Fixed-wing unmanned aerial vehicle capable of vertically and safely taking off and landing

Abstract

The utility model discloses a vertical safe take-off and landing fixed wing unmanned aerial vehicle which comprises an unmanned aerial vehicle body, two side wings distributed on the side portion of the unmanned aerial vehicle body and an empennage distributed on the tail portion of the unmanned aerial vehicle body, and the front side and the rear side of each side wing are detachably connected with a lifting driving structure. The lifting driving structure comprises a marker post and a motor fixed on the marker post, and a propeller is mounted on the motor; isolation hoops are distributed on the outer side of a rotation area formed by rotation of each propeller, and the isolation hoops are connected to the marker post in a separable mode. The isolation hoops are evenly distributed on the outer side of the rotation area formed by rotation of the propeller, the periphery of the propeller is isolated through the isolation hoops, the situation that the propeller is damaged due to the fact that the propeller collides with the ground is avoided, the isolation hoops are connected to the marker post in a separable mode, and the isolation hoops and the marker post are convenient to assemble and disengage; the design that the electromagnets are connected with the corresponding iron blocks is adopted, and the isolation hoop and the marker post are rapidly connected and separated.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a fixed-wing unmanned aerial vehicle capable of vertical safe take-off and landing. Background Art

[0002] Fixed-wing UAVs with vertical take-off and landing do not need to taxi to take off and land. The propellers of traditional fixed-wing UAVs are externally mounted without any protective measures. For model aircraft enthusiasts, especially when operating in the novice period, improper remote control during take-off can easily cause the fixed-wing UAV to lose balance during take-off and cause rollover. Since the propeller is also in a high-speed rotating state, once it rolls over, the rapidly rotating propeller will hit the ground, causing the propeller to break or even damage the motor. Therefore, this places certain requirements on the operating skills of the model aircraft operator. To this end, the present application proposes a fixed-wing UAV with vertical safe take-off and landing, which can protect the propeller components during take-off. Utility Model Content

[0003] In view of the shortcomings of the prior art, the present invention provides a fixed-wing UAV with vertical safe take-off and landing, which solves the problems raised in the above background technology. To achieve the above purpose, the present invention is implemented through the following technical solutions:

[0004] A fixed-wing UAV with vertical safe take-off and landing comprises a UAV body, two side wings distributed on the sides of the UAV body and a tail wing distributed at the tail of the UAV body, wherein the side wings are provided with flaps, and the front and rear sides of each side wing are connected to a lifting drive structure in a detachable connection manner.

[0005] The lifting drive structure comprises a pole and a motor fixed on the pole, and a propeller is installed on the motor;

[0006] Each of the rotating areas formed by the rotation of the propeller is provided with an isolation hoop on the outside. For novice model aircraft operators, the isolation hoop can be installed at the location of each propeller before takeoff, and the propeller can be isolated by the isolation hoop to avoid hitting the ground and causing damage to the propeller. The isolation hoop of the utility model is connected to the pole in a detachable manner.

[0007] Furthermore, the isolation hoop forms an upward-opening avoidance gap at a position close to the benchmark, a clamping strip is provided at the bottom of the avoidance gap, and a plurality of iron blocks are provided on the side walls of the avoidance gap and the upper end of the clamping strip. The lower section of the benchmark is provided with an inwardly concave clamping groove that can engage with the clamping strip, and electromagnets matching the corresponding iron block positions are provided at the bottom of the clamping groove and on the side walls of the benchmark close to the clamping groove.

[0008] The utility model provides a fixed-wing UAV with vertical safe take-off and landing, which has the following beneficial effects:

[0009] The utility model is provided with isolation hoops on the outside of the rotating area formed by the rotation of each propeller, and the propeller is isolated on all sides by means of the isolation hoops to avoid hitting the ground and causing damage to the propeller, and the isolation hoops are connected to the benchmark in a detachable manner, which is convenient for assembly and separation between the isolation hoops and the benchmark; the utility model adopts a connection design of an electromagnet and a corresponding iron block to achieve rapid connection and separation of the isolation hoops and the benchmark. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;

[0011] Figure 2 This is a schematic diagram of the plug interface structure of the utility model;

[0012] Figure 3 It is a three-dimensional structural schematic diagram of the isolation hoop and the lifting drive structure of the utility model;

[0013] Figure 4 It is a schematic diagram of the explosion structure of the isolation hoop and the lifting drive structure of the utility model;

[0014] Figure 5 It is a partial structural schematic diagram of the benchmark of the utility model;

[0015] Figure 6 It is a partial structural schematic diagram of the isolation hoop of the utility model.

[0016] In the figure: 1. UAV body; 2. Side wings; 3. Flaps; 4. Tail; 5. Lifting drive structure; 6. Plug interface; 7. Isolation hoop; 8. Motor; 9. Propeller; 10. Avoidance gap; 11. Marking pole; 12. Plug-in part; 13. Fixing hole; 14. Electric cable; 15. Card slot; 16. Electromagnet; 17. Card strip; 18. Iron block. DETAILED DESCRIPTION

[0017] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments.

[0018] See also Figures 1 to 6A fixed-wing UAV with vertical safe take-off and landing includes a UAV body 1, two side wings 2 distributed on the sides of the UAV body 1, and a tail 4 distributed on the tail of the UAV body 1. The side wings 2 have flaps 3, and the front and rear sides of each side wing 2 are connected to a lifting drive structure 5 in a detachable connection manner. In this way, after plugging in, on the one hand, electric energy can be obtained, and on the other hand, it can be uniformly controlled by the built-in main control board.

[0019] The lifting drive structure 5 includes a pole 11 and a motor 8 fixed on the pole 11, and a propeller 9 is installed on the motor 8;

[0020] like Figure 1 and Figure 3 As shown, the outer side of the rotation area formed by the rotation of each propeller 9 is distributed with an isolation hoop 7. For novice aircraft model operators, the isolation hoop 7 can be installed at the position of each propeller 9 before takeoff, and then the aircraft model remote control can be operated according to the operating instructions. Even if the drone overturns due to lack of proficiency in the early stage, the isolation hoop 7 can be used to isolate the propeller 9 from all sides to avoid hitting the ground and causing damage to the propeller 9. For this reason, the height measurement dimension of the isolation hoop 7 of the utility model is greater than the height dimension of the propeller 9, so that even if it overturns, the propeller 9 will not touch the ground.

[0021] The isolation hoop 7 of the utility model is connected to the pole 11 in a detachable manner. The purpose of this design is that once the take-off is successful, if the drone is at a certain height from the ground and is in a stable state, the isolation hoop 7 can be remotely controlled to detach from the pole 11, thereby reducing the load during normal flight. Of course, the isolation hoop 7 of the utility model can also be installed on the pole 11 all the time, so that protection can also be achieved during the landing process.

[0022] Specifically, the isolation hoop 7 is made of carbon fiber material, which can ensure the structural strength and reduce the overall weight of the isolation hoop 7.

[0023] like Figure 1 , Figure 3 and Figure 4 As shown, the isolation hoop 7 is an annular wall plate structure with upper and lower openings, and the isolation hoop 7 forms an upward opening avoidance gap 10 near the benchmark 11. The utility model designs the avoidance gap 10 so that once the isolation hoop 7 is freed from external force, it can fall off from the benchmark 11 by its own weight and then fall to the ground. The avoidance gap 10 can ensure that there is no external structure obstruction during the falling process of the isolation hoop 7.

[0024] As a further technical development of the present invention, it is possible to consider designing the isolation hoop 7 into a hollow grid structure, so as to further reduce the dead weight and improve the overall strength of the isolation hoop 7.

[0025] like Figure 1 and Figure 2 As shown, the wing 2 is provided with a plug port 6 for the corresponding marker 11 to be inserted and connected. When the marker 11 is inserted into the plug port 6, the power supply line of the built-in battery of the drone body 1 is led out from the plug port 6 and contacts the marker 11, so as to supply power to the marker 11 and the motor 8. The motor 8 cooperates with the marker 11 and the plug port 6 to be electrically connected to the built-in main control board of the drone body 1. The power supply line of the built-in battery of the drone body 1 of the utility model is arranged on the drone body 1 and the wing 2 in an internally buried or externally slotted manner. When the marker 11 is inserted into the plug port 6, power can be obtained from the built-in battery of the drone body 1.

[0026] like Figure 3 , Figure 4 and Figure 5 As shown, one end of the pole 11 is provided with a plug-in portion 12, and the plug-in portion 12 is provided with a connection fixing hole 13 opened up and down, and the plug-in portion 12 is installed on the side wing 2 by screws passing through the fixing hole 13. Of course, other detachable connection methods can also be used to replace the connection method of the fixing hole 13 and the screw in the utility model.

[0027] like Figure 3 , Figure 4 and Figure 5 As shown, the pole 11 has an electric cable 14 built therein and extends out from the outer end surface of the plug-in portion 12 . After the pole 11 is inserted into the plug-in port 6 , the electric cable 14 can be connected to the circuit of the drone body 1 .

[0028] As a preferred embodiment, the length, width and height of the plug-in portion 12 are smaller than those of other parts of the pole 11, forming a stepped height difference to facilitate insertion positioning.

[0029] like Figure 6As described, a clamping strip 17 is provided at the bottom of the avoidance gap 10, and a plurality of iron blocks 18 are provided in an embedded manner on the side wall of the avoidance gap 10 and the upper end of the clamping strip 17. The lower section of the benchmark 11 is provided with a concave clamping slot 15, and the clamping slot 15 can be engaged with the clamping strip 17. The bottom of the clamping slot 15 and the side wall of the benchmark 11 near the clamping slot 15 are provided with an electromagnet 16 that matches the position of the corresponding iron block 18. After the electric cable 14 is connected to the circuit of the drone body 1, the electromagnet 16 generates a magnetic attraction to adsorb the corresponding iron block 18. The electromagnet 16 is electrically connected to the built-in main control board of the drone body 1 through the electric cable 14, so that instructions can be issued by remote control, and the built-in main control board controls the circuit of the electromagnet 16 to switch between magnetic and non-magnetic states. When in a magnetic adsorption state, the electromagnet 16 can firmly absorb the iron block 18, and the effect is to fix the isolation hoop 7 on the benchmark 11; when in a non-magnetic adsorption state, the electromagnet 16 no longer absorbs the iron block 18, and the isolation hoop 7 falls off from the benchmark 11 due to its own gravity.

[0030] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes within the technical scope disclosed by the present invention according to the technical scheme and the utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A fixed-wing UAV capable of vertical take-off and landing safely, comprising a UAV body (1), two side wings (2) distributed on the sides of the UAV body (1), and a tail wing (4) distributed on the tail of the UAV body (1), characterized in that: The front and rear sides of each of the side wings (2) are connected to a lifting drive structure (5) in a detachable manner; The lifting drive structure (5) comprises a pole (11), a motor (8) fixed on the pole (11), and a propeller (9) mounted on the motor (8); An isolation hoop (7) is distributed on the outside of a rotation area formed by the rotation of each propeller (9), and the isolation hoop (7) is connected to the pole (11) in a detachable manner.

2. A fixed-wing UAV with vertical safe take-off and landing according to claim 1, characterized in that: The isolation hoop (7) is made of carbon fiber material.

3. A fixed-wing UAV with vertical safe take-off and landing according to claim 1 or 2, characterized in that: The isolation hoop (7) is in the form of an annular wall plate structure with upper and lower openings.

4. The fixed-wing UAV with vertical safe take-off and landing according to claim 1, characterized in that: The side wing (2) is provided with a plug interface (6) for inserting and connecting the pole (11). When the pole (11) is inserted into the plug interface (6), the built-in battery of the drone body (1) can supply power to the pole (11) and the motor (8).

5. The fixed-wing UAV with vertical safe take-off and landing according to claim 4, characterized in that: The motor (8) cooperates with the pole (11) and the plug interface (6) to complete the electrical connection with the built-in main control board of the drone body (1).

6. The fixed-wing UAV with vertical safe take-off and landing according to claim 1, characterized in that: A plug-in portion (12) is provided at one end of the pole (11), and an electric cable (14) is built into the pole (11) and extends out from the outer end surface of the plug-in portion (12). After the pole (11) is inserted into the plug interface (6), the electric cable (14) can be connected to the circuit of the drone body (1).

7. A vertical take-off and landing fixed-wing UAV according to claim 6, characterized in that: The plug-in portion (12) is provided with a connecting fixing hole (13) opened at the top and bottom, and the plug-in portion (12) is installed on the side wing (2) by screws passing through the fixing hole (13).

8. The fixed-wing UAV with vertical safe take-off and landing according to claim 1, characterized in that: The isolation hoop (7) is formed with an upwardly opening avoidance notch (10) at a position close to the mark rod (11), a clamping strip (17) is provided at the bottom of the avoidance notch (10), and a concave clamping groove (15) is provided on the lower section of the mark rod (11), and the clamping groove (15) can be engaged with the clamping strip (17).

9. The fixed-wing UAV with vertical safe take-off and landing according to claim 8, characterized in that: A plurality of iron blocks (18) are arranged on the side wall of the avoidance gap (10), and an electromagnet (16) matching the position of the corresponding iron block (18) is arranged on the side wall of the marking rod (11) close to the clamping slot (15).

10. The fixed-wing UAV with vertical safe take-off and landing according to claim 8, characterized in that: A plurality of iron blocks (18) are arranged at the upper end of the clamping strip (17), and an electromagnet (16) matching the position of the corresponding iron block (18) is arranged at the bottom of the clamping slot (15).

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