A kind of aircraft rotor power device

Abstract

An embodiment of the present invention provides an aircraft rotor power device, which innovatively installs blades on a flapping and pitch-changing coupling shaft of an intermediate connecting member, and is provided with a second end through hole and a second end groove for installing the blades on the flapping and pitch-changing coupling shaft, and a blade clamp lower seat is fixedly installed on the intermediate shaft of a rotary drive device, and the intermediate connecting member can be installed on both sides of the left and right sides of the blade clamp lower seat, and the intermediate connecting member and the blades are fixedly installed and connected through an upper cover of the blade clamp. The device is designed with a flapping and pitch-changing coupling shaft, so that when the aircraft flies forward, the lift of the lift device on the left and right sides of the forward direction tends to be balanced, thereby greatly reducing the vibration caused by lift imbalance, and because the flapping and pitch-changing coupling shaft and the blades are connected by a hinge, under the action of pitch change, the blades always work at a higher aerodynamic efficiency point when rotating 360 degrees, thereby greatly improving the aerodynamic efficiency of the device, saving energy consumption and extending the flight time.

Description

Technical Field

[0001] The present invention relates to the field of aviation flight technology, in particular to an aircraft rotor power device. Background Art

[0002] UAVs are aircraft that are controlled by radio remote control equipment and self-contained program control devices, or are completely or intermittently autonomously operated by on-board computers. They have wide application value in aerial photography, agriculture, plant protection, express delivery, disaster relief, wildlife observation, surveying and mapping, and other fields. Among them, the rationality of the propeller design of UAVs is crucial to the performance of UAVs. Currently, the propellers on the market generally have integrated propellers and folding propellers. These propellers are used in aviation aircraft as lift components. When the aircraft maneuvers forward, backward, left and right, the propeller vibrates more, the efficiency becomes lower, and the flight control effect becomes worse. The larger vibration is transmitted to the body or sensor, and in severe cases, it may even cause the aircraft to explode, affecting flight safety and personnel safety. This greatly restricts the scope and use scenarios of the aircraft and affects the development of aviation. Multi-rotor aircraft generally use multiple propellers, and the size of the propeller lift is changed by controlling the speed of each propeller, so as to achieve the purpose of controlling the aircraft's attitude and flight movements. At present, the lift systems used in most multi-rotor aircraft are generally integrated propellers or folding propellers. The integrated propellers are fixed in the three rotation directions of flapping, swinging and twisting. The folding propellers can rotate in the swinging direction, but are also fixed in the flapping and twisting directions. This type of fixed support will cause a relatively large bending moment when the aircraft is maneuvering, and the force on each blade will be different. Due to the asymmetric force, it will cause greater vibration. At the same time, the fixed pitch will also make the propeller less efficient and the control effect worse when the aircraft is maneuvering. In view of the above problems, the present invention designs an aircraft rotor power device that can effectively solve the problem of excessive vibration when the aircraft is maneuvering or flying against wind, and at the same time effectively improves the aerodynamic efficiency and control efficiency of the aircraft when the aircraft is maneuvering or flying against wind. The device is designed with a rotating shaft that couples the flapping motion and torsional motion of the blades. That is, when the blades flap and rotate up and down, the pitch of the blades will also change, thereby adaptively changing the size of the blade lift, making the pulling force of each blade of the propeller more balanced, achieving the purpose of reducing vibration, and also improving the aerodynamic efficiency of the propeller.

[0003] In view of the above problems, it is urgent to propose an aircraft rotor power device that can balance the lift on the left and right sides of the rotor lift system in the forward direction during forward flight, reduce the vibration caused by lift imbalance, and make the blades always work at a higher aerodynamic efficiency point when rotating 360 degrees, thereby improving the aerodynamic efficiency of the rotor lift system, saving energy and extending the flight time of the aircraft. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide an aircraft rotor power device, which is designed with a flapping variable pitch coupling shaft, so that when the aircraft flies forward, the lift of the lift device on the left and right sides of the forward direction tends to be balanced, greatly reducing the vibration caused by lift imbalance. Since the flapping variable pitch coupling shaft and the blades are connected by a hinge, under the action of variable pitch, the blades always work at a higher aerodynamic efficiency point when rotating 360 degrees, which greatly improves the aerodynamic efficiency of the device, saves energy and prolongs the flight time.

[0005] In order to solve the above problems, the present invention provides an aircraft rotor power device, including a rotary drive device, a propeller clamp lower seat, a propeller clamp upper cover, an intermediate connecting piece and a propeller blade, wherein the rotary drive device is composed of a driving body, a mounting hole and an intermediate rotating shaft, the four mounting holes are located at the upper end surface of the driving body, the intermediate rotating shaft is located at the middle position of the upper end surface of the driving body, the propeller clamp lower seat is composed of a lower seat body, a lower seat mounting countersunk hole, a lower seat side through hole, a lower seat middle through hole and a lower seat connecting hole, the lower seat mounting countersunk hole is a circular countersunk hole structure and is located at both sides of the upper end of the lower seat body, the lower seat side through hole is a circular through hole structure and is located The middle position of the lower seat installation countersunk hole, the middle through hole of the lower seat is a circular through hole structure and is located on the lower seat body, the lower seat connecting holes are four through hole structures and are located around the middle through hole of the lower seat, the paddle clamp upper cover is composed of the upper cover body, the upper cover side through holes, the upper cover countersunk hole and the upper cover middle through hole, the upper cover side through holes are circular through hole structures and are located on both sides of the upper cover body, the upper cover countersunk hole is a circular countersunk hole and is on the same center of the circle as the upper cover side through holes, the upper cover middle through hole is a circular through hole structure and is located at both ends of the paddle clamp upper cover, the intermediate connecting piece is composed of the first end connecting block, the first end through hole, the swinging pitch coupling shaft ... The propeller blade is composed of two end through holes and a second end groove, the first end connecting block is a cylindrical structure and is fixedly connected to the swinging pitch coupling shaft, the first end through hole is a circular through hole structure and is located in the middle of the upper end surface of the first end connecting block, the second end through hole is a circular through hole structure and passes through the front and rear end surfaces of the swinging pitch coupling shaft, the second end groove is a rectangular groove structure and is located at the outer circular end surface of the second end through hole, the blade is composed of a blade mounting block, a blade mounting hole and a blade blade, the blade mounting block is fixedly connected to the blade blade, the blade mounting hole is a circular through hole structure and passes through the front and rear end surfaces of the blade mounting block, The paddle clamp lower seat and the rotary drive device are connected by being installed on the intermediate rotating shaft through the middle through hole of the lower seat, and the intermediate connecting piece and the paddle clamp lower seat are connected by installing the rotating shaft in the through holes of the first end through hole and the lower seat mounting countersunk hole, the paddle clamp upper cover is installed at the upper end position of the intermediate connecting piece, the upper cover side through hole of the paddle clamp upper cover is installed on the first end through hole, the upper cover middle through hole of the paddle clamp upper cover is installed on the intermediate rotating shaft, the blade is installed on the second end groove of the intermediate connecting piece through the blade mounting block, the blade mounting hole of the blade cooperates with the second end through hole and is connected by a hinge, and the blade can rotate around the hinge.

[0006] According to an aircraft rotor power device provided by the present invention, the axis of the blade mounting hole of the blade forms an angle with the direction of the centrifugal force to which the blade is subjected when rotating, and the angle ranges from 5° to 175°.

[0007] According to an aircraft rotor power device provided by the present invention, the axial direction of the through hole at the first end of the intermediate connecting member forms an angle with the horizontal plane, and the angle is greater than 45° and less than or equal to 90°.

[0008] According to an aircraft rotor power device provided by the present invention, the axial direction of the through hole at the second end of the intermediate connecting member forms an angle with the direction of the centrifugal force exerted on the blade when it rotates, and the angle is greater than 5 degrees and less than 175 degrees.

[0009] According to an aircraft rotor power device provided by the present invention, the intermediate connecting member is rotatably connected to the blade via the second end through hole; the intermediate connecting member and the blade can rotate around the axis of the second end through hole, so that the blade is folded along the rotation direction or unfolded along the rotation direction.

[0010] According to an aircraft rotor power device provided by the present invention, at least two of the intermediate connecting members are connected to the blades, and each of the intermediate connecting members is connected to one of the blades.

[0011] The beneficial effects of the present invention are as follows: in order to achieve a more balanced pulling force on each blade of a propeller, reduce vibration and improve the aerodynamic efficiency of the propeller, the aircraft rotor power device described in the present invention has two or more intermediate connecting parts clamped between the propeller clamp lower seat and the propeller clamp upper cover, and the intermediate connecting parts are connected to the propeller clamp lower seat and the propeller clamp upper cover by means of a hole and an axis assembly, and a through hole is provided at the first end through hole of the intermediate connecting part, and the direction of the through hole can be perpendicular to the horizontal plane, or can have a certain angle with the horizontal plane. Since the first end through hole of the intermediate connecting part is connected by means of a hole and an axis assembly, the intermediate connecting part can rotate around the rotating axis of the connection position. Furthermore, the blade mounting block of the blade is connected to the through hole at the second end of the intermediate connector by assembling the hole and the shaft, so that the blade folding function of the device can be realized. During the rotation of the blade, the blade can swing up and down and change pitch around the rotating shaft at the assembly position. Because the rotating shaft forms a certain angle with the centrifugal force direction of the intermediate connector, the blade will change the windward angle of the propeller while swinging up and down, i.e., change pitch. In addition, a blade mounting hole is designed at the tail of the blade, which is connected to the through hole at the second end of the intermediate connector. The centerline direction of the through hole of the blade mounting hole is parallel to the horizontal plane, but forms a certain angle with the direction of the centrifugal force to which the blade is subjected during rotation. The aircraft rotor power device innovatively installs the blades on the flapping and pitch-changing coupling shaft of the intermediate connecting piece, and is provided with a second end through hole and a second end groove for installing the blades on the flapping and pitch-changing coupling shaft. The blade clamp lower seat is fixedly installed on the intermediate shaft of the rotary drive device, and the intermediate connecting piece can be installed on both sides of the left and right sides of the blade clamp lower seat. The intermediate connecting piece and the blades are fixedly connected and installed through the blade clamp upper cover. The device is designed with a flapping and pitch-changing coupling shaft, so that when the aircraft flies forward, the lift of the lift device on the left and right sides of the forward direction tends to be balanced, which greatly reduces the vibration caused by lift imbalance. Since the flapping and pitch-changing coupling shaft and the blades are connected by a hinge, under the action of pitch change, the blades always work at a higher aerodynamic efficiency point when rotating 360 degrees, which greatly improves the aerodynamic efficiency of the device, can save energy and extend the flight time. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] The specific embodiments of the present invention are further described in detail below in conjunction with the accompanying drawings, wherein:

[0013] Figure 1 This is a schematic diagram of the overall structure of an aircraft rotor power device of the present invention;

[0014] Figure 2 It is a schematic diagram of the overall structure of an aircraft rotor power device of the present invention when viewed from above;

[0015] Figure 3This is a schematic diagram of the overall structure of a rotary drive device of an aircraft rotor power device of the present invention;

[0016] Figure 4 It is a schematic diagram of the overall structure of a rotor blade power device of an aircraft according to the present invention and a blade clamp lower seat thereof;

[0017] Figure 5 It is a schematic diagram of the overall structure of a propeller clamp upper cover of an aircraft rotor power device of the present invention;

[0018] Figure 6 It is a schematic diagram of the overall structure of the propeller clamp upper cover of an aircraft rotor power device of the present invention in another direction;

[0019] Figure 7 This is a schematic diagram of the overall structure of an intermediate connecting member of an aircraft rotor power device of the present invention;

[0020] Figure 8 The figure is a schematic diagram of the overall structure of an intermediate connecting member of an aircraft rotor power device of the present invention in a top view, wherein α is the angle between the center line of the circular hole of the second end through hole of the intermediate connecting member and the direction of the centrifugal force it is subjected to when rotating;

[0021] Fig. 9 The present invention is a schematic diagram of the overall structure of a blade of an aircraft rotor power device.

[0022] In the figure: 1, rotary drive device; 2, paddle clamp lower seat; 3, paddle clamp upper cover; 4, intermediate connecting piece; 5, paddle blade; 101, driving body; 102, mounting hole; 103, intermediate rotating shaft; 201, lower seat body; 202, lower seat mounting countersunk hole; 203, lower seat side through hole; 204, lower seat middle through hole; 205, lower seat connecting hole; 301, upper cover body; 302, upper cover side through hole; 303, upper cover countersunk hole; 304, upper cover middle through hole; 401, first end connecting block; 402, first end through hole; 403, swinging pitch coupling rotating shaft; 404, second end through hole; 405, second end groove; 501, paddle blade mounting block; 502, paddle blade mounting hole; 503, paddle blade. DETAILED DESCRIPTION

[0023] like Figures 1 to 9 As shown, Figure 1 This is a schematic diagram of the overall structure of an aircraft rotor power device of the present invention; Figure 2 It is a schematic diagram of the overall structure of an aircraft rotor power device of the present invention when viewed from above; Figure 3 This is a schematic diagram of the overall structure of a rotary drive device of an aircraft rotor power device of the present invention; Figure 4 It is a schematic diagram of the overall structure of a rotor blade power device of an aircraft according to the present invention and a blade clamp lower seat thereof; Figure 5It is a schematic diagram of the overall structure of a propeller clamp upper cover of an aircraft rotor power device of the present invention; Figure 6 It is a schematic diagram of the overall structure of the propeller clamp upper cover of an aircraft rotor power device of the present invention in another direction; Figure 7 This is a schematic diagram of the overall structure of an intermediate connecting member of an aircraft rotor power device of the present invention; Figure 8 The figure is a schematic diagram of the overall structure of an intermediate connecting member of an aircraft rotor power device of the present invention in a top view, wherein α is the angle between the center line of the circular hole of the second end through hole of the intermediate connecting member and the direction of the centrifugal force it is subjected to when rotating; Fig. 9 This is a schematic diagram of the overall structure of the blades of an aircraft rotor power device of the present invention. Figures 1 to 9In the illustrated embodiment, an aircraft rotor power device includes a rotary drive device 1, a propeller clamp lower seat 2, a propeller clamp upper cover 3, an intermediate connecting piece 4 and a propeller blade 5. The rotary drive device 1 is composed of a driving body 101, a mounting hole 102 and an intermediate rotating shaft 103. The four mounting holes 102 are located at the upper end surface of the driving body 101, and the intermediate rotating shaft 103 is located at the middle position of the upper end surface of the driving body 101. The propeller clamp lower seat 2 is composed of a lower seat body 201, a lower seat mounting countersunk hole 202, a lower seat side through hole 203, a lower seat middle through hole 204 and a lower seat connecting hole 205. The lower seat mounting countersunk hole 202 is a circular countersunk hole structure and is located on both sides of the upper end of the lower seat body 201. The lower seat side through hole 203 is a circular through hole structure and is located at the lower seat mounting The middle position of the countersunk hole 202, the middle through hole 204 of the lower seat is a circular through hole structure and is located on the lower seat body 201, the lower seat connecting holes 205 are four through hole structures and are located around the middle through hole 204 of the lower seat, the paddle clamp upper cover 3 is composed of the upper cover body 301, the upper cover side through hole 302, the upper cover countersunk hole 303 and the upper cover middle through hole 304, the upper cover side through hole 302 is a circular through hole structure and is located on both sides of the upper cover body 301, the upper cover countersunk hole 303 is a circular countersunk hole and is on the same center of the circle as the upper cover side through hole 302, the upper cover middle through hole 304 is a circular through hole structure and is located at both ends of the paddle clamp upper cover 3, the intermediate connecting piece 4 is composed of the first end connecting block 401, the first end through hole 402, the swinging pitch coupling shaft 403, the first end through hole 404, the first end through hole 405, the first end through hole 406, the first end through hole 407, the first end through hole 408, the first end through hole 409, the first end through hole 410, the first end through hole 411, the first end through hole 412, the first end through hole 413, the first end through hole 414, the first end through hole 415, the first end through hole 416, the first end through hole 417, the first end through hole 418, the first end through hole 419, the first end through hole 420, the first end through hole 421, the first end through hole 422, the first end through hole 423, the first end through hole 424, the first end through hole 425, the first end through hole 426, the first end through hole 42 The blade 5 is composed of a blade mounting block 501, a blade mounting hole 502 and a blade blade 503. The blade mounting block 501 is a cylindrical structure and is fixedly connected to the swinging pitch coupling shaft 403. The first end through hole 402 is a circular through hole structure and is located in the middle of the upper end surface of the first end connecting block 401. The second end through hole 404 is a circular through hole structure and passes through the front and rear end surfaces of the swinging pitch coupling shaft 403. The second end groove 405 is a rectangular groove structure and is located at the outer circular end surface of the second end through hole 404. The blade 5 is composed of a blade mounting block 501, a blade mounting hole 502 and a blade blade 503. The blade mounting block 501 is fixedly connected to the blade blade 503. The blade mounting hole 502 is a circular through hole structure and passes through the front and rear ends of the blade mounting block 501. The paddle clamp lower seat 2 and the rotary drive device 1 are connected by being installed on the intermediate rotating shaft 103 through the middle through hole 204 of the lower seat, and the intermediate connecting member 4 and the paddle clamp lower seat 2 are connected by installing the rotating shaft in the through hole of the first end through hole 402 and the lower seat mounting countersunk hole 202, the paddle clamp upper cover 3 is installed at the upper end position of the intermediate connecting member 4, the upper cover side through hole 302 of the paddle clamp upper cover 3 is installed on the first end through hole 402, the upper cover middle through hole 304 of the paddle clamp upper cover 3 is installed on the intermediate rotating shaft 103, the blade 5 is installed on the second end groove 405 of the intermediate connecting member 4 through the blade mounting block 501, the blade mounting hole 502 of the blade 5 cooperates with the second end through hole 404 and is connected by a hinge, and the blade 5 can rotate around the hinge.

[0024] Specifically, the axis of the blade mounting hole 502 of the blade 5 forms an angle with the direction of the centrifugal force to which the blade 5 is subjected when rotating, and the angle range is between 5°-175°. The axis direction of the through hole 402 at the first end of the intermediate connector 4 forms an angle with the horizontal plane, and the angle is greater than 45° and ≤90. The axis direction of the through hole 404 at the second end of the intermediate connector 4 forms an angle with the direction of the centrifugal force to which the blade 5 is subjected when rotating, and the angle is greater than 5 degrees and less than 175 degrees. The intermediate connector 4 is rotatably connected to the blade 5 through the through hole 404 at the second end; the intermediate connector 4 and the blade 5 can rotate around the axis of the through hole 404 at the second end, so that the blade 5 is folded in the direction of rotation or unfolded in the direction of rotation. At least two intermediate connectors 4 are connected to the blade 5, and each intermediate connector 4 is connected to one blade 5.

[0025] The difference between the aircraft rotor power device and the existing lift device is that, in order to achieve a more balanced pulling force on each blade of the propeller, reduce vibration and improve the aerodynamic efficiency of the propeller, the device has two or more intermediate connecting parts 4 clamped between the propeller clamp lower seat 2 and the propeller clamp upper cover 3, and the intermediate connecting part 4 is connected to the propeller clamp lower seat 2 and the propeller clamp upper cover 3 by means of a hole and an axis assembly. A through hole is provided in the first end through hole 402 of the intermediate connecting part 4. Since the first end through hole 402 of the intermediate connecting part 4 is connected by means of a hole and an axis assembly, the intermediate connecting part 4 can rotate around the rotating axis of the connection position. Furthermore, the blade mounting block 501 of the blade 5 is also connected to the through hole 404 at the second end of the intermediate connector 4 by means of a hole and shaft assembly, so that the blade 5 of the device can rotate. During the rotation of the blade 5, the blade 5 can swing up and down and change pitch around the rotating shaft at the assembly position. Because the rotating shaft forms a certain angle with the centrifugal force direction of the intermediate connector 4, the blade 5 will also change the windward angle of the propeller while swinging up and down, i.e., change pitch. In addition, a blade mounting hole 502 is designed at the root of the blade 5, which is connected to the through hole 404 at the second end of the intermediate connector 4. The through hole centerline direction of the blade mounting hole 502 is parallel to the horizontal plane, but forms a certain angle with the centrifugal force direction to which the blade 5 is subjected during rotation. The aircraft rotor power device innovatively installs the blade 5 on the swinging pitch-changing coupling shaft 403 of the intermediate connecting member 4, and is provided with a second end through hole 404 and a second end groove 405 for installing the blade 5 on the swinging pitch-changing coupling shaft 403. The blade clamp lower seat 2 is fixedly installed on the intermediate shaft 103 of the rotary drive device 1. The intermediate connecting member 4 can be installed on both sides of the left and right sides of the blade clamp lower seat 2. The intermediate connecting member 4 and the blade 5 are fixedly installed and connected through the blade clamp upper cover 3. The device is designed with a swinging pitch-changing coupling shaft 403, so that when the aircraft flies forward, the lift of the lift device on the left and right sides of the forward direction tends to be balanced, which greatly reduces the vibration caused by lift imbalance. Since the swinging pitch-changing coupling shaft 403 and the blade 5 are connected by a hinge, under the action of pitch change, the blade 5 always works at a higher aerodynamic efficiency point when rotating 360 degrees, which greatly improves the aerodynamic efficiency of the device, can save energy consumption and extend the flight time.

[0026] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge scope of ordinary technicians in this field without departing from the purpose of the present invention.

Claims

1. An aircraft rotor power device, characterized in that: It includes a rotary drive device, a paddle clamp lower seat, a paddle clamp upper cover, an intermediate connecting piece and a paddle blade. The rotary drive device is composed of a driving body, a mounting hole and an intermediate rotating shaft. The four mounting holes are located at the upper end surface of the driving body, and the intermediate rotating shaft is located at the middle position of the upper end surface of the driving body. The paddle clamp lower seat is composed of a lower seat body, a lower seat mounting countersunk hole, a lower seat side through hole, a lower seat middle through hole and a lower seat connecting hole. The lower seat mounting countersunk hole is a circular countersunk hole structure and is located at both sides of the upper end of the lower seat body. The lower seat side through hole is a circular through hole structure and is located in the middle position of the lower seat mounting countersunk hole. The lower seat middle through hole is a circular through hole structure and is located on the lower seat body. The lower seat connecting holes are four through hole structures and are located around the lower seat middle through hole. Position, the paddle clamp upper cover is composed of an upper cover body, a side through hole of the upper cover, a countersunk hole of the upper cover and a middle through hole of the upper cover, the side through holes of the upper cover are circular through hole structures and are located on both sides of the upper cover body, the countersunk holes of the upper cover are circular countersunk holes and are on the same center of a circle as the side through holes of the upper cover, the middle through hole of the upper cover is a circular through hole structure and is located at both ends of the paddle clamp upper cover, the intermediate connecting piece is composed of a first end connecting block, a first end through hole, a swinging pitch coupling shaft, a second end through hole and a second end groove, the first end connecting block is a cylindrical structure and is fixedly connected to the swinging pitch coupling shaft, the first end through hole is a circular through hole structure and is located in the middle of the upper end surface of the first end connecting block, the second end through hole is a circular through hole structure and passes through The front and rear end faces of the swinging pitch coupling shaft, the second end groove is a rectangular groove structure and is located at the outer circular end face position of the second end through hole, the blade is composed of a blade mounting block, a blade mounting hole and a blade blade, the blade mounting block is fixedly connected to the blade blade, the blade mounting hole is a circular through hole structure and passes through the front and rear end faces of the blade mounting block, the blade clamp lower seat and the rotary drive device are installed on the intermediate rotating shaft through the middle through hole of the lower seat, the intermediate connecting piece and the blade clamp lower seat are connected by installing the rotating shaft in the through hole of the first end through hole and the lower seat mounting countersunk hole, the blade clamp upper cover is installed at the upper end position of the intermediate connecting piece, the upper cover side through hole of the blade clamp upper cover is installed on the first end through hole, and the middle of the upper cover of the blade clamp upper cover The through hole is installed on the intermediate rotating shaft, and the blade is installed on the groove of the second end of the intermediate connecting member through the blade mounting block. The blade mounting hole of the blade cooperates with the through hole of the second end and is connected by a hinge. The blade can rotate around the hinge, and the axis of the blade mounting hole of the blade forms an angle with the direction of the centrifugal force to which the blade is subjected when rotating, and the angle range is between 5°-175°. The axial direction of the through hole at the first end of the intermediate connecting member forms an angle with the horizontal plane, and the angle is greater than 45° and ≤90°. The axial direction of the through hole at the second end of the intermediate connecting member forms an angle with the direction of the centrifugal force to which the blade is subjected when rotating, and the angle is greater than 5 degrees and less than 175 degrees.

2. An aircraft rotor power device according to claim 1, characterized in that: The intermediate connecting member is rotatably connected to the blade via the second end through hole; the intermediate connecting member and the blade can rotate around the axis of the second end through hole, so that the blade is folded along the rotation direction or unfolded along the rotation direction.

3. An aircraft rotor power device according to claim 1, characterized in that: At least two of the intermediate connecting members are connected to the blades, and each of the intermediate connecting members is connected to one of the blades.

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