Improved unmanned aerial vehicle variable pitch mechanism

Abstract

The improved unmanned aerial vehicle variable pitch mechanism comprises a fuselage, four sets of racks are arranged on the outer side of the fuselage, driving assemblies are installed at the other ends of the racks, lifting assemblies are arranged at the lower ends of the driving assemblies and comprise lifting motors, the lifting motors are arranged at the lower ends of the racks, and threaded hollow rotating rods are arranged in the lifting motors; a lifting rod is installed at the upper end of the threaded rod through a bearing and penetrates through a driving assembly, the driving assembly comprises a driving motor, the driving motor is installed at the upper end of the rack, rotors are movably installed on the two sides of the upper end of the driving motor, and distance adjusting supports are fixed to the inner sides of the rotors; the upper end of the lifting rod is connected with the distance adjusting support through a distance changing control rod. Through the collaborative design of rigid constraint of the screw transmission threaded rod, the limiting strip groove and the limiting block, the transverse transmission path of a traditional steering engine is simplified into longitudinal coaxial linear driving, and the mechanical gap and inertia delay are remarkably reduced.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to an improved variable pitch mechanism for unmanned aerial vehicles. Background Art

[0002] Unmanned aircraft, or "drones" for short, are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices. Drones can be divided into military and civilian applications according to their application areas. In the military, drones are divided into reconnaissance aircraft and target aircraft. Civilian drones are widely used in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspections, disaster relief, and film and television shooting.

[0003] Existing multi-rotor UAVs are usually electric UAVs. The variable pitch mechanism of the UAV is the core component of flight control, and its structural design directly affects the performance and manufacturing cost of the UAV.

[0004] The Chinese patent with publication number CN209305827U discloses an improved variable pitch mechanism for unmanned aerial vehicles, which has a hollow main shaft, and the rotor is fixedly mounted on the upper end of the hollow main shaft through a mounting seat; the mounting seat has two horizontally arranged upper and lower flat plate arms extending outward from the rotation center of each rotor, and the flat plate wing root of the rotor is clamped and mounted between the two flat plate arms; two spherical joints are arranged on the flat plate wing root; the rotor can deflect around the line connecting the centers of the two spherical joints. The improved variable pitch mechanism for unmanned aerial vehicles of the present application clamps the flat plate wing root of the rotor through the flat plate arm of the mounting seat, removes the bulky disc-shaped structure, and uses a thinner flat plate arm to provide support for the rotor. The rotor can also use a flat plate wing root, and there is no need to set a heavy rotating shaft. It can greatly reduce the weight of the structure and improve the carrying capacity of the payload.

[0005] In actual use, although the present invention has made significant progress in structural design and performance optimization, the servo and transmission components are arranged laterally on the outside of the cantilever or around the main shaft, the transmission path is long, and it is easy to cause response delays due to mechanical clearance and inertia. The complex external linkage mechanism increases airflow resistance and failure risks.

[0006] Therefore, an improved UAV variable pitch mechanism is now needed to solve the above problems. Summary of the invention

[0007] Technical issues solved

[0008] In view of the shortcomings of the prior art, the present invention provides an improved UAV variable pitch mechanism to solve the problems mentioned in the above background technology that the servo and transmission components are arranged horizontally on the outside of the cantilever or around the main shaft, the transmission path is long, and response delays are easily caused by mechanical clearance and inertia, and the complex external connecting rod mechanism increases airflow resistance and failure risk.

[0009] Technical Solution

[0010] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: an improved variable pitch mechanism of an unmanned aerial vehicle, comprising a fuselage, a driving assembly and a lifting assembly, four groups of frames are arranged on the outside of the fuselage, the other end of the frame is equipped with a driving assembly, the lower end of the driving assembly is equipped with a lifting assembly, the lifting assembly comprises a lifting motor, the lifting motor is arranged at the lower end of the frame, a threaded hollow rotating rod is arranged inside the lifting motor, a threaded rod is installed inside the threaded hollow rotating rod, limiting grooves are provided on both sides of the threaded rod, a lifting rod is installed on the upper end of the threaded rod through a bearing, the lifting rod passes through the driving assembly, the driving assembly comprises a driving motor, the driving motor is installed at the upper end of the frame, rotors are movably installed on both sides of the upper end of the driving motor, a pitch adjusting bracket is fixed on the inner side of the rotor, and the upper end of the lifting rod and the pitch adjusting bracket are connected through a pitch changing joystick.

[0011] Preferably, limiting blocks are fixed on both sides of the upper end of the lifting motor, and the limiting blocks are slidably installed in the limiting strip grooves.

[0012] Preferably, a support foot is installed at the lower end of the fuselage.

[0013] Preferably, a gimbal is provided at the lower side of the front end of the fuselage, an antenna is provided at the rear end of the fuselage, and a power port is provided at the side of the antenna.

[0014] Preferably, the driving motor is a hollow structure, and the lifting rod passes through the driving motor.

[0015] Beneficial Effects

[0016] The present invention provides an improved variable pitch mechanism for unmanned aerial vehicles, which has the following beneficial effects: 1. Through the coordinated design of the threaded rod of the spiral transmission and the rigid constraint of the limit strip groove and the limit block, the lateral transmission path of the traditional servo is simplified to a longitudinal coaxial linear drive, and the intermediate transmission links such as multi-stage connecting rods and gears are completely eliminated, and the mechanical clearance and inertia delay are significantly reduced;

[0017] 2. The legs protect the core components from ground impact, the gimbal stably carries the mission payload, the antenna ensures remote communication and navigation, and the power port supports fast charging and equipment expansion. The rigid coordination between the limit block and the limit bar groove further suppresses rotation errors and ensures transmission stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the structure of the present invention;

[0019] Figure 2 It is a schematic diagram of the local structure of the present invention;

[0020] Figure 3 It is a schematic diagram of the side section structure of the present invention;

[0021] Figure 4 It is a schematic diagram of the side section structure of the present invention;

[0022] Figure 5 It is a schematic diagram of the partially disassembled structure of the present invention.

[0023] In the figure: 1. fuselage; 11. support leg; 12. gimbal; 13. antenna; 14. power port; 2. frame; 3. drive assembly; 31. drive motor; 32. rotor; 321. pitch-adjustable bracket; 4. variable pitch joystick; 5. lifting assembly; 51. lifting motor; 511. limit block; 52. threaded hollow rotating rod; 53. threaded rod; 531. limit strip groove; 532. bearing; 54. lifting rod. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0026] See also Figure 1-5The present invention provides a technical solution: an improved variable pitch mechanism of an unmanned aerial vehicle, comprising a fuselage 1, a driving assembly 3 and a lifting assembly 5, four sets of frames 2 are arranged on the outside of the fuselage 1, the driving assembly 3 is installed on the other end of the frame 2, and the lifting assembly 5 is arranged on the lower end of the driving assembly 3, the lifting assembly 5 comprises a lifting motor 51, the lifting motor 51 is arranged on the lower end of the frame 2, a threaded hollow rotating rod 52 is arranged inside the lifting motor 51, a threaded rod 53 is installed inside the threaded hollow rotating rod 52, limited position grooves 531 are provided on both sides of the threaded rod 53, a lifting rod 54 is installed on the upper end of the threaded rod 53 through a bearing 532, and the lifting rod 54 passes through the driving assembly 3, the driving assembly 3 comprises a driving motor 31, the driving motor 31 is installed on the upper end of the frame 2, rotors 32 are movably installed on both sides of the upper end of the driving motor 31, a pitch-adjusting bracket 321 is fixed on the inner side of the rotor 32, and the upper end of the lifting rod 54 is connected to the pitch-adjusting bracket 321 through a pitch-changing control lever 4;

[0027] During use, the lifting motor 51 is the power source, driving the threaded hollow rotary rod 52 to rotate, converting electrical energy into mechanical energy; the threaded hollow rotary rod 52 and the threaded rod 53 convert rotational motion into linear motion, and the threaded rod 53 is nested in the threaded hollow rotary rod 52, and the rotational freedom is constrained by the limit groove 531, ensuring that the lifting rod 54 only moves in the axial direction, reducing mechanical clearance and inertia delay; the lifting rod 54 transmits linear motion to the pitch control lever 4; the driving motor 31 drives the rotor 32 to rotate, providing lift and thrust; the pitch adjustment bracket 321 and the pitch control lever 4 are linked to adjust the pitch of the rotor 32, and the pitch adjustment bracket 321 is directly driven by the linear motion of the lifting rod 54, so as to achieve rapid pitch response without the need for a complex connecting rod mechanism.

[0028] Limit blocks 511 are fixed on both sides of the upper end of the lifting motor 51. The limit blocks 511 are slidably installed in the limit grooves 531. The limit blocks 511 prevent the threaded rod 53 from rotating with the threaded hollow rotating rod 52 by sliding cooperation with the limit grooves 531, thereby ensuring that the threaded rod 53 only moves in a straight line along the axial vertical direction, thereby eliminating rotation errors in the transmission process; the limit grooves 531 provide a precise sliding track for the limit blocks 511, forcing the threaded rod 53 to move only along the axial direction, thereby preventing response delays or position deviations caused by rotational inertia in the spiral transmission.

[0029] A support foot 11 is installed at the lower end of the fuselage 1. When the drone is parked or moving on the ground, the support foot 11 directly contacts the ground, bears the weight of the fuselage 1, avoids friction or collision between the bottom of the fuselage 1 and the ground, and protects core components from damage.

[0030] A gimbal 12 is provided at the lower side of the front end of the fuselage 1, an antenna 13 is provided at the rear end of the fuselage 1, and a power port 14 is provided on the side of the antenna 13. The gimbal 12 is a precision mechanical device that carries and stabilizes mission payloads such as cameras and sensors; the antenna 13 realizes wireless communication and navigation signal reception between the drone and ground stations, satellites or other equipment; the power port 14 enables a physical interface for external power access and data transmission.

[0031] The driving motor 31 is a hollow structure, and the lifting rod 54 passes through the driving motor 31. The driving motor 31 with a hollow structure adopts a motor body with a hollow design, allowing the lifting rod 54 to pass through from the center.

[0032] As an embodiment of the present invention: when the improved variable pitch mechanism of the UAV is used, the lifting assembly 5 uses the lifting motor 51 as the core power source, and realizes precise linear motion control through spiral transmission. After the lifting motor 51 is started, it drives the internal threaded hollow rotating rod 52 to rotate, and the threaded rod 53 nested therein is rigidly constrained by the limiting grooves 531 and the limiting blocks 511 on both sides, and can only move linearly in the vertical direction, thereby converting the rotational mechanical energy into the axial displacement of the lifting rod 54. This design greatly reduces the mechanical clearance and inertia delay by eliminating the rotational freedom and multi-stage transmission links, ensuring the high efficiency and response speed of power transmission;

[0033] The lifting rod 54 passes through the driving motor 31 of the hollow structure and is directly connected to the pitch control lever 4 at the upper end, transmitting the linear motion to the pitch adjustment bracket 321 inside the rotor 32; when the lifting rod 54 moves up and down, the pitch control lever 4 links the pitch adjustment bracket 321 to synchronously adjust the pitch of the rotor 32, thereby realizing the rapid increase or decrease of lift or the switching of thrust direction;

[0034] The precise cooperation between the limit block 511 and the limit groove 531 further constrains the motion trajectory, avoids rotation errors, and enables the pitch adjustment to be completed within milliseconds, taking into account both flight stability and maneuverability requirements, completely replacing the traditional complex external linkage mechanism.

[0035] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0036] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An improved variable pitch mechanism for an unmanned aerial vehicle, comprising a fuselage (1), a drive assembly (3) and a lifting assembly (5), characterized in that: Four sets of frames (2) are arranged outside the machine body (1), a driving assembly (3) is installed at the other end of the frame (2), and a lifting assembly (5) is arranged at the lower end of the driving assembly (3); The lifting assembly (5) comprises a lifting motor (51), the lifting motor (51) being arranged at the lower end of the frame (2), a threaded hollow rotating rod (52) being arranged inside the lifting motor (51), a threaded rod (53) being installed inside the threaded hollow rotating rod (52), limiting strip grooves (531) being arranged on both sides of the threaded rod (53), a lifting rod (54) being installed at the upper end of the threaded rod (53) via a bearing (532), and the lifting rod (54) passing through the driving assembly (3); The driving assembly (3) comprises a driving motor (31), the driving motor (31) being mounted on the upper end of the frame (2), rotors (32) being movably mounted on both sides of the upper end of the driving motor (31), and a pitch-adjusting bracket (321) being fixed inside the rotor (32); The upper end of the lifting rod (54) is connected to the pitch-adjusting bracket (321) via a pitch-changing operating rod (4).

2. The improved UAV variable pitch mechanism according to claim 1, characterized in that: Limiting blocks (511) are fixed on both sides of the upper end of the lifting motor (51), and the limiting blocks (511) are slidably installed in the limiting strip grooves (531).

3. The improved UAV variable pitch mechanism according to claim 1, characterized in that: A support foot (11) is installed at the lower end of the fuselage (1).

4. The improved UAV variable pitch mechanism according to claim 1, characterized in that: A pan / tilt platform (12) is arranged at the lower side of the front end of the fuselage (1), an antenna (13) is arranged at the rear end of the fuselage (1), and a power port (14) is arranged on the side of the antenna (13).

5. The improved UAV variable pitch mechanism according to claim 1, characterized in that: The driving motor (31) is a hollow structure, and the lifting rod (54) passes through the driving motor (31).

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