Unmanned aerial vehicle intelligent fault detection system and method for inspection

Abstract

The invention relates to an unmanned aerial vehicle intelligent fault detection system and method for routing inspection, and the system comprises an unmanned aerial vehicle fault monitoring server, a communication network, ground fault detection terminals and random fault detection terminals, and each ground fault detection terminal and at least one random fault detection terminal form a detection work group. The random fault detection terminals are in data connection with the ground fault detection terminals in the same detection working group through the communication network, and the ground fault detection terminals are in data connection with the unmanned aerial vehicle fault monitoring server through the communication network. The detection method comprises three steps of system configuration, dynamic detection and ground detection. On one hand, the requirements of fault detection and troubleshooting operation of unmanned aerial vehicles of various different structure types can be effectively met; and on the other hand, the cooperation of synchronous detection and ground static detection in the operation process of the unmanned aerial vehicle is effectively realized, so that the flexibility and convenience of unmanned aerial vehicle detection operation are greatly improved.

Description

Technical Field

[0001] The invention relates to an unmanned aerial vehicle intelligent fault detection system and method for inspection, belonging to the technical field of unmanned aerial vehicle detection. Background Art

[0002] In order to ensure the stable operation of UAV equipment, it is necessary to regularly detect faults in the operation of UAVs and synchronize the operation of UAV equipment. In actual operation, the current method is mainly to install fault detection circuits in the flight control system of UAVs, or to set up independent external detection equipment for UAVs, although it can meet the needs of UAV fault detection operations to a certain extent. However, in operation, the current fault monitoring system often monitors faults through electronic circuit systems, but the detection range is relatively one-sided, especially there are different degrees of large differences between the detection data of UAV flight control circuits and the actual flight status of UAVs. At the same time, it is often impossible to intuitively observe and detect the actual operating performance and status of UAV mechanical equipment, which leads to a certain lag and one-sidedness between the current UAV fault detection data and the operating status of UAV equipment.

[0003] To address this problem, there is an urgent need to develop an intelligent fault detection system and method for drone inspections to meet the needs of actual work. Summary of the invention

[0004] In order to address the deficiencies in the prior art, the present invention provides an intelligent fault detection system and method for unmanned aerial vehicle inspections. The system of the invention has a high degree of integration, modularization and automation. On the one hand, it can effectively meet the needs of fault detection and troubleshooting operations for unmanned aerial vehicles of various structural types, greatly improving the work efficiency and flexibility of fault detection operations; on the other hand, it enriches the detection means, and effectively realizes the coordination of synchronous detection during the operation of the unmanned aerial vehicle with ground static detection, thereby greatly improving the flexibility, comprehensiveness and timeliness of the unmanned aerial vehicle detection operations, and effectively overcoming unmanned aerial vehicle operation accidents caused by the operation of unmanned aerial vehicles with faults.

[0005] In order to achieve the above object, the present invention is implemented through the following technical solutions: An intelligent fault detection system for unmanned aerial vehicles used for inspections comprises an unmanned aerial vehicle fault monitoring server, a communication network, a ground fault detection terminal and a random fault detection terminal, wherein there is at least one ground fault detection terminal, and each ground fault detection terminal forms a detection working group with at least one random fault detection terminal, and each random fault detection terminal in the same detection work is connected to the fuselage of the same unmanned aerial vehicle to be detected, and the random fault detection terminal establishes a data connection with the ground fault detection terminal in the same detection working group through the communication network, and the ground fault detection terminal establishes a data connection with the unmanned aerial vehicle fault monitoring server through the communication network.

[0006] Furthermore, the random fault detection terminal includes a carrier box, a three-axis gyroscope, a gimbal stabilizer, a force-sensitive sensor, a carrier paddle, a surveillance camera and a non-contact speed sensor, a counterweight, a multi-channel voltage-stabilized power supply, a data processing circuit, a communication circuit and wiring terminals. The carrier box is a closed cavity structure with an ellipsoidal cross-section. The carrier box is connected to the outer side of the fuselage of the unmanned aerial vehicle to be detected through the gimbal stabilizer. At the same time, the three-axis gyroscope, the multi-channel voltage-stabilized power supply, the data processing circuit and the communication circuit are all located in the carrier box. There are a number of wiring terminals, which are embedded in the outer side of the carrier box, and the wiring terminals are respectively electrically connected to the multi-channel voltage-stabilized power supply and the communication circuit. At the same time, the data processing circuit is respectively connected to the three-axis gyroscope, the gimbal stabilizer, and the force-sensitive sensor. , a monitoring camera and a non-contact speed sensor, a multi-channel regulated power supply and a communication circuit are electrically connected, the carrying paddle is a trapezoidal plate structure, the rear end face of the carrying paddle is located in the carrying box and is connected to at least one force-sensitive sensor, the front half of the carrying paddle is located outside the carrying box, a monitoring camera and a non-contact speed sensor is provided on the front end face of the carrying paddle, and the monitoring camera and the non-contact speed sensor are distributed along the axis direction of the carrying paddle, the detection axis of the monitoring camera and the non-contact speed sensor is vertically distributed and intersects with the axis of the carrying paddle, there are four carrying paddles in total, each carrying paddle is evenly distributed around the center of the carrying box, and each carrying paddle and the axis of the carrying box are distributed in the same plane, and at least one counterweight block is further provided on the lower end face of the carrying paddle.

[0007] Furthermore, the width of the rear end face of the load-bearing paddle is 30%-70% of the width of the front end face, and its cross-section is any one of a shuttle shape, an elliptical shape and a teardrop shape. The load-bearing paddle is provided with a guide groove distributed parallel to its axis, and the load-bearing paddle is connected to the counterweight block through the guide groove. There is at least one counterweight block, and each counterweight block is evenly distributed along the axis direction of the load-bearing paddle.

[0008] Furthermore, the ground fault detection terminal includes a driving rail, a drainage cover, a jet fan, an air outlet, a winch, a sling, a water tank and a spray pump, an atomizing nozzle, a control console and a control circuit. There are two driving rails, and the two driving rails are parallel to each other and are parallel to the horizontal plane. The drainage cover is a hyperbolic hollow tubular structure, and its axis is parallel to the horizontal plane. A winch is provided at the top of the center of the drainage cover, and the winch is connected to at least one sling. The air outlet and the atomizing nozzle are all embedded in the drainage cover and connected to the front and rear halves of the drainage cover. The inner side is connected, the air outlet and the atomizing nozzle are evenly distributed around the axis of the drainage hood, and each air outlet is connected to a jet fan and coaxially distributed, and the jet fan is connected to the outer side of the drainage hood, the atomizing nozzle is connected to the spray pump through a guide pipe, there are at least two spray pumps, and they are symmetrically distributed in the front and rear halves of the drainage hood and connected to the outer side of the drainage hood, the spray pumps are connected to the water tank through the guide pipe, the water tank and the control console are both located outside the drainage hood, the control circuit is located in the control console, and are respectively electrically connected to the drive guide rail, the jet fan, the winch and the spray pump.

[0009] Furthermore, the winch is connected to the sling via a lightweight traction rope, and the sling and the lightweight traction rope are connected via a tension sensor, and the tension sensor is electrically connected to the control circuit. At the same time, the winch is slidably connected to the drainage cover via a linear guide rail distributed parallel to the axis of the drainage cover.

[0010] Furthermore, a wind speed and direction sensor is provided in the air guide cover, and there are two wind speed and direction sensors in total, which are symmetrically distributed in front of and behind the winch, and the wind speed and direction sensors are connected to the inner side of the air guide cover through a support frame.

[0011] Furthermore, the support frame includes a support, a spring sheet, a connecting spring and a connecting rib plate, wherein the support is a circular tubular structure, the support is coaxially distributed with the drainage hood, and the wind speed and direction sensor is located inside the support, coaxially distributed with the support, and connected through three connecting springs evenly distributed around the axis of the support, the outer side surface of the support is connected to the three connecting rib plates through the spring sheet, and is connected to the inner side surface of the drainage hood through the connecting rib plate, the connecting rib plates are evenly distributed around the axis of the support, and the connecting rib plates and the connecting springs are spaced apart from each other.

[0012] Furthermore, the data processing circuit is a circuit system based on FPGA, and the control circuit is a circuit system based on a programmable controller, and the control circuit is also provided with any one or several common control interfaces including but not limited to a display, a keyboard, a button, and a potentiometer.

[0013] A detection method for an intelligent fault detection system of a drone for inspection comprises the following steps: S1, system configuration, first set up a dedicated drone fault monitoring site, and build at least one ground fault detection terminal at the drone fault monitoring site, and at least one random fault detection terminal for each ground fault detection terminal, and then build a communication network and a drone fault monitoring server, and finally, on the one hand, establish a data connection between the ground fault detection terminal and the corresponding random fault detection terminal through the communication network; on the other hand, the communication network establishes a data connection between the ground fault detection terminal and the random fault detection terminal and the drone fault monitoring server through the communication network, and the system configuration is completed; S2, dynamic detection, after completing step S1, assemble at least one random fault detection terminal for the fuselage of the unmanned aerial vehicle to be detected, and electrically connect the random fault detection terminal to the main control circuit system of the unmanned aerial vehicle to be detected, and establish data communication; then drive the unmanned aerial vehicle to be detected to perform normal flight activities, and during the flight activities, the random fault detection terminal detects the flight control signal parameters of the unmanned aerial vehicle to be detected on the one hand, thereby preliminarily realizing the detection effect of the flight control circuit system of the unmanned aerial vehicle; on the other hand, detect the actual flight attitude and flight parameters of the unmanned aerial vehicle to be detected, and compare the detection results to obtain the error between the actual flight attitude of the unmanned aerial vehicle to be detected and the control parameters, thereby achieving the detection of the control accuracy and flight abnormality of the unmanned aerial vehicle to be detected; S3, ground detection, after step S2, the UAV to be detected is suspended in the ground fault detection terminal by a sling. First, the UAV to be detected is sprayed with water for detection without starting it; then the UAV to be detected is started to put its power system and control system in working state. Finally, high-speed airflow and a mixture of high-speed airflow and water mist are fully utilized to simulate different altitudes, wind speeds, air humidity and rainfall flight conditions in actual flight, and detect the faults and performance of the UAV power system, flight attitude control system and fuselage structure strength.

[0014] The system of the present invention has a high degree of integration, modularization and automation. On the one hand, it can effectively meet the needs of fault detection and troubleshooting operations of UAVs of various structural types, greatly improving the work efficiency and flexibility of fault detection operations; on the other hand, it enriches the detection means, and effectively realizes the coordination of synchronous detection during the operation of the UAV and ground static detection, thereby greatly improving the flexibility, comprehensiveness and timeliness of UAV detection operations, and effectively overcoming UAV operation accidents caused by the operation of UAVs with faults. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments; Figure 1 It is a schematic diagram of the system structure of the present invention; Figure 2It is a schematic diagram of a partial structure of a random fault detection terminal in the system of the present invention; Figure 3 It is a schematic diagram of the partial structure of the cross-section of the load-bearing paddle in the system of the present invention; Figure 4 It is a schematic diagram of a partial structure of a ground fault detection terminal in the system of the present invention; Figure 5 This is a schematic diagram of the support frame structure in the system of the present invention; Figure 6 It is a schematic diagram of the process of the present invention. DETAILED DESCRIPTION

[0016] In order to facilitate the construction of the technical means, creative features, objectives and effects achieved by the present invention, the present invention is further described below in conjunction with specific implementation methods.

[0017] like Figure 1-Figure 5 As shown, an intelligent fault detection system for unmanned aerial vehicles used for inspection includes a unmanned aerial vehicle fault monitoring server 1, a communication network 2, a ground fault detection terminal 3 and a random fault detection terminal 4, wherein there is at least one ground fault detection terminal 3, and each ground fault detection terminal 3 forms a detection working group with at least one random fault detection terminal 4, and each random fault detection terminal 4 in the same detection work is connected to the fuselage of the same unmanned aerial vehicle to be detected, and the random fault detection terminal 4 establishes a data connection with the ground fault detection terminal 3 in the same detection working group through the communication network 2, and the ground fault detection terminal 3 establishes a data connection with the unmanned aerial vehicle fault monitoring server 1 through the communication network 2.

[0018] In this embodiment, the random fault detection terminal 4 includes a carrier box 41, a three-axis gyroscope 42, a gimbal stabilizer 43, a force-sensitive sensor 44, a carrier paddle 45, a monitoring camera 46 and a non-contact speed sensor 47, a counterweight 48, a multi-channel voltage-stabilized power supply 49, a data processing circuit 40 and a communication circuit 401 and a wiring terminal 402. The carrier box 41 is a closed cavity structure with an ellipsoidal cross section. The carrier box 41 is connected to the outer side of the fuselage of the unmanned aerial vehicle to be detected through the gimbal stabilizer 43. At the same time, the three-axis gyroscope 42, the multi-channel voltage-stabilized power supply 49, the data processing circuit 40 and the communication circuit 401 are all located in the carrier box 41. There are a plurality of wiring terminals 402, which are embedded in the outer side of the carrier box 41, and the wiring terminals 402 are respectively electrically connected to the multi-channel voltage-stabilized power supply 49 and the communication circuit 401. At the same time, the data processing circuit 40 is respectively connected to the three-axis gyroscope 42, the gimbal stabilizer 4 3. The force-sensitive sensor 44, the monitoring camera 46, the non-contact speed sensor 47, the multi-channel regulated power supply 49 and the communication circuit 401 are electrically connected. The carrying paddle 45 is a trapezoidal plate structure. The rear end face of the carrying paddle 45 is located in the carrying box 41 and is connected to at least one force-sensitive sensor 44. The front half of the carrying paddle 45 is located outside the carrying box 41. A monitoring camera 46 and a non-contact speed sensor 47 are arranged on the front end face of the carrying paddle 45, and the monitoring camera 46 and the non-contact speed sensor 47 are distributed along the axis direction of the carrying paddle 45. The monitoring camera and the non-contact speed sensor detection axis are perpendicularly distributed and intersect with the axis of the carrying paddle 45. There are four carrying paddles 45 in total, and each carrying paddle 45 is evenly distributed around the center of the carrying box 41. At the same time, each carrying paddle 45 and the axis of the carrying box 41 are distributed in the same plane. At least one counterweight 48 is also arranged on the lower end face of the carrying paddle 45.

[0019] Among them, the width of the rear end face of the load-bearing paddle 45 is 30%-70% of the width of the front end face, and its cross-section is any one of a shuttle shape, an elliptical shape and a teardrop shape. The load-bearing paddle 45 is provided with a guide groove 403 distributed parallel to its axis, and the load-bearing paddle 403 is connected to the counterweight block 48 through the guide groove 403. There is at least one counterweight block 48, and each counterweight block 48 is evenly distributed along the axis direction of the load-bearing paddle 45.

[0020] It is emphasized that the ground fault detection terminal 3 includes a driving rail 31, a drainage cover 32, a jet fan 33, an air outlet 34, a winch 35, a sling 36, a water tank 37 and a spray pump 38, an atomizing nozzle 39, a control console 30 and a control circuit 301. There are two driving rails 31, and the two driving rails 31 are parallel to each other and are parallel to the horizontal plane. The drainage cover 32 is a hyperbolic hollow tubular structure, and its axis is parallel to the horizontal plane. A winch 35 is provided at the top of the center of the drainage cover 32, and the winch 35 is connected to at least one sling 36. The air outlet 34 and the atomizing nozzle 39 are all embedded in the drainage cover 32 and connected to the front and rear halves of the drainage cover 32. The inner side is connected, the air outlet 34 and the atomizing nozzle 39 are evenly distributed around the axis of the drainage hood 32, and each air outlet 34 is connected to a jet fan 33 and coaxially distributed, and the jet fan 33 is connected to the outer side of the drainage hood 32, the atomizing nozzle 39 is connected to the spray pump 38 through a guide pipe, and there are at least two spray pumps 38, which are symmetrically distributed in the front and rear halves of the drainage hood 32 and connected to the outer side of the drainage hood 32, and the spray pumps 38 are connected to the water tank 37 through the guide pipe, and the water tank 37 and the control console 30 are both located outside the drainage hood 32, and the control circuit 301 is located in the control console 30, and is electrically connected to the drive guide rail 31, the jet fan 33, the winch 35 and the spray pump 38 respectively.

[0021] Among them, the winch 35 and the sling 36 are connected by a lightweight traction rope 5, and the sling 36 and the lightweight traction rope 5 are connected by a tension sensor 6, and the tension sensor 6 is electrically connected to the control circuit 301. At the same time, the winch 35 is slidably connected to the drainage cover 32 through a linear guide rail 7 distributed parallel to the axis of the drainage cover 32.

[0022] In this embodiment, a wind speed and direction sensor 8 is provided in the drainage cover 32, and there are two wind speed and direction sensors 8 in total. The two wind speed and direction sensors 8 are symmetrically distributed in front of and behind the winch 35, and the wind speed and direction sensors 8 are connected to the inner side of the drainage cover 32 through a support frame 9.

[0023] It is particularly noted that the support frame 9 includes a support 91, a spring sheet 92, a connecting spring 93 and a connecting rib plate 94, wherein the support 91 is a circular tubular structure, the support 91 is coaxially distributed with the drainage cover 32, and the wind speed and direction sensor 8 is located in the support 9, coaxially distributed with the support 9, and connected through three connecting springs 93 evenly distributed around the axis of the support 91, the outer side surface of the support 91 is connected to three connecting rib plates 94 through the spring sheet 92, and is connected to the inner side surface of the drainage cover 32 through the connecting rib plate 94, the connecting rib plates 94 are evenly distributed around the axis of the support 91, and the connecting rib plates 94 and the connecting springs 93 are spaced apart from each other.

[0024] In this embodiment, the data processing circuit 40 is a circuit system based on FPGA, and the control circuit 301 is a circuit system based on a programmable controller, and the control circuit 301 is also provided with a common control interface 302 including but not limited to any one or more of a display, keyboard, button, and potentiometer.

[0025] like Figure 6 As shown, a detection method of an intelligent fault detection system of a drone for inspection includes the following steps: S1, system configuration, first set up a dedicated drone fault monitoring site, and build at least one ground fault detection terminal at the drone fault monitoring site, and at least one random fault detection terminal for each ground fault detection terminal, and then build a communication network and a drone fault monitoring server, and finally, on the one hand, establish a data connection between the ground fault detection terminal and the corresponding random fault detection terminal through the communication network; on the other hand, the communication network establishes a data connection between the ground fault detection terminal and the random fault detection terminal and the drone fault monitoring server through the communication network, and the system configuration is completed; S2, dynamic detection, after completing step S1, assemble at least one random fault detection terminal for the fuselage of the unmanned aerial vehicle to be detected, and electrically connect the random fault detection terminal to the main control circuit system of the unmanned aerial vehicle to be detected, and establish data communication; then drive the unmanned aerial vehicle to be detected to perform normal flight activities, and during the flight activities, the random fault detection terminal detects the flight control signal parameters of the unmanned aerial vehicle to be detected on the one hand, thereby preliminarily realizing the detection effect of the flight control circuit system of the unmanned aerial vehicle; on the other hand, detect the actual flight attitude and flight parameters of the unmanned aerial vehicle to be detected, and compare the detection results to obtain the error between the actual flight attitude of the unmanned aerial vehicle to be detected and the control parameters, thereby achieving the detection of the control accuracy and flight abnormality of the unmanned aerial vehicle to be detected; S3, ground detection, after step S2, the UAV to be detected is suspended in the ground fault detection terminal by a sling. First, the UAV to be detected is sprayed with water for detection without starting it; then the UAV to be detected is started to put its power system and control system in working state. Finally, high-speed airflow and a mixture of high-speed airflow and water mist are fully utilized to simulate different altitudes, wind speeds, air humidity and rainfall flight conditions in actual flight, and detect the faults and performance of the UAV power system, flight attitude control system and fuselage structure strength.

[0026] The system of the present invention has a high degree of integration, modularization and automation. On the one hand, it can effectively meet the needs of fault detection and troubleshooting operations of UAVs of various structural types, greatly improving the work efficiency and flexibility of fault detection operations; on the other hand, it enriches the detection means, and effectively realizes the coordination of synchronous detection during the operation of the UAV and ground static detection, thereby greatly improving the flexibility and convenience of UAV detection operations, and effectively overcoming UAV operation accidents caused by the operation of UAVs with faults.

[0027] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. An intelligent fault detection system for unmanned aerial vehicles used for inspection, characterized in that: The intelligent fault detection system for unmanned aerial vehicle inspection includes a unmanned aerial vehicle fault monitoring server, a communication network, a ground fault detection terminal and a random fault detection terminal, wherein there is at least one ground fault detection terminal, and each ground fault detection terminal forms a detection working group with at least one random fault detection terminal, and each random fault detection terminal in the same detection work is connected to the fuselage of the same unmanned aerial vehicle to be inspected, and the random fault detection terminal establishes a data connection with the ground fault detection terminal in the same detection working group through the communication network, and at the same time, the ground fault detection terminal establishes a data connection with the unmanned aerial vehicle fault monitoring server through the communication network.

2. The intelligent fault detection system for unmanned aerial vehicle used for inspection according to claim 1 is characterized in that: The random fault detection terminal includes a carrier box, a three-axis gyroscope, a gimbal stabilizer, a force-sensitive sensor, a carrier paddle, a surveillance camera, and a non-contact speed sensor, a counterweight, a multi-channel voltage-stabilized power supply, a data processing circuit, a communication circuit, and a wiring terminal. The carrier box is a closed cavity structure with an ellipsoidal cross section. The carrier box is connected to the outer side of the fuselage of the unmanned aerial vehicle to be detected through the gimbal stabilizer. At the same time, the three-axis gyroscope, the multi-channel voltage-stabilized power supply, the data processing circuit, and the communication circuit are all located in the carrier box. There are a number of wiring terminals, which are embedded in the outer side of the carrier box, and the wiring terminals are electrically connected to the multi-channel voltage-stabilized power supply and the communication circuit respectively. At the same time, the data processing circuit is respectively connected to the three-axis gyroscope, the gimbal stabilizer, the force-sensitive sensor, the carrier paddle, the surveillance camera, and the non-contact speed sensor. The carrier paddle is a trapezoidal plate-shaped structure. The rear end face of the carrier paddle is located in the carrier box and is connected to at least one force-sensitive sensor. The front half of the carrier paddle is located outside the carrier box. A monitoring camera and a non-contact speed sensor are provided on the front end face of the carrier paddle. The monitoring camera and the non-contact speed sensor are distributed along the axis direction of the carrier paddle, and the detection axis is perpendicular to and intersects with the axis of the carrier paddle. There are four carrier paddles in total, and each carrier paddle is evenly distributed around the center of the carrier box. At the same time, each carrier paddle and the axis of the carrier box are distributed in the same plane. At least one counterweight block is also provided on the lower end face of the carrier paddle.

3. The intelligent fault detection system for unmanned aerial vehicle used for inspection according to claim 2 is characterized in that: The width of the rear end face of the load-bearing paddle is 30%-70% of the width of the front end face, and its cross-section is any one of a shuttle shape, an elliptical shape and a teardrop shape. The load-bearing paddle is provided with a guide groove distributed parallel to its axis, and the load-bearing paddle is connected to the counterweight block through the guide groove. There is at least one counterweight block, and each counterweight block is evenly distributed along the axis direction of the load-bearing paddle.

4. The intelligent fault detection system for unmanned aerial vehicle used for inspection according to claim 1 is characterized in that: The ground fault detection terminal includes a driving rail, a drainage cover, a jet fan, an air outlet, a winch, a sling, a water tank and a spray pump, an atomizing nozzle, a control console and a control circuit. There are two driving rails, and the two driving rails are parallel to each other and are parallel to the horizontal plane. The drainage cover is a hyperbolic hollow tubular structure, and its axis is parallel to the horizontal plane. A winch is provided at the top of the center of the drainage cover, and the winch is connected to at least one sling. The air outlet and the atomizing nozzle are all embedded in the drainage cover and connected to the inner side of the front half and the rear half of the drainage cover. The air outlets and the atomizing nozzles are evenly distributed around the axis of the drainage hood. At the same time, each air outlet is connected to a jet fan and is coaxially distributed, and the jet fan is connected to the outer side of the drainage hood. The atomizing nozzle is connected to the spray pump through a guide pipe. There are at least two spray pumps, which are symmetrically distributed in the front and rear halves of the drainage hood and connected to the outer side of the drainage hood. The spray pumps are connected to the water tank through the guide pipe. The water tank and the control console are both located outside the drainage hood. The control circuit is located in the control console and is electrically connected to the drive guide rail, the jet fan, the winch and the spray pump respectively.

5. The intelligent fault detection system for unmanned aerial vehicle used for inspection according to claim 4 is characterized in that: The winch is connected to the sling via a lightweight traction rope, and the sling and the lightweight traction rope are connected via a tension sensor, and the tension sensor is electrically connected to the control circuit. At the same time, the winch is slidably connected to the drainage cover via a linear guide rail distributed parallel to the axis of the drainage cover.

6. The intelligent fault detection system for unmanned aerial vehicle used for inspection according to claim 4, characterized in that: The deflector is provided with two wind speed and direction sensors in total. The two wind speed and direction sensors are symmetrically distributed in front of and behind the winch, and the wind speed and direction sensors are connected to the inner side of the deflector through a support frame.

7. The intelligent fault detection system for unmanned aerial vehicle used for inspection according to claim 6, characterized in that: The support frame includes a support platform, spring plates, connecting springs and connecting ribs, wherein the support platform is a circular tubular structure, the support platform is coaxially distributed with the drainage cover, and the wind speed and direction sensor is located inside the support platform, coaxially distributed with the support platform, and connected through three connecting springs evenly distributed around the axis of the support platform, the outer side surface of the support platform is connected to the three connecting ribs through the spring plates, and is connected to the inner side surface of the drainage cover through the connecting ribs, the connecting ribs are evenly distributed around the axis of the support platform, and the connecting ribs and the connecting springs are spaced apart from each other.

8. The intelligent fault detection system for unmanned aerial vehicle used for inspection according to claim 2, characterized in that: The data processing circuit is a circuit system based on FPGA, and the control circuit is a circuit system based on a programmable controller. The control circuit is also provided with any one or several common control interfaces including but not limited to a display, a keyboard, a button and a potentiometer.

9. A detection method for an intelligent fault detection system of a drone for inspection according to claim 1, characterized in that: The detection method of the patrol drone intelligent fault detection system comprises the following steps: S1, system configuration, first set up a dedicated drone fault monitoring site, and build at least one ground fault detection terminal at the drone fault monitoring site, and at least one random fault detection terminal for each ground fault detection terminal, and then build a communication network and a drone fault monitoring server, and finally, on the one hand, establish a data connection between the ground fault detection terminal and the corresponding random fault detection terminal through the communication network; on the other hand, the communication network establishes a data connection between the ground fault detection terminal and the random fault detection terminal and the drone fault monitoring server through the communication network, and the system configuration is completed; S2, dynamic detection, after completing step S1, assemble at least one random fault detection terminal for the fuselage of the unmanned aerial vehicle to be detected, and electrically connect the random fault detection terminal to the main control circuit system of the unmanned aerial vehicle to be detected, and establish data communication; then drive the unmanned aerial vehicle to be detected to perform normal flight activities, and during the flight activities, the random fault detection terminal detects the flight control signal parameters of the unmanned aerial vehicle to be detected on the one hand, thereby preliminarily realizing the detection effect of the flight control circuit system of the unmanned aerial vehicle; on the other hand, detect the actual flight attitude and flight parameters of the unmanned aerial vehicle to be detected, and compare the detection results to obtain the error between the actual flight attitude of the unmanned aerial vehicle to be detected and the control parameters, thereby achieving the detection of the control accuracy and flight abnormality of the unmanned aerial vehicle to be detected; S3, ground detection, after step S2, the UAV to be detected is suspended in the ground fault detection terminal by a sling. First, the UAV to be detected is sprayed with water for detection without starting it; then the UAV to be detected is started to put its power system and control system in working state. Finally, high-speed airflow and a mixture of high-speed airflow and water mist are fully utilized to simulate different altitudes, wind speeds, air humidity and rainfall flight conditions in actual flight, and detect the faults and performance of the UAV power system, flight attitude control system and fuselage structure strength.

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