CN115924141B - A UAV rotor mechanism - Google Patents

Abstract

The invention belongs to the technical field of propellers, and particularly relates to an unmanned aerial vehicle rotor wing mechanism which comprises a silencing air guide sleeve fixedly installed with an unmanned aerial vehicle body and a driving shaft connected with an output shaft of a motor, wherein a propeller connecting shell is assembled at the top end of the driving shaft, a jacking block is integrally and fixedly connected to the top end of the propeller connecting shell, propeller blades are fixedly connected to the outer surface of the jacking block in an annular array mode, an inner rotating ring plate is movably installed in the propeller connecting shell, and the top end of the driving shaft and the inner rotating ring plate form a detachable connection relation. According to the invention, the horizontal airflow can be changed into the vertical airflow while the flight noise reduction is realized, so that the lifting force of the unmanned aerial vehicle is improved, and in addition, the possibility of damage to the motor and fracture of the corresponding connection part can be greatly reduced by enabling the motor to drive the driving shaft to idle when the propeller stops accidentally.

Description

A UAV rotor mechanism

technical field

The invention belongs to the technical field of propellers, and in particular relates to an unmanned aerial vehicle rotor mechanism.

Background technique

Unmanned aircraft, referred to as "UAV", is an unmanned aircraft controlled by radio remote control equipment and self-contained program control device, or is completely or intermittently operated autonomously by the on-board computer. , UAVs are often more suitable for tasks that are too "dull, dirty or dangerous". Among them, the flight of UAVs is mainly completed by the motor driving the propeller to rotate, and, in order to reduce the noise generated when the propeller rotates, it will pass Improve the structure of the propeller to complete the noise reduction effect, and this type of propeller is also called noise reduction propeller.

Problems existing in the prior art:

During the flight of existing UAVs, when the noise reduction propeller is unexpectedly blocked and stops rotating directly, the motor driving the propeller will also be blocked at the same time, which will greatly increase the working load of the motor in a short period of time, which may eventually lead to The motor is directly damaged, and when the propeller just stops rotating, the parts with too high speed stop rotating suddenly, and the inertial force generated during the process will directly act on the connection between the motor shaft and the propeller, which is likely to cause the connection to be damaged. Breakage occurs directly, and what's more, it may directly aggravate the damage of the drone, resulting in high maintenance and replacement costs.

Contents of the invention

The purpose of the present invention is to provide a UAV rotor mechanism, which can change the horizontal airflow into a vertical airflow while realizing flight noise reduction, thereby improving the lifting force of the UAV. When stopping, by making the motor drive the drive shaft to idle, the possibility of damage to the motor and breakage of the corresponding connection is greatly reduced.

The technical scheme that the present invention takes is specifically as follows:

A UAV rotor mechanism, including a sound-absorbing shroud fixedly installed with the UAV body and a drive shaft connected to the output shaft of the motor, the top of the drive shaft is equipped with a propeller housing, and the propeller housing The top of the top is integrally fixedly connected with a top joint block, and the outer surface of the top joint block is fixedly connected with propeller blades in an annular array;

The inside of the propeller housing is movably installed with an inner swivel plate, and the top end of the drive shaft forms a detachable connection relationship with the inner swivel plate, and the outer wall of the top end of the drive shaft is provided with a card ring in an annular array. holes, the upper surface of the inner swivel plate is provided with guide rod grooves in an annular array, and the lower surface of the inner swivel plate is provided with guide block grooves in an annular array;

The inner top edge of the propeller housing is rotatably connected with a connecting rod 1 in an annular array, the bottom end of the connecting rod 1 is fixedly connected with a connecting plate, and the lower surface of the end of the connecting plate is fixedly connected with a connecting rod 2 , the bottom end of the connecting rod 2 is rotatably installed with a slider, wherein the connecting rod 2 moves through the guide rod groove, and the slider is slidably installed inside the guide block groove. One end is set as a tip, and the tip of the slider is movably inserted into the locking hole.

The number of the guide rod grooves is the same as that of the guide block grooves and the positions correspond to each other, and the guide rod grooves communicate with the guide block grooves.

A spring is connected between the end of the slide block away from the tip and the inner wall of the guide block groove.

The outer diameter of the inner swivel plate is the same as the inner diameter of the propeller housing, and the inner diameter of the inner swivel plate is the same as the diameter of the drive shaft.

The end of the propeller blade is uniformly and fixedly provided with a spoiler, and the upper surface of the propeller blade close to the end of the spoiler is equidistantly provided with splitter grooves.

The side between the spoiler and the propeller blade and away from the direction of rotation of the propeller blade is set at an obtuse angle.

The lower part of the sound-absorbing air guide cover is integrally and fixedly provided with an extended cover body, and the diameter of the expanded cover body is larger than that of the sound-absorbing air guide cover.

The technical effect that the present invention obtains is:

(1) In the present invention, the design of the sound-absorbing shroud can effectively reduce the noise generated when the horizontal high-speed airflow hits the surrounding air, and further reduce the noise generated between the high-speed airflow by reducing the impact force of the airflow on the sound-absorbing shroud. In order to achieve the effect of flight noise reduction, in addition, the setting of the expansion cover can change the airflow rushing to the sound-absorbing shroud, making it change from horizontal airflow to vertical airflow, and the direction of this vertical airflow is vertical Down, thereby further improving the downward thrust generated by the propeller blade work, and indirectly improving the lift of the UAV.

(2) In the present invention, when the propeller blade is accidentally blocked and stops rotating directly, the drive shaft together with the inner rotating ring plate will rotate relative to the propeller housing, and the slider will move away from the drive along the direction of the guide block groove. The shaft moves, and when the slider breaks away from the card hole, the drive shaft is separated from the inner swivel plate, and finally the motor can drive the drive shaft to idle. The above process can directly make the drive shaft and the propeller blade stop rotating unexpectedly Disconnect the transmission connection between the propeller blades, so as to avoid hindering the work of the motor that drives the propeller blades to rotate, and by making the motor drive the drive shaft to idle, the working load of the motor is greatly reduced, the possibility of motor damage is reduced, and the motor is prevented from being directly damaged .

(3) In the present invention, when the propeller blade has just stopped rotating, the inner swivel ring plate will rotate in the propeller joint housing, and the slider will move linearly and squeeze the spring during the process, so that the drive shaft will have a certain speed before separation. A transition process, which can avoid the sudden stop of the propeller blades and cause damage to the joint between the drive shaft and the inner swivel plate.

Description of drawings

Fig. 1 is the assembling structure diagram of the sound-absorbing dome provided by the embodiment of the present invention and propeller blade;

Fig. 2 is the flow schematic diagram of the airflow when the propeller blade provided by the embodiment of the present invention works;

Fig. 3 is an internal cross-sectional view of the propeller housing provided by the embodiment of the present invention;

Fig. 4 is an assembly and exploded view of the drive shaft, the propeller housing and the inner swivel plate provided by the embodiment of the present invention;

Fig. 5 is a partially enlarged structure diagram at point A in Fig. 4 .

In the accompanying drawings, the list of parts represented by each label is as follows:

1. Silencer shroud; 101. Expansion cover body; 2. Drive shaft; 201. Clamping hole; 3. Propeller connection shell; 301. Top connection block; 302. Inner rotary ring plate; 303. Guide rod groove; 305, connecting rod one; 306, connecting plate; 307, connecting rod two; 308, slide block; 309, spring; 4, propeller blade; 401, splitter groove; 402, spoiler.

Detailed ways

In order to make the objects and advantages of the present invention clearer, the present invention will be specifically described below in conjunction with examples. It should be understood that the following words are only used to describe one or several specific implementation modes of the present invention, and do not strictly limit the protection scope of the specific claims of the present invention.

As shown in Figures 1-5, a UAV rotor mechanism includes a sound-absorbing shroud 1 fixedly installed with the UAV body and a drive shaft 2 connected to the output shaft of the motor. The top of the drive shaft 2 is equipped with a propeller The connecting shell 3 (this assembly method is detachable, and before disassembly, the fixing effect between the propeller connecting shell 3 and the drive shaft 2 remains in a good state), the top of the propeller connecting shell 3 is integrally fixedly connected with The top connecting block 301, the outer surface of the top connecting block 301 is fixedly connected with the propeller blades 4 in an annular array.

According to the above structure, when the motor on the arm of the UAV drives the drive shaft 2 to rotate, it will drive the propeller housing 3, the top block 301 and the propeller blade 4 to rotate at a high speed. The downward flow creates the thrust that does the work of flying the drone.

Referring to accompanying drawings 3, 4 and 5, an inner swivel plate 302 is movably installed inside the propeller housing 3, and the top end of the drive shaft 2 and the inner swivel plate 302 form a detachable connection relationship, and the drive shaft 2 The upper surface of the inner swivel plate 302 is provided with guide rod grooves 303 in an annular array, and the lower surface of the inner swivel plate 302 is provided with guide block grooves 304 in an annular array. The slots 303 and the guide block slots 304 have the same number and corresponding positions, and the guide rod slots 303 communicate with the guide block slots 304 .

Referring to accompanying drawings 3, 4 and 5, the inner top edge of the propeller housing 3 is rotatably connected to a connecting rod 1 305 in an annular array, and the bottom ends of the connecting rod 305 are fixedly connected to a connecting plate 306, and the connecting plate 306 The lower surface of the end is fixedly connected with the second rod 307, and the bottom end of the second rod 307 is rotated with a slider 308, wherein the second rod 307 moves through the guide rod groove 303, and the slider 308 is slidably installed in the guide groove 304. Inside, one end of the slider 308 is set as a tip, and the tip of the slider 308 is movably inserted into the card hole 201 , and a spring 309 is connected between the end of the slider 308 away from the tip and the inner wall of the guide block groove 304 .

Referring to accompanying drawing 3, the outer diameter of the inner swivel plate 302 is the same as the inner diameter of the propeller housing 3, and the inner diameter of the inner swivel plate 302 is the same as the diameter of the drive shaft 2.

According to the above structure, when the propeller blade 4 is accidentally blocked and stops rotating directly, at this time, the drive shaft 2 together with the inner rotating ring plate 302 at the top will rotate relative to the propeller housing 3, due to the connecting rod one 305 and The inner wall of the propeller housing 3 is transferred, so the connecting plate 306 will deflect, and the corresponding connecting rod 2 307 will move away from the center of the inner rotating ring plate 302 along the direction of the guide rod groove 303, and the slider 308 will move along the guide block The direction of the slot 304 moves away from the drive shaft 2, and when the slider 308 breaks away from the clamping hole 201, the drive shaft 2 is separated from the inner swivel plate 302, and finally the motor can drive the drive shaft 2 to idle. The above process can be performed in After the propeller blade 4 stops rotating unexpectedly, the transmission connection relationship between the drive shaft 2 and the propeller blade 4 is directly disconnected, thereby avoiding the accidental stop of the motor driving the propeller blade 4, and greatly reducing the The working load of the motor reduces the possibility of damage to the motor and prevents the motor from being directly damaged; in addition, when the propeller blade 4 just stops rotating, the inner rotating ring plate 302 will rotate in the propeller housing 3, and the slider 308 will rotate in the process. Move in a straight line and squeeze the spring 309, and use this process to make the drive shaft 2 have a transition process before separation, which can avoid the sudden stop of the propeller blade 4 and cause damage to the junction between the drive shaft 2 and the inner swivel plate 302.

With reference to accompanying drawing 1 and Fig. 2, the end of propeller blade 4 is uniformly fixedly provided with spoiler 402, and the upper surface of propeller blade 4 near the end of spoiler 402 is equidistantly provided with diverter groove 401, and spoiler 402 and The side between the propeller blades 4 and away from the direction of rotation of the propeller blades 4 is set at an obtuse angle, and the bottom of the sound-absorbing dome 1 is fixedly provided with an expansion cover 101 , and the diameter of the expansion cover 101 is larger than that of the sound-absorbing dome 1 diameter size.

According to the above-mentioned structure, when the propeller blade 4 rotates normally, there will be an air flow to flow horizontally from the propeller blade 4 to the sound-absorbing shroud 1 on the edge, wherein the setting of the splitter groove 401 can not only reduce the resistance when the propeller blade 4 rotates, but also improve the horizontal The flowing airflow is divided to reduce the impact of the horizontal airflow on the sound-absorbing dome 1. In addition, the spoiler 402 has a certain inclination compared with the propeller 4, and the airflow will generate airflow movement on the propeller. Flow around motion is generated, which will not only increase the resistance of the propeller, but also bring additional vibration and noise to the propeller. The spoiler 402 plays a role in blocking the airflow around the propeller wing tip position, which can reduce the resistance effect of the airflow around the propeller, and can also reduce the impact of the horizontal airflow on the sound-absorbing shroud 1. This technology The application in the prior art is relatively mature. For details, please refer to the announcement document CN 218112972 U. No more specific details will be given here. The noise generated, and by reducing the impact force of the airflow on the sound-absorbing shroud 1, the noise generated between the high-speed airflow is further reduced, so as to achieve the effect of flight noise reduction. In addition, the setting of the expanded cover body 101 can Change the airflow rushing towards the sound-absorbing shroud 1 so that it changes from a horizontal airflow to a vertical airflow, and the direction of the vertical airflow is vertically downward, thereby further improving the downward thrust generated by the propeller blade 4, indirectly improving the The lift of the drone.

The working principle of the present invention is: under the premise of the normal rotation of the propeller blade 4, when the motor on the arm of the UAV drives the drive shaft 2 to rotate, it will drive the propeller connecting shell 3, the top connecting block 301 and the propeller blade 4 to rotate at a high speed. When the propeller blade 4 rotates, a large amount of airflow flows downward to generate thrust to complete the flight of the drone. Wherein the setting of the splitter groove 401 can not only reduce the resistance when the propeller blade 4 rotates, but also divide the air flow of the horizontal flow, reduce the impact of the horizontal air flow on the sound-absorbing dome 1, and in addition, the obtuse angle disturbance with the end of the propeller blade 4 The flow plate 402 can also reduce the impact of the horizontal airflow on the sound-absorbing dome 1. In addition, the setting of the expansion cover body 101 can change the airflow rushing to the sound-absorbing dome 1, so that it changes from a horizontal airflow to a vertical airflow;

When the propeller blade 4 is accidentally blocked and stops rotating directly, at this time, the drive shaft 2 together with the inner rotating ring plate 302 at the top will rotate relative to the propeller housing 3, because the connecting rod 1 305 and the propeller housing 3. The inner wall is transferred, so the connecting plate 306 will be deflected, and the corresponding connecting rod 2 307 will move away from the center of the inner swivel ring plate 302 along the direction of the guide rod groove 303, and the slider 308 will move along the direction of the guide block groove 304 Moving away from the drive shaft 2 , when the slider 308 breaks away from the clamping hole 201 , the drive shaft 2 is separated from the inner rotating ring plate 302 , and finally the motor can drive the drive shaft 2 to idle.

The above is only a preferred embodiment of the present invention, it should be pointed out that for those of ordinary skill in the art, without departing from the principle of the present invention, some improvements and modifications can also be made, and these improvements and modifications should also be It is regarded as the protection scope of the present invention. The structures, devices and operation methods not specifically described and explained in the present invention, unless otherwise specified and limited, shall be implemented according to conventional means in the art.

Claims (7)

1. A UAV rotor mechanism, including a sound-absorbing shroud (1) fixedly installed with the UAV body and a drive shaft (2) connected to the output shaft of the motor, characterized in that: the drive shaft (2) The top end of the propeller housing (3) is equipped with a propeller housing (3), and the top end of the propeller housing (3) is integrally fixedly connected with a top joint block (301), and the outer surface of the top joint block (301) is fixed in an annular array Connected with propeller blades (4); An inner swivel plate (302) is movably installed inside the propeller housing (3), and the top end of the drive shaft (2) forms a detachable connection with the inner swivel plate (302), so The top outer wall of the drive shaft (2) is provided with card holes (201) in an annular array, the upper surface of the inner swivel plate (302) is provided with guide rod grooves (303) in an annular array, and the inner swivel The lower surface of the plate (302) is provided with guide block grooves (304) in an annular array; The inner top edge of the propeller housing (3) is rotatably connected with a connecting rod one (305) in an annular array, and the bottom ends of the connecting rod one (305) are fixedly connected with connecting plates (306). The lower surface of the end of the plate (306) is fixedly connected with the second rod (307), and the bottom end of the second rod (307) is rotatably installed with a slider (308), wherein the second rod (307) moves through The guide rod groove (303), and the slider (308) is slidably installed inside the guide groove (304), one end of the slider (308) is set as a tip, and the slider ( 308) is movably inserted into the card hole (201). 2. The UAV rotor mechanism according to claim 1, characterized in that: the guide rod grooves (303) and the guide block grooves (304) have the same number and corresponding positions, and the guide rods The slot (303) communicates with the guide block slot (304). 3. The UAV rotor mechanism according to claim 1, characterized in that: a spring (309) is connected between the end of the slider (308) away from the tip and the inner wall of the guide block groove (304) ). 4. The UAV rotor mechanism according to claim 1, characterized in that: the outer diameter of the inner rotating ring plate (302) is the same as the inner diameter of the propeller housing (3), so The inner diameter of the inner swivel plate (302) is the same as the diameter of the drive shaft (2). 5. The UAV rotor mechanism according to claim 1, characterized in that: the ends of the propeller blades (4) are uniformly fixed with a spoiler (402), and the propeller blades (4) ) is equidistantly provided with splitter slots (401) on the upper surface near one end of the spoiler (402). 6. The UAV rotor mechanism according to claim 5, characterized in that: one side between the spoiler (402) and the propeller blade (4) and away from the direction of rotation of the propeller blade (4) The sides are set at obtuse angles. 7. The UAV rotor mechanism according to claim 1, characterized in that: an expansion cover (101) is integrally and fixedly arranged under the sound-absorbing wind deflector (1), and the expansion cover (101) The diameter of (101) is larger than the diameter of the sound-absorbing windshield (1).

Images