Improved unmanned aerial vehicle variable pitch mechanism

Abstract

The utility model discloses an improved unmanned aerial vehicle variable pitch mechanism which 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 utility model relates to unmanned plane technical field, concretely is an improved unmanned plane variable pitch mechanism. BACKGROUND

[0002] The unmanned plane is short for "unmanned aerial vehicle", is with the wireless radio control equipment and the self -provided program control device and is manipulated without the pilot plane. Unmanned plane according to application field, can be divided into military and civilian. Military, unmanned plane is divided into reconnaissance aircraft and target aircraft. Civilian unmanned plane is widely applied in aerial photography, agriculture, plant protection, miniature self -photography, express delivery, disaster rescue, observation wild animal, monitoring infectious disease, survey, news report, power patrol, disaster relief, film and television shooting and so on.

[0003] The existing multicopter unmanned plane is usually electric unmanned plane, and the unmanned plane variable pitch mechanism is a core component of flight control, and the structural design directly affects the performance and manufacturing cost of the unmanned plane.

[0004] The utility model discloses an improved unmanned plane variable pitch mechanism, with a hollow main shaft, a rotor is fixedly installed on the upper end of the hollow main shaft through a mounting seat. The mounting seat has two horizontally arranged upper and lower plate arms extending outward from the center of each rotor. The flat blade root of the rotor is clamped between the two plate arms. Two spherical joints are arranged on the flat blade root. The rotor can be deflected around the center line of the two spherical joints. The improved unmanned plane variable pitch mechanism of the application clamps the flat blade root of the rotor through the plate arms of the mounting seat, removes the heavy disc structure, and uses lighter plate arms to provide support for the rotor. The rotor can also use a flat blade root without a heavy rotating shaft. The structure weight is greatly reduced, and the payload carrying capacity is improved.

[0005] In actual use, although the application has made significant progress in structural design and performance optimization, the rudder and transmission assembly are arranged transversely on the outside of the cantilever or the periphery of the main shaft, the transmission path is long, the response is delayed due to mechanical clearance and inertia, and the complex external linkage mechanism increases air resistance and failure risk.

[0006] Therefore, there is a need for an improved unmanned plane variable pitch mechanism to solve the above problems. Utility model content

[0007] Technical problems solved

[0008] The improved unmanned aerial vehicle variable pitch mechanism provided by the utility model solves the problems of arranging the steering engine and the transmission assembly horizontally on the outer side of the cantilever or the periphery of the main shaft, the long transmission path, the response delay caused by mechanical clearance and inertia, and the problems of airflow resistance and failure risk caused by the complex external connecting rod mechanism.

[0009] Technical solution

[0010] To achieve the above object, the utility model provides the following technical scheme: an improved unmanned aerial vehicle variable pitch mechanism, including fuselage, drive assembly and lifting assembly, four groups of racks are arranged on the outer side of the fuselage, drive assembly is installed on the other end of the rack, lifting assembly is arranged at the lower end of the drive assembly, the lifting assembly includes lifting motor, the lifting motor is arranged at the lower end of the rack, the screw hollow rotating rod is arranged in the lifting motor, the screw rod is installed in the screw hollow rotating rod, the limit strip slot is formed in the two sides of the screw rod, the lifting rod is installed on the upper end of the screw rod through the bearing, the lifting rod penetrates the drive assembly, the drive assembly includes drive motor, the drive motor is installed on the upper end of the rack, the rotor is movably installed on the upper end of the drive motor, the distance adjusting support is fixedly installed on the inner side of the rotor, the variable pitch control rod is connected between the upper end of the lifting rod and the distance adjusting support.

[0011] Preferably, the lifting motor is provided with the limit block on the two sides of the upper end, and the limit block is slidably installed in the limit strip slot.

[0012] Preferably, the lower end of the fuselage is provided with the supporting leg.

[0013] Preferably, the lower side of the front end of the fuselage is provided with the holder, the rear end of the fuselage is provided with the antenna, and the power supply port is arranged on the side of the antenna.

[0014] Preferably, the drive motor is of a hollow structure, and the lifting rod penetrates the drive motor.

[0015] Beneficial effects

[0016] The improved unmanned aerial vehicle variable pitch mechanism has the following beneficial effects: 1. The screw rod and the limit strip slot are cooperatively designed to rigidly constrain the limit block, the horizontal transmission path of the traditional steering engine is simplified into a vertical coaxial straight line drive, the intermediate transmission links such as the multi-stage connecting rod and the gear are completely eliminated, and the mechanical clearance and the inertia delay are significantly reduced;

[0017] 2. The supporting leg protects the core components from the ground impact, the holder stably carries the task load, the antenna guarantees the remote communication and navigation, the power supply port supports the rapid energy charging and equipment expansion, and the rigid cooperation of the limit block and the limit strip slot further suppresses the rotation error and ensures the transmission stability. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 is a schematic view of the structure of the present application;

[0019] Figure 2 is a schematic view of the structure of the present application;

[0020] Figure 3 is a schematic view of the structure of the present application;

[0021] Figure 4 is a schematic view of the structure of the present application;

[0022] Figure 5 is a schematic view of the structure of the present application.

[0023] In the figure: 1, fuselage; 11, support leg; 12, holder; 13, antenna; 14, power supply port; 2, rack; 3, driving assembly; 31, driving motor; 32, rotor; 321, pitch adjusting support; 4, pitch adjusting lever; 5, lifting assembly; 51, lifting motor; 511, limit block; 52, threaded hollow rotating rod; 53, threaded rod; 531, limit strip slot; 532, bearing; 54, lifting rod. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0025] In the description of the present application, it should be understood that the orientations or positional relationships indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0026] Please refer to Figures 1-5The utility model provides a technical scheme: an improved unmanned plane variable pitch mechanism, including fuselage 1, drive assembly 3 and elevating assembly 5, four groups of racks 2 are arranged outside fuselage 1, and drive assembly 3 is installed on the other end of rack 2, and elevating assembly 5 is arranged at the lower end of drive assembly 3, elevating assembly 5 includes elevating motor 51, and elevating motor 51 is arranged at the lower end of rack 2, and screw hollow rotary rod 52 is arranged in elevating motor 51, and screw rod 53 is installed in screw hollow rotary rod 52, and limit strip slot 531 is formed in the both sides of screw rod 53, and elevating rod 54 is installed on the upper end of screw rod 53 through bearing 532, and elevating rod 54 penetrates drive assembly 3, and drive assembly 3 includes drive motor 31, and drive motor 31 is installed on the upper end of rack 2, and rotary wing 32 is movably installed on the both sides of the upper end of drive motor 31, and pitch adjusting support 321 is fixed in the inner side of rotary wing 32, and the upper end of elevating rod 54 is connected with pitch adjusting support 321 through variable pitch control rod 4,

[0027] In use, elevating motor 51 is the power source, drives screw hollow rotary rod 52 to rotate, converts electric energy into mechanical energy, screw hollow rotary rod 52 and screw rod 53 convert rotary motion into linear motion, screw rod 53 is nested in screw hollow rotary rod 52, and the rotary degree of freedom is restricted through limit strip slot 531, ensures that elevating rod 54 only moves along the axial direction, reduces mechanical clearance and inertia delay, elevating rod 54 transmits linear motion to variable pitch control rod 4, drive motor 31 drives rotary wing 32 to rotate, provides lifting force and thrust, pitch adjusting support 321 is linked with variable pitch control rod 4 and adjusts the pitch of rotary wing 32, directly drives pitch adjusting support 321 through the linear motion of elevating rod 54, realizes the quick response of pitch, and does not need complex connecting rod mechanism.

[0028] The both sides of the upper end of elevating motor 51 are fixed with limit block 511, limit block 511 is slidably installed in limit strip slot 531, limit block 511 prevents screw rod 53 from rotating with screw hollow rotary rod 52 through the sliding fit with limit strip slot 531, ensures that screw rod 53 only moves along the axial vertical direction linearly, eliminates the rotary error in the transmission process, limit strip slot 531 provides accurate sliding track for limit block 511, forces screw rod 53 to only move along the axial direction, prevents the response delay or position deviation caused by rotary inertia in screw transmission.

[0029] The lower end of fuselage 1 is installed with support leg 11, when the unmanned plane is parked or moved on the ground, support leg 11 directly contacts the ground, bears the weight of fuselage 1, avoids the friction or collision of the bottom of fuselage 1 with the ground, and protects the core components from being damaged.

[0030] The gimbal 12 is arranged at the lower side of the front end of the fuselage 1, the antenna 13 is arranged at the rear end of the fuselage 1, the power supply port 14 is arranged at the side of the antenna 13, the gimbal 12 is a precision mechanical device for carrying and stabilizing the task load such as a camera and a sensor, the antenna 13 realizes wireless communication and navigation signal receiving between the unmanned aerial vehicle and a ground station, a satellite or other equipment, and the power supply port 14 is a physical interface for external power supply access and data transmission.

[0031] The driving motor 31 is a hollow structure, the lifting rod 54 penetrates through the driving motor 31, the hollow structure driving motor 31 adopts a hollow motor body, and the lifting rod 54 is allowed to penetrate from the center.

[0032] As an embodiment of the utility model: when the improved unmanned aerial vehicle variable pitch mechanism is used, the lifting assembly 5 takes the lifting motor 51 as a core power source, and realizes precise linear motion control through screw transmission. After the lifting motor 51 is started, the threaded hollow rotating rod 52 in the interior is driven to rotate, the threaded rod 53 nested in the threaded hollow rotating rod 52 is rigidly constrained by the two side limiting strip grooves 531 and the limiting blocks 511, and can only move linearly in the vertical direction, so that the rotating mechanical energy is converted into the axial displacement of the lifting rod 54. This design eliminates the rotating degree of freedom and the multi-stage transmission link, greatly reduces the mechanical gap and inertia delay, and ensures the efficiency and response speed of power transmission;

[0033] The lifting rod 54 penetrates through the hollow structure driving motor 31, is directly connected with the variable-pitch control rod 4 at the upper end, and transmits linear motion to the pitch adjusting support 321 inside the rotor 32; when the lifting rod 54 moves up and down, the variable-pitch control rod 4 links the pitch adjusting support 321 to synchronously adjust the pitch of the rotor 32, so that the lift force is quickly increased or decreased or the thrust direction is switched;

[0034] The precise cooperation of the limiting blocks 511 and the limiting strip grooves 531 further constrains the motion trajectory, avoids rotation error, and makes the pitch adjustment be completed within milliseconds, so that the flight stability and maneuverability requirements are considered, and the traditional complex external connecting rod mechanism is completely replaced.

[0035] It should be noted that, in the present document, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily implying any actual relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0036] Although the embodiments of the present application have been shown and described, it is to be understood that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present application, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An improved unmanned aerial vehicle pitch mechanism comprising a body (1), a drive assembly (3) and a lifting assembly (5), characterised in that: The machine body (1) outside sets four groups of frame (2), the other end of frame (2) is installed with drive assembly (3), the lower end of drive assembly (3) is provided with lifting assembly (5); The lifting assembly (5) includes lifting motor (51), the lifting motor (51) is arranged at the lower end of frame (2), the lifting motor (51) is internally provided with screw hollow rotating rod (52), the screw hollow rotating rod (52) is internally installed with threaded rod (53), the threaded rod (53) both sides are provided with limit strip slot (531), the threaded rod (53) upper end is installed with lifting rod (54) through bearing (532), the lifting rod (54) penetrates drive assembly (3); The drive assembly (3) includes drive motor (31), the drive motor (31) is installed on the upper end of frame (2), the drive motor (31) upper end both sides are movably installed with rotor (32), the rotor (32) inner side is fixed with distance adjusting support (321); The lifting rod (54) upper end and distance adjusting support (321) are connected through variable pitch control rod (4).

2. An improved unmanned aerial vehicle pitch mechanism as claimed in claim 1, wherein: The lifting motor (51) upper end both sides are fixed with limit block (511), the limit block (511) is slidably installed in limit strip slot (531).

3. An improved unmanned aerial vehicle pitch mechanism as claimed in claim 1, wherein: The lower end of machine body (1) is installed with support leg (11).

4. The improved unmanned aerial vehicle pitch mechanism according to claim 1, wherein: The front end of machine body (1) lower side is provided with holder (12), the rear end of machine body (1) is provided with antenna (13), the side of antenna (13) is provided with power supply port (14).

5. The improved unmanned aerial vehicle pitch mechanism according to claim 1, wherein: The drive motor (31) is hollow structure, the lifting rod (54) penetrates drive motor (31).

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