CN108945395B

CN108945395B - Prevent rotor system and unmanned aerial vehicle of kinking

Info

Publication number: CN108945395B
Application number: CN201810827652.0A
Authority: CN
Inventors: 张宇; 朱张赈; 李平
Original assignee: Zhejiang University ZJU
Current assignee: Zhejiang University ZJU
Priority date: 2018-07-25
Filing date: 2018-07-25
Publication date: 2020-11-17
Anticipated expiration: 2038-07-25
Also published as: CN108945395A

Abstract

The invention relates to a rotor system for preventing winding and an unmanned aerial vehicle, wherein the rotor system for preventing winding comprises a propeller, a rotary driving device, a mounting bracket, a first steering engine, a second steering engine and a horn, wherein the first steering engine is used for driving the rotary driving device to rotate around the X direction; the second steering engine is used for driving the first steering engine to rotate around the Y direction; the X direction and the Y direction are perpendicular to each other, the Y direction is the length direction of the horn, a second steering engine disc is fixed on a second steering engine, a torsion transmission piece is fixedly connected to the second steering engine disc and abuts against the inner ring of the bearing, an inner hole is formed in the torsion transmission piece, a connecting pipe is arranged in the inner hole, the connecting pipe is fixed with the horn after penetrating through the bearing, the electric slip ring is sleeved outside the connecting pipe, wherein a rotary terminal of the electric slip ring is fixedly connected with the connecting pipe, a connecting plate is arranged on a static terminal on the electric slip ring in a protruding mode, a connecting column is arranged above the bearing seat, and the connecting plate is fixedly connected. Therefore, the invention can solve the problem of easy winding.

Description

Prevent rotor system and unmanned aerial vehicle of kinking

Technical Field

The invention relates to the technical field of aircrafts, in particular to a rotor wing system capable of preventing winding and an unmanned aerial vehicle.

Background

At present, the most widely used unmanned aerial vehicle is a quad-rotor unmanned aerial vehicle, which drives an aircraft to fly by utilizing a motor to drive propellers, and realizes various flight attitudes such as forward flight, backward flight, left-right turning and the like by utilizing the rotation speed difference of each propeller. Various functional devices such as a camera, a thermal sensor and the like are generally mounted below the aircraft, and the devices are required to be connected with a holder so as to realize all-directional monitoring visual field at all angles. When the robot moves, the lifting force is adjusted by increasing and decreasing the rotating speed of the motor, so that the robot can move in the vertical direction, and if the robot wants to move in the horizontal direction, the robot needs to obtain the force in the horizontal direction by inclining the robot body, so that the robot body is pushed to move forwards. Obviously, such a forward motion is inefficient. The controllable parameters in the whole body model are smaller than the freedom of motion, so that the whole body model is an under-actuated assumed wing aircraft.

Therefore, the existing unmanned aerial vehicle needs to adjust the posture when the position is adjusted during flying, for example, the unmanned aerial vehicle needs to roll the body to realize the forward, backward or steering actions, thereby reducing the maneuverability and the sensitivity; the change of the motion attitude of the unmanned aerial vehicle is realized by the rotating speed difference of the propeller, so that the unmanned aerial vehicle has general maneuverability, slow response time for changing the course, insufficient cruising ability, and omnibearing monitoring visual field of mounted equipment can be realized by means of the holder; in addition, when the unmanned aerial vehicle flies flatly, the horizontal component force in the advancing direction needs to be generated by means of the inclination of the body, so that the body projection area in the flying direction is inevitably generated, and when the flying speed is increased or other airflow disturbance interference exists, the body resistance is increased, so that the energy consumption is high, and the cruising ability is insufficient.

And the rotor system of the existing unmanned aerial vehicle only has the freedom degree that the propeller rotates around the axis direction of the propeller, and the freedom degree is less. In addition, the electric wire twines easily on the screw, influences the rotation of screw, causes unmanned aerial vehicle to fall even.

Disclosure of Invention

The invention aims to provide a rotor system with multiple degrees of freedom, which aims to solve the technical problem of low degree of freedom in the prior art.

The technical problem of the invention is mainly solved by the following technical scheme: a multi-degree-of-freedom rotor wing system comprises a propeller, a rotary driving device, a mounting bracket, a first steering engine, a second steering engine and a horn, wherein the rotary driving device is used for driving the propeller to rotate around the axis direction of the propeller; the second steering engine is connected with the first steering engine through the horn and used for driving the first steering engine to rotate around the Y direction; the X direction and the Y direction are perpendicular to each other, and the Y direction is the length direction of the machine arm.

Wherein the rotation driving device includes, but is not limited to, a motor. According to the invention, the first steering engine is arranged to drive the mounting bracket to rotate, so that the rotary driving device, namely the propeller, is driven to rotate around the X direction; and the second steering engine is arranged to drive the machine arm to rotate, so that the first steering engine is driven to rotate around the Y direction, and the propeller can be driven to rotate around the Y direction. Therefore, the invention increases the freedom degree of the propeller rotating around the X direction and the Y direction, and has more freedom degrees and better maneuverability.

Preferably, the horn is a pipe type and is fixedly connected with the first steering engine through a connecting piece, the connecting piece comprises a U-shaped support and a pipe clamp which are connected with each other, the first steering engine is clamped between two end parts of an opening of the U-shaped support, and the pipe clamp is sleeved outside the horn.

The horn is the cast, namely the hollow setting in it, has lightened the weight of the invention, improve maneuverability and duration of the invention. The horn includes, but is not limited to, a long carbon fiber tube. The connecting piece comprises U-shaped support and pipe clamp, and the structure is retrencied and the steadiness is good. The symmetrical axis between the two ends of the opening of the U-shaped support is overlapped with the axis of the pipe clamp, so that when the first steering engine is not started, namely the inclination angle along the X direction is 0 degree, the stable arrangement of the first steering engine, the rotary driving device and the propeller is ensured; and the influence of the gravity of the first steering engine, the rotary driving device and the propeller on the stable posture maintenance after the rotation of the propeller is stopped is also reduced.

The machine arm can be arranged in a telescopic mode or in a folding mode, occupied space of the machine arm in the non-use state is reduced, and the machine arm is convenient to store.

Preferably, the mounting bracket is U-shaped, the first steering engine is clamped between two end parts of the opening of the mounting bracket through a first steering engine disc, and the two end parts of the opening of the mounting bracket and the two end parts of the opening of the U-shaped bracket are arranged in parallel or in perpendicular.

The arrangement of the first steering engine disc is not only used for transmitting the swing amplitude of the first steering engine, but also can enable the two end parts of the opening of the mounting bracket and the two end parts of the opening of the U-shaped bracket to be arranged in parallel or vertically by utilizing the thickness of the first steering engine disc, namely, the two end parts and the two end parts are not on the same plane, so that the rotation angle of the mounting bracket is not influenced by the U-shaped bracket, and the structure of the steering engine disc is more simplified and the maneuverability is.

Preferably, the two end parts of the opening of the U-shaped bracket are provided with second limiting blocks, and the second limiting blocks can abut against the mounting bracket after the mounting bracket rotates.

And the second limiting block is used for limiting the rotating angle of the mounting bracket, namely the rotating angle of the propeller around the X direction. The invention adds a mechanical protection measure on the basis of realizing braking by utilizing the self-locking property of the steering engine. It should be noted that the rotation angle range of the propeller around the X direction is between-130 degrees and +30 degrees, so that the propeller is prevented from hitting the horn, the flight stability of the unmanned aerial vehicle is influenced when the unmanned aerial vehicle is applied, and the falling accident of the unmanned aerial vehicle is caused.

The thickness sum of the opening end part of the U-shaped support and the thickness sum of the second limiting block are larger than or equal to the thickness sum of the disc of the first steering engine and the opening end part of the mounting support, and the lengths of the second limiting block exceeding the two ends of the U-shaped support can be set differently.

The invention also aims to provide a rotor system for preventing winding so as to solve the technical problem of easy winding in the prior art.

The technical problem of the invention is mainly solved by the following technical scheme: the utility model provides a prevent rotor system of kinking, includes foretell multi freedom's rotor system, still includes electric sliding ring, bearing and is used for the installation the bearing frame of bearing, the second steering wheel on be fixed with second steering wheel disc, the rigid coupling has the transmission piece of twisting on the second steering wheel disc, twist reverse the transmission piece with the inner circle of bearing offsets, it is equipped with the hole on the transmission piece to twist reverse, the hole in wear to be equipped with the connecting pipe, the connecting pipe pass behind the bearing with the horn is fixed, the electric sliding ring overlaps establishes outside the connecting pipe, wherein, the rotary terminal of electric sliding ring with the connecting pipe rigid coupling, the last static terminal epirelief of electric sliding ring is equipped with the connecting plate, the top of bearing frame is equipped with the orientation the bellied spliced pole of electric sliding ring, the connecting plate with the spliced pole rigid coupling.

Since the rotor system with multiple degrees of freedom described above has the above-described technical effects, the rotor system with the entanglement prevention of the rotor system also has the same technical effects. In practical application, one end of the horn is in transmission connection with the second steering engine, and the other end of the horn is connected with the first steering engine, the rotation driving device and the propeller, so that when the second steering engine drives the horn to rotate, conditions such as winding and knotting of electric wires are easily caused, even the propeller is controlled to incline by the first steering engine, so that the electric wires wind the propeller or the propeller is prevented from rotating around the axis direction of the propeller, and the maneuverability of the electric wire rope.

Preferably, the outer wall of the torsion transmission piece is provided with a convex block, the bearing seat is provided with a first limiting block, and the first limiting block can abut against the convex block after the torsion transmission piece rotates.

Because the torsion transmission piece is used for transmitting torque, the first limit block can be used for limiting the rotation angle of the torsion transmission piece, and the effect of limiting the rotation angle of the propeller around the Y direction, namely the horn, is achieved. According to the invention, the rotation angle of the propeller around the Y direction is limited to +/-90 degrees through the matching of the first limiting block and the convex block, and a mechanical protection measure is added on the basis of realizing braking by utilizing the self-locking property of the steering engine. Wherein, the lug can be along the rectangular shape of circumference setting, increases its steadiness.

Preferably, the bearing seat is provided with a bearing retainer ring which abuts against an outer ring of the bearing, the connecting pipe is provided with a flange which can abut against an inner ring of the bearing, the flange and the bearing retainer ring are positioned on one side of the bearing, and the torsion transmission piece is positioned on the other side of the bearing.

The arrangement of the bearing retainer ring, the flange and the torsion transmission piece can make the bearing give full play to and keep the due performance for a long time, improve the precision and prolong the service life.

The invention further aims to provide the unmanned aerial vehicle to solve the technical problems of poor maneuverability and insufficient cruising ability in the prior art.

The technical problem of the invention is mainly solved by the following technical scheme: an unmanned aerial vehicle, includes frame and rotor system, and this rotor system is foretell rotor system of multi freedom.

Because foretell rotor system of multi freedom has foretell technological effect, the unmanned aerial vehicle who has this rotor system also has same technological effect. Therefore, the invention can change the inclination angle of the propeller, namely change the helicoidal lifting surface, and realize the advancing, retreating or steering action of the unmanned aerial vehicle. For example: if the aircraft needs to move in the vertical direction, each rotor wing needs to be vertically upwards, and if the aircraft needs to horizontally fly, the rotor wings can be properly tilted towards the direction to be flown, and the whole aircraft body does not need to be tilted first and then flies, so the aircraft can carry out more complex space curve movement, the constructed algorithm model is better, the maneuverability is strong, the sensitivity is high, the maneuverability is better, the resistance brought by the inclined aircraft body is reduced, the energy consumption is lower, and the endurance is better.

The technical problem of the invention is mainly solved by the following technical scheme: an unmanned aerial vehicle, includes frame and rotor system, and this rotor system is foretell rotor system who prevents kinking.

Because foretell rotor system that prevents kinking has foretell technological effect, the unmanned aerial vehicle that has this rotor system also has same technological effect.

Preferably, the number of the rotor systems is at least 2, the rotor systems are distributed on the rack in a circumferential array mode, the rack comprises an upper platform and a lower platform which are arranged at an upper interval and a lower interval, the second steering engine is fixed on the lower platform through the second steering engine mounting seat, and the bearing seat and the second steering engine mounting seat are clamped between the upper platform and the lower platform and enable the upper platform and the lower platform to be fixed.

The frame comprises an upper platform and a lower platform, which is convenient for installation and reduces the weight of the invention, and a camera, a landing gear and the like can be arranged on the frame.

Preferably, the upper platform and the lower platform are arranged in the same size and shape and are provided with hollow holes.

The arrangement of the hollow holes can be used for reducing the weight and improving the maneuverability and the cruising ability of the invention. The hollow holes of the upper platform and the hollow holes of the lower platform are aligned with each other and can be used for air and airflow to pass through.

Preferably, the rotor systems are three, and the included angle between adjacent rotor systems is 120 degrees.

The rotary wing systems are three, the included angle between the adjacent rotary wing systems is 120 degrees, and each rotary wing system comprises the rotating speed of three controllable motors, namely the rotating speed of a propeller, and also has two tilting degrees of freedom. Therefore, the whole machine body has nine controllable parameters, so that the invention has strong maneuverability and better maneuverability, can carry out more complex space curvilinear motion, and has better adaptability of the constructed algorithm model and more proper calculation complexity and time cost.

Based on this, compared with the prior art, the invention has the advantages of high degree of freedom, no winding, more complex space curve motion, better constructed algorithm model, strong maneuverability, high sensitivity, better maneuverability, reduced resistance brought by the inclined machine body, less energy consumption and better cruising ability.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

FIG. 1 is a schematic structural view of a rotor system of the present invention;

fig. 2 is a schematic structural diagram of the unmanned aerial vehicle of the present invention;

FIG. 3 is a cross-sectional view of FIG. 2;

fig. 4 is an enlarged view of a portion a of fig. 3.

Reference numerals:

1-a frame; 11-an upper platform; 12-a lower platform;

13-hollowing out the holes; 2-a rotor system; 21-a propeller;

22-a rotary drive; 23-mounting a bracket; 24-a first steering engine;

241-a first steering engine disk; 25-a second steering engine; 251-a second steering engine disk;

252-a torsion transfer; 2521-inner bore; 2522-a bump;

253-connecting tube; 2531-flange; 26-a horn;

261-a connector; 2611-a U-shaped bracket; 2612-pipe clamp;

2613-a second limiting block; 27-an electrical slip ring; 271-connecting plate;

28-a bearing; 29-a bearing seat; 291-connecting column;

292-a first stopper; 293-bearing retainer ring; 254-second steering engine mount.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "front", "rear", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

The first embodiment of the rotor system with multiple degrees of freedom:

referring to fig. 1, 2 and 3, the device comprises a propeller 21, a rotation driving device 22, a mounting bracket 23, a first steering engine 24, a second steering engine 25 and a horn 26, wherein the rotation driving device 22 is connected with the propeller 21 and is used for driving the propeller 21 to rotate around the axis direction thereof; the first steering engine 24 is connected with the rotary driving device 22 through a mounting bracket 23 and is used for driving the rotary driving device 22 to rotate around the X direction; the second steering engine 25 is connected with the first steering engine 24 through a horn 26 and is used for driving the first steering engine 24 to rotate around the Y direction; the X direction and the Y direction are perpendicular to each other, and the Y direction is the longitudinal direction of the horn 26.

Referring to fig. 1, 2 and 3, the horn 26 is a tube and is fixedly connected to the first steering gear 24 through a connecting member 261, the connecting member 261 includes a U-shaped bracket 2611 and a pipe clamp 2612 which are connected to each other, the first steering gear 24 is clamped between two open ends of the U-shaped bracket 2611, and the pipe clamp 2612 is sleeved outside the horn 26.

Referring to fig. 1, 2 and 3, the mounting bracket 23 is U-shaped, the first steering gear 24 is clamped between two opening ends of the mounting bracket 23 through the first steering gear disc 241, and the two opening ends of the mounting bracket 23 are parallel to or perpendicular to the two opening ends of the U-shaped bracket 2611.

Referring to fig. 1, 2 and 3, the two ends of the opening of the U-shaped bracket 2611 are provided with second limiting blocks 2613, and the second limiting blocks 2613 can abut against the mounting bracket 23 after the mounting bracket 23 rotates.

And the second limiting block is used for limiting the rotating angle of the mounting bracket, namely the rotating angle of the propeller around the X direction. The invention adds a mechanical protection measure on the basis of realizing braking by utilizing the self-locking property of the steering engine. It should be noted that the rotation angle of the propeller around the X direction is in the range of-130 degrees to +30 degrees, so that the propeller is prevented from hitting the horn, the flight stability of the invention is influenced, and the falling accident of the invention is avoided.

First embodiment of the anti-kinking rotor system:

referring to fig. 1, 3 and 4, the rotor system capable of preventing wire winding comprises the rotor system with multiple degrees of freedom, and further comprises an electric slip ring 27, a bearing 28 and a bearing seat 29 for mounting the bearing 28, a second steering engine disk 251 is fixed on a second steering engine 25, a torsion transmission member 252 is fixedly connected to the second steering engine disk 251, the torsion transmission member 252 abuts against an inner ring of the bearing 28, an inner hole 2521 is formed in the torsion transmission member 252, a connecting pipe 253 penetrates through the inner hole 2521, the connecting pipe 253 is fixed to the horn 26 after penetrating through the bearing 28, the electric slip ring 27 is sleeved outside the connecting pipe 253, wherein a rotating terminal of the electric slip ring 27 is fixedly connected to the connecting pipe 253, a connecting plate 271 is convexly arranged on a stationary terminal of the electric slip ring 27, a connecting post 291 protruding towards the electric slip ring 27 is arranged on the bearing seat 29, and the connecting plate 271.

Referring to fig. 1, 3, and 4, a protrusion 2522 is disposed on an outer wall of the torsion transmission member 252, a first stopper 292 is disposed on the bearing 28, and the first stopper 292 can abut against the protrusion 2522 after the torsion transmission member 252 rotates.

Referring to fig. 1 and 4, a bearing retainer 293 is disposed on the bearing seat 29 to abut against an outer ring of the bearing 28, a flange 2531 is disposed on the connecting pipe 253 to abut against an inner ring of the bearing 28, the flange 2531 and the bearing retainer 293 are disposed on one side of the bearing 28, and the torsion transmitter 252 is disposed on the other side of the bearing 28.

The first embodiment of the unmanned aerial vehicle:

see fig. 2, comprising a frame 1 and a rotor system 2, which rotor system is a multiple degree of freedom rotor system as described above.

Embodiment two of unmanned aerial vehicle:

see fig. 2, comprising a frame 1 and a rotor system 2, which is the above-described anti-kinking rotor system.

Referring to fig. 1, 2 and 3, the frame 1 includes an upper platform 11 and a lower platform 12 which are arranged at an interval from top to bottom, the second steering engine 25 is fixed on the lower platform 12 through a second steering engine mounting seat 254, and the bearing seat 29 and the second steering engine mounting seat 254 are clamped between the upper platform 11 and the lower platform 12 to fix the upper platform 11 and the lower platform 12.

Referring to fig. 1, three rotor systems 2 are provided, and the included angle between adjacent rotor systems 2 is 120 °.

Finally, it is to be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A wind-up prevention rotor system comprising a rotor and a rotary drive device for driving the rotor to rotate about its axis, characterized in that: the first steering engine is connected with the rotary driving device through the mounting bracket and is used for driving the rotary driving device to rotate around the X direction; the second steering engine is connected with the first steering engine through the horn and used for driving the first steering engine to rotate around the Y direction; the X direction and the Y direction are perpendicular to each other, and the Y direction is the length direction of the machine arm;

the second steering wheel on be fixed with the second steering wheel disc, the rigid coupling has the transmission piece of twisting on the second steering wheel disc, the transmission piece of twisting with the inner circle of bearing offsets, twist and be equipped with the hole on the transmission piece, the hole in wear to be equipped with the connecting pipe, the connecting pipe pass behind the bearing with the horn is fixed, the electricity sliding ring overlaps to be established outside the connecting pipe, wherein, the rotary terminal of electricity sliding ring with the connecting pipe rigid coupling, the last static terminal epirelief of electricity sliding ring is equipped with the connecting plate, the top of bearing frame is equipped with the orientation the bellied spliced pole of electricity sliding ring, the connecting plate with the spliced pole rigid coupling.

2. The anti-kinking rotor system of claim 1, wherein: the mechanical arm is a pipe type and is fixedly connected with the first steering engine through a connecting piece, the connecting piece comprises a U-shaped support and a pipe clamp which are connected with each other, the first steering engine is clamped between two end portions of an opening of the U-shaped support, and the pipe clamp is sleeved outside the mechanical arm.

3. The anti-kinking rotor system of claim 2, wherein: the mounting bracket is U-shaped, the first steering engine is clamped between the two ends of the opening of the mounting bracket through a first steering engine disc, and the two ends of the opening of the mounting bracket and the two ends of the opening of the U-shaped bracket are arranged in parallel or vertically.

4. The anti-kinking rotor system of claim 3, wherein: and second limiting blocks are arranged at two end parts of the opening of the U-shaped support, and the second limiting blocks can be abutted against the mounting support after the mounting support rotates.

5. The anti-kinking rotor system of any of claims 1-4, wherein: the outer wall of the torsion transmission piece is provided with a convex block, the bearing seat is provided with a first limiting block, and the first limiting block can abut against the convex block after the torsion transmission piece rotates.

6. The anti-kinking rotor system of any of claims 1-4, wherein: the bearing seat is provided with a bearing retainer ring which is abutted against the outer ring of the bearing, the connecting pipe is provided with a flange which can be abutted against the inner ring of the bearing, the flange and the bearing retainer ring are positioned on one side of the bearing, and the torsion transmission piece is positioned on the other side of the bearing.

7. An unmanned aerial vehicle, includes frame and rotor system, its characterized in that: the rotor system is a kinking-preventing rotor system as recited in any one of claims 1 to 6.

8. A drone according to claim 7, characterized in that: the rotor system is equipped with 2 at least, and each the rotor system becomes the circumference array and distributes in the frame, the frame includes upper mounting plate and lower platform that becomes upper and lower interval setting, the second steering wheel passes through the second steering wheel mount pad to be fixed on the platform down, the bearing frame with the second steering wheel mount pad presss from both sides and establishes upper mounting plate with between the platform down, and make upper mounting plate with the platform is fixed down.

9. An unmanned aerial vehicle, includes frame and rotor system, its characterized in that: the rotor system comprises a propeller and a rotary driving device for driving the propeller to rotate around the axis direction of the propeller, and is characterized in that: the first steering engine is connected with the rotary driving device through the mounting bracket and is used for driving the rotary driving device to rotate around the X direction; the second steering engine is connected with the first steering engine through the horn and used for driving the first steering engine to rotate around the Y direction; the X direction and the Y direction are perpendicular to each other, and the Y direction is the length direction of the machine arm;

the horn is fixedly connected with the first steering engine through a connecting piece, and the connecting piece comprises a U-shaped bracket;

second limiting blocks are arranged at two end parts of the opening of the U-shaped bracket, and the second limiting blocks can be abutted against the mounting bracket after the mounting bracket rotates;

the horn is the cast, the connecting piece still include with U-shaped support interconnect's pipe clamp, first steering wheel clamp establish between U-shaped support opening both ends, the pipe clamp cover is established outside the horn.