Unmanned aerial vehicle aileron structural component and unmanned aerial vehicle

Abstract

The unmanned aerial vehicle aileron structural member comprises an unmanned aerial vehicle body, a bottom plate is fixedly arranged on the inner bottom wall of the unmanned aerial vehicle body, an empennage is fixedly arranged at the rear end of the top face of the bottom plate, and a pair of L-shaped supports is fixedly arranged on the front side of the top face of the bottom plate; horizontally-distributed canards are mounted in openings of the L-shaped supports in a hinged mode, and the L-shaped supports are connected with the canards on the same side through hinge mechanisms; two pairs of L-shaped side plates are fixedly arranged on the rear side of the top face of the bottom plate, a first main wing is installed between the top ends of each pair of L-shaped side plates in a hinged mode, a second main wing is installed between the bottom ends of each pair of L-shaped side plates in a hinged mode, and the bottom plate is connected with the first main wings and the second main wings through limiting mechanisms. The storage convenience and flight reliability are both considered, through collaborative optimization of all the components, the problems of lift force adjustment, attitude control and storage of the unmanned aerial vehicle are solved, the structure is compact, transmission is stable, the practicability of the unmanned aerial vehicle is remarkably improved, and the adaptive scene range of the unmanned aerial vehicle is remarkably widened.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a UAV aileron structure and the UAV itself. Background Technology

[0002] Current UAV aileron structures are evolving towards lightweighting, foldability, and precise attitude control. Mainstream designs often employ a lift structure combining canards and main wings, with attitude adjustment achieved through hinged components. In existing technologies, canards are mostly fixed or simply foldable, while main wing adjustment relies on a single drive component. Some structures enhance power performance through a combination of motors and propellers.

[0003] However, in the overall design, the compatibility between the support carrier and the transmission mechanism is insufficient. Most structures are difficult to balance storage convenience and flight stability. Furthermore, the coordination efficiency of the drive components and linkage mechanisms needs to be improved, and there is still room for optimization in attitude controllability under complex flight scenarios.

[0004] The canard folding and unfolding lacks smoothness and precision, limiting the optimization of storage volume; the main wing attitude adjustment synchronization is poor, and the controllability of the swing direction is insufficient. At the same time, the power transmission efficiency of the transmission mechanism is low, and the stability of the support system is insufficient, making it difficult for the UAV's takeoff power, flight adaptability, and overall performance to meet diverse usage requirements. Summary of the Invention

[0005] The purpose of this invention is to solve the problems existing in the prior art, and to propose a drone aileron structure and a drone.

[0006] To address the problems existing in the prior art, the present invention adopts the following technical solution: A cannon aileron structure includes a base plate, on the front side of the top face of the base plate, a pair of symmetrically distributed L-shaped brackets are fixedly arranged, and a horizontally distributed canard is hingedly installed in the opening of each L-shaped bracket. Each L-shaped bracket is connected to the canard on the same side through a hinge mechanism. Two pairs of L-shaped side plates are fixedly installed on the rear side of the top surface of the base plate. A first main wing is hinged between the top ends of each pair of L-shaped side plates, and a second main wing is hinged between the bottom ends of each pair of L-shaped side plates. The base plate is connected to the first main wing and the second main wing through a limiting mechanism.

[0007] Preferably, a pair of fixed brackets are fixedly provided on the front side of the bottom of the canard wing, and a fixed motor is fixedly installed inside each fixed bracket. Several evenly distributed propellers are fixedly provided at the end of the motor shaft of each fixed motor.

[0008] Preferably, a through-type fixed shaft is rotatably inserted between the top ends of the pair of L-shaped brackets, a U-shaped connecting plate is fixedly installed in the middle of the fixed shaft, and a pair of third L-shaped connecting plates are fixedly installed at both ends of the fixed shaft.

[0009] Preferably, a U-shaped lug is fixedly provided on the front side of the top of the base plate, and a telescopic cylinder is hingedly installed in the opening of the U-shaped lug. The end of the telescopic rod of the telescopic cylinder extends into the opening of the U-shaped connecting plate and is hinged to the U-shaped connecting plate.

[0010] Preferably, the hinge mechanism includes a first L-shaped connecting plate and a second L-shaped connecting plate. The first L-shaped connecting plate is fixedly provided on the inner side of the canard. One end of the first L-shaped connecting plate is hinged to the other end of the third L-shaped connecting plate. The bottom end of the L-shaped bracket is hinged to the second L-shaped connecting plate. The top end of the second L-shaped connecting plate is hinged to one end of the first L-shaped connecting plate.

[0011] Preferably, a first connecting shaft is rotatably inserted between the top ends of the pair of L-shaped side plates, a first roller is fixedly sleeved in the middle of the first connecting shaft, and the first roller is fixedly connected to the inner side of the first main wing on the same side. A second connecting shaft is rotatably inserted between the bottom ends of the pair of L-shaped side plates. A second roller is fixedly sleeved in the middle of the second connecting shaft. The second roller is fixedly connected to the second main wing on the same side.

[0012] Preferably, a pair of rectangular slide blocks are fixedly provided on the rear side of the top surface of the base plate, and a rectangular slide plate is slidably inserted inside each rectangular slide block. A limit pin is fixedly provided on the inner end of each rectangular slide plate, and a vertically distributed limit connecting plate is fixedly provided on the outer end of each rectangular slide plate.

[0013] Preferably, a servo motor is fixedly installed on the rear side of the top surface of the base plate. The servo motor is located between a pair of rectangular slides. A turntable is fixedly sleeved on the end of the motor shaft of the servo motor. A pair of staggered oblique pin holes are opened on the turntable. The outer end of each limiting pin shaft is slidably inserted into the oblique pin hole on the same side.

[0014] Preferably, the limiting mechanism includes a first pin and a second pin, and the limiting connecting plate has an elliptical pin hole. An elliptical connecting rod is fixedly provided at the front end of the first connecting rod, and the first pin is fixedly provided at the outer end of the elliptical connecting rod. An L-shaped connecting rod is fixedly provided at the front end of the second connecting rod, and the second pin is fixedly provided at the outer end of the L-shaped connecting rod. The first pin and the second pin are slidably inserted into the elliptical pin hole on the same side.

[0015] The present invention also provides a drone, including the drone aileron structure as described above, wherein the base plate is fixedly disposed on the bottom wall of the drone body, and a tail fin penetrating the drone body is fixedly disposed at the rear end of the top surface of the base plate.

[0016] Compared with the prior art, the beneficial effects of the present invention are: 1. In this invention, the canard structure design is optimized, and the folding and unfolding attitudes are switched through the hinge mechanism. When folded, the storage volume is greatly reduced, making it easy to carry and store. When unfolded, it works with a fixed motor and propeller to provide auxiliary lift, which significantly improves the take-off power and flight stability of the UAV and ensures attitude controllability. 2. In this invention, the main wing adopts a double-layer hinged design. The first and second main wings, together with the limiting mechanism, achieve precise lift adjustment, solving the problem of poor synchronization of traditional main wing attitude adjustment. The linkage component driven by the servo motor can achieve precise swinging of the main wings relative to or in opposite directions, enhancing flight adaptability. 3. In this invention, the overall structure adopts L-shaped brackets, U-shaped lugs and other components to build a stable support system. The hinge mechanism achieves smooth transmission through multi-link linkage, which has both driving force transmission efficiency and motion accuracy. The components work together to ensure controllable flight attitude and improve the overall flight performance of the UAV. In summary, this invention balances ease of storage with flight reliability. Through coordinated optimization of various components, it solves the challenges of lift adjustment, attitude control, and storage for drones. The structure is compact and the transmission is stable, significantly improving the practicality and adaptability of drones. Attached Figure Description

[0017] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this application, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings: Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the structure of the base plate, canard, first main wing, and second tail wing of the present invention. Figure 3 This is a schematic diagram of the structure of a pair of canards and the hinge mechanism of the present invention; Figure 4 This is an exploded view of the structure of a pair of canards and the hinge mechanism of the present invention; Figure 5 This is a schematic diagram of the first main wing, the second main wing, and the limiting mechanism of the present invention; Figure 6 This is an exploded view of the structure of the first main wing, the second main wing, and the limiting mechanism of the present invention; The numbers in the diagram are as follows: 100, UAV body; 101, base plate; 102, tail fin; 200, canard wing; 201, fixed bracket; 202, fixed motor; 204, propeller; 205, first L-shaped connecting plate; 206, L-shaped bracket; 207, second L-shaped connecting plate; 208, fixed shaft; 209, U-shaped connecting plate; 210, third L-shaped connecting plate; 211, U-shaped lug; 212, telescopic cylinder; 300, L-shaped side plate; 301, first connecting shaft; 302, first main wing; 303, second connecting shaft; 304, second main wing; 305, elliptical connecting rod; 306, first pin; 307, L-shaped connecting rod; 308, second pin; 309, rectangular slide; 310, rectangular sliding plate; 311, limiting connecting plate; 312, limiting pin; 313, servo motor; 314, turntable. Detailed Implementation

[0018] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0019] Example 1: This example provides a drone aileron structural component, see [link / reference]. Figures 1 to 6 Specifically, including the base plate 101, a pair of symmetrically distributed L-shaped brackets 206 are fixedly installed on the front side of the top of the base plate 101. The L-shaped brackets 206 provide a hinge support base for the canard 200 and also serve as the mounting carrier for the hinge mechanism, ensuring the stability of the canard 200's flipping action. Each L-shaped bracket 206 has a horizontally distributed canard wing 200 hinged in its opening. Each L-shaped bracket 206 is connected to the canard wing 200 on the same side through a hinge mechanism. The canard wing 200 serves as the front lifting component of the drone. With the hinge mechanism, it can switch between folding and unfolding attitudes. When folded, it reduces the storage volume of the drone. When unfolded, it provides stable lift and ensures the controllability of the flight attitude. A pair of fixed brackets 201 are fixedly installed on the front side of the bottom of the canard 200. The fixed brackets 201 provide a stable mounting position for the fixed motor 202. The fixed motor 202 is fixedly installed inside each fixed bracket 201. Several evenly distributed propellers 204 are fixedly installed at the end of the motor shaft of each fixed motor 202. The fixed motor 202 drives the propellers 204 to rotate, providing auxiliary lift for the canard 200 and improving the dynamic performance of the UAV take-off and flight. Two pairs of L-shaped side plates 300 are fixedly installed on the rear side of the top surface of the base plate 101. The L-shaped side plates 300 provide hinge support points for the first main wing 302 and the second main wing 304. The first main wing 302 is hinged between the top ends of each pair of L-shaped side plates 300, and the second main wing 304 is hinged between the bottom ends of each pair of L-shaped side plates 300. The base plate 101 is connected to the first main wing 302 and the second main wing 304 through a limiting mechanism. The first main wing 302 and the second main wing 304 cooperate to adjust the main lift of the UAV and improve flight stability.

[0020] It should be noted that: such as Figure 3 and Figure 4 As shown, the hinge mechanism includes a first L-shaped connecting plate 205, a second L-shaped connecting plate 207, a fixed shaft 208 rotatably inserted between the top ends of a pair of L-shaped brackets 206, a U-shaped connecting plate 209 fixedly installed in the middle of the fixed shaft 208, and a pair of third L-shaped connecting plates 210 fixedly installed at both ends of the fixed shaft 208. The fixed shaft 208, the U-shaped connecting plate 209, and the third L-shaped connecting plate 210 convert the linear driving force of the telescopic cylinder 212 into the turning torque of the canard 200. A U-shaped lug 211 is fixedly installed on the front side of the top of the base plate 101. A telescopic cylinder 212 is hingedly installed in the opening of the U-shaped lug 211. The telescopic cylinder 212 provides driving force for the attitude switching of the canard 200. The telescopic rod end of the telescopic cylinder 212 extends into the opening of the U-shaped connecting plate 209 and is hinged to the U-shaped connecting plate 209. A first L-shaped connecting plate 205 is fixedly installed on the inner side of the canard 200. One end of the first L-shaped connecting plate 205 is hinged to the other end of the third L-shaped connecting plate 210. A second L-shaped connecting plate 207 is hinged to the bottom end of the L-shaped bracket 206. The top end of the second L-shaped connecting plate 207 is hinged to one end of the first L-shaped connecting plate 205. The first L-shaped connecting plate 205 and the second L-shaped connecting plate 207 form a linkage limiting structure to ensure the stability and accuracy of the canard 200 during the flipping process.

[0021] The working principle of this embodiment is as follows: When the canard wing 200 needs to be folded, the telescopic cylinder 212 is activated. Under the driving force of the telescopic cylinder 212, its telescopic rod extends outward. Since the end of the telescopic rod of the telescopic cylinder 212 is hinged to the U-shaped connecting plate 209 in the middle of the fixed shaft 208, the extension of the telescopic rod will drive the U-shaped connecting plate 209 to rotate synchronously, thereby driving the fixed shaft 208 that passes through the top of a pair of L-shaped brackets 206 to rotate accordingly. When the fixed shaft 208 rotates, a pair of third L-shaped connecting plates 210 fixed at both ends of the fixed shaft 208 will rotate synchronously with the fixed shaft 208. Since one end of the third L-shaped connecting plate 210 is hinged to the first L-shaped connecting plate 205 fixed on the inner side of the canard 200, the rotation of the third L-shaped connecting plate 210 will drive the first L-shaped connecting plate 205 to move through the hinge point. Meanwhile, the second L-shaped connecting plate 207, which is hinged to the bottom of the L-shaped bracket 206, has its top end hinged to the other end of the first L-shaped connecting plate 205, forming a stable linkage structure that guides and limits the movement direction of the first L-shaped connecting plate 205. Under the combined action of the above components, the first L-shaped connecting plate 205 drives the canard 200 to flip backward around the hinge point in the opening of the L-shaped bracket 206, and finally completes the folding action of the canard 200; conversely, when the telescopic cylinder 212 retracts, the canard 200 can be unfolded and reset through the above reverse linkage process, ensuring the normal working attitude switching of the UAV aileron structure.

[0022] Example 2: Based on Example 1, this example solves the problems of poor synchronization and insufficient controllability of the swing direction in the attitude adjustment of the first main wing 302 and the second main wing 304 of the UAV by adding a drive assembly consisting of a servo motor 313, a turntable 314, a rectangular slide block 309, and a matching limiting mechanism, thereby achieving precise attitude switching of the main wings. It also includes: In the specific implementation process, such as Figure 5 and Figure 6 As shown, a first connecting shaft 301 is rotatably inserted between the top ends of a pair of L-shaped side plates 300, and a first roller is fixedly sleeved in the middle of the first connecting shaft 301. The first roller is fixedly connected to the inner side of the first main wing 302 on the same side. A second connecting shaft 303 is rotatably inserted between the bottom ends of a pair of L-shaped side plates 300, and a second roller is fixedly sleeved in the middle of the second connecting shaft 303. The second roller is fixedly connected to the second main wing 304 on the same side.

[0023] A pair of rectangular slide blocks 309 are fixedly installed on the rear side of the top surface of the base plate 101. A rectangular slide block 310 is slidably inserted inside each rectangular slide block 309. A limit pin 312 is fixedly installed on the inner end of each rectangular slide block 310. A vertically distributed limit connecting plate 311 is fixedly installed on the outer end of each rectangular slide block 310. A servo motor 313 is fixedly installed on the rear side of the top surface of the base plate 101. The servo motor 313 is located between a pair of rectangular slides 309. A turntable 314 is fixedly sleeved on the end of the motor shaft of the servo motor 313. A pair of staggered oblique pin holes are opened on the turntable 314. The outer end of each limiting pin 312 is slidably inserted into the oblique pin hole on the same side. The servo motor 313 drives the turntable 314 to rotate. Through the cooperation of the oblique pin hole and the limiting pin 312, the rectangular slide plate 310 is driven to perform horizontal reciprocating motion along the rectangular slide 309. The limiting mechanism includes a first pin 306 and a second pin 308. An elliptical pin hole is provided on the limiting connecting plate 311. An elliptical connecting rod 305 is fixedly provided at the front end of the first connecting rod 301. The first pin 306 is fixedly provided at the outer end of the elliptical connecting rod 305. An L-shaped connecting rod 307 is fixedly provided at the front end of the second connecting rod 303. The second pin 308 is fixedly provided at the outer end of the L-shaped connecting rod 307. The first pin 306 and the second pin 308 are slidably inserted into the elliptical pin hole on the same side. The limiting connecting plate 311 drives the first connecting rod 301 and the second connecting rod 303 to swing the first main wing 302 and the second main wing 304 in relative or opposite directions through the sliding cooperation of the elliptical pin hole with the first pin 306 and the second pin 308.

[0024] The working principle of this embodiment is as follows: Start the servo motor 313. Under its driving force, the motor shaft drives the turntable 314 fixedly sleeved at the end to rotate synchronously. A pair of staggered oblique pin holes on the turntable 314 form a sliding limit engagement with the limiting pin 312 at the inner end of the rectangular slide plate 310, thereby driving the rectangular slide plate 310 to slide horizontally back and forth along the rectangular slide block 309, and move synchronously with the limiting connecting plate 311 fixedly connected to the outer end of the rectangular slide plate 310. The elliptical pin hole on the limiting plate 311 forms a sliding limiting fit with the first pin 306 at the outer end of the elliptical connecting rod 305 at the front end of the first connecting shaft 301 and the second pin 308 at the outer end of the L-shaped connecting rod 307 at the front end of the second connecting shaft 303. As the limiting plate 311 slides, the first connecting shaft 301 and the first roller fixedly sleeved in the middle are driven to swing synchronously through the first pin 306 and the elliptical connecting rod 305, thereby driving the first main wing 302 fixedly connected to the first roller to swing. Simultaneously, the second connecting shaft 308 and the L-shaped connecting rod 307 drive the second connecting shaft 303 and the second roller fixedly sleeved in the middle to swing in the opposite direction, thereby driving the second main wing 304 fixedly connected to the second roller to swing, ultimately realizing the precise relative or opposite swing adjustment of the first main wing 302 and the second main wing 304.

[0025] Example 3: The present invention also provides a drone, including the drone aileron structure as described in Examples 1 and 2 above. The base plate 101 is fixedly installed on the inner bottom wall of the drone body 100. A tail wing 102 with a T-shaped structure is fixedly installed at the rear end of the top surface of the base plate 101, and the tail wing 102 penetrates the drone body 100.

[0026] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A type of aileron structure for a drone, comprising a base plate (101), characterized in that: A pair of L-shaped brackets (206) are fixedly installed on the front side of the top of the base plate (101). A canard (200) is hingedly installed in the opening of the L-shaped bracket (206). The L-shaped bracket (206) is connected to the canard (200) on the same side through a hinge mechanism. Two pairs of L-shaped side plates (300) are fixedly installed on the rear side of the top surface of the base plate (101). A first main wing (302) is hinged between the top ends of each pair of L-shaped side plates (300), and a second main wing (304) is hinged between the bottom ends of each pair of L-shaped side plates (300). The base plate (101) is connected to the first main wing (302) and the second main wing (304) through a limiting mechanism.

2. The aileron structure of a UAV according to claim 1, characterized in that: A pair of fixed brackets (201) are fixedly installed on the front side of the bottom of the canard (200). A fixed motor (202) is fixedly installed inside the fixed bracket (201). Several propellers (204) are fixedly installed at the end of the motor shaft of the fixed motor (202).

3. The aileron structure of a UAV according to claim 1, characterized in that: A fixed shaft (208) is rotatably inserted between the top ends of a pair of L-shaped brackets (206). A U-shaped connecting plate (209) is fixedly installed in the middle of the fixed shaft (208). A pair of third L-shaped connecting plates (210) are fixedly installed at both ends of the fixed shaft (208).

4. The aileron structure of a UAV according to claim 3, characterized in that: A U-shaped lug (211) is fixedly provided on the front side of the top of the base plate (101). A telescopic cylinder (212) is hingedly installed in the opening of the U-shaped lug (211). The end of the telescopic rod of the telescopic cylinder (212) extends into the opening of the U-shaped connecting plate (209) and is hinged to the U-shaped connecting plate (209).

5. The aileron structure of a UAV according to claim 3, characterized in that: The hinge mechanism includes a first L-shaped connecting plate (205) and a second L-shaped connecting plate (207). The first L-shaped connecting plate (205) is fixedly installed on the inner side of the canard (200). One end of the first L-shaped connecting plate (205) is hinged to the other end of the third L-shaped connecting plate (210). The bottom end of the L-shaped bracket (206) is hinged to the second L-shaped connecting plate (207). The top end of the second L-shaped connecting plate (207) is hinged to one end of the first L-shaped connecting plate (205).

6. The aileron structure of a UAV according to claim 1, characterized in that: A first connecting shaft (301) is rotatably inserted between the top ends of a pair of L-shaped side plates (300), and a first roller is fixedly sleeved in the middle of the first connecting shaft (301). The first roller is fixedly connected to the inner side of the first main wing (302) on the same side. A second connecting shaft (303) is rotatably inserted between the bottom ends of a pair of L-shaped side plates (300). A second roller is fixedly sleeved in the middle of the second connecting shaft (303). The second roller is fixedly connected to the second main wing (304) on the same side.

7. A UAV aileron structure according to claim 6, characterized in that: A pair of rectangular slide blocks (309) are fixedly provided on the rear side of the top surface of the base plate (101). A rectangular slide block (310) is slidably inserted inside the rectangular slide block (309). A limit pin (312) is fixedly provided on the inner end of the rectangular slide block (310), and a limit connecting plate (311) is fixedly provided on the outer end of the rectangular slide block (310).

8. The aileron structure of a UAV according to claim 7, characterized in that: A servo motor (313) is fixedly installed on the rear side of the top surface of the base plate (101). The servo motor (313) is located between a pair of rectangular slides (309). A turntable (314) is fixedly sleeved on the end of the motor shaft of the servo motor (313). A pair of staggered oblique pin holes are opened on the turntable (314). The outer end of the limiting pin (312) is slidably inserted into the oblique pin hole on the same side.

9. A UAV aileron structure according to claim 7, characterized in that: The limiting mechanism includes a first pin (306) and a second pin (308). An elliptical pin hole is provided on the limiting connecting plate (311). An elliptical connecting rod (305) is fixedly provided at the front end of the first connecting rod (301). The first pin (306) is fixedly provided at the outer end of the elliptical connecting rod (305). An L-shaped connecting rod (307) is fixedly provided at the front end of the second connecting rod (303). The second pin (308) is fixedly provided at the outer end of the L-shaped connecting rod (307). The first pin (306) and the second pin (308) are slidably inserted into the elliptical pin hole on the same side.

10. A drone, characterized in that, The unmanned aerial vehicle (UAV) aileron structure according to any one of claims 1 to 9, wherein the base plate (101) is fixedly disposed on the inner bottom wall of the UAV body (100), and a tail fin (102) penetrating the UAV body (100) is fixedly disposed at the rear end of the top surface of the base plate (101).

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