Tilt-rotor unmanned aerial vehicle flight control test bench

Abstract

The utility model relates to the field of unmanned aerial vehicle flight control test, and provides a tilt-rotor unmanned aerial vehicle flight control test bench which comprises a base. The bottom rod is arranged at the center of one side of the base through a bearing, and one end of the bottom rod is provided with a supporting seat through a bearing. When a flight control test is carried out on the unmanned aerial vehicle, the unmanned aerial vehicle is placed on the supporting seat, the unmanned aerial vehicle is controlled to hover, an external power switch of a driving motor is turned on, and the driving motor is supported by the two fixing rods; an output shaft of a driving motor drives a rotating rod to rotate, fan blades are further made to rotate, gas is driven to flow when the fan blades rotate, the blown gas is blown to the unmanned aerial vehicle, the stability of hovering of the unmanned aerial vehicle during blowing is simulated, the fan blades are made to rotate through a push plate to blow the gas at different positions, and therefore when flight control testing is conducted on the unmanned aerial vehicle, the stability of the unmanned aerial vehicle is improved. The influence of different wind directions on the hovering stability of the unmanned aerial vehicle can be tested, and the practicability of the testboard is improved.

Description

Technical Field

[0001] This application relates to the field of UAV flight control testing, and particularly to a tilt-rotor UAV flight control test bench. Background Art

[0002] A tilt-rotor UAV is an aircraft that combines the characteristics of a helicopter and a fixed-wing aircraft. It has adjustable rotors that provide lift during vertical takeoff and landing, and converts the rotors into a fixed-wing mode during horizontal flight to improve efficiency. The performance of the UAV can be tested through a flight control test bench.

[0003] Currently, the Chinese patent with the publication number CN216375056U discloses a construction hanging basket. This utility model relates to the technical field of test benches and discloses a tilt-rotor UAV flight control test bench, which includes a test bench and a tilt-rotor UAV arranged above the test bench. The upper end of the test bench is provided with a tabletop, the upper end of the tabletop is provided with a dial, the surface of the dial is provided with scales, the bottom surface of the tilt-rotor UAV is provided with a suction cup, the lower end of the suction cup is provided with a first fixed platform, and the lower end of the first fixed platform is provided with a laser. The deviation of the light beam emitted by the laser when it shines on the scales can intuitively show the stability of the tilt-rotor UAV after hovering.

[0004] Although the above solution has the above advantages, the disadvantages of the above solution are that when the UAV hovers, the natural wind will affect its hovering stability. When some existing test benches are testing, it is difficult to test the hovering stability of the UAV in the case of wind. Some test benches can test this content, but the natural wind direction often changes, and the influence of the wind direction in different directions on the hovering stability of the UAV cannot be tested. Moreover, during the test, sometimes the UAV has problems and causes the UAV to fly randomly, which may hit the test personnel and cause harm to the personnel. Summary of the Utility Model

[0005] A tilt-rotor UAV flight control test bench provided by this application can test the influence of different wind directions on the hovering stability of the UAV during the flight control test of the UAV, improve the practicability of the test bench, and can prevent the UAV from hitting the test personnel and protect the test personnel when the UAV has problems during the flight control test of the UAV, thereby improving the safety of the test bench.

[0006] To achieve the above object, this application adopts the following technical solution: A tilt-rotor UAV flight control test bench, which includes:

[0007] A base;

[0008] The bottom rod is arranged at the center on one side of the base through a bearing, and a support seat is arranged at one end of the bottom rod through a bearing. When the bottom rod rotates, the base and the support seat do not rotate together due to the bearing.

[0009] The gear is fixedly sleeved on the outer surface of the bottom rod, and a rack is meshed on the outer surface of the gear. When the rack moves, it drives the gear to rotate, further causing the bottom rod to rotate.

[0010] The groove plate is fixedly arranged on one side of the base close to the gear, and one side of the rack is slidably arranged on the inner wall of the groove plate, and the rack can slide on the inner wall of the groove plate.

[0011] The connecting plate is fixedly arranged on one side of the rack, and a push plate is fixedly arranged on one side of the connecting plate. The push plate facilitates the pushing or pulling of the connecting plate.

[0012] The transmission rod is fixedly arranged on the outer surface of the bottom rod, and an arc plate is fixedly arranged at one end of the transmission rod. The rotation of the transmission rod drives the arc plate to rotate.

[0013] As a further improvement of this application: A round rod is fixedly arranged on one side of the arc plate, a hollow cylinder is fixedly arranged at one end of the round rod, two fixed rods are fixedly arranged on the inner wall of the hollow cylinder, and a driving motor is installed on the opposite sides of the two fixed rods. When the bottom rod rotates, it drives the arc plate to slide on one side of the support seat through the transmission rod, and further drives the hollow cylinder to be in different positions through the round rod, so that the fan blades rotate to blow out gas at different positions.

[0014] As a further improvement of this application: The arc plate is slidably arranged on one side of the support seat, and an arc groove is opened on one side of the support seat. The support seat slides inside the arc groove, and the arc groove limits the movement of the support seat.

[0015] As a further improvement of this application: Two frames are fixedly arranged on one side of the base. A threaded rod is arranged on both sides of the inner wall of one of the frames through bearings, and a rotating ring is fixedly arranged on one side of the threaded rod. The threaded rod can rotate, and the rotating ring facilitates the rotation of the threaded rod.

[0016] As a further improvement of this application: A sleeve is threadedly sleeved on the outer surface of the threaded rod. Vertical rods are fixedly arranged on both sides of the inner wall of the other frame. The sleeve is connected to the sliding cylinder through two cross plates and a protective cylinder. Thus, when the threaded rod rotates in different directions, the sleeve moves up and down on the outer surface of the threaded rod.

[0017] As a further improvement of this application: A sliding cylinder is movably sleeved on the outer surface of the vertical rod, and cross plates are fixedly arranged on the outer surfaces of the sleeve and the sliding cylinder. The sliding cylinder can slide on the outer surface of the vertical rod.

[0018] As a further improvement of the present application: on the opposite sides of the two cross plates, a protective cylinder is fixedly arranged, and glass is installed on the outer surface of the protective cylinder. Through the transparency of the glass, the test situation of the drone can be observed. When the drone has problems, the drone will hit the glass and will not hit the test personnel.

[0019] As a further improvement of the present application: a rotating rod is fixedly arranged on the output shaft of the driving motor, and a fan blade is installed at one end of the rotating rod. Turn on the external power switch of the driving motor, and the output shaft of the driving motor drives the fan blade to rotate through the rotating rod. When the fan blade rotates, it drives the flow of gas, and the blown gas blows onto the drone, simulating the hovering stability of the drone when blown by the wind.

[0020] Compared with the prior art, the advantages and positive effects of the present application are as follows:

[0021] 1. In the present application, when performing flight control testing on the drone, place the drone on the support base, control the drone to hover, turn on the external power switch of the driving motor. The two fixing rods support the driving motor, and then the output shaft of the driving motor drives the rotating rod to rotate, further causing the fan blade to rotate. When the fan blade rotates, it drives the flow of gas, and the blown gas blows onto the drone, simulating the hovering stability of the drone when blown by the wind. By pushing the push plate to drive the connecting plate forward, the rack slides on the inner wall of the groove plate, further driving the gear to rotate, thereby driving the bottom rod to rotate counterclockwise. Through the transmission rod, the arc plate slides on one side of the support base, and further drives the hollow cylinder to be in different positions through the round rod, so that the gas blown by the rotating fan blade is in different positions. By pulling the push plate to drive the gear to rotate clockwise, and then making the hollow cylinder rotate clockwise, so that the blown gas is in different positions. Thus, when performing flight control testing on the drone, different wind directions can be tested, and the influence on the hovering stability of the drone can be determined, improving the practicability of the test bench.

[0022] 2. In the present application, when performing flight control testing on the drone, the sliding cylinder can slide on the outer surface of the vertical rod, and the sleeve is connected to the sliding cylinder through the two cross plates and the protective cylinder. Thus, when the threaded rod rotates in different directions, the sleeve moves up and down on the outer surface of the threaded rod. During the test, by rotating the rotating ring clockwise to drive the threaded rod to rotate clockwise, the sleeve moves downward, that is, moves towards the base side. Thus, the protective cylinder is driven to move through the two cross plates, so that the protective cylinder surrounds the tested drone. At this time, through the transparency of the glass, the test situation of the drone can be observed. When the drone has problems, the drone will hit the glass and will not hit the test personnel. Thus, when the drone has problems during the flight control testing of the drone, it can prevent the drone from hitting the test personnel and protect the test personnel, improving the safety of the test bench. Description of the Drawings

[0023] Figure 1 This is a schematic side three-dimensional structure diagram of a tilt-rotor UAV flight control test bench proposed in this application.

[0024] Figure 2 This is a schematic bottom three-dimensional structure diagram of a tilt-rotor UAV flight control test bench proposed in this application.

[0025] Figure 3 This is a schematic three-dimensional structure diagram of a tilt-rotor UAV flight control test bench excluding the support base proposed in this application.

[0026] Figure 4 This is a schematic sectional three-dimensional structure diagram of two frames in a tilt-rotor UAV flight control test bench proposed in this application.

[0027] Figure 5 This is a schematic sectional three-dimensional structure diagram of a hollow cylinder in a tilt-rotor UAV flight control test bench proposed in this application.

[0028] Legend: 1. Base; 2. Bottom rod; 201. Support base; 202. Gear; 203. Grooved plate; 204. Rack; 205. Connecting plate; 206. Pusher plate; 207. Transmission rod; 208. Arc plate; 209. Round rod; 210. Hollow cylinder; 211. Fixed rod; 212. Driving motor; 213. Rotating rod; 214. Fan blade; 3. Frame; 301. Threaded rod; 302. Sleeve; 303. Vertical rod; 304. Slide cylinder; 305. Horizontal plate; 306. Protection cylinder; 307. Glass; 308. Rotating ring. Detailed implementation manners

[0029] In order to more clearly understand the above objects, features and advantages of this application, the following further describes this application with reference to the drawings and embodiments. It should be noted that, without conflict, the embodiments of this application and the features in the embodiments can be combined with each other.

[0030] Many specific details are set forth in the following description in order to fully understand this application. However, this application can also be implemented in other ways different from those described herein. Therefore, this application is not limited by the specific embodiments disclosed in the following specification.

[0031] Embodiment 1, as Figures 1 to 5 shown, this application provides a tilt-rotor UAV flight control test bench, and the test bench includes:

[0032] Base 1;

[0033] Bottom rod 2, which is arranged at the center of one side of the base 1 through a bearing, and one end of the bottom rod 2 is provided with a support base 201 through a bearing. When the bottom rod 2 rotates, the base 1 and the support base 201 do not rotate together because of the bearing;

[0034] The gear 202 is fixedly sleeved on the outer surface of the bottom rod 2, and a rack 204 is meshed on the outer surface of the gear 202. When the rack 204 moves, it drives the gear 202 to rotate, further causing the bottom rod 2 to rotate;

[0035] The groove plate 203 is fixedly arranged on one side of the base 1 close to the gear 202, and one side of the rack 204 is slidably arranged on the inner wall of the groove plate 203, and the rack 204 can slide on the inner wall of the groove plate 203;

[0036] The connecting plate 205 is fixedly arranged on one side of the rack 204, and a push plate 206 is fixedly arranged on one side of the connecting plate 205. The push plate 206 facilitates the pushing or pulling of the connecting plate 205;

[0037] The transmission rod 207 is fixedly arranged on the outer surface of the bottom rod 2, and an arc plate 208 is fixedly arranged at one end of the transmission rod 207. When the transmission rod 207 rotates, it drives the arc plate 208 to rotate.

[0038] As Figures 1 to 5 shown, a round rod 209 is fixedly arranged on one side of the arc plate 208, a hollow cylinder 210 is fixedly arranged at one end of the round rod 209, two fixing rods 211 are fixedly arranged on the inner wall of the hollow cylinder 210, and a driving motor 212 is installed on the opposite sides of the two fixing rods 211. When the bottom rod 2 rotates, the arc plate 208 is driven by the transmission rod 207 to slide on one side of the support base 201, and further the hollow cylinder 210 is driven by the round rod 209 to be in different positions, so that the fan blade 214 rotates to blow out gas at different positions.

[0039] As Figures 1 to 5 shown, the arc plate 208 is slidably arranged on one side of the support base 201, an arc groove is formed on one side of the support base 201, and the support base 201 slides inside the arc groove, and the arc groove limits the movement of the support base 201.

[0040] As Figures 1 to 5 shown, two frames 3 are fixedly arranged on one side of the base 1. The two sides of the inner wall of one of the frames 3 are provided with a threaded rod 301 through bearings, and a rotating ring 308 is fixedly arranged on one side of the threaded rod 301. The threaded rod 301 can rotate, and the rotating ring 308 facilitates the rotation of the threaded rod 301.

[0041] As Figures 1 to 5 shown, a sleeve 302 is threadedly sleeved on the outer surface of the threaded rod 301. The two sides of the inner wall of the other frame 3 are fixedly provided with vertical rods 303. The sleeve 302 is connected to the sliding cylinder 304 through two cross plates 305 and a protective cylinder 306. Thus, when the threaded rod 301 rotates in different directions, the sleeve 302 moves up and down on the outer surface of the threaded rod 301.

[0042] As Figures 1 to 5 shown, a sliding cylinder 304 is movably sleeved on the outer surface of the vertical rod 303. Horizontal plates 305 are fixedly arranged on the outer surfaces of the sleeve 302 and the sliding cylinder 304, and the sliding cylinder 304 can slide on the outer surface of the vertical rod 303.

[0043] As Figures 1 to 5 shown, protective cylinders 306 are fixedly arranged on the opposite sides of the two horizontal plates 305. Glass 307 is installed on the outer surface of the protective cylinder 306. The test situation of the drone can be observed through the transparency of the glass 307. When the drone has problems, the drone will hit the glass 307 and will not hit the test personnel.

[0044] As Figures 1 to 5 shown, a rotating rod 213 is fixedly arranged on the output shaft of the driving motor 212. A fan blade 214 is installed at one end of the rotating rod 213. When the external power switch of the driving motor 212 is turned on, the output shaft of the driving motor 212 drives the fan blade 214 to rotate through the rotating rod 213. When the fan blade 214 rotates, it drives the flow of gas, and the blown gas blows onto the drone to simulate the hovering stability of the drone when it is blown by the wind.

[0045] Working principle: When conducting flight control tests on the drone, place the drone on the support base 201, control the drone to hover, and turn on the external power switch of the drive motor 212. The two fixed rods 211 support the drive motor 212. Then, the output shaft of the drive motor 212 drives the rotating rod 213 to rotate, further causing the fan blade 214 to rotate. When the fan blade 214 rotates, it drives the flow of gas, and the blown gas hits the drone, simulating the hovering stability of the drone when blown by the wind. By pushing the push plate 206, the connecting plate 205 is driven forward, causing the rack 204 to slide on the inner wall of the groove plate 203, further driving the gear 202 to rotate, thereby driving the bottom rod 2 to rotate counterclockwise. Through the transmission rod 207, the arc plate 208 slides on one side of the support base 201, and further drives the hollow cylinder 210 to be in different positions through the round rod 209, so that the gas blown by the rotation of the fan blade 214 is in different positions. By pulling the push plate 206, the gear 202 rotates clockwise, and then the hollow cylinder 210 rotates clockwise, making the blown gas in different positions. Thus, when conducting flight control tests on the drone, different wind directions can be tested, and the influence on the hovering stability of the drone can be evaluated, improving the practicality of the test bench. When conducting flight control tests on the drone, the sliding cylinder 304 can slide on the outer surface of the vertical rod 303, and the sleeve 302 is connected to the sliding cylinder 304 through two cross plates 305 and the protective cylinder 306. Thus, when the threaded rod 301 rotates in different directions, the sleeve 302 moves up and down on the outer surface of the threaded rod 301. During the test, by rotating the rotating ring 308 clockwise, the threaded rod 301 rotates clockwise, causing the sleeve 302 to move downward, that is, move towards the base 1 side. Thus, the protective cylinder 306 is driven to move through the two cross plates 305, surrounding the tested drone. At this time, the test situation of the drone can be observed through the transparency of the glass 307. When the drone has problems, the drone will hit the glass 307 and will not hit the test personnel. Thus, when the drone has problems during the flight control test of the drone, it can prevent the drone from hitting the test personnel and protect the test personnel, improving the safety of the test bench.

[0046] The above are only the preferred embodiments of the application, and it is not intended to limit the present invention in other forms. Any person skilled in the relevant art may use the disclosed technical content to make changes or modifications into equivalent embodiments with equivalent changes and apply them to other fields. However, as long as it does not depart from the technical solution content of the present invention, any simple modification, equivalent change, and modification made to the above embodiments based on the technical essence of the present invention still fall within the protection scope of the technical solution of the present invention.

Claims

1. A tilt-rotor UAV flight control test bench, characterized in that: The rig includes: Base (1); A bottom rod (2) is arranged at the center of one side of the base (1) via a bearing, and a support seat (201) is arranged at one end of the bottom rod (2) via a bearing; A gear (202) is fixedly sleeved on the outer surface of the bottom rod (2), and a rack (204) is meshedly provided on the outer surface of the gear (202); A slot plate (203) is fixedly arranged on a side of the base (1) close to the gear (202), and one side of the rack (204) is slidably arranged on the inner wall of the slot plate (203); A connecting plate (205) is fixedly arranged on one side of the rack (204), and a push plate (206) is fixedly arranged on one side of the connecting plate (205); The transmission rod (207) is fixedly arranged on the outer surface of the bottom rod (2), and an arc-shaped plate (208) is fixedly arranged on one end of the transmission rod (207).

2. The tilt-rotor UAV flight control test bench according to claim 1, characterized in that: A round rod (209) is fixedly provided on one side of the arc-shaped plate (208), a hollow cylinder (210) is fixedly provided on one end of the round rod (209), two fixed rods (211) are fixedly provided on the inner wall of the hollow cylinder (210), and a driving motor (212) is installed on opposite sides of the two fixed rods (211).

3. The tilt-rotor UAV flight control test bench according to claim 1, characterized in that: The arc-shaped plate (208) is slidably arranged on one side of the support seat (201).

4. The tilt-rotor UAV flight control test bench according to claim 1, characterized in that: Two frames (3) are fixedly provided on one side of the base (1), wherein threaded rods (301) are provided on both sides of the inner wall of one of the frames (3) via bearings, and a rotating ring (308) is fixedly provided on one side of the threaded rod (301).

5. The tilt-rotor UAV flight control test bench according to claim 4, characterized in that: The outer surface of the threaded rod (301) is threadedly sleeved with a sleeve (302), and vertical rods (303) are fixedly arranged on both sides of the inner wall of the other frame (3).

6. The tilt-rotor UAV flight control test bench according to claim 5, characterized in that: A slide cylinder (304) is movably sleeved on the outer surface of the vertical rod (303), and a transverse plate (305) is fixedly disposed on the outer surfaces of the sleeve (302) and the slide cylinder (304).

7. The tilt-rotor UAV flight control test bench according to claim 6, characterized in that: A protective tube (306) is fixedly provided on one side opposite to the two horizontal plates (305), and a glass (307) is installed on the outer surface of the protective tube (306).

8. The tilt-rotor UAV flight control test bench according to claim 2, characterized in that: A rotating rod (213) is fixedly disposed on the output shaft of the driving motor (212), and a fan blade (214) is mounted on one end of the rotating rod (213).

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