresponding positions of the outer tube, a reduction motor is fixedly arranged at the corresponding positions of the top plate, and a driving gear is fixedly arranged on the output shaft of the reduction motor; the driving gear is meshed with the driven gear; a mounting plate is fixedly arranged at the corresponding position of the front end of the power device of the aircraft; the two ends of the conductive slip ring are fixedly connected to the corresponding positions of the bottom plate and the mounting plate respectively; the front end of the driving shaft of the power device passes through the mounting plate, the conductive slip ring, the bottom plate, and is then fixedly connected to the inner hole of the inner tube;

[0008] 8. The corresponding rotating shaft passes through the corresponding axial hole of the outer tube and the corresponding axial hole of the inner tube to form a two-point distributed force structure;

[0009] 9. The two ends of the corresponding connecting cable are electrically connected to the output terminal of the conductive slip ring and the input terminal of the reduction motor respectively; the two ends of the corresponding connecting cable are electrically connected to the input terminal of the conductive slip ring and the output terminal of the control host respectively;

[0010] 10. When the pitch angle of the movable blades of the electrically controlled variable pitch aircraft propeller needs to be adjusted, the control host controls the reduction motor to drive forward / reverse through the corresponding connecting cables, conductive slip rings, and corresponding connecting cables. The reduction motor drives the driving gear, the driven gear, and the worm gear group to drive the shaft and the blades to rotate, and the movable blades are locked after the pitch angle is adjusted to the right position.

[0011] 11. Compared with the prior art, the utility model has achieved the following technical effects:

[0012] 12. The utility model is an electrically controlled variable pitch aircraft propeller. When the pitch angle of the movable blades needs to be adjusted, the electrical circuit is connected through a conductive slip ring to control the forward / reverse rotation of the reduction motor to drive the driving gear, the driven gear, the worm gear set, and the rotating shaft to achieve controllable rotation of the movable blades, thereby completing the synchronous adjustment of the pitch angles of each movable blade.

[0013] 13. With such a configuration, compared with the method of high-pressure lubricating oil drive, the utility model provides an electrically controlled variable pitch aircraft propeller, which controls the forward / reverse rotation of the reduction motor by connecting the electrical circuit through a conductive slip ring to drive the driving gear, the driven gear, and the worm gear assembly to drive the rotating shaft to realize the controllable rotation of the movable blades, thereby achieving the effect of synchronously adjusting the pitch angle of the movable blades. It has a simple structure, high reliability, and low maintenance cost. At the same time, the rotating shaft of the movable blade adopts a distributed force structure with shaft holes at both ends, which can reduce the diameter of the rotating shaft and reduce the weight of the hub unit assembly while ensuring the strength redundancy of the mechanical performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] 14. The accompanying drawings illustrate exemplary embodiments of the present invention and are used to explain the principles of the present invention together with the description. These drawings are included to provide a further understanding of the present invention, and the drawings are included in and constitute a part of this specification.

[0015] 15. Figure 1 It is a left-side overall structural schematic diagram of an embodiment of the utility model;

[0016] 16. Figure 2 This is a schematic diagram of the overall structure of an embodiment of the utility model;

[0017] 17. Figure 3 The utility model embodiment is Figure 1 A schematic diagram of the enlarged structure of the middle A area;

[0018] 18. Figure 4 This is the electrical schematic diagram of the embodiment of the utility model;

[0019] 19. Explanation of reference numerals:

[0020] 20.1-outer tube; 2-inner tube; 3-bottom plate; 4-flange plate; 5-top plate; 6-shaft hole; 7-rotating shaft; 8-worm gear set; 9-driven gear; 10-driving gear; 11-reduction motor; 12-blade; 13-drive shaft; 14-conductive slip ring; 15-mounting plate; 16-control host; 17-connecting cable; 18-power unit; DETAILED DESCRIPTION

[0021] 21. The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of them. Based on the embodiments of the utility model, all other embodiments obtained by other technicians in the field without creative work are within the scope of protection of the utility model.

[0022] 22. In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0023] 23.Reference Figure 1-Figure 4 As shown, an electrically controlled variable pitch aircraft propeller provided in an embodiment of the utility model is introduced.

[0024] 24. Specifically, it includes: 1-outer tube; 2-inner tube; 3-bottom plate; 4-flange plate; 5-top plate; 6-shaft hole; 7-rotating shaft; 8-worm gear set; 9-driven gear; 10-driving gear; 11-reduction motor; 12-blade; 13-driving shaft; 14-conductive slip ring; 15-mounting plate; 16-control host; 17-connecting cable; 18-power device;

[0025] 25. The outer tube 1, the inner tube 2 and the bottom plate 3 are fixedly connected at the corresponding positions to form a rigid main structure of the hub. The outer tube 1 and the inner tube 2 are coaxial. Coaxial and through-type shaft holes 6 are evenly arranged at the corresponding positions of the outer tube 1 and the inner tube 2. The axis of the shaft hole 6 is 90° perpendicular to the axis of the inner tube 2. The root of the blade 12 is fixedly connected to one end of the rotating shaft 7 to form a movable blade. The movable blade is rotatably connected to the shaft hole 6 through the rotating shaft 7. The flange plate 4 is fixedly connected to the corresponding position of the inner tube 2. The worm wheel of the worm gear set 8 is fixedly connected to the corresponding position of the rotating shaft 7. The worm of the worm gear set 8 is respectively connected to the corresponding axes of the flange plate 4 and the bottom plate 3. The inner hole of the bearing is movably connected, and the driven gear 9 is fixedly connected to the corresponding shaft head of the worm of the worm gear set 8; the top plate 5 is fixedly connected to the corresponding position of the outer tube 1, and the reduction motor 11 is fixedly arranged at the corresponding position of the top plate 5, and the output shaft of the reduction motor 11 is fixedly arranged with a driving gear 10; the driving gear 10 is meshed with the driven gear 9; the mounting plate 15 is fixedly arranged at the corresponding position of the front end of the power device 18 of the aircraft; the two ends of the conductive slip ring 14 are fixedly connected to the corresponding positions of the bottom plate 3 and the mounting plate 15 respectively; the front end of the driving shaft 13 of the power device 18 passes through the mounting plate 15, the conductive slip ring 14, the bottom plate 3 and then is fixedly connected to the inner hole of the inner tube 2;

[0026] 26. The corresponding rotating shaft 7 passes through the corresponding axial hole 6 of the outer tube 1 and the corresponding axial hole 6 of the inner tube 2 to form a two-point distributed force structure;

[0027] 27. The two ends of the corresponding connecting cable 17 are electrically connected to the output terminal of the conductive slip ring 14 and the input terminal of the reduction motor 11 respectively; the two ends of the corresponding connecting cable 17 are electrically connected to the input terminal of the conductive slip ring 14 and the output terminal of the control host 16 respectively;

[0028] 28. When the pitch angle of the movable blade of the electrically controlled variable pitch aircraft propeller needs to be adjusted, the control host 16 controls the reduction motor 11 to perform forward / reverse driving action through the corresponding connecting cable 17, the conductive slip ring 14, and the corresponding connecting cable 17. The reduction motor 11 drives the driving gear 10, the driven gear 9, and the worm gear set 8 to drive the rotating shaft 7 and the blade 12 to perform a rotation action, and the movable blade is locked after the pitch angle is adjusted to the right position.

[0029] 29. This specification uses specific examples to illustrate the principles and implementation methods of the utility model. The above examples are only used to help understand the method and core idea of ​​the utility model. At the same time, for those skilled in the art, according to the idea of ​​the utility model, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the utility model.

[0030] 30. It should be understood by those skilled in the art that the above embodiments are only for the purpose of clearly illustrating the present invention, and are not intended to limit the scope of the present invention. For those skilled in the art, other changes or modifications may be made based on the above disclosure, and these changes or modifications are still within the scope of the present invention.

Claims

1. An electrically controlled variable pitch aircraft propeller, characterized in that: The outer tube (1), the inner tube (2) and the bottom plate (3) are fixedly connected at corresponding positions to form a rigid main body structure of the hub. The outer tube (1) and the inner tube (2) are coaxial. Coaxial and through-type shaft holes (6) are evenly arranged at corresponding positions of the outer tube (1) and the inner tube (2). The axis of the shaft hole (6) is perpendicular to the axis of the inner tube (2) at 90 degrees. The root of the blade (12) is fixedly connected to one end of the rotating shaft (7) to form a movable blade. The movable blade is rotatably connected to the shaft hole (6) through the rotating shaft (7). The flange plate (4) is fixedly connected to the corresponding position of the inner tube (2). The worm wheel of the worm gear group (8) is fixedly connected to the corresponding position of the rotating shaft (7). The worm of the worm gear group (8) is respectively connected to the corresponding bearing inner ends of the flange plate (4) and the bottom plate (3). The top plate (5) is fixedly connected to the corresponding position of the outer tube (1), a reduction motor (11) is fixedly arranged at the corresponding position of the top plate (5), and a driving gear (10) is fixedly arranged on the output shaft of the reduction motor (11); the driving gear (10) is meshed with the driven gear (9); a mounting plate (15) is fixedly arranged at the corresponding position of the front end of the power device (18) of the aircraft; two ends of the conductive slip ring (14) are fixedly connected to the corresponding positions of the bottom plate (3) and the mounting plate (15); the front end of the driving shaft (13) of the power device (18) passes through the mounting plate (15), the conductive slip ring (14), the bottom plate (3), and is then fixedly connected to the inner hole of the inner tube (2).

2. The electrically controlled variable pitch aircraft propeller according to claim 1, characterized in that: The corresponding rotating shaft (7) passes through the corresponding axial hole (6) of the outer tube (1) and the corresponding axial hole (6) of the inner tube (2) to form a two-point distributed force structure.

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