CN116812166A - Unmanned aerial vehicle environment test comprehensive experiment cabin - Google Patents

Abstract

The invention provides an unmanned aerial vehicle environment test comprehensive experiment cabin, which comprises an experiment cabin body and an environment auxiliary system connected with the experiment cabin body; the environment auxiliary system comprises an air pressure simulation system, a temperature simulation system, a humidity simulation system, a sand simulation system, a high-concentration gas simulation system, a wind speed simulation system and a rainfall simulation system. The comprehensive experimental cabin for the unmanned aerial vehicle environment test can solve the problem that the conventional unmanned aerial vehicle test technology cannot realize rapid multiple environment tests on the unmanned aerial vehicle.

Description

UAV environmental testing comprehensive experimental cabin

Technical field

The present invention relates to the technical field of UAV design, and more specifically, to a comprehensive experimental cabin for UAV environmental testing.

Background technique

With the rapid development of science and technology, in recent years, the application of drones in various industries has become increasingly widespread. At this stage, the application of drones has involved aerial photography, agriculture and forestry plant protection, geological exploration, power inspection, oil and gas inspection, etc. Applications in gas pipeline inspection, highway accident management, forest fire inspection, polluted environment survey, emergency rescue and rescue, rescue and disaster relief, coastline inspection and other fields.

Our country has a land area of 9.6 million square kilometers, a vast territory, and a complex climate and geographical environment. Air temperature, humidity, dust and plateau low-pressure environment all pose severe challenges to the performance of drones. During the design, testing, and debugging stages of the UAV, it is difficult to quickly conduct tests in multiple environments. The aircraft parameters can only be debugged according to the local environment first. When the UAV reaches the destination, it still needs to be debugged according to the actual local conditions. , sometimes a lot of modifications to the aircraft are required to complete the test, which is very inconvenient.

Based on the above technical problems, there is an urgent need for a device that can quickly conduct multiple environmental tests on drones without sending them to different environmental sites.

Contents of the invention

In view of the above problems, the purpose of the present invention is to provide a comprehensive experimental cabin for UAV environmental testing to solve the problem that existing UAV testing technology cannot quickly conduct multiple environmental tests on UAVs.

The comprehensive experimental cabin for UAV environmental testing provided by the present invention includes an experimental cabin body and an environmental auxiliary system connected to the experimental cabin body; wherein,

The environmental auxiliary system includes an air pressure simulation system, a temperature simulation system, a humidity simulation system, a sand and dust simulation system, a high concentration gas simulation system, a wind speed simulation system, and a rainfall simulation system; wherein,

The air pressure simulation system is used to control the air pressure inside the experimental cabin body, the temperature simulation system is used to control the internal temperature of the experimental cabin body, and the humidity simulation system is used to control the internal air pressure of the experimental cabin body. The humidity inside the experimental cabin body is controlled, the sand and dust simulation system is used to control the dust density inside the experimental cabin body, and the high-concentration gas simulation system is used to ventilate the inside of the experimental cabin body. The wind speed simulation system is used to add a preset wind speed to the inside of the experimental cabin body, and the rainfall simulation system is used to add rainfall to the inside of the experimental cabin body.

In addition, a preferred solution is that the air pressure simulation system includes an air pump, an air duct connected to the air pump, a vacuum pump, a vacuum air duct connected to the vacuum pump, a first solenoid valve, and an air duct connected to the experimental cabin body. internally connected air pressure ducts; among them,

The two input ends of the first solenoid valve are connected to the charging air duct and the vacuum air duct respectively, and the output end of the first solenoid valve is connected to the air pressure air duct.

In addition, a preferred solution is that the temperature simulation system includes a refrigeration compressor, an evaporator connected to the refrigeration compressor through a refrigerant pipeline, a refrigeration air duct connected to the interior of the experimental cabin body, and an evaporator provided in the experimental chamber. The heating tube inside the cabin body; among them,

A refrigeration box is connected to the side of the refrigeration air duct away from the experimental cabin body. The evaporator is arranged in the refrigeration box. A first axial flow fan is also provided on the refrigeration air duct. The refrigerant pipeline is equipped with a condenser and an expansion valve.

In addition, a preferred solution is that a drainage pipe is connected to the bottom of the refrigeration box, a water tank is connected to an end of the drainage pipe away from the refrigeration box, and a timing drain valve is provided at the upper end of the drainage pipe.

In addition, a preferred solution is that the humidity simulation system includes an industrial humidifier arranged inside the experimental cabin body;

The wind speed simulation system includes an industrial fan installed inside the experimental cabin body;

The rainfall simulation system includes a sprinkler head arranged inside the experimental cabin body.

In addition, a preferred solution is that the sand and dust simulation system includes a sand and dust generator, a vibration generator connected to the sand and dust generator, and a sand and dust system air duct connected to the interior of the experimental cabin body. The sand output port of the sand generator is connected with the air duct of the sand and dust system, and a second axial flow fan is provided on the air duct of the sand and dust system.

In addition, a preferred solution is that the high-concentration gas simulation system includes a gas cylinder to be tested and a gas pipeline to be tested that is connected to the interior of the experimental cabin body, and the gas pipeline to be tested is away from one end of the experimental cabin body. Connected to the gas cylinder to be measured, a second solenoid valve is provided on the gas pipeline to be measured.

In addition, a preferred solution is that an in-cabin controller is provided inside the experimental cabin body, and the in-cabin controller is connected to an air pressure sensor, a temperature sensor, a humidity sensor, a dust sensor, a gas concentration sensor and an electronic wind speed sensor. detection device.

In addition, a preferred solution is that an outboard controller is provided outside the experimental cabin body, and the air pump, the vacuum pump, the first solenoid valve, the refrigeration compressor, the first axial flow The fan, the industrial humidifier, the industrial fan, the sprinkler head and the second axial flow fan are all electrically connected to the outboard controller; and,

The outside controller is electrically connected to the inside controller.

In addition, a preferred solution is that a lighting lamp and a camera are provided inside the experimental cabin body, and a hatch and an observation window are provided on the experimental cabin body.

Compared with the existing technology, the above-mentioned comprehensive experimental cabin for UAV environmental testing according to the present invention has the following beneficial effects:

The comprehensive experimental cabin for UAV environmental testing provided by the invention is equipped with an air pressure simulation system, a temperature simulation system, a humidity simulation system, a sand and dust simulation system, a high concentration gas simulation system, a wind speed simulation system and a rainfall simulation system on the experimental cabin body. ; It can change the air pressure, temperature, humidity, wind speed, dust concentration, gas concentration (nitrogen, oxygen, etc.), rainfall and other environmental factors in the experimental cabin body according to the needs, so as to achieve the purpose of simulating the geographical environment of the destination. No need By taking the drone to multiple destinations for actual testing, the multi-environment test of the drone can be realized, which can significantly improve the efficiency of the multi-environment test of the drone.

To achieve the above and related objects, one or more aspects of the invention include the features hereinafter described in detail and particularly pointed out in the claims. The following description and accompanying drawings detail certain exemplary aspects of the invention. These aspects are indicative, however, of but a few of the various ways in which the principles of the invention may be employed. Furthermore, the invention is intended to include all such aspects and their equivalents.

Description of the drawings

By referring to the following description and claims in conjunction with the accompanying drawings, and with a more comprehensive understanding of the present invention, other objects and results of the present invention will be clearer and easier to understand. In the attached picture:

Figure 1 is a schematic structural diagram of a comprehensive experimental cabin for UAV environmental testing provided by an embodiment of the present invention;

Reference signs: 1.1 air pump; 1.2 vacuum pump; 1.3 first solenoid valve; 1.4 air duct; 1.5 vacuum air duct; 1.6 air pressure air duct; 2.1 gas cylinder to be measured; 2.2 second solenoid valve; 2.3 gas pipeline to be measured ;3.1 Dust generator; 3.2 Second axial flow fan; 3.3 Vibration generator; 3.4 Dust output port; 3.5 Dust system air duct; 4.1 First axial flow fan; 4.2 Refrigeration compressor; 4.3 Condenser; 4.4 Evaporation 4.5 refrigerant pipeline; 4.6 expansion valve; 4.7 timing drain valve; 4.8 drainage pipe; 4.9 water tank; 4.10 refrigeration air duct; 5 industrial fan; 6 camera; 7 heating pipe; 8 industrial humidifier; 9 lighting; 10 cabin Internal controller; 11 sprinkler heads; 12 hatches; 13 observation windows; 14 external controllers.

The same reference numbers throughout the drawings indicate similar or corresponding features or functions.

Detailed ways

In the following description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of one or more embodiments. It will be apparent, however, that these embodiments may be practiced without these specific details. In other instances, well-known structures and devices are shown in block diagram form in order to facilitate describing one or more embodiments.

Figure 1 shows a schematic structural diagram of a comprehensive experimental cabin for UAV environmental testing provided by an embodiment of the present invention.

As shown in Figure 1, the comprehensive experimental cabin for UAV environmental testing provided by the present invention includes a comprehensive experimental cabin for UAV environmental testing, including an experimental cabin body for carrying and accommodating the UAV to be tested, and an experimental cabin body connected to the experimental cabin body. Environmental auxiliary system. The environmental auxiliary system is used to adjust the environmental parameters inside the experimental cabin body according to needs to simulate environmental scenarios at different destinations.

Specifically, the environmental auxiliary system mainly includes an air pressure simulation system, a temperature simulation system, a humidity simulation system, a sand and dust simulation system, a high concentration gas simulation system, a wind speed simulation system, and a rainfall simulation system; wherein, the air pressure simulation system is used for The internal air pressure of the experimental cabin body is controlled to simulate the air pressure of the destination; the temperature simulation system is used to control the internal temperature of the experimental cabin body to simulate the temperature of the destination; the humidity The simulation system is used to control the humidity inside the experimental cabin body to simulate the humidity of the destination; the sand and dust simulation system is used to control the dust density inside the experimental cabin body. The high concentration The gas simulation system is used to introduce different high-concentration gases required into the interior of the experimental cabin body to simulate the concentrations of different gases at the destination (such as nitrogen, oxygen, etc.); the wind speed simulation system is used to provide A preset wind speed is added to the interior of the experimental cabin body to simulate the wind speed at the destination; the rainfall simulation system is used to add rainfall to the interior of the experimental cabin body to simulate the rainfall at the destination.

The comprehensive experimental cabin for UAV environmental testing provided by the invention is equipped with an air pressure simulation system, a temperature simulation system, a humidity simulation system, a sand and dust simulation system, a high concentration gas simulation system, a wind speed simulation system and a rainfall simulation system on the experimental cabin body. ; It can change the air pressure, temperature, humidity, wind speed, dust concentration, gas concentration, rainfall and other environmental factors in the experimental cabin body according to the needs, so as to achieve the purpose of simulating the geographical environment of the destination. There is no need to bring the drone to it in turn. Conducting actual measurements at multiple destinations can realize multi-environment testing of UAVs, which can significantly improve the efficiency of multi-environment testing of UAVs.

In order to realize the simulation of destination air pressure by the air pressure simulation system, the air pressure simulation system can be divided into a high air pressure simulation system and a low air pressure simulation system. The high air pressure simulation system can include an air pump 1.1 and an air duct 1.4 connected to the air pump 1.1. , the first solenoid valve 1.3 and the air pressure air duct 1.6 connected with the interior of the experimental cabin body. The charging air duct 1.4 is connected to the air pressure air duct 1.6 through the first solenoid valve 1.3.

During the pressurization process in the cabin, the air outside the cabin enters the inflation pump 1.1 through the air filter element of the inflation pump 1.1. After the air is pressurized, it passes through the inflation air duct 1.4, and then the preset external cabin controller 14 opens the first solenoid valve. 1.3, allowing high-pressure air to enter the cabin through the first solenoid valve 1.3 and the air pressure duct 1.6. Thereby, the pressure in the cabin is increased; and then the cabin pressure is detected through the pressure sensor connected to the preset cabin controller 10. When the cabin pressure reaches the target pressure, the external controller 14 controls the air pump 1.1 and the solenoid valve. closure.

The low pressure simulation system may include a vacuum pump 1.2 and a vacuum air duct 1.5 connected to the vacuum pump 1.2. The vacuum air duct 1.5 is also connected to the air pressure air duct 1.6 through a first solenoid valve 1.3. The first solenoid valve 1.3 is a two-in and one-out electromagnetic valve, the two input ends of the first solenoid valve 1.3 are connected to the inflation air duct 1.4 and the vacuum air duct 1.5 respectively, and the output end of the first solenoid valve 1.3 is connected to the air pressure air duct 1.6.

During the depressurization process in the cabin, the air in the cabin enters the vacuum air duct 1.5 through the air pressure duct 1.6 and the first solenoid valve 1.3, and enters the vacuum pump 1.2 through the air filter element of the vacuum pump 1.2, and the gas is discharged out of the cabin; then it passes through the cabin controller The pressure sensor connected to 10 detects the pressure in the cabin. When the pressure in the cabin reaches the target pressure, the first solenoid valve 1.3 and the vacuum pump 1.2 are closed under the control of the external controller 14.

In order to realize the simulation of the destination temperature by the temperature simulation system, the temperature simulation system can be divided into a high-temperature simulation system and a low-temperature simulation system. The high-temperature simulation system includes a heating pipe 7 set inside the experimental cabin body (usually set in the bulkhead). surface, it can be replaced by a wall-mounted heating device). During the heating process in the cabin, open the heating pipe 7 in the cabin, and at the same time open the industrial fan 5 in the cabin (belonging to the wind speed simulation system) to circulate the air in the cabin and prevent local temperature Too high; detect the temperature inside the cabin through the temperature sensor connected to the cabin controller 10 (multiple can be installed on the bulkhead to improve the temperature detection accuracy). When the temperature inside the cabin reaches the target temperature, the outside controller 14 Control the heating pipe 7 and the industrial fan 5 to close.

The low-temperature simulation system includes a refrigeration compressor 4.2, an evaporator 4.4 connected to the refrigeration compressor 4.2 through a refrigerant pipe 4.5, and a refrigeration air duct 4.10 connected to the interior of the experimental cabin body; among which, the refrigeration air duct 4.10 is far away from the experimental cabin body A refrigeration box (not marked in the figure) is connected to one side of regulator 4.3 and expansion valve 4.6. In addition, in order to collect water at the bottom of the refrigeration box, a drainage pipe 4.8 is connected to the bottom of the refrigeration box, a water tank 4.9 is connected to the end of the drainage pipe 4.8 away from the refrigeration box, and a timing drain valve 4.7 is provided at the upper end of the drainage pipe 4.8.

It should be noted that the low-temperature simulation system not only has the effect of cooling the cabin, but also has the effect of drying the cabin. During the specific cooling and drying process, the refrigerant is compressed by the refrigeration compressor 4.2 and passes through the refrigerant pipe 4.5 It enters the condenser 4.3, and then enters the evaporator 4.4 through the expansion valve 4.6. After absorbing the internal energy, it flows back to the refrigeration compressor 4.2 through the refrigerant pipe 4.5. The air in the cabin enters the refrigeration air duct 4.10, and after passing through the first axial flow fan 4.1, it contacts the evaporator 4.4 of the refrigeration system, transferring the internal energy of the air to the evaporator 4.4. At the same time, due to the cooling of the air, the water vapor in the air condenses and precipitates. On the surface of the evaporator 4.4, the collected condensed water flows into the drainage pipe 4.8 through the timing drain valve 4.7 and enters the water tank 4.9 located outside the cabin (this part belongs to the cabin air drying process, which is equivalent to a drying system, and is related to the subsequent humidity Used in conjunction with the simulation system to achieve control of the actual humidity in the cabin). The cooled and dried air returns to the cabin through the cooling air duct 4.10. The cabin temperature is detected through a temperature sensor connected to the cabin controller 10. When the cabin temperature reaches the target temperature, the external controller 14 controls the refrigeration compressor 4.2 and the first axial flow fan 4.1 to be turned off.

In order to realize the simulation of destination humidity by the temperature simulation system, the humidity simulation system can include an industrial humidifier 8 installed inside the experimental cabin body. During the actual humidification process, the industrial humidifier 8 is turned on to increase the humidity in the cabin; through the cabin The humidity sensor connected to the controller 10 detects the humidity in the cabin. When the humidity in the cabin reaches the target humidity, the outside controller 14 controls the industrial humidifier 8 to be turned off.

In order to realize the wind speed simulation system to simulate the destination wind speed, the wind speed simulation system can include an industrial fan 5 installed inside the experimental cabin body; in the actual process, the industrial fan 5 is turned on, and the electronic wind speed connected to the cabin controller 10 is used. The detection device detects the wind speed in the cabin, and then the external controller 14 controls the industrial fan 5 and adjusts the rotation speed of the industrial fan 5 to achieve the purpose of achieving the specified wind speed.

In order to realize the simulation of rainfall at the destination by the rainfall simulation system, the rainfall simulation system can include a sprinkler head 11 installed inside the experimental cabin body; in the actual process, the sprinkler head 11 is turned on and the sprinkler is controlled by the external controller 14. Shower head 11, adjust the opening size of the sprinkler head 11 to achieve the purpose of achieving precipitation.

In order to realize the sand and dust simulation system to simulate the density of sand and dust at the destination, the sand and dust simulation system may include a sand and dust generator 3.1, a vibration generator 3.3 connected to the sand and dust generator 3.1, and a sand and dust connected to the interior of the experimental cabin body. The system air duct 3.5, the sand output port 3.4 of the sand and dust generator 3.1 are connected with the sand and dust system air duct 3.5, and a second axial flow fan 3.2 is provided on the sand and dust system air duct 3.5.

In the actual sand and dust simulation process, first put the specified fineness of sand into the sand and dust generator 3.1, then turn on the vibration generator 3.3, turn on the second axial flow fan 3.2, so that the dust in the sand and dust system air duct 3.5 The air circulates, and then the dust output port 3.4 is opened to allow the dust to enter the cabin through the dust system air duct 3.5, and finally the dust density (i.e., sand density) in the cabin is detected through the dust sensor connected to the cabin controller 10 , when the dust density in the cabin reaches the target dust density, the external controller 14 controls the dust output port 3.4 at the lower end of the dust generator 3.1 and the axial flow fan to be closed.

In order to realize the high-concentration gas simulation system to simulate the high-concentration gas concentration at the destination, the high-concentration gas simulation system may include a gas cylinder 2.1 to be measured and a gas pipeline 2.3 to be measured that is connected to the interior of the experimental cabin body. The gas pipeline to be measured 2.3 The end far away from the experimental cabin body is connected to the gas cylinder 2.1 to be tested, and a second solenoid valve 2.2 is provided on the gas pipeline 2.3 to be tested.

During the actual concentration gas simulation process, connect the gas cylinder 2.1 to be measured to the gas pipe 2.3 to be measured, and then open the second solenoid valve 2.2 to allow the gas to be measured to enter the cabin through the gas pipe 2.3 to be measured, and finally pass through The corresponding gas sensor connected to the cabin controller 10 detects the corresponding gas concentration in the cabin. When the gas concentration in the cabin reaches the target concentration, the solenoid valve is closed under the control of the external controller 14.

It should be noted that during the high-concentration gas simulation process, the concentration simulation of different gases in the cabin can be realized by replacing the gas cylinder 2.1 to be measured (such as oxygen cylinder, nitrogen cylinder, etc.).

For the detection of various parameters inside the experimental cabin body, an in-cabin controller 10 can be installed inside the experimental cabin body. The in-cabin controller 10 is connected to an air pressure sensor, a temperature sensor, a humidity sensor, a dust sensor, a gas concentration sensor, Detection devices such as electronic wind speed detection devices are used to accurately detect various parameters inside the experimental cabin body.

For controlling the working status of different devices in each simulation system, an extravehicular controller 14 can be set outside the experimental cabin body. The above-mentioned air pump 1.1, vacuum pump 1.2, first solenoid valve 1.3, refrigeration compressor 4.2, Controllable devices such as the first axial flow fan 4.1, industrial humidifier 8, industrial fan 5, sprinkler head 11 and second axial flow fan 3.2 all need to be electrically connected to the extravehicular controller 14, and controlled by the extravehicular controller 14 control; and, the extravehicular controller 14 is electrically connected to the in-vehicle controller 10, thereby realizing operation control of the entire UAV environmental test comprehensive experimental cabin.

It should be noted that for the experimental cabin body, the interior of the cabin needs to be an integral closed structure. The bulkhead can be made of rigid and corrosion-resistant materials, and can be welded from large-diameter circular tubes with smooth inner walls or plates of other shapes. The bulkhead can be a double-layer or multi-layer composite structure, and the interlayer can be filled with insulation materials for sealing and heat insulation. The top of the cabin can be set in a dome or other shape to enhance the pressure resistance of the entire cabin. An observation window 13 made of high-strength transparent plastic PC or other materials can be provided on the bulkhead to observe the situation in the cabin and transmit wireless signals in an emergency. A hatch 12 is provided on the body of the experimental cabin. The hatch 12 should be made of the same material as the cabin or a material of the same grade. It should be surrounded by sealing strips and locking structures. It should be able to be equipped with handles on both sides inside and outside the cabin. , the hatch door 12 should be able to be opened in an emergency, and at the same time, when the hatch door 12 is closed, the overall airtight environment in the cabin must be ensured. A lighting lamp 9 and a camera 6 are provided inside the experimental cabin body, and the conditions inside the cabin can be monitored through the control end of the camera 6 outside the cabin.

The following is a detailed description of the use of the UAV environmental testing comprehensive experimental cabin provided by the present invention to simulate the plateau climate to test the UAV. The plateau climate is a low pressure simulation system, a low temperature simulation system and a drying system, and a sand and dust simulation. The system and wind speed simulation system are running at the same time. The specific steps are as follows:

1. Turn on the lighting 9 and camera 6, turn on the outboard controller 14, and check whether the video transmission of camera 6 is normal.

2. Prepare the drone to be tested and place it in the center of the ground inside the cabin. When there are people working in the cabin, make sure the door 12 is open to prevent emergencies; personnel withdraw from the cabin, close and lock it. The cabin door 12 ensures a sealed environment in the cabin.

3. Turn on the low pressure simulation system, so that the air in the cabin enters the vacuum air duct 1.5 through the air pressure duct 1.6 and the first solenoid valve 1.3, and enters the vacuum pump 1.2 through the air filter element to discharge the gas out of the cabin; pass the air in the cabin controller 10 The pressure sensor detects the pressure in the cabin. When the pressure in the cabin reaches the target pressure, the first solenoid valve 1.3 and the vacuum pump 1.2 are closed under the control of the external controller 14.

4. Turn on the low temperature simulation system and drying system. The air in the cabin enters the refrigeration air duct 4.10. After passing through the axial flow fan, it contacts the evaporator 4.4 of the refrigeration system and transfers the internal energy of the air to the evaporator 4.4. At the same time, due to the cooling of the air, The water vapor in the air condenses and precipitates on the surface of the evaporator 4.4. The collected condensed water flows into the drainage pipe 4.8 through the timing drain valve 4.7 and enters the water tank 4.9 located outside the cabin; the cooled and dried air returns through the cooling air duct 4.10 Go to the cabin; detect the cabin temperature through the temperature sensor in the cabin controller 10. When the cabin temperature reaches the target temperature, the external controller 14 controls the refrigeration compressor 4.2 and the axial flow fan to be turned off.

5. Turn on the sand and dust simulation system. First, put the sand of specified fineness into the sand and dust generator 3.1, turn on the vibration generator 3.3, and turn on the axial flow fan to circulate the air in the air duct 3.5 of the sand and dust system. Open the sand and dust output port 3.4 to allow the sand and dust to enter the cabin through the sand and dust system air duct 3.5. The humidity in the cabin is detected through the dust sensor in the cabin controller 10. When the dust density in the cabin reaches the target dust density, the external controller 14 controls the dust output port 3.4 and the second axial flow fan 3.2 to close.

6. Turn on the wind speed simulation system, turn on the industrial fan 5, and detect the wind speed in the cabin through the electronic wind speed detection device in the cabin controller 10. The external controller 14 controls the industrial fan 5 and adjusts the speed of the industrial fan 5 to achieve the desired result. The purpose of specifying wind speed.

7. Start the specified test on the drone.

The comprehensive experimental cabin for UAV environmental testing according to the present invention is described above by way of example with reference to FIG. 1 . However, those skilled in the art should understand that various improvements can be made to the comprehensive experimental cabin for UAV environmental testing proposed by the present invention without departing from the content of the present invention. Therefore, the protection scope of the present invention should be determined by the content of the appended claims.

Claims (10)

1. An unmanned aerial vehicle environment test comprehensive experiment cabin; the environment-friendly experimental cabin is characterized by comprising an experimental cabin body and an environment auxiliary system connected with the experimental cabin body; wherein,,

the environment auxiliary system comprises an air pressure simulation system, a temperature simulation system, a humidity simulation system, a sand simulation system, a high-concentration gas simulation system, a wind speed simulation system and a rainfall simulation system; wherein,,

the air pressure simulation system is used for controlling the air pressure in the experiment cabin body, the temperature simulation system is used for controlling the temperature in the experiment cabin body, the humidity simulation system is used for controlling the humidity in the experiment cabin body, the sand dust simulation system is used for controlling the dust density in the experiment cabin body, the high-concentration gas simulation system is used for introducing high-concentration gas into the experiment cabin body, the air speed simulation system is used for adding a preset air speed into the experiment cabin body, and the rainfall simulation system is used for adding rainfall into the experiment cabin body.

2. The unmanned aerial vehicle environmental test comprehensive experiment module of claim 1, wherein,

the air pressure simulation system comprises an air pump, an air inflation channel connected with the air pump, a vacuum channel connected with the vacuum pump, a first electromagnetic valve and an air pressure channel communicated with the inside of the experiment cabin body; wherein,,

the two input ends of the first electromagnetic valve are respectively connected with the inflation air duct and the vacuum air duct, and the output end of the first electromagnetic valve is connected with the air pressure air duct.

3. The unmanned aerial vehicle environmental test composite laboratory of claim 2, wherein,

the temperature simulation system comprises a refrigeration compressor, an evaporator connected with the refrigeration compressor through a refrigerant pipeline, a refrigeration air duct communicated with the inside of the experiment cabin body and a heating pipe arranged in the experiment cabin body; wherein,,

one side of the refrigerating air duct, which is far away from the experiment cabin body, is connected with a refrigerating box, the evaporator is arranged in the refrigerating box, a first axial flow fan is further arranged on the refrigerating air duct, and a condenser and an expansion valve are arranged on the refrigerant pipeline.

4. The unmanned aerial vehicle environmental test comprehensive experiment module of claim 3, wherein,

the bottom of the refrigeration box is connected with a drain pipe, one end of the drain pipe away from the refrigeration box is connected with a water tank, and the upper end of the drain pipe is provided with a timing drain valve.

5. The unmanned aerial vehicle environmental test composite experimental cabin of claim 4, wherein,

the humidity simulation system comprises an industrial humidifier arranged inside the experiment cabin body;

the wind speed simulation system comprises an industrial fan arranged inside the experiment cabin body;

the rainfall simulation system comprises a spray header arranged in the experimental cabin body.

6. The unmanned aerial vehicle environmental test comprehensive experiment module of claim 5, wherein,

the sand and dust simulation system comprises a sand and dust generator, a vibration generator connected with the sand and dust generator and a sand and dust system air channel communicated with the inside of the experiment cabin body, a sand and dust output port of the sand and dust generator is communicated with the sand and dust system air channel, and a second axial fan is arranged on the sand and dust system air channel.

7. The unmanned aerial vehicle environmental test composite laboratory of claim 6, wherein,

the high-concentration gas simulation system comprises a gas cylinder to be tested and a gas pipeline to be tested which is communicated with the inside of the experiment cabin body, wherein one end, far away from the experiment cabin body, of the gas pipeline to be tested is connected with the gas cylinder to be tested, and a second electromagnetic valve is arranged on the gas pipeline to be tested.

8. The unmanned aerial vehicle environmental test composite laboratory of claim 7, wherein,

an intra-cabin controller is arranged in the experiment cabin body, and an air pressure sensor, a temperature sensor, a humidity sensor, a dust sensor, a gas concentration sensor and an electronic wind speed detection device are connected to the intra-cabin controller.

9. The unmanned aerial vehicle environmental test composite laboratory of claim 8, wherein,

an outdoor controller is arranged outside the experiment cabin body, and the inflator pump, the vacuum pump, the first electromagnetic valve, the refrigeration compressor, the first axial flow fan, the industrial humidifier, the industrial fan, the spray header and the second axial flow fan are electrically connected with the outdoor controller; and, in addition, the processing unit,

the outside cabin controller is electrically connected with the inside cabin controller.

10. The unmanned aerial vehicle environmental test composite laboratory of any of claims 1 to 9,

the experimental cabin is characterized in that an illuminating lamp and a camera are arranged in the experimental cabin body, and a cabin door and an observation window are arranged on the experimental cabin body.