Pneumatic ejection quick response vertical take-off and landing unmanned aerial vehicle

Abstract

The invention discloses a pneumatic ejection quick-response vertical take-off and landing unmanned aerial vehicle which comprises an unmanned aerial vehicle body and an ejection mechanism, the ejection mechanism comprises a fixing frame, a placement frame, a hollow pipe, a piston block, a steel wire rope, a fixed pulley, a supporting rod and an angle adjusting mechanism, and the angle adjusting mechanism is arranged at the lower end of the fixing frame; the supporting rod is fixed to one side of the lower end of the fixing frame, and the placement frame is slidably arranged on the outer side of the fixing frame through the rolling wheels. When the unmanned aerial vehicle is used and catapult-assisted take-off is carried out, the propellers are located at the horizontal position, when vertical take-off and landing are needed, the tilting rotor driving steering engines are started and drive the swing arms to rotate, and motor bases of the propellers are driven by the spherical universal connecting rods to rotate around mounting points to the position perpendicular to the unmanned aerial vehicle; and then the propellers are started to facilitate the vertical take-off and landing work of the unmanned aerial vehicle, so that the unmanned aerial vehicle can be catapulted and also can take off and land vertically, and the applicability of the unmanned aerial vehicle is greatly improved.

Description

Technical Field

[0001] The invention relates to the field of unmanned aerial vehicle equipment, in particular to a pneumatic ejection rapid response vertical take-off and landing unmanned aerial vehicle. Background Art

[0002] Most traditional drones require a certain runway or open space for takeoff and landing, and the design lacks consideration for drone payload and aerodynamics during flight. Many vertical take-off and landing drones are not very efficient in vertical mode, and often need to sacrifice a certain range and speed to convert to horizontal flight, making it difficult to respond quickly when performing related emergency tasks. For example, in the oil and gas industry, drones can be used to monitor pipeline leaks, but untimely deployment or slow response of drones will result in oil and gas leaks not being discovered in time, further leading to environmental pollution and increased repair costs. Therefore, a drone with both catapult and vertical take-off and landing functions is urgently needed to solve the above problems. Summary of the invention

[0003] The purpose of the present invention is to provide a pneumatic ejection rapid response vertical take-off and landing UAV to solve the problems raised in the above background technology.

[0004] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a pneumatic ejection fast response vertical take-off and landing UAV, comprising a UAV and an ejection mechanism, wherein the ejection mechanism comprises a fixing frame, a placement frame, a hollow tube, a piston block, a steel wire rope, a fixed pulley, a support rod and an angle adjustment mechanism, wherein the angle adjustment mechanism is arranged at the lower end of the fixing frame, the support rod is fixed to one side of the lower end of the fixing frame, the placement frame is slidingly arranged on the outside of the fixing frame through rollers, the hollow tube is fixed at the inner center position of the fixing frame, the fixed pulley is movably installed on one side of the fixing frame, the piston block is slidingly arranged inside the hollow tube, the steel wire rope is wound and fixed on one side of the piston block, and when in use, the UAV is placed on the top of the placement frame, and then the air compressor is fixed to one side of the hollow tube through a pipeline, and then high-pressure gas is injected into the hollow tube, so that the piston block moves rapidly along the inside of the hollow tube, and the placement frame is pulled by the steel wire rope to move rapidly along the fixing frame, so that the UAV is ejected and flies.

[0005] Preferably, the angle adjustment mechanism includes an extension plate, a movable shaft, an identification block, an angle ruler, a bottom plate, a slide groove, a slider, a screw, a vertical rod, a slide rail and an extension rod, the extension plate is fixed to the top of the bottom plate, the movable shaft is movably embedded between the extension plates, the support rod is fixed to the outside of the movable shaft, the identification block is fixed to one side of the movable shaft, the angle ruler is embedded and fixed to the outside of the extension plate, the slide rail is fixed to the lower end of the fixed frame, the slide groove is opened at the top position of the bottom plate, the slider is slidably arranged inside the slide groove, the vertical rod is fixed to the top position of the slider, and the screw is threaded through The slider passes through the vertical rod, and the top end of the vertical rod extends to the position between the slide rails. The extension rod is fixed to the top end of the vertical rod. When in use, the slider is moved along the slide groove, so that the vertical rod moves along the side close to the support rod, thereby making the extension rod move along the slide rail. The vertical rod lifts the fixed frame, and one side of the support rod at the lower end of the fixed frame rotates through the movable shaft, and then the screw is rotated to make the screw move downward along the slider, squeezing the bottom end of the slide groove, and fixing the position of the slider by friction. In this way, the adjusted angle can be fixed, and the identification block is driven to rotate when the movable shaft rotates, and the specific rotation angle can be determined by cooperating with the angle ruler.

[0006] Preferably, the UAV further comprises a propeller, a tiltrotor drive servo, a swing arm and a spherical universal joint, wherein three propellers are provided, wherein the motor seats of two of the propellers are hingedly mounted on the same side of the UAV, and the other is fixedly mounted on the top of the UAV, the tiltrotor drive servo is embedded and fixed inside the UAV, the swing arm is fixed at the output end position of the tiltrotor drive servo, the spherical universal joint is mounted at the lower end of the swing arm, and the other side of the spherical universal joint is mounted on one side of the motor seat of the propeller. When in use, during catapult take-off, the propeller is in a horizontal position, and when vertical take-off and landing are required, the tiltrotor drive servo is started at this time, and the tiltrotor drive servo drives the swing arm to rotate, and the motor seat of the propeller is driven to rotate around the installation point to a vertical position with the UAV through the spherical universal joint, and then the propeller is started to facilitate the UAV to perform vertical take-off and landing. In this way, the UAV can be ejected and can also perform vertical take-off and landing, which greatly improves the applicability of the UAV.

[0007] Preferably, one side of the steel wire rope passes around a fixed pulley and is then fixed to one side of the mounting frame.

[0008] Preferably, two extension plates are provided and symmetrically installed on both sides of the fixing frame.

[0009] Preferably, one side of the movable shaft movably passes through the extension plate.

[0010] Preferably, two slide rails are provided and symmetrically installed at both sides of the lower end of the fixing frame.

[0011] Preferably, the extension rod is slidably arranged inside the slide rail.

[0012] Preferably, a rotating block is fixedly provided at the top end of the screw rod for facilitating the rotation of the screw rod.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] 1. When in use, the present invention places the drone on the top of the mounting frame, then fixes the air compressor to one side of the hollow tube through a pipeline, and then injects high-pressure gas into the hollow tube, so that the piston block moves quickly along the inside of the hollow tube, and the mounting frame is pulled by the wire rope to move quickly along the fixing frame, so that the drone is ejected and flies;

[0015] 2. When the present invention is in use, the slider is moved along the slide groove, so that the vertical rod moves along the side close to the support rod, so that the extension rod moves along the slide rail, the vertical rod lifts the fixed frame, and one side of the support rod at the lower end of the fixed frame rotates through the movable shaft, and then the screw rod is rotated to make the screw rod move downward along the slider, squeezing the bottom end of the slide groove, and fixing the position of the slider by friction, so that the adjusted angle can be fixed, and when the movable shaft rotates, the identification block is driven to rotate, and the specific rotation angle can be determined by cooperating with the angle ruler;

[0016] 3. When the present invention is in use, during catapult take-off, the propeller is in a horizontal position. When vertical take-off and landing is required, the tilt-rotor drive servo is started, and the tilt-rotor drive servo drives the swing arm to rotate, and the motor seat of the propeller is driven to rotate around the installation point to a vertical position with the UAV through the spherical universal connecting rod. Then, the propeller is started to facilitate the vertical take-off and landing of the UAV. In this way, the UAV can be ejected and can also perform vertical take-off and landing, which greatly improves the applicability of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the overall structure of a pneumatic ejection rapid response vertical take-off and landing UAV of the present invention;

[0018] Figure 2 This is a cross-sectional view of a hollow tube of a pneumatic ejection rapid response vertical take-off and landing UAV of the present invention;

[0019] Figure 3 It is an enlarged schematic diagram of a pneumatic ejection rapid response vertical take-off and landing UAV A of the present invention;

[0020] Figure 4 It is an enlarged schematic diagram of a pneumatic ejection rapid response vertical take-off and landing UAV B of the present invention;

[0021] Figure 5 It is an enlarged schematic diagram of a pneumatic ejection rapid response vertical take-off and landing UAV C of the present invention;

[0022] Figure 6 It is an enlarged schematic diagram of a pneumatic ejection rapid response vertical take-off and landing UAV D of the present invention.

[0023] In the figure: 1. fixed frame; 2. mounting frame; 3. drone; 4. hollow tube; 5. bottom plate; 6. piston block; 7. wire rope; 8. slide groove; 9. slider; 10. screw rod; 11. vertical rod; 12. slide rail; 13. extension rod; 14. extension plate; 15. support rod; 16. angle ruler; 17. movable shaft; 18. identification block; 19. propeller; 20. tilt-rotor drive servo; 21. swing arm; 22. spherical universal connecting rod; 23. fixed pulley. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] See also Figure 1-6 The present invention provides a technical solution: a pneumatic ejection fast response vertical take-off and landing UAV, including a UAV 3 and an ejection mechanism, the ejection mechanism includes a fixing frame 1, a placement frame 2, a hollow tube 4, a piston block 6, a wire rope 7, a fixed pulley 23, a support rod 15 and an angle adjustment mechanism, the angle adjustment mechanism is arranged at the lower end of the fixing frame 1, the support rod 15 is welded and fixed to one side of the lower end of the fixing frame 1, the placement frame 2 is arranged on the outside of the fixing frame 1 through roller sliding, the hollow tube 4 is welded and fixed to the inner center position of the fixing frame 1, the fixed pulley 23 is fixed to the inner center position of the fixing frame 1, and the fixed pulley 23 is fixed to the inner center position of the fixing frame 1. It is movably installed on one side of the fixing frame 1, and the piston block 6 is slidably arranged inside the hollow tube 4. The steel wire rope 7 is wound and fixed on one side of the piston block 6, and one side of the steel wire rope 7 passes around the fixed pulley 23 and is then fixed on one side of the mounting frame 2. When in use, the UAV 3 is placed on the top of the mounting frame 2, and then the air compressor is fixed to one side of the hollow tube 4 through a pipeline, and then high-pressure gas is injected into the hollow tube 4, so that the piston block 6 moves quickly along the inside of the hollow tube 4, and the mounting frame 2 is pulled by the steel wire rope 7 to move quickly along the fixing frame 1, so that the UAV 3 is ejected and flies.

[0026] The angle adjustment mechanism includes an extension plate 14, a movable shaft 17, an identification block 18, an angle ruler 16, a base plate 5, a slide groove 8, a slider 9, a screw 10, a vertical rod 11, a slide rail 12 and an extension rod 13. The extension plate 14 is welded and fixed to the top of the base plate 5. Two extension plates 14 are provided, which are symmetrically installed on both sides of the fixed frame 1. The movable shaft 17 is movably embedded between the extension plates 14. One side of the movable shaft 17 movably passes through the extension plate 14. The support rod 15 is welded and fixed to the outside of the movable shaft 17. The identification block 18 is welded and fixed to one side of the movable shaft 17. The angle ruler 16 is embedded and fixed to the outside of the extension plate 14. The slide rail 12 is welded and fixed to the lower end of the fixed frame 1. Two slide rails 12 are provided, which are symmetrically installed on both sides of the lower end of the fixed frame 1. The slide groove 8 is opened at the top position of the base plate 5. The slider 9 is slidably set in the slide groove 8 The vertical rod 11 is welded and fixed at the top position of the slider 9, the screw 10 penetrates the slider 9 through a thread, the top of the vertical rod 11 extends to the position between the slide rails 12, and the extension rod 13 is welded and fixed at the top of the vertical rod 11. The extension rod 13 is slidably arranged inside the slide rail 12. When in use, the slider 9 is moved along the slide groove 8, so that the vertical rod 11 moves along the side close to the support rod 15, so that the extension rod 13 moves along the slide rail 12, and the vertical rod 11 lifts the fixed frame 1, and one side of the support rod 15 at the lower end of the fixed frame 1 is rotated through the movable shaft 17, and then the screw 10 is rotated so that the screw 10 moves downward along the slider 9, squeezing the bottom end of the slide groove 8, and fixing the position of the slider 9 by friction, so that the adjusted angle can be fixed, and when the movable shaft 17 rotates, it drives the identification block 18 to rotate, and the specific rotation angle can be determined in conjunction with the angle ruler 16.

[0027] The UAV 3 further includes a propeller 19, a tilt-rotor drive servo 20, a swing arm 21 and a spherical universal joint 22. The propeller 19 is provided with three, two of which have motor seats hingedly mounted on the same side of the UAV 3, and the other is fixedly mounted on the top of the UAV 3. The tilt-rotor drive servo 20 is embedded and fixed inside the UAV 3. The swing arm 21 is fixed to the output end of the tilt-rotor drive servo 20 through a coupling. The spherical universal joint 22 is mounted at the lower end of the swing arm 21, and the other side of the spherical universal joint 22 is mounted on the lower end of the swing arm 21. Installed on one side of the motor base of the propeller 19, when in use, when the catapult takes off, the propeller 19 is in a horizontal position. When vertical take-off and landing are required, the tilt-rotor driving servo 20 is started, and the tilt-rotor driving servo 20 drives the swing arm 21 to rotate, and drives the motor base of the propeller 19 to rotate around the installation point to a vertical position with the UAV 3 through the spherical universal connecting rod 22. Then, starting the propeller 19 can facilitate the vertical take-off and landing of the UAV 3. In this way, the UAV 3 can be launched and can also perform vertical take-off and landing, which greatly improves the applicability of the UAV 3.

[0028] Working principle: When in use, the drone 3 is placed on the top of the mounting frame 2, and then the air compressor is fixed to one side of the hollow tube 4 through a pipeline, and then high-pressure gas is injected into the hollow tube 4, so that the piston block 6 moves quickly along the inside of the hollow tube 4, and the mounting frame 2 is pulled by the wire rope 7 to move quickly along the fixing frame 1, so that the drone 3 is ejected and flies;

[0029] When in use, the slider 9 is moved along the slide groove 8, so that the vertical rod 11 moves along the side close to the support rod 15, so that the extension rod 13 moves along the slide rail 12, and the vertical rod 11 lifts the fixed frame 1. The support rod 15 at the lower end of the fixed frame 1 is rotated through the movable shaft 17, and then the screw rod 10 is rotated so that the screw rod 10 moves downward along the slider 9, squeezing the bottom end of the slide groove 8, and fixing the position of the slider 9 by friction. In this way, the adjusted angle can be fixed, and when the movable shaft 17 rotates, the identification block 18 is driven to rotate, and the specific rotation angle can be determined in conjunction with the angle ruler 16;

[0030] During use, when catapulting for takeoff, the propeller 19 is in a horizontal position. When vertical takeoff and landing is required, the tilt-rotor driving servo 20 is started, and the tilt-rotor driving servo 20 drives the swing arm 21 to rotate, and the motor seat of the propeller 19 is driven to rotate around the installation point to a vertical position with respect to the UAV 3 through the spherical universal connecting rod 22. Then, the propeller 19 is started to facilitate the vertical takeoff and landing of the UAV 3. In this way, the UAV 3 can be ejected and can also be vertically landed, which greatly improves the applicability of the UAV 3.

[0031] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0032] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A pneumatic ejection rapid response vertical take-off and landing UAV, comprising a UAV (3) and an ejection mechanism, characterized in that: The ejection mechanism comprises a fixed frame (1), a placement frame (2), a hollow tube (4), a piston block (6), a steel wire rope (7), a fixed pulley (23), a support rod (15) and an angle adjustment mechanism, wherein the angle adjustment mechanism is arranged at the lower end of the fixed frame (1), the support rod (15) is fixed to one side of the lower end of the fixed frame (1), the placement frame (2) is slidably arranged on the outside of the fixed frame (1) through a roller, the hollow tube (4) is fixed to the center position of the inner side of the fixed frame (1), the fixed pulley (23) is movably installed on one side of the fixed frame (1), the piston block (6) is slidably arranged inside the hollow tube (4), and the steel wire rope (7) is wound and fixed to one side of the piston block (6).

2. The pneumatic ejection rapid response vertical take-off and landing UAV according to claim 1, characterized in that: The angle adjustment mechanism comprises an extension plate (14), a movable shaft (17), an identification block (18), an angle ruler (16), a base plate (5), a slide groove (8), a slider (9), a screw rod (10), a vertical rod (11), a slide rail (12) and an extension rod (13); the extension plate (14) is fixed to the top of the base plate (5); the movable shaft (17) is movably embedded between the extension plates (14); the support rod (15) is fixed to the outside of the movable shaft (17); and the identification block (18) is fixed to the movable shaft (17). On one side, the angle ruler (16) is embedded and fixed on the outer side of the extension plate (14), the slide rail (12) is fixed on the lower end of the fixed frame (1), the slide groove (8) is opened at the top position of the bottom plate (5), the slider (9) is slidably arranged inside the slide groove (8), the vertical rod (11) is fixed at the top position of the slider (9), the screw rod (10) penetrates the slider (9) through a thread, the top end of the vertical rod (11) extends to the position between the slide rails (12), and the extension rod (13) is fixed at the top end of the vertical rod (11).

3. The pneumatic ejection rapid response vertical take-off and landing UAV according to claim 2, characterized in that: The unmanned aerial vehicle (3) further comprises a propeller (19), a tilt-rotor driving steering gear (20), a swing arm (21) and a spherical universal joint (22). The propeller (19) is provided with three propellers, the motor seats of two of which are hingedly mounted on the same side of the unmanned aerial vehicle (3), and the other is fixedly mounted on the top of the unmanned aerial vehicle (3). The tilt-rotor driving steering gear (20) is embedded and fixed inside the unmanned aerial vehicle (3). The swing arm (21) is fixed at the output end position of the tilt-rotor driving steering gear (20). The spherical universal joint (22) is mounted at the lower end of the swing arm (21), and the other side of the spherical universal joint (22) is mounted on one side of the motor seat of the propeller (19).

4. The pneumatic ejection rapid response vertical take-off and landing UAV according to claim 3, characterized in that: One side of the steel wire rope (7) passes around a fixed pulley (23) and is then fixed to one side of the mounting frame (2).

5. The pneumatic ejection rapid response vertical take-off and landing UAV according to claim 4, characterized in that: Two extension plates (14) are provided and are symmetrically mounted on both sides of the fixing frame (1).

6. The pneumatic ejection rapid response vertical take-off and landing UAV according to claim 5, characterized in that: One side of the movable shaft (17) movably penetrates the extension plate (14).

7. The pneumatic ejection rapid response vertical take-off and landing UAV according to claim 6, characterized in that: Two slide rails (12) are provided and are symmetrically mounted at two sides of the lower end of the fixing frame (1).

8. The pneumatic ejection rapid response vertical take-off and landing UAV according to claim 7, characterized in that: The extension rod (13) is slidably arranged inside the slide rail (12).

9. The pneumatic ejection rapid response vertical take-off and landing UAV according to claim 8, characterized in that: A rotating block is fixedly arranged at the top end of the screw rod (10) for facilitating the rotation of the screw rod (10).

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