Multifunctional unmanned aerial vehicle wind tunnel experiment module

Abstract

The utility model provides a multifunctional unmanned aerial vehicle wind tunnel experiment cabin, which comprises a test cabin, a wind power generator and a control box fixed on the test cabin, the wind power generator is fixed at the right end of the test cabin, and the test cabin comprises a wind guide section, an experiment section and an exhaust section which are sequentially and fixedly connected from right to left. An air guide channel, an experiment channel and an air exhaust channel which are communicated with one another are arranged in the air guide section, the experiment section and the air exhaust section respectively, the wind power generator comprises an installation frame and multiple sets of wind source modules, the installation frame is fixed to the right end of the air guide section, and the multiple sets of wind source modules are arranged in the installation frame in a matrix mode and are in signal connection with the control box; the wind source modules are internally provided with a plurality of groups of wind source fans which are arranged in a matrix, the wind source modules which can be independently controlled are arranged, and the control box can control the opening, closing, wind speed and the like of each wind source module, so that various wind types such as turbulent flow, shear flow, transformation airflow, gust and the like are simulated, and the test accuracy and reliability can be improved.

Description

Technical Field

[0001] The utility model relates to the field of UAV test equipment, and particularly relates to a multifunctional UAV wind tunnel test chamber. Background Art

[0002] In recent years, with the booming development of the UAV field, the performance requirements for UAVs have become increasingly strict. When a UAV is flying, it will face many influencing factors. Except for the hardware conditions of the UAV itself, environmental factors such as wind, rain, clouds, temperature, and magnetic field also have a great impact. Among them, the influence of wind is the most common and the greatest. The traditional wind tunnel test chamber mainly detects the anti-wind flight ability of the UAV by controlling the magnitude of the wind force, and cannot simulate complex wind patterns in reality, such as turbulent flow, shear flow, changing airflow, gusts, etc., resulting in inaccurate test results of the UAV. Therefore, it is necessary to make a multifunctional UAV wind tunnel test chamber to solve the above problems. Content of the Utility Model

[0003] The purpose of the utility model is to provide a multifunctional UAV wind tunnel test chamber to solve the problems mentioned in the background art.

[0004] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0005] A multifunctional UAV wind tunnel test chamber includes a test chamber, a wind generator, and a control box fixed on the test chamber. The wind generator is fixed at the right end of the test chamber. The test chamber includes a wind guiding section, an experimental section, and an exhaust section that are fixedly connected in sequence from right to left. A wind guiding channel, an experimental channel, and an exhaust channel that are interconnected are respectively arranged in the wind guiding section, the experimental section, and the exhaust section. The wind generator includes an installation frame and multiple groups of wind source modules. The installation frame is fixed at the right end of the wind guiding section. Multiple groups of wind source modules are fixed in the installation frame in a matrix arrangement and are respectively signal-connected to the control box. Multiple groups of wind source fans arranged in a matrix are provided in the wind source module.

[0006] A further description of the utility model: It further includes a spraying mechanism. The spraying mechanism includes a conveying water pipe, a high-pressure nozzle, and a water pump. Multiple groups of conveying water pipes are arranged and uniformly fixed on the top of the experimental section. Multiple groups of high-pressure nozzles are arranged and uniformly fixed below the conveying water pipe. One end of the conveying water pipe is communicated with the water pump, and the water pump is signal-connected to the control box.

[0007] A further description of the utility model: The test chamber is made of a transparent material.

[0008] A further description of the utility model: A cross-section control component is arranged in the wind guiding section.

[0009] A further description of the utility model: An operation door is arranged on the front side of the experimental section.

[0010] Further description of the present utility model: A floor mat is provided at the bottom inside the experimental section, and the floor mat is made of an elastic material.

[0011] Further description of the present utility model: A protective net is provided on the right side of the experimental section.

[0012] Further description of the present utility model: An exhaust fan is provided inside the exhaust section.

[0013] Further description of the present utility model: It further includes a tracer particle generator, which is fixed inside the experimental section and is signal-connected to the control box.

[0014] Further description of the present utility model: It further includes a temperature and humidity controller, which is fixed inside the experimental section and is signal-connected to the control box.

[0015] The beneficial effects of the present utility model are as follows: This design sets multiple independently controllable air source modules. The control box can control the opening and closing, wind speed, etc. of each air source module, so as to simulate various wind types, such as turbulent flow, shear flow, variable air flow, gust, etc., and can improve the accuracy and reliability of the test. The air flow passes through the air guiding channel, the experimental channel and the exhaust channel in sequence. The unmanned aerial vehicle (UAV) flies inside the experimental channel. By equipping the test UAV with external gyroscopes and other equipment, based on Wi-Fi and not relying on the UAV's data transmission protocol, the real-time flight state of the UAV is detected. The supporting UAV motion analysis system reads the flight control data of the UAV and transmits it back to the data analysis software at the same time. Description of the Drawings

[0016] Figure 1 is the overall structure diagram of the present utility model;

[0017] Figure 2 is the left view of the wind generator in the present utility model;

[0018] Figure 3 is the structure diagram of the air source module in the present utility model;

[0019] Explanation of the Reference Numerals in the Drawings:

[0020] 1. Test chamber; 11. Air guiding section; 111. Air guiding channel; 112. Cross-section control component; 12. Experimental section; 121. Experimental channel; 122. Operation door; 123. Floor mat; 124. Protective net; 13. Exhaust section; 131. Exhaust channel; 132. Exhaust fan; 2. Wind generator; 21. Installation frame; 22. Air source module; 221. Air source fan; 3. Control box; 4. Spraying mechanism; 41. Delivery water pipe; 42. High-pressure nozzle; 43. Water pump. Specific Embodiments

[0021] The present utility model is further described below with reference to the accompanying drawings:

[0022] As shown Figures 1 to 3 in the figure, a multi-functional UAV wind tunnel test chamber includes a test chamber 1, a wind generator 2, and a control box 3 fixed on the test chamber 1. The wind generator 2 is fixed at the right end of the test chamber 1. The test chamber 1 includes a wind guiding section 11, an experimental section 12, and an exhaust section 13 that are fixedly connected in sequence from right to left. A wind guiding channel 111, an experimental channel 121, and an exhaust channel 131 that are interconnected are respectively provided in the wind guiding section 11, the experimental section 12, and the exhaust section 13. The wind generator 2 includes a mounting frame 21 and multiple groups of wind source modules 22. The mounting frame 21 is fixed at the right end of the wind guiding section 11. Multiple groups of wind source modules 22 are fixedly arranged in the mounting frame 21 in a matrix and are respectively signal-connected to the control box 3. Multiple groups of wind source fans 221 arranged in a matrix are provided in the wind source modules 22.

[0023] When the wind force is greater than the maximum wind resistance limit of the UAV power system, the UAV will not be able to work properly, and even a crash accident may occur. Therefore, it is particularly important to test the wind resistance of the UAV. Natural wind is divided by factors such as wind volume and wind speed, forming wind patterns such as turbulence, shear flow, changing airflow, and gusts, all of which affect UAV flight to varying degrees. This design sets multiple groups of wind source modules 22 that can be individually controlled. The control box 3 can control the opening and closing, wind speed, etc. of each wind source module 22, so as to simulate various wind patterns, such as turbulence, shear flow, changing airflow, gusts, etc., and can improve the accuracy and reliability of the test. The air flow passes through the wind guiding channel 111, the experimental channel 121, and the exhaust channel 131 in sequence. The UAV flies in the experimental channel 121. By equipping the test UAV with external gyroscopes and other equipment, and based on wifi and not relying on the UAV's data transmission protocol, the real-time flight state of the UAV is detected, and the UAV motion analysis system is used to read the flight control data of the UAV and transmit it back to the data analysis software at the same time.

[0024] In this design, a spraying mechanism 4 is further included. The spraying mechanism 4 includes a water delivery pipe 41, a high-pressure nozzle 42, and a water pump 43. Multiple groups of water delivery pipes 41 are provided and uniformly fixed on the top of the experimental section 12. Multiple groups of high-pressure nozzles 42 are provided and uniformly fixed below the water delivery pipes 41. One end of the water delivery pipe 41 is communicated with the water pump 43, and the water pump 43 is signal-connected to the control box 3.

[0025] The simulation of rainfall function is completed through the high-pressure nozzle 42 and the water pump 43. The water pump 43 is connected to the control box 3. By controlling the water supply pressure of the water pump 43, weather conditions such as heavy rain, moderate rain, light rain, and cloud are simulated.

[0026] The test chamber 1 is made of a transparent material, such as an acrylic board. The test chamber 1 is designed to be transparent, which can facilitate the observation of the test state of the UAV.

[0027] A cross-section control component 112 is arranged inside the air guiding section 11, which can reduce the cross-sectional area of the air guiding channel 111 to provide a greater wind force output and simulate more real scenarios.

[0028] An operation door 122 is arranged on the front side of the experimental section 12, which is convenient for taking and placing the unmanned aerial vehicle and dealing with the accumulated water generated by weather simulation.

[0029] A floor mat 123 is arranged at the bottom inside the experimental section 12. The floor mat 123 is made of an elastic material, which is beneficial to the landing of the unmanned aerial vehicle after the test. By using different types of elastic materials, ground conditions such as grassland and soil can also be simulated.

[0030] A protective net 124 is arranged on the right side of the experimental section 12 to prevent the unmanned aerial vehicle from entering the air guiding section 11 and avoid the collision between the unmanned aerial vehicle and the wind generator 2.

[0031] An exhaust fan 132 is arranged inside the exhaust section 13. The exhaust fan 132 assists in exhausting the air flow, thereby increasing the air flow rate.

[0032] In this design, a tracer particle generator is also included. The tracer particle generator is fixed inside the experimental section 12 and is signal-connected to the control box 3. In the navigation and control system of the unmanned aerial vehicle, electronic devices such as magnetic compasses are very sensitive to magnetic fields and are easily interfered by external magnetic fields. And a changing current generates a magnetic field. Therefore, when the unmanned aerial vehicle approaches a high-voltage wire, it is easily interfered by a strong magnetic field, resulting in the loss of control of the unmanned aerial vehicle and crashing. The tracer particle generator can simulate the electromagnetic interference in the flight environment of the unmanned aerial vehicle, so as to test the motion state of the unmanned aerial vehicle under different degrees of electromagnetic interference.

[0033] In this design, a temperature and humidity controller is also included. The temperature and humidity controller is fixed inside the experimental section 12 and is signal-connected to the control box 3.

[0034] Too low temperature will cause the battery's discharge capacity to become weak, thus shortening the flight time of the unmanned aerial vehicle. Similarly, too high temperature is also not conducive to the flight of the unmanned aerial vehicle. The temperature and humidity controller cooperates with control electrical appliances such as air conditioners and humidifiers to simulate and detect the temperature and humidity of the environment in real time, and feedback the motion state of the unmanned aerial vehicle and the battery endurance time under different temperature and humidity states by collecting data.

[0035] The above does not impose any limitation on the technical scope of the present utility model. Any modification, equivalent change and modification made to the above embodiments based on the technical essence of the present utility model still fall within the scope of the technical solution of the present utility model.

Claims

1. A multifunctional UAV wind tunnel test cabin, characterized by: It includes a test cabin, a wind generator and a control box fixed on the test cabin, the wind generator is fixed at the right end of the test cabin, the test cabin includes an air guide section, an experimental section and an exhaust section fixedly connected from right to left in sequence, the air guide section, the experimental section and the exhaust section are respectively provided with an air guide channel, an experimental channel and an exhaust channel interconnected with each other, the wind generator includes a mounting frame and a plurality of wind source modules, the mounting frame is fixed at the right end of the air guide section, a plurality of wind source modules are fixed in the mounting frame in a matrix arrangement and are respectively connected to the control box signal, and a plurality of wind source fans arranged in a matrix are provided in the wind source module.

2. The multifunctional UAV wind tunnel test chamber according to claim 1, characterized in that: It also includes a spray mechanism, which includes a water delivery pipe, a high-pressure nozzle and a water pump. The water delivery pipes are arranged in multiple groups and are evenly fixed on the top of the experimental section. The high-pressure nozzles are arranged in multiple groups and are evenly fixed under the water delivery pipes. One end of the water delivery pipe is connected to the water pump, and the water pump is connected to the control box signal.

3. The multifunctional UAV wind tunnel test chamber according to claim 1 is characterized in that: The test chamber is made of transparent material.

4. The multifunctional UAV wind tunnel test chamber according to claim 1, characterized in that: A cross-section control component is arranged in the air guide section.

5. The multifunctional UAV wind tunnel test chamber according to claim 1, characterized in that: An operating door is arranged at the front side of the experimental section.

6. The multifunctional UAV wind tunnel test chamber according to claim 1 is characterized by: A floor mat is arranged at the bottom of the experimental section, and the floor mat is made of elastic material.

7. The multifunctional UAV wind tunnel test chamber according to claim 1 is characterized by: A protective net is provided on the right side of the experimental section.

8. The multifunctional UAV wind tunnel test chamber according to claim 1 is characterized by: An exhaust fan is arranged in the exhaust section.

9. The multifunctional UAV wind tunnel test chamber according to claim 1, characterized in that: It also includes a tracer particle generator, which is fixed in the experimental section and connected to the control box signal.

10. The multifunctional UAV wind tunnel test chamber according to claim 1, characterized in that: It also includes a temperature and humidity controller, which is fixed in the experimental section and is connected to the control box signal.

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