CN115924141B - Unmanned aerial vehicle rotor mechanism - Google Patents
Unmanned aerial vehicle rotor mechanism Download PDFInfo
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- CN115924141B CN115924141B CN202310016349.3A CN202310016349A CN115924141B CN 115924141 B CN115924141 B CN 115924141B CN 202310016349 A CN202310016349 A CN 202310016349A CN 115924141 B CN115924141 B CN 115924141B
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- aerial vehicle
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- ring plate
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- 230000007246 mechanism Effects 0.000 title claims abstract description 14
- 230000030279 gene silencing Effects 0.000 claims abstract description 16
- 230000009467 reduction Effects 0.000 claims abstract description 10
- 238000000034 method Methods 0.000 description 9
- 230000008569 process Effects 0.000 description 8
- 230000000694 effects Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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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
Technical Field
The invention belongs to the technical field of propellers, and particularly relates to an unmanned aerial vehicle rotor wing mechanism.
Background
Unmanned aircraft is simply referred to as "unmanned aircraft", which is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated entirely or intermittently autonomously by a vehicle-mounted computer, and is often more suitable for tasks that are too "fooled, dirty or dangerous" than unmanned aircraft, wherein the unmanned aircraft's flight is mainly accomplished by driving a propeller to rotate by a motor, and the noise reduction effect is accomplished by structural improvement of the propeller in order to reduce the noise generated when the propeller rotates, and such propellers are also referred to as noise reduction propellers.
Problems of the prior art:
in the flight process of the existing unmanned aerial vehicle, when the noise reduction propeller is accidentally blocked to directly stop rotating, the motor for driving the propeller to rotate is blocked at the same time, so that the work load of the motor is greatly increased in a short time, the motor is possibly damaged directly, and when the propeller just stops rotating, the rotating is suddenly stopped due to the component with the over-high rotating speed, the inertia force generated in the process directly acts on the joint of the motor shaft and the propeller, the joint is very likely to be broken, and even more, the damage degree of the unmanned aerial vehicle is possibly increased directly, and high maintenance and replacement cost are further generated.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle rotor wing mechanism, which can change horizontal airflow into vertical airflow while realizing flight noise reduction, so that the lifting force of an unmanned aerial vehicle is improved, and in addition, the possibility of damage to a motor and breakage of a corresponding connecting position is greatly reduced by a mode that the motor drives a driving shaft to idle when a propeller stops accidentally.
The technical scheme adopted by the invention is as follows:
the unmanned aerial vehicle rotor wing mechanism 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 top end integrated type of the propeller connecting shell is fixedly connected with a top connection block, and a propeller blade is fixedly connected to the outer surface of the top connection block in an annular array mode;
an inner rotating ring plate is movably arranged in the propeller connecting shell, the top end of the driving shaft and the inner rotating ring plate form a detachable connection relationship, clamping holes are formed in the outer wall of the top end of the driving shaft in an annular array mode, guide rod grooves are formed in the upper surface of the inner rotating ring plate in an annular array mode, and guide block grooves are formed in the lower surface of the inner rotating ring plate in an annular array mode;
the screw propeller connecting shell is characterized in that a first connecting rod is connected to the edge of the inner top end of the screw propeller connecting shell in an annular array mode, a second connecting rod is fixedly connected to the bottom end of the first connecting rod, a sliding block is rotatably installed at the bottom end of the second connecting rod, the second connecting rod penetrates through the guide rod groove in a movable mode, the sliding block is slidably installed in the guide block groove, one end of the sliding block is provided with a tip, and the tip of the sliding block is movably inserted into the clamping hole.
The guide rod grooves are the same in number and corresponding in position to the guide block grooves, and are communicated with the guide block grooves.
And a spring is connected between one end of the sliding block, which is away from the tip end, and the inner wall of the guide block groove.
The outer diameter of the inner rotating ring plate is the same as the inner diameter of the propeller connecting shell, and the inner diameter of the inner rotating ring plate is the same as the diameter of the driving shaft.
The end uniform type of screw blade is fixed and is provided with the spoiler, just the upper surface equidistance that screw blade is close to spoiler one end has seted up the splitter box.
One side between the spoiler and the propeller blade, which is away from the rotation direction of the propeller blade, is set to be an obtuse angle.
An expansion cover body is fixedly arranged below the silencing guide cover in an integrated mode, and the diameter size of the expansion cover body is larger than that of the silencing guide cover.
The invention has the technical effects that:
(1) According to the invention, the noise generated when the horizontal high-speed airflow collides with the peripheral air can be effectively reduced by the design of the silencing guide cover, and the noise generated between the high-speed airflows is further reduced by reducing the impact force of the airflows on the silencing guide cover, so that the effect of flight noise reduction is realized.
(2) When the propeller blade is accidentally blocked to cause direct stop rotation, the driving shaft and the inner rotating ring plate are relatively rotated with the propeller receiving shell, the sliding block moves away from the driving shaft along the direction of the guide block groove, the driving shaft is separated from the inner rotating ring plate after the sliding block is separated from the clamping hole, and finally the driving shaft can be driven to idle by the motor.
(3) According to the invention, when the propeller blade just stops rotating, the inner rotating ring plate can rotate in the propeller connecting shell, and the sliding block moves linearly and presses the spring in the process, so that the driving shaft has a transition process before separation, and the phenomenon that the switching part of the driving shaft and the inner rotating ring plate is damaged due to sudden stopping of the propeller blade can be avoided.
Drawings
FIG. 1 is a block diagram of an assembly of a sound attenuating pod and propeller blades provided by an embodiment of the present invention;
FIG. 2 is a schematic flow diagram of the air flow of a propeller blade in operation provided by an embodiment of the present invention;
FIG. 3 is an internal cross-sectional view of a propeller housing provided by an embodiment of the present invention;
FIG. 4 is an assembled exploded view of a drive shaft, a propeller housing, and an inner race plate provided by an embodiment of the present invention;
fig. 5 is a partially enlarged structural view at a in fig. 4.
In the drawings, the list of components represented by the various numbers is as follows:
1. a silencing pod; 101. expanding the cover body; 2. a drive shaft; 201. a clamping hole; 3. rotating the propeller to connect with the shell; 301. a top connection block; 302. an inner rotating ring plate; 303. a guide bar groove; 304. a guide block groove; 305. a first connecting rod; 306. a connecting plate; 307. a second connecting rod; 308. a slide block; 309. a spring; 4. propeller blades; 401. a shunt channel; 402. a spoiler.
Detailed Description
The present invention will be specifically described with reference to examples below in order to make the objects and advantages of the present invention more apparent. It should be understood that the following text is intended to describe only one or more specific embodiments of the invention and does not limit the scope of the invention strictly as claimed.
As shown in fig. 1-5, an unmanned aerial vehicle rotor mechanism comprises a silencing air guide sleeve 1 fixedly installed with an unmanned aerial vehicle body and a driving shaft 2 connected with an output shaft of a motor, wherein a propeller connecting shell 3 is assembled at the top end of the driving shaft 2 (the assembly mode is detachable, and before the assembly mode is not detached, the fixing effect between the propeller connecting shell 3 and the driving shaft 2 is kept in a better state), a top end integrated type of the propeller connecting shell 3 is fixedly connected with a top connection block 301, and an annular array type of the outer surface of the top connection block 301 is fixedly connected with a propeller blade 4.
According to the above structure, when the motor on the unmanned aerial vehicle arm drives the driving shaft 2 to rotate, it will drive the propeller to connect the shell 3, the top connection block 301 and the propeller blade 4 to rotate at a high speed, and when the propeller blade 4 rotates, a large amount of air flows downwards to generate thrust so as to complete the unmanned aerial vehicle flight work.
Referring to fig. 3, 4 and 5, an inner rotating ring plate 302 is movably mounted in the rotor housing 3, the top end of the driving shaft 2 and the inner rotating ring plate 302 form a detachable connection relationship, a clamping hole 201 is formed in an annular array manner on the outer wall of the top end of the driving shaft 2, a guide rod groove 303 is formed in an annular array manner on the upper surface of the inner rotating ring plate 302, guide rod grooves 304 are formed in an annular array manner on the lower surface of the inner rotating ring plate 302, the guide rod grooves 303 are the same as the guide rod grooves 304 in number and correspond to each other in position, and the guide rod grooves 303 are communicated with the guide rod grooves 304.
Referring to fig. 3, 4 and 5, a first connecting rod 305 is rotatably connected to an edge of an inner top end of the propeller connecting shell 3 in an annular array manner, a second connecting rod 307 is fixedly connected to a bottom end of the first connecting rod 305, a second connecting rod 307 is fixedly connected to a lower surface of an end of the second connecting rod 306, a sliding block 308 is rotatably mounted at the bottom end of the second connecting rod 307, the second connecting rod 307 movably penetrates through the guide rod groove 303, the sliding block 308 is slidably mounted in the guide block groove 304, one end of the sliding block 308 is provided with a tip, the tip of the sliding block 308 is movably inserted into the clamping hole 201, and a spring 309 is connected between one end of the sliding block 308, which is away from the tip, and an inner wall of the guide block groove 304.
Referring to fig. 3, the outer diameter of the inner ring plate 302 is the same as the inner diameter of the propeller housing 3, and the inner diameter of the inner ring 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 to cause direct stop rotation, at this time, the driving shaft 2 and the inner rotating ring plate 302 at the top end will generate relative rotation with the propeller connecting shell 3, because the first connecting rod 305 is in switching connection with the inner wall of the propeller connecting shell 3, the second connecting rod 306 will deflect, the second corresponding connecting rod 307 will move away from the center of the inner rotating ring plate 302 along the direction of the guide rod groove 303, the sliding block 308 will move away from the driving shaft 2 along the direction of the guide block groove 304, after the sliding block 308 is separated from the clamping hole 201, the driving shaft 2 is separated from the inner rotating ring plate 302, and finally the driving shaft 2 can be driven to idle by the motor. In addition, when the propeller blades 4 just stop rotating, the inner ring plate 302 will rotate in the propeller housing 3, and the sliding block 308 will move linearly and press the spring 309 in the process, so that the driving shaft 2 has a transition process before separation, and the damage to the junction between the driving shaft 2 and the inner ring plate 302 caused by sudden stopping of the propeller blades 4 can be avoided.
Referring to fig. 1 and 2, a spoiler 402 is fixedly arranged at the tail end of a propeller blade 4 in a uniform manner, a shunt groove 401 is formed in the upper surface of the propeller blade 4, which is close to one end of the spoiler 402, at equal intervals, one side, which is between the spoiler 402 and the propeller blade 4 and is away from the rotation direction of the propeller blade 4, is arranged to be an obtuse angle, an expansion cover body 101 is fixedly arranged below the silencing guide cover 1 in an integrated manner, and the diameter size of the expansion cover body 101 is larger than that of the silencing guide cover 1.
According to the above structure, when the propeller blade 4 rotates normally, there is a horizontal flow of air from the propeller blade 4 to the noise reduction guide cover 1 at the edge, wherein the arrangement of the shunt grooves 401 not only can reduce the resistance of the propeller blade 4 when rotating, but also can shunt the horizontally flowing air, reduce the impact of the horizontal air on the noise reduction guide cover 1, in addition, the spoiler 402 has a certain inclination compared with the propeller 4, the air can generate air flow movement on the propeller, the air flow can generate flow-around movement in the movement process, the flow-around movement not only can increase the resistance of the propeller, but also can bring additional vibration and noise to the propeller. The spoiler 402 is used to block the airflow from flowing around the tip of the propeller, so as to reduce the resistance of the airflow flowing around the propeller and reduce the impact of the horizontal airflow on the noise-reducing air guide cover 1, the technology is mature in the prior art, and reference is made to the publication CN 218112972U, which is not specifically described herein, so that the noise generated when the horizontal high-speed airflow collides with the peripheral air can be effectively reduced by the design of the noise-reducing air guide cover 1, and the noise generated between the high-speed airflows can be further reduced by reducing the impact force of the airflow on the noise-reducing air guide cover 1, so as to achieve the effect of flight noise reduction.
The working principle of the invention is as follows: on the premise that the propeller blades 4 normally rotate, when a motor on an unmanned aerial vehicle arm drives the driving shaft 2 to rotate, the motor drives the propeller connecting shell 3, the jacking block 301 and the propeller blades 4 to rotate at a high speed, when the propeller blades 4 rotate, a large amount of air flow downwards to generate thrust so as to finish the flying work of the unmanned aerial vehicle, in the process, the air flow horizontally flows from the propeller blades 4 to the silencing guide cover 1 at the edge, the flow dividing grooves 401 can reduce the resistance of the rotating propeller blades 4 and divide the horizontally flowing air flow, the impact of the horizontal air flow on the silencing guide cover 1 is reduced, in addition, the spoiler 402 which forms an obtuse angle with the tail end of the propeller blades 4 can also reduce the impact of the horizontal air flow on the silencing guide cover 1, and in addition, the arrangement of the expansion cover body 101 can change the air flow rushing towards the silencing guide cover 1 to change the horizontal air flow into the vertical air flow;
when the propeller blade 4 is accidentally blocked and thus directly stops rotating, at this time, the driving shaft 2 and the inner rotating ring plate 302 at the top end will rotate relatively with the propeller connecting shell 3, and as the first connecting rod 305 is connected with the inner wall of the propeller connecting shell 3, the second connecting rod 306 will deflect, the second corresponding connecting rod 307 will move away from the center of the inner rotating ring plate 302 along the direction of the guide rod groove 303, the sliding block 308 will move away from the driving shaft 2 along the direction of the guide block groove 304, after the sliding block 308 is separated from the clamping hole 201, the driving shaft 2 is separated from the inner rotating ring plate 302, and finally the driving shaft 2 can be driven by the motor to idle.
The foregoing is merely a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention, which are intended to be comprehended within the scope of the present invention. Structures, devices and methods of operation not specifically described and illustrated herein, unless otherwise indicated and limited, are implemented according to conventional means in the art.
Claims (7)
1. Unmanned aerial vehicle rotor mechanism includes noise reduction kuppe (1) and drive shaft (2) that are connected with motor output shaft with unmanned aerial vehicle fixed mounting, its characterized in that: the top end of the driving shaft (2) is provided with a propeller connecting shell (3), the top end of the propeller connecting shell (3) is integrally and fixedly connected with a jacking block (301), and the outer surface of the jacking block (301) is fixedly connected with propeller blades (4) in an annular array manner;
an inner rotating ring plate (302) is movably mounted in the propeller connecting shell (3), the top end of the driving shaft (2) and the inner rotating ring plate (302) form a separable connection relationship, clamping holes (201) are formed in an annular array mode on the outer wall of the top end of the driving shaft (2), guide rod grooves (303) are formed in an annular array mode on the upper surface of the inner rotating ring plate (302), and guide block grooves (304) are formed in an annular array mode on the lower surface of the inner rotating ring plate (302);
the screw propeller connecting shell comprises a screw propeller connecting shell body (3), wherein a first connecting rod (305) is rotatably connected to the edge of the top end of the inner part of the screw propeller connecting shell body in an annular array mode, a second connecting rod (307) is fixedly connected to the bottom end of the first connecting rod (305), a sliding block (308) is rotatably arranged at the bottom end of the second connecting rod (307), the second connecting rod (307) movably penetrates through the guide rod groove (303), the sliding block (308) is slidably arranged in the guide rod groove (304), one end of the sliding block (308) is provided with a tip, and the tip of the sliding block (308) is movably inserted into the clamping hole (201).
2. The unmanned aerial vehicle rotor mechanism of claim 1, wherein: the guide rod grooves (303) are the same as the guide block grooves (304) in number and correspond to each other in position, and the guide rod grooves (303) are communicated with the guide block grooves (304).
3. The unmanned aerial vehicle rotor mechanism of claim 1, wherein: a spring (309) is connected between one end of the sliding block (308) deviating from the tip and the inner wall of the guide block groove (304).
4. The unmanned aerial vehicle rotor mechanism of claim 1, wherein: the outer diameter of the inner rotating ring plate (302) is the same as the inner diameter of the propeller connecting shell (3), and the inner diameter of the inner rotating ring plate (302) is the same as the diameter of the driving shaft (2).
5. The unmanned aerial vehicle rotor mechanism of claim 1, wherein: the end of the propeller blade (4) is uniformly and fixedly provided with a spoiler (402), and the upper surface of the propeller blade (4) close to one end of the spoiler (402) is provided with splitter boxes (401) at equal intervals.
6. The unmanned aerial vehicle rotor mechanism of claim 5, wherein: one side between the spoiler (402) and the propeller blade (4) and facing away from the rotation direction of the propeller blade (4) is arranged at an obtuse angle.
7. The unmanned aerial vehicle rotor mechanism of claim 1, wherein: an expansion cover body (101) is integrally and fixedly arranged below the silencing guide cover (1), and the diameter size of the expansion cover body (101) is larger than that of the silencing guide cover (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310016349.3A CN115924141B (en) | 2023-01-06 | 2023-01-06 | Unmanned aerial vehicle rotor mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310016349.3A CN115924141B (en) | 2023-01-06 | 2023-01-06 | Unmanned aerial vehicle rotor mechanism |
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| Publication Number | Publication Date |
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| CN115924141A CN115924141A (en) | 2023-04-07 |
| CN115924141B true CN115924141B (en) | 2023-05-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202310016349.3A Active CN115924141B (en) | 2023-01-06 | 2023-01-06 | Unmanned aerial vehicle rotor mechanism |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7413408B1 (en) * | 2007-02-22 | 2008-08-19 | Samuel B Tafoya | Vibration-reducing and noise-reducing spoiler for helicopter rotors, aircraft wings, propellers, and turbine blades |
| CN107614379A (en) * | 2015-05-25 | 2018-01-19 | 多特瑞尔技术有限公司 | Shield for aircraft |
| CN108202863A (en) * | 2016-12-16 | 2018-06-26 | 深圳光启合众科技有限公司 | Propeller set |
| CN108382566A (en) * | 2018-01-22 | 2018-08-10 | 武汉理工大学 | A kind of magnetic suspension rotor structure |
| CN109153449A (en) * | 2017-12-21 | 2019-01-04 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and unmanned vehicle |
| CN110273933A (en) * | 2019-06-28 | 2019-09-24 | 石愈超 | A kind of shaft coupling |
| CN218112972U (en) * | 2022-08-19 | 2022-12-23 | 深圳远行智能航空科技有限公司 | Screw and unmanned aerial vehicle |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6672834B2 (en) * | 2001-12-21 | 2004-01-06 | Turning Point Propellers, Inc. | Removable propeller assembly incorporating breakaway elements |
| DE10343055B4 (en) * | 2003-09-16 | 2007-03-29 | Eurocopter Deutschland Gmbh | rotor brake |
-
2023
- 2023-01-06 CN CN202310016349.3A patent/CN115924141B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7413408B1 (en) * | 2007-02-22 | 2008-08-19 | Samuel B Tafoya | Vibration-reducing and noise-reducing spoiler for helicopter rotors, aircraft wings, propellers, and turbine blades |
| CN107614379A (en) * | 2015-05-25 | 2018-01-19 | 多特瑞尔技术有限公司 | Shield for aircraft |
| CN108202863A (en) * | 2016-12-16 | 2018-06-26 | 深圳光启合众科技有限公司 | Propeller set |
| CN109153449A (en) * | 2017-12-21 | 2019-01-04 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and unmanned vehicle |
| CN108382566A (en) * | 2018-01-22 | 2018-08-10 | 武汉理工大学 | A kind of magnetic suspension rotor structure |
| CN110273933A (en) * | 2019-06-28 | 2019-09-24 | 石愈超 | A kind of shaft coupling |
| CN218112972U (en) * | 2022-08-19 | 2022-12-23 | 深圳远行智能航空科技有限公司 | Screw and unmanned aerial vehicle |
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| CN115924141A (en) | 2023-04-07 |
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Effective date of registration: 20240522 Address after: 210000 science and technology innovation space 504, building 6-A, No. 75, Tiansheng Road, Changlu street, Jiangbei new area, Nanjing, Jiangsu Province Patentee after: Nanjing Liuwan Technology Co.,Ltd. Country or region after: China Patentee after: Nanjing Yangsuo Automation Co.,Ltd. Address before: 210000 science and technology innovation space 504, building 6-A, No. 75, Tiansheng Road, Changlu street, Jiangbei new area, Nanjing, Jiangsu Province Patentee before: Nanjing Liuwan Technology Co.,Ltd. Country or region before: China |