Vertical take-off and landing fixed-wing unmanned aerial vehicle with foldable wings

Abstract

The vertical take-off and landing fixed-wing unmanned aerial vehicle with the foldable wings comprises a wing body fusion body, driving assemblies are arranged at the two ends of the wing body fusion body, each driving assembly comprises a main wing, an X-wing, a wingtip rectification body and a motor, the main wings are installed at the two ends of the wing body fusion body, and the X-wing is installed at the two ends of the wing body fusion body. An X wing is rotationally connected to one end of the main wing, a wingtip rectification body is mounted at the top end of the X wing, a motor is mounted at the top of the wingtip rectification body, and in the using process, the motor on the wingtip rectification body is started, so that the X wing and the main wing are used for performing the flying process on the wing body fusion body; the technical problem that an existing fixed-wing unmanned aerial vehicle cannot be switched from a vertical state to a level flight mode in the air in the prior art is solved.

Description

Technical Field

[0001] The utility model relates to the technical field of vertical take-off and landing unmanned aerial vehicles, and more specifically, to a vertical take-off and landing fixed-wing unmanned aerial vehicle with foldable wings. Background Art

[0002] Vertical take-off and landing fixed-wing unmanned aerial vehicle (VTOL UAV) is a type of unmanned aerial vehicle system with vertical take-off and landing capabilities. It combines the advantages of helicopters and traditional fixed-wing aircraft and has become one of the important development directions in the field of unmanned aerial systems. The development of the technical route behind it benefits from the continuous pursuit of aerial maneuverability and multi-task execution capabilities to meet various mission requirements, including monitoring, reconnaissance, emergency rescue, etc. To this end, we have developed a wing-body fusion X-wing fixed-wing technology, in which propeller power units are installed at the four wingtips. Before take-off, the fixed-wing UAV is on the ground in a vertical posture and four motors are started for vertical take-off. In the air, the fixed-wing UAV is switched from a vertical state to a level flight mode through pitch deflection, completing the state switch of the fixed-wing flight mode.

[0003] Existing aircraft lack vertical takeoff and landing landing gear at the bottom, and lack a mechanism behind the wing that can specifically control the fixed-wing flight control surface, making it impossible to achieve precise control of the aircraft.

[0004] The existing X-wing part does not have the ability to fold inward, which makes the fixed-wing drone not easy to carry. This design makes it difficult for the fixed-wing drone to adapt to different environments and needs more easily during transportation and deployment. Utility Model Content

[0005] 1. Technical issues to be resolved

[0006] In view of the problems existing in the prior art, the utility model provides a vertical take-off and landing fixed-wing UAV with foldable wings to solve the technical problem mentioned in the background technology that the existing fixed-wing UAVs cannot switch from a vertical state to a level flight mode in the air.

[0007] (II) Technical solution

[0008] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a vertical take-off and landing fixed-wing UAV with foldable wings, comprising a wing-body fusion body, drive components are arranged at both ends of the wing-body fusion body, the drive component comprises a main wing, an X-wing, a wingtip fairing and a motor, the main wing is installed at both ends of the wing-body fusion body, one end of the main wing is rotatably connected with the X-wing, the top of the X-wing is installed with a wingtip fairing, and the top of the wingtip fairing is installed with a motor; the main wing and the X-wing are installed with a fixing component, the fixing component comprises a landing gear, a groove and a servo drive, the landing gear is fixedly installed at the bottom of the X-wing, the bottom of the main wing is provided with a groove, and the servo drive is fixedly installed on the groove.

[0009] The utility model is further configured that the output end of the motor is connected to a propeller, and the rotation process of the propeller is completed through the coordinated use of various components.

[0010] The utility model is further configured that one end of the servo driver is hingedly provided with a pneumatic control rudder surface, and the rotation process of starting the control rudder surface is completed through the coordinated use of various components.

[0011] The utility model is further configured that a rotating column is fixedly installed on the pneumatic control rudder surface, and the fixing process of the pneumatic control rudder surface is completed through the coordinated use of various components.

[0012] The utility model is further configured that one end of the rotating column is rotatably connected with a hinge seat, and the hinge seat is fixedly installed in the groove, so that the rotation process of the rotating column is completed through the coordinated use of various components.

[0013] The utility model is further configured such that a rotating mechanism is installed between the X-wing and the main wing, the rotating mechanism includes a mounting seat, a rotating seat and a rotating rod, the mounting seat is fixedly mounted on the main wing, the main wing is equipped with a rotating seat, and the rotating seat is rotatably connected to the rotating rod, and the rotating and folding process of the X-wing is completed through the coordinated use of various components.

[0014] The utility model is further configured that one end of the rotating rod is connected to a fixing seat, and the fixing seat is fixedly installed on the X-wing, so that the rotating rod is rotated on the fixing seat through the coordinated use of various components.

[0015] The utility model is further configured such that a camera gimbal is fixedly installed at the bottom of the wing-body fusion body, and the remote control process is completed through the coordinated use of various components such as the flight control and the link system.

[0016] (III) Beneficial effects

[0017] Compared with the prior art, the utility model provides a vertical take-off and landing fixed-wing UAV with foldable wings, which has the following beneficial effects:

[0018] 1. Through the coordinated use of various components, this wing-body fusion X-wing fixed-wing is innovatively equipped with a propeller power unit at the wing tip. Before takeoff, it aligns with the ground in a vertical posture and starts four motors to achieve vertical takeoff. In the air, through clever pitch deflection, it successfully completes the smooth transition from vertical state to level flight mode, realizing the intelligent switching of fixed-wing flight mode. This design not only improves flight performance, but also demonstrates the significant benefits of wing-body fusion technology.

[0019] 2. Through the coordinated use of various components, we have successfully achieved stable support during vertical takeoff by extending the landing gear at the four wingtips. The control surfaces are cleverly installed on the trailing edge of the wing. These control surfaces play a key control role in fixed-wing flight, ensuring stability and precise control during flight. This innovative design not only enhances the function of the landing gear, but also improves the overall performance of the aircraft.

[0020] 3. Through the coordinated use of various components, we have successfully achieved the portability of the fixed-wing UAV by enabling the 4-piece X-wing part to be folded inward. This innovative design allows the wing to be compactly folded when not in flight, making it easy to carry and store. This not only improves the flexibility of the fixed-wing UAV, but also makes it more suitable for use in various occasions and environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0022] Figure 2 It is a side view structural schematic diagram of the utility model;

[0023] Figure 3 It is a schematic diagram of the combined structure of the rotating mechanism;

[0024] Figure 4 It is a schematic diagram of the combined structure of the wing-body fusion body and the main wing;

[0025] Figure 5 It is a schematic diagram of the enlarged structure of A in the utility model.

[0026] In the figure: 1. Wing-body fusion; 2. Main wing; 3. X-wing; 4. Wingtip fairing; 5. Motor; 6. Landing gear; 7. Groove; 8. Servo drive; 9. Propeller; 10. Pneumatic control surface; 11. Rotating column; 12. Articulated seat; 13. Mounting seat; 14. Rotating seat; 15. Rotating rod; 16. Fixed seat; 17. Camera gimbal. DETAILED DESCRIPTION

[0027] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present utility model will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0028] It should be noted that, unless otherwise specified, all technical and scientific terms used in this application have the same meanings as commonly understood by ordinary technicians in the technical field to which this application belongs.

[0029] In the present invention, unless otherwise specified, directions such as "up" and "down" are usually used in reference to the directions shown in the drawings, or in reference to the vertical, perpendicular or gravity direction; similarly, for ease of understanding and description, "left" and "right" are usually used in reference to the left and right shown in the drawings; "inside" and "outside" refer to the inside and outside relative to the outline of each component itself, but the above-mentioned directions are not used to limit the present invention.

[0030] See also Figure 1-5 A vertical take-off and landing fixed-wing UAV with foldable wings comprises a wing-body fusion body 1, drive components are arranged at both ends of the wing-body fusion body 1, the drive components comprise a main wing 2, an X-wing 3, a wingtip fairing body 4 and a motor 5, the main wing 2 is mounted at both ends of the wing-body fusion body 1, one end of the main wing 2 is rotatably connected with the X-wing 3, the top of the X-wing 3 is mounted with a wingtip fairing body 4, and the top of the wingtip fairing body 4 is mounted with a motor 5; a fixing component is mounted on the main wing 2 and the X-wing 3, the fixing component comprises a landing gear 6, a groove 7 and a servo driver 8, the landing gear 6 is fixedly mounted on the bottom of the X-wing 3, a groove 7 is opened at the bottom of the main wing 2, and a servo driver 8 is fixedly mounted on the groove 7.

[0031] In this embodiment, during the use of the driving assembly, the motor 5 on the wingtip fairing 4 is started to make the X-wing 3 and the main wing 2 perform the flight process of the wing-body fusion body 1.

[0032] More specifically, when the utility model lands, the landing gear 6 is used to perform a fixed landing process.

[0033] See also Figure 1-Figure 5 , as a driving component of a vertical take-off and landing fixed-wing UAV with foldable wings: the output end of the motor 5 is connected to a propeller 9.

[0034] Specifically, the motor 5 is manually started to drive the propeller 9 to rotate, thereby driving the utility model to rotate and fly.

[0035] Please refer to Figure 1-Figure 5 As a further implementation of the fixed component: a pneumatic control rudder surface 10 is hingedly provided at one end of the servo drive 8.

[0036] Specifically, the servo driver 8 is manually started to adjust the pneumatic control surface 10 .

[0037] Please refer to Figure 1-Figure 5 As a further implementation of the fixed component: a rotating column 11 is fixedly installed on the pneumatic control control surface 10.

[0038] Specifically, when the pneumatic control control surface 10 rotates, the rotating column 11 is driven to rotate.

[0039] Please refer to Figure 1-Figure 5 As a further implementation of the fixing assembly: one end of the rotating column 11 is rotatably connected to a hinge seat 12 , and the hinge seat 12 is fixedly installed in the groove 7 .

[0040] Specifically, during the rotation of the rotating column 11 , it is caused to rotate on the hinge seat 12 at the groove 7 .

[0041] Please refer to Figure 1-Figure 5 As a further implementation of the rotating mechanism: a rotating mechanism is installed between the X wing 3 and the main wing 2, and the rotating mechanism includes a mounting seat 13, a rotating seat 14 and a rotating rod 15. The mounting seat 13 is fixedly installed on the main wing 2, the main wing 2 is equipped with a rotating seat 14, and the rotating seat 14 is rotatably connected to the rotating rod 15.

[0042] Specifically, when the X-wing 3 is folded, it is rotated along the rotating rod 15 on the mounting seat 13 .

[0043] Please refer to Figure 1-Figure 5 As a further implementation of the rotating mechanism: one end of the rotating rod 15 is connected to a fixing seat 16 , and the fixing seat 16 is fixedly installed on the X-wing 3 .

[0044] Specifically, during the rotation of the rotating rod 15 , the rotating rod 15 drives the fixing seat 16 on the X-wing 3 to rotate, thereby driving the folding process of the X-wing 3 .

[0045] Please refer to Figure 1-Figure 5 As a further implementation of the rotating mechanism: a camera gimbal 17 is fixedly installed at the bottom of the wing-body fusion body 1.

[0046] Specifically, the camera pan / tilt 17 is manually remotely controlled to remotely control the utility model.

[0047] To sum up, when the overall equipment is in use:

[0048] When the utility model is in a flying state, the motor 5 on the wingtip fairing 4 is started to drive the propeller 9 to rotate, thereby driving the utility model to rotate and fly, so that the X-wing 3 and the main wing 2 are used to fly the wing-body fusion body 1.

[0049] When the adjustment state is performed during the flight, when the utility model lands, the landing gear 6 is used to perform a fixed landing process, and the pneumatic control control surface 10 is adjusted by manually starting the servo driver 8. During the rotation of the pneumatic control control surface 10, the rotating column 11 is driven to rotate. During the rotation of the rotating column 11, it rotates on the articulated seat 12 at the groove 7.

[0050] When the X-wing 3 is in the folding state, when the X-wing 3 is folded, it is rotated along the rotating rod 15 on the mounting seat 13. During the rotation of the rotating rod 15, the fixing seat 16 on the X-wing 3 is driven to rotate, thereby driving the folding process of the X-wing 3. The camera gimbal 17 is manually remotely controlled to remotely control the utility model.

[0051] In all the schemes mentioned above, the connection between two parts can be selected according to actual conditions by welding, bolt and nut matching connection, bolt or screw connection or other well-known connection methods, which are not described here one by one. In the above, all fixed connections are preferably welded. Although the embodiments of the utility model have been shown and described, it can be understood by ordinary technicians in this field that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principle and spirit of the utility model. The scope of the utility model is defined by the attached claims and their equivalents.

Claims

1. A vertical take-off and landing fixed-wing UAV with foldable wings, comprising a wing-body fusion body (1), characterized in that: The wing-body fusion body (1) is provided with a driving assembly at both ends, the driving assembly comprising a main wing (2), an X-wing (3), a wingtip fairing (4) and a motor (5); the main wing (2) is mounted at both ends of the wing-body fusion body (1); one end of the main wing (2) is rotatably connected to the X-wing (3); the top of the X-wing (3) is provided with a wingtip fairing (4); the top of the wingtip fairing (4) is provided with a motor (5); the main wing (2) and the X-wing (3) are provided with a fixing assembly, the fixing assembly comprising a landing gear (6), a groove (7) and a servo drive (8); the landing gear (6) is fixedly mounted on the bottom of the X-wing (3); the bottom of the main wing (2) is provided with a groove (7); the servo drive (8) is fixedly mounted on the groove (7).

2. The vertical take-off and landing fixed-wing UAV with foldable wings according to claim 1, characterized in that: The output end of the motor (5) is connected to a propeller (9).

3. The vertical take-off and landing fixed-wing UAV with foldable wings according to claim 2, characterized in that: A pneumatic control rudder surface (10) is hingedly provided at one end of the servo driver (8).

4. The vertical take-off and landing fixed-wing UAV with foldable wings according to claim 3 is characterized by: A rotating column (11) is fixedly mounted on the pneumatic control rudder surface (10).

5. The vertical take-off and landing fixed-wing UAV with foldable wings according to claim 4, characterized in that: One end of the rotating column (11) is rotatably connected to a hinge seat (12), and the hinge seat (12) is fixedly mounted on the groove (7).

6. The vertical take-off and landing fixed-wing UAV with foldable wings according to claim 4, characterized in that: A rotating mechanism is installed between the X-wing (3) and the main wing (2), the rotating mechanism comprising a mounting seat (13), a rotating seat (14) and a rotating rod (15), the mounting seat (13) being fixedly mounted on the main wing (2), the rotating seat (14) being installed on the main wing (2), and the rotating seat (14) being rotatably connected to the rotating rod (15).

7. The vertical take-off and landing fixed-wing UAV with foldable wings according to claim 6, characterized in that: One end of the rotating rod (15) is connected to a fixing seat (16), and the fixing seat (16) is fixedly mounted on the X-wing (3).

8. The vertical take-off and landing fixed-wing UAV with foldable wings according to claim 6, characterized in that: A camera pan platform (17) is fixedly mounted on the bottom of the front end of the wing-body fusion body (1).

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