Quick propeller dismounting and mounting mechanism of coaxial unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and discloses a quick propeller dismounting and mounting mechanism of a coaxial unmanned aerial vehicle, which comprises a central bearing seat, a swash plate connecting pull rod, a motor seat, an arm bearing sleeve, a detachable propeller hub, a propeller clamp and a propeller blade, a quick dismounting mechanism is arranged between the detachable propeller hub and the arm bearing sleeve, two L-shaped grooves are formed in the detachable propeller hub, bulges corresponding to the two L-shaped grooves are arranged in the arm bearing sleeve, after the detachable propeller hub is inserted into the arm bearing sleeve, the bulges enter the L-shaped grooves, and the detachable propeller hub rotates by 90 degrees to be connected with the arm bearing sleeve; a spring is arranged in the engine arm bearing sleeve, and the detachable propeller hub is fixed in the engine arm bearing sleeve. Compared with the prior art, the engine arm bearing sleeve has the advantages that the structure is simple, the engine arm bearing sleeve and the detachable propeller hub can be rapidly disassembled and assembled through matching of the protrusions, the L-shaped grooves and the springs, and the engine arm bearing sleeve and the detachable propeller hub are firmly fixed after being installed.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, specifically point to a kind of propeller quick dismounting mechanism of coaxial unmanned plane. BACKGROUND

[0002] Traditional helicopter is single-rotor helicopter, all rotors are rotated along a rotating direction, so that the helicopter will be affected by rotor counter torque and spin, so tail rotor is needed to offset counter torque, realize heading stability and deflection. Compared with coaxial dual-rotor helicopter, because the rotating directions of upper and lower rotors are different, the generated rotation moment can be freely adjusted, and the counter torques of the two groups of rotors cancel each other out, so that spinning does not occur, because tail rotor is not needed, the horizontal direction size of the helicopter is greatly reduced, and the helicopter body is generally in the shape of a cylinder, and the spread size of the blades is the maximum size of the helicopter in the horizontal direction. However, when packaging and transporting, the size of the helicopter also needs to be reduced as much as possible, so that the helicopter occupies a smaller space and more unmanned aerial vehicles can be placed in the limited space.

[0003] In the existing coaxial dual-rotor helicopter technology, the fixing of the blades is basically by bolts, and the quick installation and disassembly of the blades are not considered. Even if the blades need to be disassembled, special tools are needed, and a lot of time is spent. Moreover, the anti-loosening performance of the blades is affected after multiple disassembly and reinstallation, and there is a risk of falling off during operation.

[0004] In view of the above technical problems, the present application provides a propeller quick dismounting mechanism of coaxial unmanned plane. CONTENT OF UTILITY MODEL

[0005] I. Technical problem to be solved

[0006] The technical problem to be solved by the utility model is that the blades are fixed by bolts, cannot be quickly installed and disassembled, a lot of time is spent, the anti-loosening performance of the blades is affected after multiple disassembly and reinstallation, and there is a risk of falling off during operation.

[0007] II. Technical scheme

[0008] To solve the above technical problems, the utility model provides a technical scheme: a propeller quick dismounting mechanism of coaxial unmanned plane, comprising a central bearing seat, an inclined disc connecting pull rod, a motor seat, an arm bearing sleeve, a detachable hub, a blade clamp and a blade.

[0009] The detachable hub and the arm bearing sleeve are a quick dismounting mechanism, two L-shaped grooves are arranged on the detachable hub, a protrusion corresponding to the two L-shaped grooves is arranged in the arm bearing sleeve, after the detachable hub is inserted into the arm bearing sleeve, the protrusion enters the L-shaped groove, and the detachable hub is connected with the arm bearing sleeve by rotating 90°.

[0010] The arm bearing sleeve is internally provided with a spring, and the detachable hub is fixed in the arm bearing sleeve.

[0011] As an improvement, the paddle clamp is fixedly installed on the detachable hub, and the tilt disc connecting pull rod is fixedly installed on the arm bearing sleeve.

[0012] As an improvement, the central bearing seat, the tilt disc connecting pull rod, the motor seat and the arm bearing sleeve are assembled through screws, and the detachable hub, the paddle clamp and the paddle blade are assembled through screws.

[0013] As an improvement, the protrusion and the spring are installed on the detachable hub, and the L-shaped groove is arranged on the inner wall of the arm bearing sleeve.

[0014] III. Advantages

[0015] Compared with the prior art, the utility model has the advantages of simple structure, quick disassembly and assembly of the arm bearing sleeve and the detachable hub through cooperation of the protrusion, the L-shaped groove and the spring, and firm fixing after installation. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 is a rotor assembly perspective view of the utility model discloses a kind of coaxial unmanned aerial vehicle's propeller quick disassembly mechanism.

[0017] Figure 2 is the quick disassembly mechanism structure schematic view of the utility model discloses a kind of coaxial unmanned aerial vehicle's propeller quick disassembly mechanism.

[0018] Figure 3 is the arm bearing sleeve structure schematic view of the utility model discloses a kind of coaxial unmanned aerial vehicle's propeller quick disassembly mechanism.

[0019] Figure 4 is the detachable hub structure schematic view of the utility model discloses a kind of coaxial unmanned aerial vehicle's propeller quick disassembly mechanism.

[0020] As shown in the figure: 1, central bearing seat;2, tilt disc connecting pull rod;3, motor seat;4, arm bearing sleeve;5, detachable hub;6, paddle clamp;7, paddle blade;8, L-shaped groove;9, protrusion;10, spring. DETAILED DESCRIPTION

[0021] Clearly, the described embodiments are merely a part of the embodiments of the present utility model, rather than all the embodiments; based on the embodiments in the present utility model, all the other embodiments obtained by the person of ordinary skill in the art without making creative labor belong to the range protected by the present utility model.

[0022] Embodiment one

[0023] As shown in the accompanying Figure 1 , a kind of propeller quick dismounting mechanism of coaxial unmanned aerial vehicle, including center bearing seat 1, tilt disc connection pull rod 2, motor seat 3, arm bearing sleeve 4, detachable hub 5, paddle clamp 6 and paddle 7, the paddle clamp 6 is fixedly installed on detachable hub 5, the tilt disc connection pull rod 2 is fixedly installed on arm bearing sleeve 4, pull connection rod drives arm bearing sleeve rotation, simultaneously drives paddle 7 to do overturning motion, the center bearing seat 1, tilt disc connection pull rod 2, motor seat 3 and arm bearing sleeve 4 are assembled by screw, the detachable hub 5, paddle clamp 6 and paddle 7 are assembled by screw.

[0024] As shown in the accompanying Figure 2 , accompanying Figure 3 And accompanying Figure 4 , detachable hub 5 and arm bearing sleeve 4 between the quick dismounting mechanism, detachable hub 5 is equipped with two L-shaped grooves 8, arm bearing sleeve 4 is equipped with protrusion 9 corresponding to two L-shaped grooves 8, after detachable hub 5 is inserted into arm bearing sleeve 4 inside, protrusion 9 enters L-shaped groove 8 inside, detachable hub 5 is rotated 90 ° and is connected with arm bearing sleeve 4;

[0025] The arm bearing sleeve 4 is equipped with spring 10 in inside, detachable hub 5 is fixed in arm bearing sleeve 4 inside.

[0026] The operation steps of installation are:

[0027] 1, the aperture of detachable hub 5 is aligned with the protrusion 9 in arm bearing sleeve 4, and is inserted into arm bearing sleeve 4, to the bottom.

[0028] 2, detachable hub is rotated 90 ° clockwise.

[0029] The operation steps of dismounting are:

[0030] 1, detachable hub 5 is pushed to the bottom in the direction of arm bearing sleeve 4.

[0031] 2, detachable hub is rotated 90 ° counterclockwise.

[0032] A spring 10 is arranged inside the arm bearing sleeve 4, and after the detachable hub 5 and the arm bearing sleeve 4 are installed together, only by pressing the spring 10 through the detachable hub 5 by external force, the protrusion 9 inside the arm bearing sleeve 4 can be axially rotated along the L-shaped groove 8 of the detachable hub 5. When the propeller rotates, the direction of centrifugal force and the direction of spring 10 elastic force are the same, because only the force opposite to the two can be removed by rotating the detachable hub 5, so when the propeller rotates, the quick detachable mechanism is more reliable, and in the design of the cooperation tolerance, the cooperation relationship between the protrusion 9 and the L-shaped groove 8 is interference fit, and there is no gap between the two after installation, so there will be no vibration due to the gap.

[0033] Embodiment two

[0034] On the basis of embodiment one, the protrusion 9 and the spring 10 are installed on the detachable hub 5, and the L-shaped groove 8 is arranged on the inner wall of the arm bearing sleeve 4, and the arm bearing sleeve 4 is inserted into the inside of the detachable hub 5.

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

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

[0037] The above describes the present application and its embodiments, which is not restrictive, and the drawings shown are only one of the embodiments of the present application, and the actual structure is not limited thereto. In general, if a person skilled in the art is inspired by it, without departing from the creative purpose of the present application, without creative design, similar structure and embodiments of the technical scheme can be designed, which should belong to the protection scope of the present application.

Claims

1. A quick disassembly mechanism of a coaxial unmanned aerial vehicle propeller, comprising a central bearing seat (1), an inclined disc connecting pull rod (2), a motor seat (3), an arm bearing sleeve (4), a detachable hub (5), a propeller clamp (6) and a propeller blade (7), characterized in that: The detachable hub (5) and the arm bearing sleeve (4) are quick disassembly mechanisms, the detachable hub (5) is provided with two L-shaped grooves (8), the arm bearing sleeve (4) is internally provided with protrusions (9) corresponding to the two L-shaped grooves (8), the protrusions (9) enter the L-shaped grooves (8) after the detachable hub (5) is inserted into the arm bearing sleeve (4), and the detachable hub (5) is connected with the arm bearing sleeve (4) by rotating 90°. The arm bearing sleeve (4) is internally provided with a spring (10) for fixing the detachable hub (5) in the arm bearing sleeve (4).

2. A quick release mechanism for propeller of coaxial unmanned aerial vehicle as claimed in claim 1, wherein: The propeller clamp (6) is fixedly installed on the detachable hub (5), and the inclined disc connecting pull rod (2) is fixedly installed on the arm bearing sleeve (4), the connecting rod is pulled to drive the arm bearing sleeve to rotate, and the propeller blade (7) is simultaneously driven to perform a turnover motion.

3. A quick release mechanism for propellers of a coaxial unmanned aerial vehicle as claimed in claim 2, wherein: The central bearing seat (1), the inclined disc connecting pull rod (2), the motor seat (3) and the arm bearing sleeve (4) are assembled by screws, and the detachable hub (5), the propeller clamp (6) and the propeller blade (7) are assembled by screws.

4. A quick release mechanism for propeller of coaxial unmanned aerial vehicle as claimed in claim 1, wherein: The protrusions (9) and the spring (10) are installed on the detachable hub (5), and the L-shaped grooves (8) are arranged on the inner wall of the arm bearing sleeve (4).

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