Flying power device with adaptive adjustment of blade angle

Abstract

This invention relates to a flight propeller angle adaptive adjustment device. The flight propeller is installed within the ducted body of a UAV and includes a propeller support cylinder, propeller blades, roller bearings, a brushless motor, a base, and a propeller angle adjustment mechanism. Multiple propeller blades are evenly distributed circumferentially around the outer periphery of the propeller support cylinder via roller bearings. The brushless motor, fixed to the base, drives the propeller support cylinder and propeller blades to perform circular motion around the entire device's axis. An inner protrusion is located on the horizontal reference plane of the propeller's rear end face, on the same side as the blade's trailing edge. The propeller angle adjustment mechanism adjusts the propeller angle by driving the inner protrusion up and down. This invention solves the problem of the fixed propeller angle in existing electrically driven UAVs by adjusting the propeller angle through the propeller angle adjustment mechanism. This addresses the technical issues of the UAV's endurance, operating noise, and stability being affected by environmental factors during flight.

Description

Technical Field

[0001] This invention belongs to the field of flight propulsion, specifically relating to a flight propulsion device with adaptive blade angle adjustment. Background Technology

[0002] A drone is an unmanned, autonomous, or remotely controlled aircraft that integrates multiple high technologies such as aerospace, mechatronics, computers, communications, and navigation. It boasts advantages such as small size, light weight, and low operating costs, and has broad application prospects in military aerospace, commercial aerial photography, power line inspection, precision agriculture, and emergency rescue. The working principle of a drone is to achieve various flight missions through pre-programming or remote human control. It consists of five major systems: a power system, a control system, a communication system, a navigation system, and a payload. The power system provides the drone with power and flight capability; the control system ensures stable flight status control and executes flight commands; the communication system enables communication between the drone and the ground station; the navigation system provides the drone with autonomous navigation capabilities; and the payload consists of equipment or sensors that perform specific tasks. Depending on mission requirements, drones can be equipped with various payloads such as optical cameras, multispectral cameras, infrared thermal imagers, and synthetic aperture radar.

[0003] Currently, drone technology is developing rapidly, and the industry generally believes that drones represent the third revolution in the aerospace field after manned aircraft and satellites. With advancements in key technologies such as autopilot, obstacle avoidance, and precise positioning, the intelligence and automation levels of drones have greatly improved, enabling them to play a vital role in more fields. However, currently available drones, including military drones, are affected by numerous factors during flight, such as terrain, weather, wind speed, and wind direction. Furthermore, the drones' own endurance, operating noise, and stability are also significant issues. Overall analysis reveals that the propeller angles of currently available drones are not adjustable, leading to the following problems:

[0004] 1. A fixed blade angle will prevent the rotor from generating lift under low power conditions, resulting in an unstable takeoff for the drone;

[0005] 2. A fixed propeller angle will severely affect the maneuverability of the UAV in harsh environments, including the loss of balance control such as pitch and roll control;

[0006] 3. Fixing the blade angle will cause the blades to operate in a suboptimal state, which will limit the flight of the drone;

[0007] 4. Fixed propellers cannot cope with strong winds or the need for rapid turns, directly affecting flight safety.

[0008] 5. Non-adjustable propellers require a lot of energy to fly, accelerate battery consumption, and shorten the drone's flight time.

[0009] 6. Fixed blades place a greater load on the mechanical transmission system, making them more prone to wear and failure. Therefore, fixed blades are more susceptible to environmental influences during flight, which is a major reason why endurance, operating noise, and stability are affected. Summary of the Invention

[0010] The purpose of this invention is to provide a flight propulsion device with adaptive blade angle adjustment.

[0011] The technical solution to achieve the purpose of this invention is: a flight power device with adaptive blade angle adjustment, the flight power device is installed in the duct body of the UAV, the flight power device includes a blade support cylinder, blades, roller bearings, a brushless motor, a base and a blade angle adjustment mechanism.

[0012] Multiple blades are evenly distributed around the outer periphery of the blade support cylinder via roller bearings. The blade support cylinder and blades are driven to rotate around the entire axis of the device by a brushless motor fixed to the base. An inner boss is provided on the blade's horizontal reference plane at the rear end face of the blade, on the same side as the blade's trailing edge. The blade angle adjustment mechanism adjusts the blade angle by driving the inner boss to move up and down.

[0013] Furthermore, the blade angle adjustment mechanism includes a base cylinder support cylinder and a micro power unit.

[0014] The base cylinder support cylinder is coaxially fitted with the base and is set inside the blade support cylinder. The base cylinder support cylinder has multiple bosses and grooves on its circumference that match the inner bosses of the blades. After assembly, the inner bosses of the blades are located in the boss grooves. A micro power unit is set in the base to drive the base cylinder support cylinder to move up and down. The up and down movement of the base cylinder support cylinder realizes the up and down movement of the inner bosses of the blades, thereby achieving blade angle adjustment.

[0015] Furthermore, the micro-power unit is a micro-cylinder.

[0016] Furthermore, the number of blades is four.

[0017] Furthermore, it also includes a brushless motor mounting platform, which is installed on the base through the center hole at the bottom of the cylinder support cylinder, and the brushless motor is fixed on the brushless motor mounting platform.

[0018] Furthermore, the output shaft of the brushless motor is coupled with the coupling rod inside the blade support cylinder.

[0019] An unmanned aerial vehicle (UAV) includes the aforementioned flight propulsion device.

[0020] Compared with the prior art, the significant advantages of this invention are:

[0021] This invention ensures that the propeller blades rotate at high speed around the flight power unit, while driving a micro cylinder through an adjustment control system. The micro cylinder pushes the base cylinder support cylinder to move up and down. The four grooved bosses on the upper side wall of the support cylinder drive the inner boss of the propeller blade to move in a circular motion around the propeller blade boss, thereby adjusting the angle of the propeller blade. This solves the problem that the propeller blade angle of existing electrically driven UAVs cannot be changed, and can solve the technical problems of the UAV's endurance, operating noise and stability being affected by the environment during flight. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of an unmanned aerial vehicle (UAV) employing the flight propulsion device of the present invention.

[0023] Figure 2 This is a schematic diagram of the flight propulsion device with adaptive blade angle adjustment according to the present invention.

[0024] Figure 3 This is an exploded view of the structure of the flight propulsion device with adaptive blade angle adjustment according to the present invention.

[0025] Figure 4 This is a schematic diagram of a roller bearing assembly.

[0026] Figure 5 This is a schematic diagram of a miniature cylinder assembly.

[0027] Figure 6 This is a schematic diagram of a brushless motor assembly.

[0028] Figure 7 This is a schematic diagram of the coupling assembly.

[0029] Figure 8 This is a schematic diagram of the propeller blades.

[0030] Figure 9 This is a schematic diagram of the base cylinder support cylinder.

[0031] Figure 10 This is a schematic diagram of the base.

[0032] Explanation of reference numerals in the attached figures:

[0033] 1-UAV duct body, 2-Flight power unit, 3-Propeller support cylinder, 4-Propeller blade, 5-Roller bearing, 6-Base cylinder support cylinder, 7-Brushless motor, 8-Base, 9-Brushless motor mounting platform, 10-Miniature cylinder, 31-Coupling rod, 41-Propeller blade inner boss, 61-Boss groove. Detailed Implementation

[0034] The present invention will now be described in further detail with reference to the accompanying drawings.

[0035] Reference Figure 1-10An adaptively adjustable unmanned aerial vehicle (UAV) flight propulsion system assembly, such as Figure 1-2 As shown, it includes the UAV duct body 1, the adaptive UAV flight power device 2, and the adaptive UAV flight power device 2 includes the blade support cylinder 3, the blade 4, the roller bearing 5, the base cylinder support cylinder 6, the brushless motor 7, the base 8, the brushless motor fixing platform 9, and the miniature cylinder 10.

[0036] like Figure 4 As shown, the blade support cylinder 3 has four blade mounting holes, and the blade 4 is connected to the blade support cylinder 3 via roller bearings 5.

[0037] like Figure 5 As shown, the blade support cylinder 3 and the base cylinder support cylinder 6 are coaxially installed, and the boss 41 on the blade 4 matches the boss groove 61 on the base cylinder support cylinder 6.

[0038] like Figure 6 As shown, the base cylinder support cylinder 6 is coaxially fitted with the base 8, and the miniature cylinder 10 is installed next to the center of the base 8. The brushless motor mounting platform 9 passes through the center hole at the bottom of the base cylinder support cylinder 6 and is installed on the base 8. The miniature cylinder 10 is fitted with the bottom of the base cylinder support cylinder 6.

[0039] like Figure 7 As shown, the bottom of the brushless motor 7 is fixed on the brushless motor mounting platform 9, and the motor output shaft is engaged with the connecting rod 31 inside the blade support cylinder 3.

[0040] like Figure 8 As shown, the center point of the upper end face of the boss 41 on the blade 4 is in the horizontal reference plane of the blade and is on the same side as the trailing edge of the blade.

[0041] The base cylinder support cylinder 6 is connected to the base 8. A limit ring is designed on the top of the base. The bottom of the base cylinder support cylinder 6 is fixedly connected to the miniature cylinder 10 on the base.

[0042] The base cylinder support cylinder 6 has the characteristic of reciprocating up and down along the same axis as the base.

[0043] The brushless motor 7 is connected to the center fixed platform of the base with screws, and the output shaft of the brushless motor 7 is matched with the connecting rod inside the blade support cylinder;

[0044] During operation, the brushless motor 7, via coupling 31, drives the propeller support cylinder 3 and the propeller 4 to rotate around the entire device axis. Simultaneously, the miniature cylinder 10 on the base 8 drives the base cylinder support cylinder 6 to move up and down along the device axis. The boss and groove 61 on the base cylinder support cylinder 6 drive the boss 41 on the propeller 4 to rotate, thus changing the angle of the propeller 4. This solves the problem of the non-adjustable angle of the propeller 4 in existing electrically driven drones. When the boss 41 moves upward, the trailing edge of the propeller deviates from the reference plane and faces upward. At this time, the angle of attack is above the reference plane. The further the deviation, the larger the angle of attack, and the greater the drone's descent rate. When the boss 41 moves downward, the trailing edge of the propeller deviates from the reference plane and faces downward. At this time, the angle of attack is above and below the reference plane. The further the deviation, the larger the angle of attack, and the greater the drone's ascent rate. This achieves the angle change of the propeller 4, thus solving the problem of the non-adjustable angle of the propeller 4 in existing electrically driven drones. According to the principles of flight aerodynamics, because the propeller angle changes, the power required for the aircraft to move in the air is greatly reduced.

[0045] Working principle: After receiving flight commands from the onboard computer, the micro cylinder 10 moves to the initial scale. The boss groove 61 on the base cylinder support cylinder 6 drives the boss 41 on the propeller 4 to move to the initial position and remain stationary. At this time, the brushless motor 7 starts working, and the propeller support cylinder 3 starts to rotate through the coupling rod 31 inside the propeller support cylinder 3. At the same time, it drives the propeller 4 to rotate around the axis of the device, so that the UAV leaves the ground. During the flight, when the UAV propeller 4 needs to adjust its angle, the sensor senses the current position environment, and the onboard computer issues an adjustment command after comprehensive evaluation. The micro cylinder 10 on the base 8 starts to push the base cylinder support cylinder 6 to move up or down. The boss groove 61 on the base cylinder support cylinder 6 drives the boss 41 on the propeller 4 to rotate to the command angle. At this time, the propeller 4 is adjusted to the optimal angle to adapt to the current environment.

Claims

1. A propeller angle adaptive flight propulsion device, wherein the flight propulsion device is installed inside the duct body (1) of an unmanned aerial vehicle, characterized in that, The flight power unit includes a blade support cylinder (3), blades (4), roller bearings (5), a brushless motor (7), a base (8), and a blade angle adjustment mechanism; Multiple blades (4) are evenly arranged on the outer periphery of the blade support cylinder (3) via roller bearings (5) in the circumferential direction. The blade support cylinder (3) and blades (4) are driven to make circular motion around the axis of the entire device by a brushless motor (7) fixed to the base (8). An inner boss (41) is provided in the blade horizontal reference plane on the rear end face of the blade and on the same side as the rear edge of the blade. The blade angle adjustment mechanism adjusts the blade angle by driving the inner boss (41) of the blade to move up and down. The blade angle adjustment mechanism includes a base cylinder support cylinder (6) and a micro power unit. The base cylinder support cylinder (6) is coaxially fitted with the base (8). The base cylinder support cylinder (6) is set inside the blade support cylinder (3). The base cylinder support cylinder (6) has multiple boss grooves (61) that match the inner boss (41) of the blade in the circumferential direction. After assembly, the inner boss (41) of the blade is located in the boss groove (61). The micro power device is set in the base (8) to drive the base cylinder support cylinder (6) to move up and down. The up and down movement of the inner boss (41) of the blade is realized through the up and down movement of the base cylinder support cylinder (6), thereby realizing the blade angle adjustment. It also includes a brushless motor mounting platform (9), which is installed on the base (8) through the center hole at the bottom of the seat cylinder support cylinder (6), and the brushless motor (7) is fixed on the brushless motor mounting platform (9).

2. The flight propulsion device according to claim 1, characterized in that, The micro power unit is a micro cylinder (10).

3. The flight propulsion device according to claim 2, characterized in that, The number of blades (4) is four.

4. The flight propulsion device according to claim 3, characterized in that, The output shaft of the brushless motor (7) is engaged with the coupling rod (31) inside the blade support cylinder (3).

5. A drone, characterized in that, Includes the flight propulsion device as described in any one of claims 1-4.

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