A test bench for electric UAV navigation and flight control system

Abstract

The present invention discloses an electric unmanned aerial vehicle navigation flight control system test bench, which relates to the technical field of electric unmanned aerial vehicle navigation flight control system test benches, and comprises a bottom plate, a housing is fixedly connected to the upper surface of the bottom plate, a motor is fixedly connected to the inner bottom wall of the cavity, an annular rack is slidably connected to the inner side wall of the cavity, a slide rail is fixedly connected to the upper surface of the bottom plate, a slider is slidably connected to the inner side wall of the slide rail, the outer surface of the slider is rotatably connected to a transmission rod through an axle rod, one end of the transmission rod is rotatably connected to a mounting block through an axle rod, a shock absorbing device is fixedly connected to the upper surface of the bottom plate, and a laser rangefinder is fixedly connected to the upper surface of the camera. The present invention achieves the purpose of facilitating the buffering of the unmanned aerial vehicle through the arrangement of the slide rail, the slider, the first spring, the mounting block and the shock absorbing device, and achieves the purpose of facilitating the automatic measurement of the take-off and landing positions of the unmanned aerial vehicle through the arrangement of the camera and the laser rangefinder.

Description

Technical Field

[0001] The invention relates to the technical field of an electric unmanned aerial vehicle navigation and flight control system test bench, in particular to an electric unmanned aerial vehicle navigation and flight control system test bench. Background Art

[0002] Unmanned aerial vehicles, or UAVs for short, are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices, or are operated completely or intermittently autonomously by onboard computers. Compared with manned aircraft, drones are often more suitable for tasks that are too "dull, dirty or dangerous". Drones can be divided into military and civilian applications according to their application areas. In the military, drones are divided into reconnaissance aircraft and target aircraft. In the civilian sector, drones + industry applications are the real rigid demand for drones; currently, drones are used in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspections, disaster relief, film and television shooting, creating romance, etc., which greatly expands the use of drones themselves. Developed countries are also actively expanding industry applications and developing drone technology. In order to advance science and technology, it is often necessary to test the navigation accuracy of drones, and at this time, a flight control system test bench is needed.

[0003] At present, the electric UAV navigation and flight control system test bench in the prior art is usually a fixed landing platform, which can often only be used for take-off and landing of the UAV. When the UAV lands, due to its own weight and flight inertia, it often generates a large impact force on the test bench. Since the force acts on each other, the large impact force can easily cause damage to the UAV. In addition, the traditional UAV navigation and flight control system usually requires manual measurement of the position difference of the UAV take-off and landing during testing. Manual measurement will produce large errors and low measurement efficiency. Therefore, the existing electric UAV navigation and flight control system test bench has the disadvantages of being inconvenient for cushioning the UAV and being inconvenient for automatic measurement of the take-off and landing position of the UAV. Summary of the invention

[0004] 1. Technical issues to be resolved

[0005] In view of the deficiencies in the prior art, the present invention provides an electric UAV navigation and flight control system test bench, which solves the problems raised in the above-mentioned background technology.

[0006] (II) Technical solution

[0007] To achieve the above objectives, the present invention is implemented through the following technical solutions: an electric unmanned aerial vehicle navigation flight control system test bench, comprising a base plate, the upper surface of the base plate is fixedly connected to a shell, a cavity is formed between the upper surface of the base plate and the lower surface of the shell, the inner bottom wall of the cavity is fixedly connected to a motor, the inner side wall of the cavity is slidably connected to an annular rack, the upper surface of the base plate is fixedly connected to a slide rail, the inner side wall of the slide rail is slidably connected to a slider, the inner side wall of the slide rail is fixedly connected to a first spring, the outer surface of the slider is rotatably connected to a transmission rod through a shaft rod, one end of the transmission rod is rotatably connected to a mounting block through a shaft rod, one end of the mounting block is fixedly connected to a test bench, the outer surface of the test bench is fixedly connected to an oblique guard plate, the upper surface of the base plate is fixedly connected to a shock absorbing device, the outer surface of the annular rack is fixedly connected to a fixed block, the upper surface of the fixed block is fixedly connected to an electric telescopic rod, one end of the electric telescopic rod is fixedly connected to a camera, and the upper surface of the camera is fixedly connected to a laser rangefinder.

[0008] The lower surface of the base plate is rotatably connected to a universal wheel, the upper surface of the base plate is fixedly connected to a first telescopic rod, and one end of the first telescopic rod is fixedly connected to a handrail rod.

[0009] Preferably, a gear is fixedly connected to the outer surface of the output shaft of the motor, and the outer surface of the gear is meshed with the outer surface of the annular rack.

[0010] The selected shock absorbing device includes a device shell, a shock absorbing telescopic tube, a sliding plate, a second spring and a sliding telescopic rod, the inner bottom wall of the device shell is fixedly connected to the shock absorbing telescopic tube, one end of the shock absorbing telescopic tube is fixedly connected to the sliding plate, the upper surface of the sliding plate is fixedly connected to the second spring, and the upper surface of the sliding plate is fixedly connected to the sliding telescopic rod.

[0011] The selected shock absorbing devices are four and evenly distributed in a circular array, the shock absorbing telescopic tubes are two, and the sliding plates are two and fixedly connected to each other and the two ends of the second spring.

[0012] The upper surface of the experimental table is fixedly connected with a positioning mark, and there are four slide rails that are evenly distributed in a circular array.

[0013] (III) Beneficial effects

[0014] The present invention provides a test bench for an electric unmanned aerial vehicle navigation and flight control system, which has the following beneficial effects:

[0015] 1. The electric UAV navigation and flight control system test bench has a buffering effect on the UAV through the arrangement of the slide rail, the slider, the first spring, the mounting block and the shock absorbing device. During use, when the UAV lands on the upper surface of the test bench, the test bench is subjected to the impact force to squeeze the mounting block downward, and then the slider is driven to slide inside the slide rail through the action of the transmission rod, and the impact force is absorbed by the action of the first spring. The second spring and the shock absorbing telescopic tube inside the shock absorbing device can also absorb the impact force received by the test bench, thereby achieving the purpose of facilitating the buffering of the UAV.

[0016] 2. The electric UAV navigation and flight control system test bench, through the setting of the camera and the laser rangefinder, enables the electric UAV navigation and flight control system test bench to have the effect of facilitating automatic measurement of the landing position. During use, after the UAV automatically navigates and lands, the rotation of the annular rack is controlled to drive the camera and the laser rangefinder to rotate around the test bench, so that during the rotation process, the distance between the outer shell of the UAV and the edge of the test bench is measured respectively through the action of the laser rangefinder, making the measurement more convenient and quick, thereby achieving the purpose of facilitating automatic measurement of the take-off and landing position of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0018] Figure 2 It is a schematic diagram of the structure of the present invention from the front;

[0019] Figure 3 It is a schematic diagram of the structure of the front cross section of the present invention;

[0020] Figure 4 It is a schematic diagram of the structure of the top cross section of the present invention;

[0021] Figure 5 For the present invention Figure 3 Schematic diagram of the structure at A in the middle.

[0022] In the figure: 1, bottom plate; 2, universal wheel; 3, first telescopic rod; 4, handrail rod; 5, shell; 6, cavity; 7, motor; 8, gear; 9, ring rack; 10, slide rail; 11, slider; 12, first spring; 13, transmission rod; 14, mounting block; 15, laboratory table; 16, oblique guard plate; 17, shock absorbing device; 1701, device shell; 1702, shock absorbing telescopic tube; 1703, sliding plate; 1704, second spring; 1705, sliding telescopic rod; 18, positioning mark; 19, fixing block; 20, electric telescopic rod; 21, camera; 22, laser rangefinder. DETAILED DESCRIPTION

[0023] 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 the embodiments.

[0024] See also Figures 1 to 5 The present invention provides a technical solution: an electric unmanned aerial vehicle navigation and flight control system test bench, comprising a bottom plate 1, a universal wheel 2 is rotatably connected to the lower surface of the bottom plate 1, a first telescopic rod 3 is fixedly connected to the upper surface of the bottom plate 1, one end of the first telescopic rod 3 is fixedly connected to a handrail 4, a shell 5 is fixedly connected to the upper surface of the bottom plate 1, a cavity 6 is formed between the upper surface of the bottom plate 1 and the lower surface of the shell 5, a motor 7 is fixedly connected to the inner bottom wall of the cavity 6, a gear 8 is fixedly connected to the outer surface of the output shaft of the motor 7, and the outer surface of the gear 8 is connected to the annular rack 9 The outer surface of the cavity 6 is meshed, the inner wall of the cavity 6 is slidably connected with an annular rack 9, the upper surface of the bottom plate 1 is fixedly connected with a slide rail 10, the inner wall of the slide rail 10 is slidably connected with a slider 11, the inner wall of the slide rail 10 is fixedly connected with a first spring 12, the outer surface of the slider 11 is rotatably connected with a transmission rod 13 through an axis rod, one end of the transmission rod 13 is rotatably connected with a mounting block 14 through an axis rod, one end of the mounting block 14 is fixedly connected with a laboratory table 15, and the upper surface of the laboratory table 15 is fixedly connected with a positioning mark 18, and the slide rail 10 has four and annular array The outer surface of the experimental table 15 is fixedly connected with an oblique guard plate 16, and the upper surface of the bottom plate 1 is fixedly connected with a shock absorbing device 17. There are four shock absorbing devices 17 and they are evenly distributed in a circular array. There are two shock absorbing telescopic tubes 1702, and there are two sliding plates 1703. They are fixedly connected to the two ends of the second spring 1704. The shock absorbing device 17 includes a device shell 1701, a shock absorbing telescopic tube 1702, a sliding plate 1703, a second spring 1704 and a sliding telescopic rod 1705. The inner shell 1701 of the device The bottom wall is fixedly connected with a shock-absorbing telescopic tube 1702, one end of the shock-absorbing telescopic tube 1702 is fixedly connected with a sliding plate 1703, the upper surface of the sliding plate 1703 is fixedly connected with a second spring 1704, the upper surface of the sliding plate 1703 is fixedly connected with a sliding telescopic rod 1705, the outer surface of the annular rack 9 is fixedly connected with a fixed block 19, the upper surface of the fixed block 19 is fixedly connected with an electric telescopic rod 20, one end of the electric telescopic rod 20 is fixedly connected with a camera 21, and the upper surface of the camera 21 is fixedly connected with a laser rangefinder 22.

[0025] When in use, first place the drone on the upper surface of the experimental table 15, push the device to the desired location through the handrail 4, shorten the first telescopic rod 3 downward, and then control the rotation of the motor 7. Through the meshing of the gear 8 and the annular rack 9, the annular rack 9 is driven to rotate, and then the fixed block 19 is driven to rotate. The rotation of the fixed block 19 drives the camera 21 and the laser rangefinder 22 to rotate through the electric telescopic rod 20, so that the distance between various parts of the drone shell and the laser rangefinder 22 can be measured. Then the drone is controlled to take off for flight control. When the drone automatically navigates back, it automatically lands on the upper surface of the experimental table 15. The impact force during landing drives the experimental table 15 to move downward, and then drives the mounting block 14 to descend. The slider 11 is driven to slide to one side inside the slide rail 10 through the action of the transmission rod 13. During the sliding process of the slider 11, the first spring 12 is squeezed. At this time, the first spring 12 will absorb part of the drone's impact on the experimental table 15, and when the experimental table 15 falls, the sliding telescopic rod 1705 is driven to retract into the inside of the device shell 1701, squeezing the sliding plate 1703, and the two sliding plates 1703 squeeze the second spring 1704, so that the second spring 1704 absorbs part of the impact force, and when the sliding plate 1703 descends, it squeezes the shock-absorbing telescopic tube 1702, so that the shock-absorbing telescopic tube 1702 absorbs part of the impact force, so that the UAV can achieve a better buffering effect when it contacts the upper surface of the experimental table 15, avoiding damage to the UAV during landing. After the UAV stops, the rotation of the motor 7 is controlled to drive the camera 21 and the laser rangefinder 22 to rotate around the experimental table 15 again, and during the rotation process, the distance between the position of each part of the UAV shell and the laser rangefinder 22 is measured again, so as to automatically calculate the difference and distance between the take-off position and the landing position, thereby achieving a better use effect.

[0026] In summary, the present invention provides the electric UAV navigation flight control system test bench with a buffering effect on the UAV through the arrangement of the slide rail 10, the slider 11, the first spring 12, the mounting block 14 and the shock absorbing device 17. During use, when the UAV lands on the upper surface of the test bench 15, the test bench 15 is subjected to an impact force to press the mounting block 14 downward, and then the slider 11 is driven to slide inside the slide rail 10 through the action of the transmission rod 13, and the impact force is absorbed by the action of the first spring 12. The second spring 1704 and the shock absorbing telescopic tube 1702 inside the shock absorbing device 17 can also absorb the impact force received by the test bench 15, thereby The purpose of facilitating the buffering of the UAV is achieved. Through the arrangement of the camera 21 and the laser rangefinder 22, the electric UAV navigation flight control system test bench has the effect of facilitating the automatic measurement of the landing position. During use, after the UAV automatically navigates and lands, the rotation of the annular rack 9 is controlled to drive the camera 21 and the laser rangefinder 22 to rotate around the test bench 15, so that during the rotation process, the distance between the outer shell of the UAV and the edge of the test bench 15 is measured respectively through the action of the laser rangefinder 22, making the measurement more convenient and quick, thereby achieving the purpose of facilitating the automatic measurement of the take-off and landing position of the UAV.

[0027] 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 according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An electric unmanned aerial vehicle navigation and flight control system test bench, comprising a base plate (1), characterized in that: The upper surface of the base plate (1) is fixedly connected to a shell (5), a cavity (6) is formed between the upper surface of the base plate (1) and the lower surface of the shell (5), the inner bottom wall of the cavity (6) is fixedly connected to a motor (7), the inner side wall of the cavity (6) is slidably connected to an annular rack (9), the upper surface of the base plate (1) is fixedly connected to a slide rail (10), the inner side wall of the slide rail (10) is slidably connected to a slider (11), the inner side wall of the slide rail (10) is fixedly connected to a first spring (12), the outer surface of the slider (11) is rotatably connected to a transmission rod (13) via a shaft, and the transmission rod ( One end of the mounting block (13) is rotatably connected to a mounting block (14) through an axle rod, one end of the mounting block (14) is fixedly connected to a test bench (15), the outer surface of the test bench (15) is fixedly connected to an oblique guard plate (16), the upper surface of the bottom plate (1) is fixedly connected to a shock absorbing device (17), the outer surface of the annular rack (9) is fixedly connected to a fixing block (19), the upper surface of the fixing block (19) is fixedly connected to an electric telescopic rod (20), one end of the electric telescopic rod (20) is fixedly connected to a camera (21), and the upper surface of the camera (21) is fixedly connected to a laser rangefinder (22); The shock absorbing device (17) comprises a device housing (1701), a shock absorbing telescopic tube (1702), a sliding plate (1703), a second spring (1704) and a sliding telescopic rod (1705); the inner bottom wall of the device housing (1701) is fixedly connected to the shock absorbing telescopic tube (1702); one end of the shock absorbing telescopic tube (1702) is fixedly connected to the sliding plate (1703); the upper surface of the sliding plate (1703) is fixedly connected to the second spring (1704); and the upper surface of the sliding plate (1703) is fixedly connected to the sliding telescopic rod (1705); There are four shock absorbing devices (17) which are evenly distributed in a circular array, there are two shock absorbing telescopic tubes (1702), and there are two sliding plates (1703) which are fixedly connected to each other and to the two ends of the second spring (1704).

2. The electric UAV navigation and flight control system test bench according to claim 1, characterized in that: The lower surface of the base plate (1) is rotatably connected to a universal wheel (2), the upper surface of the base plate (1) is fixedly connected to a first telescopic rod (3), and one end of the first telescopic rod (3) is fixedly connected to a handrail rod (4).

3. The electric UAV navigation and flight control system test bench according to claim 1, characterized in that: The outer surface of the output shaft of the motor (7) is fixedly connected with a gear (8), and the outer surface of the gear (8) is meshed with the outer surface of the annular rack (9).

4. The electric UAV navigation and flight control system test bench according to claim 1, characterized in that: A positioning mark (18) is fixedly connected to the upper surface of the experimental table (15), and there are four slide rails (10) which are evenly distributed in a circular array.

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