Universal cycloid spindle blade rotor lifting device

Abstract

The invention discloses a universal cycloid spindle blade rotor lifting device, and relates to the technical field of unmanned aerial vehicles. The universal cycloid spindle paddle rotor wing lifting device comprises a shell, a main shaft, a main taper sleeve, a main paddle, an auxiliary paddle and a universal adjusting mechanism. The universal adjusting mechanism comprises a conical fluted disc, a paddle connecting shaft, a driven bevel gear, an electromagnetic telescopic sleeve A, an electromagnetic telescopic sleeve B and a driving control module; the main paddle and the auxiliary paddle are installed at the two ends of the paddle connecting shaft, each paddle is of a spindle-shaped structure with the surface being a cycloid curved surface, the middle of each paddle is thickened, and the edge of each paddle is provided with a flow guide edge protruding outwards. The driving control module controls the two groups of electromagnetic telescopic sleeves to synchronously push and pull to force the paddle connecting shaft to axially translate so as to drive the driven bevel gear to be instantly meshed with or separated from the bevel gear disc on the main shaft; transient micro-adjustment of the attack angle of the blade is achieved through a pure mechanical structure of rigid meshing of the electromagnetic clutch and the gear, the cycloid gradual change pneumatic curved surface is matched, response delay is effectively overcome, blade tip vortex is restrained, and the anti-crosswind stability and the heavy load structure rigidity under complex turbulence are improved.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a universal cycloidal spindle rotor lifting device. Background Technology

[0002] With the deepening development of the low-altitude economy, drones, as key space operation equipment, have been widely used in low-altitude logistics delivery, high-voltage line inspection, field environmental monitoring, and heavy-load transportation. In these high-frequency and complex operational scenarios, the rotor lifting device, as the core power equipment that provides lift and controls flight attitude, directly determines the operational safety and operational boundaries of the drone due to its aerodynamic efficiency, wind resistance stability, and structural load-bearing capacity. Since the low-altitude environment is often accompanied by complex nonlinear airflows such as building shear winds and valley gusts, extremely high mechanical coordination requirements are placed on the aerodynamic surface design and dynamic attitude adjustment mechanism of the lifting device.

[0003] Existing rotor lift devices have undergone numerous structural design explorations. For example, Chinese patent document CN111776208B discloses "an aircraft and its rotor head assembly." This existing technical solution mainly includes a power unit with an output shaft, multiple propellers, and a transmission assembly. Its main working principle is to accelerate or decelerate the rotation of the power unit, which, in conjunction with the rotating shaft with an angle and the transmission assembly, drives the propellers to deflect around the rotating shaft, thereby changing the angle between the blade profile chord and the plane of rotation. This physical structure, which relies on acceleration and deceleration combined with a purely mechanical linkage to achieve unidirectional pitch change, solves to some extent the problem of difficult attitude adjustment of traditional fixed-pitch propellers and meets the basic flight control requirements under normal conditions.

[0004] However, the aforementioned existing technologies still have significant structural defects when dealing with complex low-altitude turbulence and high-load operations. First, their attitude adjustment relies heavily on the speed change of the main propulsion motor to passively achieve pitch change. This coupled mechanical transmission has serious response lag, and the uniaxial hinged structure cannot achieve all-round, blind-angle transient dynamic deflection, resulting in poor crosswind stability. Second, the structure generally uses traditional straight blades, which are prone to airflow separation and severe tip vortices on the blade surface when subjected to deflection forces, resulting in violent fluctuations in lift and large energy loss. In addition, the load distribution of traditional straight blades is uneven, and stress is excessively concentrated at the blade root. Under heavy loads or violent maneuvers, fatigue deformation is likely to occur, and the structural rigidity is insufficient to support the requirements of heavy-load operations. Furthermore, the overall structure lacks active airflow guidance and attachment optimization structures, making it unsuitable for high-precision fixed-point hovering tasks under complex airflow conditions. Summary of the Invention

[0005] To address the shortcomings of existing rotor lifting devices, such as response lag and poor crosswind stability caused by passive pitch adjustment relying on a main motor for acceleration and deceleration, as well as the tendency of traditional straight blades to generate airflow separation and tip vortices under complex airflow conditions, and the inability of structural rigidity to support heavy-load operations, this invention provides a universal cycloidal spindle blade rotor lifting device. It achieves active adjustment of the blade's slight deflection through a mechanical linkage structure with electromagnetically driven gear meshing, and optimizes the lift and load distribution by combining the aerodynamic blade shape.

[0006] The technical solution adopted by this invention to solve its technical problem is: A universal cycloidal spindle rotor lifting device includes: a housing; a main shaft passing through the housing; a main conical sleeve disposed at the end of the main shaft; a main blade and an auxiliary blade; and a universal adjustment mechanism. The universal adjustment mechanism is the core mechanical component for realizing dynamic adjustment of the blade attitude, including a bevel gear disk, a blade connecting shaft, a driven bevel gear, an electromagnetic telescopic sleeve A, an electromagnetic telescopic sleeve B, and a drive control module. The main blade and the auxiliary blade are respectively installed at both ends of the blade connecting shaft, and the driven bevel gear is fixedly sleeved on the blade connecting shaft. The electromagnetic telescopic sleeve A and the electromagnetic telescopic sleeve B are respectively disposed at both ends of the blade connecting shaft. The drive control module is electrically connected to the electromagnetic telescopic sleeve A and the electromagnetic telescopic sleeve B, respectively, and is used to control the movement of the two sets of electromagnetic telescopic sleeves, causing the blade connecting shaft to move axially, thereby driving the driven bevel gear on it to mesh or disengage with the bevel gear disk, realizing a minute adjustment of the deflection angle of each blade.

[0007] Furthermore, the bevel gear disk is coaxially sleeved outside the main shaft, and the blade connecting shaft passes through the main bevel sleeve in a direction perpendicular to the main shaft axis. When the electromagnetic telescopic sleeve A is energized and extends while the electromagnetic telescopic sleeve B simultaneously shortens, it drives the blade connecting shaft to translate to one side, causing the driven bevel gear to engage rigidly in the tooth groove of the bevel gear disk; when the power is de-energized and reset, the blade connecting shaft returns to center, and the driven bevel gear disengages from the bevel gear disk.

[0008] Furthermore, in order to ensure precise guidance of translation and telescopic movement, both electromagnetic telescopic sleeve A and electromagnetic telescopic sleeve B include an outer shell, an internal electromagnetic coil, and a return spring; the two ends of the blade connecting shaft are respectively movably inserted into the armature ends of both; the outer wall of the main cone sleeve is symmetrically provided with limiting guide holes for the extension and retraction of the armature.

[0009] Furthermore, the main blade and the auxiliary blade are integrally spindle-shaped, with cycloidal surfaces whose curvature changes linearly from the blade root to the blade tip to optimize airflow adhesion. The thickness of the middle part of the main blade and the auxiliary blade is twice the thickness of the blade tip, and the blade edges are provided with integrally formed guide edges; the cross-section of the guide edges is arc-shaped and protrudes outward from the blade, with the inner surface smoothly transitioning to the cycloidal surface of the blade.

[0010] Furthermore, both the main blade and the auxiliary blade are provided with reinforcing ribs extending along the blade length direction. One end of the reinforcing rib is fixedly connected to the blade root, and the other end extends to the blade tip. The cross-section of the reinforcing rib is circular, and the diameter of the reinforcing rib gradually decreases from the blade root to the blade tip, so that the blade's resistance to deformation matches the force distribution.

[0011] Furthermore, the bottom end of the spindle extends to the outside of the housing and is connected to a drive assembly, which includes a brushless DC motor and heat dissipation fins on the housing; the outside of the housing is also equipped with an air-cooling system consisting of a cooling fan and an air guide shroud, with the air guide shroud covering the outside of the heat dissipation fins to guide airflow for forced heat dissipation.

[0012] This invention also provides a cycloidal spindle rotor lifting system based on the above-mentioned device, comprising a data acquisition module, a drive control module, and a cycloidal adjustment execution module. The data acquisition module collects environmental aerodynamic parameters and fuselage attitude parameters in real time during the operation of the rotor lifting device; the drive control module is communicatively connected to the data acquisition module and generates micro-blade deflection adjustment commands based on the received parameters; the cycloidal adjustment execution module receives and responds to the adjustment commands, realizing dynamic wind resistance correction of the system attitude.

[0013] Furthermore, the data acquisition module includes a pressure sensor and a UAV attitude sensor embedded within the mechanism; the drive control module has a built-in storage unit and a data processing module, with the storage unit pre-stored with a wind-resistant control algorithm program. The communication module connects to an external flight control system via a CAN bus interface, and a cable with a metal shielding layer enables low-latency hardware command interaction.

[0014] Furthermore, the system operation coordination logic of the omnidirectional adjustment execution module is as follows: When the data processing module calls the wind-resistant control algorithm program to calculate the deflection angle that needs to be compensated, the drive control module sends an excitation drive electrical signal. The drive control module energizes electromagnetic telescopic sleeve A to apply thrust, and simultaneously energizes electromagnetic telescopic sleeve B to apply tension, causing axial displacement of the blade connecting shaft, which drives the driven bevel gear to mesh with the bevel gear disc. Under the power of the main shaft rotation, the driven bevel gear rotates along the bevel gear disk, which in turn drives the blade connecting shaft to rotate, adjusting the deflection angle of the main blade and the auxiliary blade in a purely mechanical transmission manner. When the target deflection angle is reached, the drive control module sends a power-off reset signal to electromagnetic telescopic sleeve A and electromagnetic telescopic sleeve B. The armature returns to its original position under the action of the reset spring, and the driven bevel gear disengages, completing a single micro-adjustment action of the blade.

[0015] Compared with the prior art, the beneficial effects of the present invention are: Compared with existing technologies that rely on passive pitch control via a main motor for acceleration and deceleration, this invention significantly improves the response speed of attitude adjustment and crosswind stability. The device innovatively employs a purely mechanical clutch transmission structure combining an electromagnetic telescopic sleeve and a gear set. The control module precisely applies excitation signals to control the extension and retraction of electromagnetic telescopic sleeves A and B, causing axial displacement of the blade connecting shaft, which in turn drives the driven bevel gear to rigidly mesh with the bevel gear disc. This structure cleverly utilizes the powerful mechanical force of the main shaft's rotation and directly converts it into the driving force for blade deflection, completely eliminating the transmission lag caused by main motor speed regulation. Simultaneously, this electromagnetically triggered, purely physical gear adjustment mechanism enables transient, high-frequency, micro-adjustments to the blade deflection angle, allowing for dynamic attitude correction with extremely high mechanical response speed when facing complex low-altitude turbulence and shear winds, significantly enhancing the lifting device's crosswind resistance.

[0016] To address the shortcomings of traditional straight blades, which are prone to airflow separation and severe tip vortices under deflection forces, this invention significantly optimizes aerodynamic efficiency and reduces lift fluctuations and energy loss. The main and auxiliary blades are designed as special cycloidal spindle-shaped structures, with the curvature of the cycloidal surface changing linearly with the radius. This gradually changing surface, conforming to fluid dynamics principles, effectively suppresses airflow stripping during high-speed rotation and changes in angle of attack. Simultaneously, the integrally formed outward-protruding arc-shaped guide edge of the blade forces the airflow to smoothly adhere to the blade surface, minimizing tip vortex generation from an aerodynamic perspective. This optimized shape significantly improves airflow adhesion, effectively smoothing out severe lift fluctuations in complex turbulent environments and significantly reducing ineffective air resistance work, thereby improving the overall mechanical power conversion efficiency of the device.

[0017] To address the problems of uneven load distribution and excessive stress concentration at the root of existing straight blades, leading to insufficient structural rigidity under heavy loads, this invention effectively enhances the load-bearing rigidity and reliability of the device during high-load operations. This device breaks away from the conventional design limitations of uniform blade thickness, setting the thickness of the blade's middle section to three times that of the tip, significantly strengthening the structural compressive strength of the core stress-bearing area from a macroscopic perspective. Combined with internal circular reinforcing ribs extending along the blade's length and gradually decreasing in diameter from the root to the tip, a gradually changing rigid skeleton conforming to the stress gradient is constructed from the inside out. This stress-distributed solid structure design perfectly matches the physical stress distribution of the rotor during heavy-load hovering and violent maneuvers, fundamentally overcoming the potential for fatigue deformation at the blade root, and providing a solid hardware foundation and structural support for high-load transportation and high-precision stationary hovering. Attached Figure Description

[0018] The present invention will be further described below with reference to the accompanying drawings and embodiments: Figure 1 This is a structural diagram of the universal adjustment mechanism of the present invention; Figure 2 This is a perspective view A of the present invention; Figure 3 This is a cross-sectional view A of the present invention; Figure 4 This is a cross-sectional view B of the present invention; Figure 5 This is a cross-sectional view C of the present invention; Figure 6 This is perspective view B of the present invention; Figure 7 This is a flowchart of the control module of the present invention.

[0019] Reference numerals: 1. Housing; 2. Main shaft; 3. Main blade; 4. Secondary blade; 5. Main cone sleeve; 6. Universal adjustment mechanism; 61. Bevel gear disc; 62. Blade connecting shaft; 63. Driven bevel gear; 64. Electromagnetic telescopic sleeve A; 65. Electromagnetic telescopic sleeve B; 66. Drive control module. Detailed Implementation

[0020] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that the following embodiments are only used to explain the principle of cooperation between the purely mechanical transmission structure and pneumatic hardware of the present invention, and do not constitute a limitation on the scope of protection of the present invention.

[0021] Please refer to the accompanying drawings. The universal cycloidal spindle rotor lifting device provided by the present invention includes a housing 1, a main shaft 2 passing through the inside of the housing 1, and a main cone sleeve 5 fixedly installed at the top of the main shaft 2.

[0022] 1. Structure of pneumatic propeller assembly The main blade 3 and the auxiliary blade 4 are the components that provide aerodynamic lift to the device. The blades are spindle-shaped variable cross-section structures with cycloidal surfaces designed using pure physical fluid dynamics. The curvature of the surface changes linearly from the blade root to the blade tip with respect to the radius. To support high-load operation, the cross-sectional thickness of the main blade 3 and the auxiliary blade 4 is unevenly distributed. The thickness of the middle part of the core stress area is set to be three times the thickness of the blade tip. In addition, the blade edge is provided with an integrally formed guide edge with an arc-shaped cross-section that bulges outward. The inner surface smoothly transitions to the cycloidal surface. Both the main blade 3 and the auxiliary blade 4 have integrally cast rigid reinforcing ribs extending along the length direction. One end of the reinforcing rib is fixedly connected to the blade root, and the other end extends to the blade tip. The diameter of its circular cross-section gradually decreases from the blade root to the blade tip to match the centrifugal stress distribution.

[0023] 2. Assembly relationship of the universal adjustment mechanism To achieve high-frequency micro-physical pitch variation of the blade angle of attack, this embodiment innovatively integrates a universal adjustment mechanism 6 within the main cone sleeve 5. This mechanism mainly includes a bevel gear disk 61, a blade connecting shaft 62, a driven bevel gear 63, an electromagnetic telescopic sleeve A64, an electromagnetic telescopic sleeve B65, and a drive control module 66.

[0024] In mechanical linkage assembly: Main power input: The bottom end of the spindle 2 extends to the outside of the housing 1 and is connected to the bottom brushless DC motor rotor. The bevel gear disk 61 is coaxially rigidly sleeved and fixed to the upper middle part of the spindle 2, and rotates synchronously at high speed with the spindle 2.

[0025] Lateral deflection bearing load: The blade connecting shaft 62 is transversely inserted into the inner cavity of the main cone sleeve 5 in a direction perpendicular to the axis of the main shaft 2. The blade roots of the main blade 3 and the auxiliary blade 4 are respectively locked to the two ends of the blade connecting shaft 62 extending out of the main cone sleeve 5 by high-strength flanges.

[0026] Clutch transmission assembly: The driven bevel gear 63 is fixedly sleeved on the middle of the blade connecting shaft 62 by a spline, and is arranged relative to the bevel gear disk 61 with a small gap in the initial state.

[0027] Electromagnetic push-pull assembly: Electromagnetic telescopic sleeves A64 and B65 are respectively flanged and connected to the two end areas of the blade connecting shaft 62 (located between the wall of the main cone sleeve 5 and the blade root); both sets of telescopic sleeves have built-in high-power excitation coils and return springs, and their internal movable armatures are connected to the shoulder of the blade connecting shaft 62 through thrust bearings, allowing the connecting shaft to rotate while forcibly controlling its axial translation.

[0028] In terms of system-level hardware integration, the device is equipped with a hardware data acquisition module that collects ambient airflow and the physical tilt angle of the fuselage in real time. This module includes a pressure sensor and a drone attitude sensor embedded in the fuselage.

[0029] The drive control module 66 is fixedly installed in the housing 1 or the sealed fuselage compartment. It is connected to the coil terminals of the electromagnetic telescopic sleeve A64 and the electromagnetic telescopic sleeve B65 respectively using anti-interference shielded hard wires. The drive control module 66 has a built-in storage unit and a hard-coded data processing module. It is connected to the external flight control system through a cable with a metal shielding layer and a CAN bus interface. The bus interface is equipped with a shielded connector to isolate high-frequency electromagnetic interference and ensure transient and lossless transmission of adjustment electrical signals.

[0030] The lifting device of this invention utilizes the engagement of an electromagnetic clutch and mechanical gears to adjust the blade angle of attack. The specific working process is as follows: 1. Normal hovering / level flight state (power-off ionized state) When there is no sudden change in crosswind or no attitude compensation is required, the drive control module 66 does not output an excitation signal, and both the electromagnetic telescopic sleeve A64 and the electromagnetic telescopic sleeve B65 are in a de-energized state. At this time, the blade connecting shaft 62 remains axially centered under the symmetrical pre-tension of the return springs on both sides. The driven bevel gear 63 and the bevel gear disk 61 are in a physically separated free state. The brushless DC motor drives the main shaft 2 to rotate at high speed, and directly drives the blade connecting shaft 62 to revolve around the main shaft 2 through the main cone sleeve 5. The main blade 3 and the auxiliary blade 4 generate stable lift by relying on the set initial angle of attack. During operation, the gradually curved surface of the cycloidal spindle blade and the outwardly protruding guide edge work together to force the airflow to be physically guided, effectively suppressing the stripping of the tip vortex and reducing rotational wind resistance and energy loss.

[0031] 2. Transient attitude correction state (energized meshing variable pitch state) When the aircraft encounters complex low-altitude turbulence, causing the pressure sensor to detect a sudden change in external pressure, the data processing module quickly calculates the angle of attack compensation value based on the internal hard-coded program and triggers the drive control module 66 to output transient excitation current.

[0032] The control actions are as follows: Electromagnetic axial push-pull: The drive control module 66 is energized in the forward direction for the electromagnetic telescopic sleeve A64, causing its coil to generate an electromagnetic repulsive force that pushes one armature to extend outward; simultaneously, the electromagnetic telescopic sleeve B65 is energized in the reverse direction, generating an electromagnetic attraction force that pulls the other armature to retract inward; the combined force of this push and pull instantaneously overcomes the resistance of the return spring, forcing the blade connecting shaft 62 to undergo a slight translation along its own axial direction along a set stroke; Rigid tooth meshing: The translation of the blade connecting shaft 62 drives the driven bevel gear 63 in the middle to instantly engage with the tooth groove of the bevel gear disk 61 that is rotating at high speed, forming a tight rigid meshing.

[0033] Mechanical deflection transmission: Driven by the powerful rotational force of the main shaft 2, the rotating bevel gear disk 61 forcibly drives the meshing driven bevel gear 63 to rotate, thereby driving the blade connecting shaft 62 to rotate slightly in its axial direction, thus accurately and quickly changing the mechanical and aerodynamic angle of attack of the main blade 3 and the auxiliary blade 4 to complete the wind resistance lift compensation.

[0034] Power-off reset lock: When the deflection reaches the preset angle, the drive control module 66 immediately cuts off the excitation current; the electromagnetic telescopic sleeve A64 and electromagnetic telescopic sleeve B65 lose their electromagnetic constraints, and the mechanical elasticity of the reset springs on both sides is released instantly, forcing the blade connecting shaft 62 to return to the center in the opposite direction; the driven bevel gear 63 then disengages from the meshing area of ​​the bevel gear disk 61, and the blade angle of attack is fixed at this position, completing a millisecond-level pure mechanical clutch and pitch change action.

Claims

1. A universal cycloidal spindle blade rotor lifting device, characterized in that, include: Housing (1); main shaft (2) passing through the inside of the housing (1); main cone sleeve (5) disposed at the end of the main shaft (2); main blade (3) and auxiliary blade (4); and universal adjustment mechanism (6); The universal adjustment mechanism (6) includes a bevel gear disc (61), a blade connecting shaft (62), a driven bevel gear (63), an electromagnetic telescopic sleeve A (64), an electromagnetic telescopic sleeve B (65), and a drive control module (66). The main blade (3) and the auxiliary blade (4) are respectively installed at both ends of the blade connecting shaft (62), and the driven bevel gear (63) is fixedly sleeved on the blade connecting shaft (62). The electromagnetic telescopic sleeve A (64) and the electromagnetic telescopic sleeve B (65) are respectively located at both ends of the blade connecting shaft (62). The drive control module (66) is electrically connected to the electromagnetic telescopic sleeve A (64) and the electromagnetic telescopic sleeve B (65) respectively, and is used to control the movement of the two sets of electromagnetic telescopic sleeves, so that the blade connecting shaft (62) moves axially, thereby driving the driven bevel gear (63) on it to mesh or separate from the bevel gear disc (61), so as to realize the micro-adjustment of each blade.

2. The universal cycloidal spindle blade rotor lifting device according to claim 1, characterized in that, The bevel gear disk (61) is coaxially sleeved outside the main shaft (2), and the blade connecting shaft (62) passes through the main cone sleeve (5) in a direction perpendicular to the axis of the main shaft (2). When the electromagnetic telescopic sleeve A (64) is energized and extends while the electromagnetic telescopic sleeve B (65) shortens synchronously, the blade connecting shaft (62) is driven to move to one side, so that the driven bevel gear (63) cuts into the tooth groove of the bevel gear disk (61) to form a rigid engagement. When the power is de-energized and reset, the blade connecting shaft (62) returns to the center, and the driven bevel gear (63) disengages from the bevel gear disk (61).

3. The universal cycloidal spindle blade rotor lifting device according to claim 1, characterized in that, The main blade (3) and the auxiliary blade (4) are spindle-shaped in whole, and their surfaces are cycloidal surfaces. The curvature of the surface changes linearly from the blade root to the blade tip with the radius. The thickness of the middle part of the main blade (3) and the auxiliary blade (4) is 3 times the thickness of the blade tip, and the blade edge is provided with an integrally formed guide edge. The cross section of the guide edge is arc-shaped and protrudes outward from the blade. The inner side surface smoothly transitions with the cycloidal surface of the blade.

4. The universal cycloidal spindle blade rotor lifting device according to claim 3, characterized in that, Both the main blade (3) and the auxiliary blade (4) are provided with reinforcing ribs extending along the blade length direction. One end of the reinforcing rib is fixedly connected to the blade root, and the other end extends to the blade tip. The cross-section of the reinforcing rib is circular, and the diameter of the reinforcing rib gradually decreases from the blade root to the blade tip.

5. The universal cycloidal spindle blade rotor lifting device according to claim 1, characterized in that, The electromagnetic telescopic sleeve A (64) and electromagnetic telescopic sleeve B (65) both include a shell, an internal electromagnetic coil and a return spring; the two ends of the blade connecting shaft (62) are respectively movably inserted into the armature ends of the electromagnetic telescopic sleeve A (64) and electromagnetic telescopic sleeve B (65); the outer wall of the main cone sleeve (5) is symmetrically provided with limiting guide holes for the extension and retraction of the armature.

6. The universal cycloidal spindle blade rotor lifting device according to claim 1, characterized in that, The bottom end of the spindle (2) extends to the outside of the housing (1) and is connected to a drive assembly. The drive assembly includes a brushless DC motor and heat dissipation fins on the housing. The outside of the housing (1) is also equipped with a wind-cooling system consisting of a cooling fan and a shroud. The shroud covers the outside of the heat dissipation fins.

7. A universal cycloidal spindle blade rotor lifting system using the apparatus described in any one of claims 1 to 6, characterized in that, Include: The data acquisition module is used to collect environmental aerodynamic parameters and fuselage attitude parameters in real time during the operation of the rotor lifting device; The drive control module (66) is communicatively connected to the data acquisition module and is used to generate a micro-deflection adjustment command for the blade based on the received parameters. The universal adjustment execution module includes a bevel gear disk (61), a blade connecting shaft (62), a driven bevel gear (63), an electromagnetic telescopic sleeve A (64), and an electromagnetic telescopic sleeve B (65) in the universal adjustment mechanism (6). The universal adjustment execution module receives and responds to the adjustment command to realize dynamic wind resistance correction of the system attitude.

8. The universal cycloidal spindle blade rotor lifting system according to claim 7, characterized in that, The data acquisition module includes a pressure sensor and a UAV attitude sensor embedded inside the mechanism; the system also includes a communication module, which is connected to an external flight control system via a CAN bus interface; the CAN bus interface is equipped with a shielded connector, and the communication module and the flight control system exchange commands via a cable with a metal shielding layer.

9. The universal cycloidal spindle blade rotor lifting system according to claim 7, characterized in that, The drive control module (66) has a built-in storage unit and a data processing module; the storage unit has a pre-stored wind-resistant control algorithm program; when the data acquisition module detects a sudden change in airflow pressure, the data processing module calls the wind-resistant control algorithm program to calculate the required deflection angle and converts it into an excitation drive electrical signal for the electromagnetic telescopic sleeve A (64) and the electromagnetic telescopic sleeve B (65).

10. A universal cycloidal spindle blade rotor lifting system according to claim 7, characterized in that, The system operation coordination logic of the universal adjustment execution module is as follows: After receiving the fine-tuning instruction, the drive control module (66) energizes the electromagnetic telescopic sleeve A (64) to apply thrust, and simultaneously energizes the electromagnetic telescopic sleeve B (65) to apply tension, causing the blade connecting shaft (62) to undergo axial displacement, which drives the driven bevel gear (63) to mesh with the bevel gear disk (61); Under the power of the rotation of the main shaft (2), the driven bevel gear (63) rotates along the bevel gear disk (61), which in turn drives the blade connecting shaft (62) to rotate, so as to adjust the deflection angle of the main blade (3) and the auxiliary blade (4); When the target deflection angle is reached, the drive control module (66) sends a power-off reset signal to the electromagnetic telescopic sleeve A (64) and the electromagnetic telescopic sleeve B (65), and the driven bevel gear (63) disengages, completing a single micro-adjustment action of the blade.

Images