Easy-to-adjust aircraft stability test equipment carried by camera device

Abstract

The invention discloses an easy-to-adjust aircraft stability test device carried by a camera device, and relates to the technical field of aircraft testing. The unmanned aerial vehicle comprises an oval flight track, a throwing pipe and an air bellow are fixedly installed at the two ends of the oval flight track respectively, and the throwing pipe and the air bellow are both communicated with the interior of the oval flight track. The unmanned aerial vehicle flies in the oval flight track and shoots a static landscape plate and a dynamic screen, meanwhile, a high-power draught fan starts to convey strong wind into the oval flight track, and two air blowers at the center position of the oval flight track blow air to four air outlet pipes on the upper side and the lower side through T-shaped three-way air pipes correspondingly; therefore, the shooting stability and the shooting quality of the unmanned aerial vehicle during the shooting operation of the dynamic and static landscapes under the action of multi-directional strong wind are tested, and the testing environment of the stability of the camera device of the unmanned aerial vehicle is closer to the actual working environment.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft testing, and particularly to a flight vehicle stability testing device with an easily adjustable camera device mounted thereon. Background Art

[0002] In recent years, unmanned aircraft technology has developed rapidly. UAVs can be used to carry shooting devices for aerial photography, mapping, reconnaissance, etc. They are safe, fast, and convenient. UAV aerial photography and mapping technology, with its high precision, high efficiency, and powerful data analysis capabilities, is gradually becoming a key role in surveying and mapping engineering. The stability of the gimbal used to carry the camera device will greatly affect aspects such as the clarity, light, and color reproduction of the captured image. Therefore, to ensure the shooting quality, it is necessary to pre-test the stability of the gimbal on the UAV.

[0003] Currently, the general method for testing the camera stability of UAVs is to launch the UAV outdoors for on-site shooting, or directly place the gimbal loaded with the camera device on a movable bracket indoors, and drive the gimbal to move through the bracket, so as to detect the stability of the gimbal by the captured image. However, the outdoor testing method has high requirements for the testing site and environmental factors during testing, and the indoor testing method for the gimbal is difficult to simulate the real situation during UAV flight. Therefore, an easily adjustable flight vehicle stability testing device with a camera device mounted thereon is proposed. Summary of the Invention

[0004] The purpose of the present invention is to solve the problems that the current method for testing the gimbal stability outdoors has high requirements for the testing site and environmental factors during testing, and the indoor testing method for the gimbal stability is difficult to simulate the real situation during UAV flight. The present invention provides an easily adjustable flight vehicle stability testing device with a camera device mounted thereon.

[0005] The present invention specifically adopts the following technical solutions to achieve the above purpose:

[0006] An aircraft stability test device equipped with an easily adjustable camera device, including an elliptical flight track. Both ends of the elliptical flight track are fixedly installed with a delivery pipe and a bellows respectively. The delivery pipe and the bellows are both communicated with the inside of the elliptical flight track. A drone platform for providing a take-off and docking site for the drone is fixedly installed on the bottom inner wall of the elliptical flight track. A high-power blower is fixedly installed inside the bellows. A plurality of static landscape boards and dynamic screens for being photographed by the drone are arranged on the bottom inner wall of the elliptical flight track. Two first brackets distributed from top to bottom are fixedly installed on the central side wall of the elliptical flight track. Blowers are fixedly installed on the tops of the first brackets. T-shaped three-way air pipes are fixedly installed at the air delivery ends of the blowers. Four horizontally arranged air outlet pipes are rotatably installed inside the elliptical flight track. One ends of the four air outlet pipes all extend to the outside of the elliptical flight track and are respectively rotatably connected to both ends of the two T-shaped three-way air pipes. Air outlet holes are opened on one side of the two air outlet pipes located at the same place and close to each other.

[0007] Furthermore, a plurality of uniformly distributed assembly holes are opened on the bottom inner wall of the elliptical flight track. Static assembly plates are arranged at the bottoms of the static landscape boards. Dynamic assembly plates are fixedly installed at the bottoms of the dynamic screens. The plurality of static assembly plates and the plurality of dynamic assembly plates are respectively located inside the plurality of assembly holes. Placement grooves are opened on the tops of the static assembly plates. The static landscape boards are located inside the placement grooves. A limiting pressure frame is arranged above the static assembly plates. Limiting slide rods are fixedly installed at the four corners of the bottom of the limiting pressure frame. Pressure frame slide holes are opened at the four corners of the top of the static assembly plate. The bottom ends of the limiting slide rods located at the same place penetrate through the pressure frame slide holes. A plurality of assembly sockets are fixedly installed at the bottom of the elliptical flight track. The plurality of assembly sockets are symmetrically distributed on both sides of the plurality of assembly holes. Spring slide boxes are fixedly installed on both sides of the bottoms of the static assembly plates and the dynamic assembly plates. Assembly pins adapted to the assembly sockets are slidably installed inside the spring slide boxes. Limiting toggle rods are fixedly installed at the bottoms of the assembly pins. Limiting slide holes are opened at the bottoms of the spring slide boxes. The limiting toggle rods located at the same place penetrate through the limiting slide holes and extend to the outside of the spring slide boxes.

[0008] Furthermore, a plurality of power connection sockets are fixedly installed at the bottom of the elliptical flight track. The plurality of power connection sockets are respectively located on one side of the plurality of assembly holes. Power plugs connected to the dynamic screens are fixedly installed at the bottoms of the dynamic assembly plates. The power plugs are adapted to the power connection sockets.

[0009] Furthermore, chamfered angles are provided at the bottom ends of the assembly pins located outside the spring slide box, and rubber frames are fixedly sleeved at the bottoms of the static assembly plate and the dynamic assembly plate.

[0010] Furthermore, two second brackets are fixedly installed on the central side wall of the elliptical flight track and are distributed from top to bottom. An air preheater is fixedly installed on the lower second bracket. Air inlet pipes are fixedly installed at the air inlet ends of the limiting slide rods. The air preheater is communicated with the lower air inlet pipe.

[0011] Furthermore, an air cooler is fixedly installed on the upper second bracket. The air cooler is communicated with the upper air inlet pipe.

[0012] Furthermore, two gear boxes are fixedly installed on both sides of the elliptical flight track. The four gear boxes are respectively drivingly connected to one ends of the four air outlet pipes. A steering motor is fixedly installed on one side of each gear box. The output shafts of the four steering motors respectively extend into the interiors of the four gear boxes and are drivingly connected to the four gear boxes.

[0013] Furthermore, a protective transparent plate is fixedly installed inside the elliptical flight track. The protective transparent plate is located above the plurality of static landscape plates and the plurality of dynamic screens. Two ventilation holes corresponding to the positions of the air outlet pipes are provided at the top of the protective transparent plate.

[0014] The beneficial effects of the present invention are as follows:

[0015] 1. The present invention enables the unmanned aerial vehicle to fly inside the elliptical flight track and photograph the static landscape plates and the dynamic screens. At the same time, the high-power blower starts to convey strong wind into the elliptical flight track. The two blowers at the central position of the elliptical flight track respectively blow air into the four air outlet pipes on the upper and lower sides through the T-shaped three-way air pipes, thereby testing the shooting stability and shooting quality of the unmanned aerial vehicle when shooting the dynamic and static landscapes under the action of strong wind in multiple directions, and making the test environment of the stability of the camera device of the unmanned aerial vehicle closer to the actual working environment;

[0016] 2. By providing the static assembly plate and the dynamic assembly plate, the present invention enables the distribution of the static landscape plates and the dynamic screens to be planned in advance. The static assembly plate loaded with the static landscape plates and the dynamic assembly plate equipped with the dynamic screens are respectively placed into different assembly holes in sequence, and the static assembly plate and the dynamic assembly plate are installed inside the elliptical flight track, realizing the rapid loading and unloading of the static landscape plates and the dynamic screens and facilitating the adjustment of the distribution of the dynamic and static landscapes;

[0017] 3. By providing an air preheater and an air cooler, the present invention enables the two blowers located below to extract air from the air preheater and the air cooler respectively, causing hot air to gush upward from the air outlet holes of the lower air outlet pipe to form a hot air current, and cold air to gush downward from above the unmanned aerial vehicle to form a cold air current, thereby testing the camera stability of the unmanned aerial vehicle under the alternating or dual action of cold and hot air currents.

[0018] 4. By providing a steering motor, when the blowers deliver cold and hot air into the inner part of the elliptical flight orbit through the air outlet pipe and the air outlet, the two steering motors on both sides drive the four air outlet pipes on the upper and lower sides to deflect back and forth slightly and slowly through the transmission gears inside the gearbox, thereby further changing the wind direction, increasing the complexity of the test environment, and making the test environment closer to the actual camera environment.

[0019] 5. By providing a protective transparent plate, the protective transparent plate can be located above multiple static landscape plates and dynamic screens to protect the static landscape plates and dynamic screens. When the unmanned aerial vehicle is out of balance or out of control, it can prevent the unmanned aerial vehicle from directly contacting the static landscape plates and dynamic screens. The ventilation holes can prevent the protective transparent plate from blocking the hot air current output from the air outlet below. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 is a three-dimensional structure schematic diagram of the first perspective of the present invention;

[0021] Figure 2 is a three-dimensional structure schematic diagram of the second perspective of the present invention;

[0022] Figure 3 is a three-dimensional structure schematic diagram inside the elliptical flight orbit of the present invention;

[0023] Figure 4 is a three-dimensional structure schematic diagram of the cooperation between the static landscape plate, the dynamic screen and the elliptical flight orbit of the present invention;

[0024] Figure 5 is a three-dimensional structure schematic diagram of the first perspective of the static assembly plate of the present invention;

[0025] Figure 6 is a three-dimensional structure schematic diagram of the second perspective of the static assembly plate of the present invention;

[0026] Figure 7 is a three-dimensional structure schematic diagram of the cooperation between the static landscape plate and the static assembly plate of the present invention;

[0027] Figure 8 is a three-dimensional structure schematic diagram of the first perspective of the dynamic assembly plate of the present invention;

[0028] Figure 9 is a three-dimensional structure schematic diagram of the second perspective of the dynamic assembly plate of the present invention;

[0029] Reference signs: 1, oval flight orbit; 2, delivery pipe; 3, UAV platform; 4, bellows; 5, high-power blower; 6, static landscape board; 7, dynamic screen; 8, first bracket; 9, blower; 10, T-shaped three-way ventilation pipe; 11, air outlet pipe; 12, static assembly plate; 1201, press frame slide hole; 13, limit press frame; 14, limit slide bar; 15, dynamic assembly plate; 16, assembly socket; 17, spring slide box; 1701, limit slide hole; 18, assembly bolt; 19, limit lever; 20, inclined guide angle; 21, power connection socket; 22, power-on plug; 23, rubber frame; 24, second bracket; 25, air preheater; 26, air cooler; 27, intake pipe; 28, gearbox; 29, steering motor; 30, protective transparent plate; 3001, ventilation hole. Detailed implementation manners

[0030] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Apparently, the described embodiments are some but not all of the embodiments of the present invention. The components of the embodiments of the present invention usually described and illustrated in the accompanying drawings here can be arranged and designed in various different configurations.

[0031] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed present invention, but merely represents selected embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0032] It should be noted that similar reference signs and letters indicate similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings. In addition, terms such as "first" and "second" are only used for descriptive distinction and cannot be understood as indicating or implying relative importance.

[0033] In the description of the embodiments of the present invention, it should be noted that the orientation or positional relationship indicated by terms such as "inside", "outside", "above", etc. is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of the present invention is usually placed during use. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the present invention.

[0034] Such as Figures 1 to 9As shown in the figure, an aircraft stability test device equipped with an easily adjustable camera device includes an elliptical flight track 1. In this embodiment, lamps can be arranged inside the elliptical flight track 1 to imitate environmental light, such as Figure 1 As shown in the figure, a delivery pipe 2 and a bellows 4 are fixedly installed at both ends of the elliptical flight track 1 respectively. The delivery pipe 2 and the bellows 4 are both communicated with the inside of the elliptical flight track 1. A drone platform 3 for providing a take-off and docking site for the drone is fixedly installed on the bottom inner wall of the elliptical flight track 1, such as Figure 3 As shown in the figure, a high-power blower 5 is fixedly installed inside the bellows 4, such as Figure 4 As shown in the figure, a plurality of static landscape boards 6 and dynamic screens 7 for being photographed by the drone are arranged on the bottom inner wall of the elliptical flight track 1. Two first brackets 8 distributed from top to bottom are fixedly installed on the central side wall of the elliptical flight track 1. Blowers 9 are fixedly installed on the tops of the first brackets 8. In this embodiment, the elliptical flight track 1 is of an elliptical structure, and the central position is an empty area communicated up and down. The blowers 9 and the first brackets 8 are both located in this area, such as Figure 3 As shown in the figure, the air delivery ends of the blowers 9 are both fixedly installed with T-shaped three-way air pipes 10. Four horizontally arranged air outlet pipes 11 are rotatably installed inside the elliptical flight track 1. One ends of the four air outlet pipes 11 all extend to the outside of the elliptical flight track 1 and are respectively rotatably connected to both ends of the two T-shaped three-way air pipes 10. Air outlet holes are formed on the sides of the two air outlet pipes 11 located at the same place and close to each other. In this embodiment, the four air outlet pipes 11 are distributed on both sides inside the elliptical flight track 1 and are respectively close to the top and bottom inner walls of the elliptical flight track 1. The drone travels between the upper and lower two air outlet pipes 11. Specifically, when the aircraft stability test device equipped with this camera device is in use, the drone is placed on the drone platform 3 inside the delivery pipe 2, and the drone is started to fly inside the elliptical flight track 1 and photograph the various static landscape boards 6 and dynamic screens 7 below. Static scenes are drawn on the static landscape boards 6, and dynamic landscapes are played on the dynamic screens 7. At the same time, the high-power blower 5 inside the bellows 4 starts to deliver strong wind into the elliptical flight track 1. The two blowers 9 at the central position of the elliptical flight track 1 respectively blow air to the four air outlet pipes 11 on the upper and lower sides through the T-shaped three-way air pipes 10. When the drone passes through the two air outlet pipes 11, it will be affected by the wind forces of the air outlet holes on the upper and lower sides, so as to test the shooting stability and shooting quality of the drone when photographing the static and dynamic landscapes on the static landscape boards 6 and dynamic screens 7 under the action of strong winds in multiple directions, making the test environment of the stability of the camera device of the drone closer to the actual working environment.

[0035] As Figure 2As shown, a plurality of uniformly distributed assembly holes are provided on the inner wall of the bottom of the elliptical flight track 1. Static mounting plates 12 are provided at the bottoms of the static landscape plates 6, and dynamic mounting plates 15 are fixedly installed at the bottoms of the dynamic screens 7. The plurality of static mounting plates 12 and the plurality of dynamic mounting plates 15 are respectively located inside the plurality of assembly holes, as Figure 7 shown, placing grooves are provided at the tops of the static mounting plates 12, and the static landscape plates 6 are located inside the placing grooves, as Figure 5 shown, a limiting pressure frame 13 is provided above the static mounting plate 12, as Figure 6 shown, limiting slide rods 14 are fixedly installed at the four corners of the bottom of the limiting pressure frame 13, and pressure frame slide holes 1201 are provided at the four corners of the top of the static mounting plate 12. The bottom ends of the limiting slide rods 14 at the same position penetrate through the pressure frame slide holes 1201, as Figure 2 shown, a plurality of assembly sockets 16 are fixedly installed at the bottom of the elliptical flight track 1. The plurality of assembly sockets 16 are symmetrically distributed on both sides of the plurality of assembly holes, as Figure 6 、 Figure 9 shown, spring slide boxes 17 are fixedly installed on both sides of the bottoms of the static mounting plates 12 and the dynamic mounting plates 15. Assembly bolts 18 adapted to the assembly sockets 16 are slidably installed inside the spring slide boxes 17. In this embodiment, a plurality of horizontal reset springs are provided inside the spring slide boxes 17 to provide elastic force for the ejection of the assembly bolts 18. Limiting dial rods 19 are fixedly installed at the bottoms of the assembly bolts 18, and limiting slide holes 1701 are provided at the bottoms of the spring slide boxes 17. The limiting dial rods 19 at the same position penetrate through the limiting slide holes 1701 and extend to the outside of the spring slide boxes 17; specifically, by providing the static mounting plates 12 and the dynamic mounting plates 15, the distribution of the static landscape plates 6 and the dynamic screens 7 can be planned in advance. Lift the limiting pressure frame 13 and place the corresponding number of static landscape plates 6 into the placing grooves on each static mounting plate 12 respectively, then lower the limiting pressure frame 13 to limit the static landscape plates 6, and then reverse the two limiting dial rods 19 to make the assembly bolts 18 retract into the spring slide boxes 17. Place the static mounting plates 12 loaded with static landscape plates 6 and the dynamic mounting plates 15 equipped with dynamic screens 7 into different assembly holes in sequence, and release the limiting dial rods 19 to make the assembly bolts 18 pop into the assembly sockets 16 on both sides under the action of spring force, so as to install the static mounting plates 12 and the dynamic mounting plates 15 inside the elliptical flight track 1, realizing the quick loading and unloading of the static landscape plates 6 and the dynamic screens 7, and facilitating the adjustment of the distribution of the dynamic and static landscapes.

[0036] As Figure 2 shown, a plurality of power connection sockets 21 are fixedly installed at the bottom of the elliptical flight track 1. The plurality of power connection sockets 21 are respectively located on one side of the plurality of assembly holes, as Figure 9As shown, power plugs 22 connected to the dynamic screen 7 are fixedly installed at the bottom of the dynamic assembly plate 15. The power plugs 22 are adapted to the power sockets 21. Specifically, by providing the power plugs 22, when the dynamic assembly plate 15 is placed into the assembly hole, the power plug 22 on one side of the bottom of the dynamic assembly plate 15 will be inserted into the power socket 21 at the bottom of the oval flight track 1, so that the dynamic screen 7 is powered through the power plug 22 and the power socket 21, facilitating the power supply and remote control of the dynamic screen 7 and solving the problems of the battery life of the dynamic screen 7 and the replacement of the dynamic landscape.

[0037] As Figure 6 shown, chamfered guides 20 are provided at the bottom of the outer ends of the assembly pins 18 located outside the spring slide boxes 17. In this embodiment, a ramp structure adapted to the chamfered guides 20 is provided inside the assembly sockets 16. Rubber frames 23 are fixedly sleeved at the bottoms of the static assembly plate 12 and the dynamic assembly plate 15. Specifically, by providing the chamfered guides 20, when the limiting lever 19 is released and the assembly pins 18 spring into the assembly sockets 16 on both sides, the chamfered guides 20 at the bottom of the assembly pins 18 will contact the ramp structure inside the assembly sockets 16, thereby driving the static assembly plate 12 and the dynamic assembly plate 15 to move upward a short distance as a whole, so that the rubber frames 23 can closely adhere to the oval flight track 1, sealing the gaps of the assembly holes, reducing air leakage, and at the same time improving the fastening of the connection between the power plug 22 and the power socket 21.

[0038] As Figure 2 shown, two second brackets 24 distributed from top to bottom are fixedly installed on the central side wall of the oval flight track 1. As Figure 4 shown, an air preheater 25 is fixedly installed on the lower second bracket 24. Air inlet pipes 27 are fixedly installed at the air inlet ends of the limiting slide rods 14. The air preheater 25 is communicated with the lower air inlet pipe 27. Specifically, by providing the air preheater 25, when the blower 9 blows air into the oval flight track 1, the lower blower 9 will draw air from the air preheater 25, allowing external air to enter the interior of the air preheater 25, and then being heated by the air preheater 25 and conveyed through the air inlet pipe 27 and the blower 9 into the interior of the oval flight track 1, so that hot air gushes upward from the air outlet holes of the lower air outlet pipe 11 to form a hot air flow, thereby testing the camera stability of the drone under the action of the hot air flow.

[0039] As Figure 4As shown in the figure, an air cooler 26 is fixedly installed on the upper second bracket 24, and the air cooler 26 is communicated with the upper intake pipe 27; specifically, by arranging the air cooler 26, the air will be cooled after entering the air cooler 26, and then be conveyed to the inside of the elliptical flight track 1 by the blower 9, and gush downward from the upper part of the drone to form a cold air flow, so as to test the camera stability of the drone under the action of alternating or dual cold and hot air flows.

[0040] As Figure 3 shown in the figure, two gear boxes 28 are fixedly installed on both sides of the elliptical flight track 1, and the four gear boxes 28 are respectively drivingly connected to one end of the four air outlet pipes 11. A steering motor 29 is fixedly installed on one side of each gear box 28. The output shafts of the four steering motors 29 respectively extend into the gear boxes 28 and are drivingly connected to the four gear boxes 28. In this embodiment, a pair of meshing transmission gears are arranged inside the gear box 28. One of the transmission gears is fixedly sleeved on one end of the air outlet pipe 11, and the other transmission gear is fixedly sleeved on the output shaft of the steering motor 29. The steering motor 29 adopts a stepping motor; specifically, by arranging the steering motor 29, when the blower 9 conveys cold and hot air flows into the elliptical flight track 1 through the air outlet pipes 11 and the air outlet, the two side steering motors 29 will drive the four air outlet pipes 11 on the upper and lower sides to deflect back and forth in a small amplitude and at a low speed through the transmission gears inside the gear box 28, so as to further change the wind direction, increase the complexity of the test environment, and make the test environment closer to the actual camera environment.

[0041] As Figure 3 shown in the figure, a protective transparent plate 30 is fixedly installed inside the elliptical flight track 1. In this embodiment, the protective transparent plate 30 can be installed inside the elliptical flight track 1 through a spring bracket. When the drone is out of balance or out of control, the protective transparent plate 30 can play a buffering and protective role for the drone. The protective transparent plate 30 is located above the plurality of static landscape plates 6 and the plurality of dynamic screens 7. Two ventilation holes 3001 corresponding to the positions of the air outlet pipes 11 are opened at the top of the protective transparent plate 30. In this embodiment, the protective transparent plate 30 is located between the upper and lower air outlet pipes 11 and close to the lower air outlet pipe 11, and the drone flies above the protective transparent plate 30; specifically, by arranging the protective transparent plate 30, the protective transparent plate 30 can be located above the plurality of static landscape plates 6 and the dynamic screens 7 to protect the static landscape plates 6 and the dynamic screens 7. When the drone is out of balance or out of control, it can prevent the drone from directly contacting the static landscape plates 6 and the dynamic screens 7, and the ventilation holes 3001 can prevent the protective transparent plate 30 from blocking the hot air flow output from the air outlet below.

[0042] In summary, when the aircraft stability test equipment carried by the camera device is in use, place the drone on the drone platform 3 inside the delivery tube 2, start the drone, and let it fly inside the elliptical flight track 1 and take pictures of the various static landscape boards 6 and dynamic screens 7 below. Static scenes are drawn on the static landscape boards 6, and dynamic landscapes are played on the dynamic screens 7. At the same time, the high-power blower 5 inside the air box 4 starts to deliver strong wind into the elliptical flight track 1. The two blowers 9 at the center position of the elliptical flight track 1 respectively blow air through the T-shaped three-way air ducts 10 to the four air outlet pipes 11 on the upper and lower sides. When the drone passes through the two air outlet pipes 11, it will be affected by the wind from the upper and lower air outlet holes, so as to test the shooting stability and shooting quality of the drone when taking pictures of the static and dynamic landscapes on the static landscape boards 6 and dynamic screens 7 under the action of strong wind in multiple directions, making the test environment of the stability of the camera device of the drone closer to the actual working environment. By setting the static assembly plate 12 and the dynamic assembly plate 15, the distribution of the static landscape boards 6 and dynamic screens 7 can be planned in advance. Lift the limit pressing frame 13 and place the corresponding number of static landscape boards 6 into the placement grooves on each static assembly plate 12 respectively, and then lower the limit pressing frame 13 to limit the static landscape boards 6. Then, reverse the two limit levers 19 to make the assembly pins 18 retract into the spring slide boxes 17, and place the static assembly plates 12 loaded with static landscape boards 6 and the dynamic assembly plates 15 equipped with dynamic screens 7 into different assembly holes in sequence. Release the limit levers 19 to make the assembly pins 18 pop into the assembly sockets 16 on both sides under the action of the spring force, so as to install the static assembly plates 12 and the dynamic assembly plates 15 inside the elliptical flight track 1, realizing the quick loading and unloading of the static landscape boards 6 and dynamic screens 7 and facilitating the adjustment of the distribution of the static and dynamic landscapes. By setting the power-on plug 22, when the dynamic assembly plate 15 is placed into the assembly hole, the power-on plug 22 on one side of the bottom of the dynamic assembly plate 15 will be inserted into the power connection socket 21 at the bottom of the elliptical flight track 1, so that the dynamic screen 7 is powered on through the power-on plug 22 and the power connection socket 21, facilitating the power supply and remote control of the dynamic screen 7 and solving the problems of the battery life of the dynamic screen 7 and the replacement of the dynamic landscape. By setting the inclined guide angle 20, when the limit levers 19 are released and the assembly pins 18 pop into the assembly sockets 16 on both sides, the inclined guide angle 20 at the bottom of the assembly pin 18 will contact the ramp structure inside the assembly socket 16, driving the static assembly plate 12 and the dynamic assembly plate 15 to move up a short distance as a whole, so that the rubber frame 23 can be tightly attached to the elliptical flight track 1 to seal the gap of the assembly hole, reduce air leakage, and improve the fastening of the power-on plug 22 and the power connection socket 21. By setting the air preheater 25, when the blower 9 blows air into the elliptical flight track 1, the blower 9 below will draw air from the air preheater 25, allowing external air to enter the air preheater 25.Furthermore, after being heated by the air preheater 25, it is transported to the inside of the elliptical flight orbit 1 through the intake pipe 27 and the blower 9, so that the hot air gushes upward from the air outlet holes of the air outlet pipe 11 below, forming a hot air flow, thereby testing the camera stability of the drone under the action of the hot air flow. By setting the air cooler 26, the air will be cooled after entering the air cooler 26, and then be transported to the inside of the elliptical flight orbit 1 by the blower 9, gushing downward from above the drone, forming a cold air flow, thereby testing the camera stability of the drone under the alternating or dual action of cold and hot air flows. By setting the steering motor 29, when the blower 9 transports cold and hot air flows to the inside of the elliptical flight orbit 1 through the air outlet pipe 11 and the air outlet, the two steering motors 29 on both sides will drive the four air outlet pipes 11 on the upper and lower sides to deflect back and forth slightly and slowly through the transmission gears inside the gearbox 28, thereby further changing the wind direction, increasing the complexity of the test environment, and making the test environment closer to the actual camera environment. By setting the protective transparent plate 30, the protective transparent plate 30 can be located above the plurality of static landscape plates 6 and the dynamic screen 7 to protect the static landscape plates 6 and the dynamic screen 7. When the drone is out of balance or out of control, it can prevent the drone from directly contacting the static landscape plates 6 and the dynamic screen 7. The ventilation holes 3001 can prevent the protective transparent plate 30 from blocking the hot air flow output from the air outlet below.,

[0043] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. What is described in the above embodiments and the specification is only the principle of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed. The scope of protection required by the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft stability test device equipped with an easily adjustable imaging device, characterized in that, It includes an elliptical flight orbit (1), with a delivery pipe (2) and a bellows (4) fixedly installed at both ends of the elliptical flight orbit (1) respectively. Both the delivery pipe (2) and the bellows (4) are communicated with the inside of the elliptical flight orbit (1). A drone platform (3) for providing a take-off and docking site for the drone is fixedly installed on the bottom inner wall of the elliptical flight orbit (1). A high-power blower (5) is fixedly installed inside the bellows (4). A plurality of static landscape boards (6) and dynamic screens (7) for being photographed by the drone are arranged on the bottom inner wall of the elliptical flight orbit (1). Two first brackets (8) distributed from top to bottom are fixedly installed on the central side wall of the elliptical flight orbit (1). Blowers (9) are fixedly installed on the tops of the first brackets (8). T-shaped three-way air pipes (10) are fixedly installed at the air delivery ends of the blowers (9). Four horizontally arranged air outlet pipes (11) are rotatably installed inside the elliptical flight orbit (1). One ends of the four air outlet pipes (11) extend to the outside of the elliptical flight orbit (1) and are respectively rotatably connected to both ends of the two T-shaped three-way air pipes (10). Air outlet holes are formed on the sides of the two air outlet pipes (11) located at the same place and close to each other.

2. The aircraft stability testing device for an easily adjustable camera device according to claim 1, wherein, A plurality of uniformly distributed assembly holes are formed on the bottom inner wall of the elliptical flight orbit (1). Static assembly plates (12) are arranged at the bottoms of the static landscape boards (6). Dynamic assembly plates (15) are fixedly installed at the bottoms of the dynamic screens (7). The plurality of static assembly plates (12) and the plurality of dynamic assembly plates (15) are respectively located inside the plurality of assembly holes. Placement grooves are formed at the tops of the static assembly plates (12). The static landscape boards (6) are located inside the placement grooves. A limit pressing frame (13) is arranged above the static assembly plates (12). Limit sliding rods (14) are fixedly installed at the four corners of the bottom of the limit pressing frame (13). Pressing frame sliding holes (1201) are formed at the four corners of the top of the static assembly plates (12). The bottom ends of the limit sliding rods (14) located at the same place penetrate through the pressing frame sliding holes (1201). A plurality of assembly sockets (16) are fixedly installed at the bottom of the elliptical flight orbit (1). The plurality of assembly sockets (16) are symmetrically distributed on both sides of the plurality of assembly holes. Spring sliding boxes (17) are fixedly installed on both sides of the bottoms of the static assembly plates (12) and the dynamic assembly plates (15). Assembly bolts (18) adapted to the assembly sockets (16) are slidably installed inside the spring sliding boxes (17). Limit shifting rods (19) are fixedly installed at the bottoms of the assembly bolts (18). Limit sliding holes (1701) are formed at the bottoms of the spring sliding boxes (17). The limit shifting rods (19) located at the same place penetrate through the limit sliding holes (1701) and extend to the outside of the spring sliding boxes (17).

3. The flight vehicle stability test equipment for an easily adjustable camera device according to claim 2, characterized in that, A plurality of power receptacles (21) are fixedly installed at the bottom of the elliptical flight orbit (1), and the plurality of power receptacles (21) are respectively located on one side of the plurality of assembly holes. Electric plugs (22) connected to the dynamic screen (7) are fixedly installed at the bottom of the dynamic assembly plate (15), and the electric plugs (22) are adapted to the power receptacles (21).

4. The flight vehicle stability test equipment for an easily adjustable camera device according to claim 2, characterized in that, Oblique guide chamfers (20) are formed at the bottoms of the outer ends of the assembly pins (18) located outside the spring slide box (17), and rubber frames (23) are fixedly sleeved at the bottoms of the static assembly plate (12) and the dynamic assembly plate (15).

5. The aircraft stability testing device for an easily adjustable camera device according to claim 2, characterized in that Two second brackets (24) distributed from top to bottom are fixedly installed on the central side wall of the elliptical flight orbit (1). An air preheater (25) is fixedly installed on the lower second bracket (24). Air inlet pipes (27) are fixedly installed at the air inlet ends of the limit slide rods (14), and the air preheater (25) is communicated with the lower air inlet pipe (27).

6. An aircraft stability test device for an easily adjustable camera device according to claim 5, characterized in that, An air cooler (26) is fixedly installed on the upper second bracket (24), and the air cooler (26) is communicated with the upper air inlet pipe (27).

7. An aircraft stability testing device for an easily adjustable camera device according to claim 1, characterized in that, Two gear boxes (28) are fixedly installed on both sides of the elliptical flight orbit (1). The four gear boxes (28) are respectively drivingly connected to one ends of the four air outlet pipes (11). A steering motor (29) is fixedly installed on one side of each gear box (28). The output shafts of the four steering motors (29) respectively extend into the interiors of the four gear boxes (28) and are drivingly connected to the four gear boxes (28).

8. The flight vehicle stability test device carried by an easily adjustable camera device according to claim 1, characterized in that, A protective transparent plate (30) is fixedly installed inside the elliptical flight orbit (1). The protective transparent plate (30) is located above the plurality of static landscape plates (6) and the plurality of dynamic screens (7). Two ventilation holes (3001) corresponding to the positions of the air outlet pipes (11) are formed at the top of the protective transparent plate (30).

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