Aircraft fuselage skin detection device

Abstract

The utility model relates to the technical field of aircraft maintenance inspection and repair inspection, and discloses an aircraft fuselage skin detection device which comprises a trolley body, a lifting assembly arranged in the middle of the trolley body, and a PTZ ball machine assembly connected to the top of the lifting assembly in a telescopic mode. The lifting assembly comprises a lifting base arranged in the middle of the trolley body, a first direct current motor arranged on the lifting base and a lifting support, the first direct current motor drives the lifting support to ascend and descend, the PTZ dome camera assembly comprises a camera support and a PTZ dome camera installed at the bottom of the camera support, and the camera support is installed at the top of the lifting support. The airplane fuselage skin detection device is provided with the lifting assembly, the PTZ ball machine assembly is installed on the top of the lifting assembly, the PTZ ball machine assembly can change the current detection area by means of lifting of the lifting assembly, and the detection range is larger. The device is simple and efficient in overall structure and easy to manufacture, and has the characteristics of low cost and flexibility and portability in use.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft maintenance inspection and repair inspection, in particular to an aircraft fuselage skin detection device. Background Art

[0002] Aircraft skin refers to the external material covering the surface of the aircraft to protect the aircraft structure from the external environment and airflow. This skin is usually made of light and strong materials, such as aluminum alloy, composite materials or titanium alloy. The skin must not only have the characteristics of light weight and high strength, but also have good aerodynamic performance to reduce air resistance and improve flight efficiency.

[0003] There are many reasons why aircraft skin may be damaged. Some common situations include mechanical damage, such as airport ground operations, collisions with ground service equipment or other objects may cause scratches, dents or tears on the skin surface; temperature changes. Aircraft fly in high and low temperature environments and usually experience rapid changes in temperature. These changes may cause the skin material to shrink and expand, resulting in damage.

[0004] Aircraft skin damage threatens flight safety. Skin damage reduces the air tightness and waterproofness of the aircraft, which may cause air or water to penetrate into the aircraft structure during flight, thereby affecting the normal operation of the aircraft system. Severe damage may cause the structural strength to decrease, thereby affecting the flight performance and stability of the aircraft. Therefore, in order to ensure the continued airworthiness of the aircraft, regular inspections of the aircraft skin structure safety must be carried out.

[0005] At present, the existing technical solutions for aircraft fuselage skin inspection are mainly divided into two types: one is that about 90% of the aircraft skin damage detection tasks are mainly based on manual visual inspection, supplemented by some handheld detection equipment, which has problems such as high work intensity, low operation efficiency, inability to ensure detection coverage, low positioning and recognition accuracy, and strong subjectivity, and cannot meet the fundamental requirements for efficient and accurate aircraft skin detection operations; the other is to detect the aircraft skin by carrying corresponding sensors on some transportation equipment. For example, using drones equipped with cameras and other sensor equipment, the drones fly around the aircraft and take pictures of the aircraft surface skin for inspection. However, drones are strictly prohibited from flying around airports, and the use of drones to inspect the aircraft surface skin will be subject to regional restrictions. The second is to use a trolley equipped with relevant sensor equipment to detect the aircraft surface skin. Chinese patent CN117862992A discloses an aircraft skin forming system, including a mobile trolley, the mobile trolley is provided with a motor to drive the wheels to run, a vertical plate is provided above the mobile trolley, a scanner is provided on the top of the vertical plate, and the scanner is connected to a central controller. By moving the cart around the aircraft, the scanner can scan the aircraft surface skin at the corresponding height. Although this improves efficiency, there are also problems such as the sensor installation position is fixed and cannot be flexibly detected. The detection area is limited by the installation position, and areas higher than the installation position cannot be detected. Utility Model Content

[0006] In order to overcome the problems existing in the related art, the utility model provides an aircraft fuselage skin detection device, which has a lifting component, and the PTZ ball camera component is installed on the top of the lifting component. The current detection area of ​​the PTZ ball camera is changed by lifting the lifting component, which effectively expands the detection range of the PTZ ball camera, making the detection of the aircraft fuselage skin more flexible and capable of detecting a larger area. The lifting component of the aircraft fuselage skin detection device has a simple structure and no complex mechanical design, making the entire fuselage skin detection process more convenient to operate.

[0007] The technical solution adopted by the utility model is: an aircraft fuselage skin detection device, comprising a trolley body, a lifting assembly arranged in the middle of the trolley body, and a PTZ ball camera assembly telescopically connected to the top of the lifting assembly;

[0008] The lifting assembly includes a lifting base arranged in the middle of the trolley body, a first DC motor and a lifting bracket arranged on the lifting base, the first DC motor drives the lifting bracket to rise and fall, the PTZ ball camera assembly includes a camera bracket and a PTZ ball camera installed at the bottom of the camera bracket, and the camera bracket is installed on the top of the lifting bracket.

[0009] Furthermore, the lifting component includes a driving unit and a first DC power supply, the driving unit includes an embedded control board and a dual H-bridge driving board, the first DC power supply is electrically connected to the embedded control board, the dual H-bridge driving board and the first DC motor respectively, the general input and output GPIO1 and the general input and output GPIO2 of the embedded control board are respectively connected to the input terminal in1 and the input terminal in2 of the dual H-bridge driving board, the PWM output terminal of the embedded control board is connected to the enable terminal ENA of the dual H-bridge driving board, and the output terminal out of the dual H-bridge driving board is connected to the first DC motor.

[0010] Furthermore, the lifting assembly also includes a pull-wire sensor arranged at the bottom of the camera bracket, the pull-wire sensor is electrically connected to the embedded control board, and the pull wire of the pull-wire sensor is fixedly connected to the top surface of the lifting base.

[0011] Furthermore, a communication module is provided on the trolley body, and the communication module includes an RS485 communication serial port and a conversion interface. The first DC power supply and the pull-wire sensor are electrically connected, the UART1 communication serial port of the embedded control board is connected to the communication serial port of the host computer, the UART2 communication serial port of the embedded control board is connected to the input end of the conversion interface, the output end of the conversion interface is connected to the input end of the RS485 communication serial port, and the output end out1 and the output end out2 of the pull-wire sensor are respectively connected to the A signal end and the B signal end of the RS485 communication serial port.

[0012] Furthermore, when the lifting assembly is at the lowest point, the horizontal height of the PTZ ball camera is not higher than the height of the front of the trolley body.

[0013] Furthermore, it also includes an anti-collision component arranged on the front and rear sides of the trolley body, the anti-collision component includes an anti-collision rod and a collision sensor, the anti-collision rod is elastically connected to the collision sensor, the trolley body is provided with a collision detection module, and the collision detection module is connected to the collision sensor signal.

[0014] Furthermore, a computer is arranged inside the vehicle body, a communication serial port of the computer is communicatively connected with UART1 of the embedded control board, and the computer is provided with an LCD touch screen.

[0015] Furthermore, a laser radar is arranged at the front of the vehicle body, and GNSS antennas are arranged on the left and right sides of the front of the vehicle body. Both the laser radar and the GNSS antennas are connected to the computer signal.

[0016] The aircraft fuselage skin detection device of the utility model has the following technical effects: 1. By arranging a lifting assembly in the middle of the trolley body, installing the PTZ ball camera assembly on the top of the lifting assembly, and changing the current detection area of ​​the PTZ ball camera assembly by lifting and lowering the lifting assembly, the detection range of the PTZ ball camera assembly is effectively expanded. 2. By installing the PTZ ball camera assembly on the trolley body, the trolley travels around the aircraft fuselage, so that the PTZ ball camera can detect the aircraft fuselage skin more quickly, without the need for staff to hold the detection equipment for inspection, saving labor costs and improving detection efficiency. 3. The overall structure of the aircraft fuselage skin detection device of the utility model is simple and efficient, easy to manufacture, low cost, flexible and light to use.

[0017] Other features and advantages disclosed in the present invention will be described in detail in the subsequent specific implementation section. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings are used to provide a further understanding of the present disclosure and constitute a part of the specification. Together with the following specific embodiments, they are used to explain the present disclosure but do not constitute a limitation of the present disclosure. In the accompanying drawings:

[0019] Figure 1 1 is a schematic diagram of the overall structure of an aircraft fuselage skin detection device according to an exemplary embodiment (I).

[0020] Figure 2 2 is a schematic diagram of the overall structure of an aircraft fuselage skin detection device according to an exemplary embodiment.

[0021] Figure 3 The present invention is a schematic diagram of the internal circuit connection structure of a lifting assembly of an aircraft fuselage skin detection device according to an exemplary embodiment.

[0022] Figure numerals: 10, trolley body; 20, lifting assembly; 21, lifting base; 22, first DC motor; 23, lifting bracket; 24, wire sensor; 30, PTZ ball camera assembly; 31, camera bracket; 32, PTZ ball camera; 40, anti-collision assembly; 41, anti-collision rod; 42, collision sensor; 50, LCD touch screen; 60, laser radar; 70, GNSS antenna; 80, embedded control board; 90, dual-channel H-bridge driver board; 100, conversion interface; 110, RS485 communication serial port, 120, indicator light; 130, buzzer. DETAILED DESCRIPTION

[0023] The specific implementation methods disclosed in the present utility model are described in detail below in conjunction with the accompanying drawings. It should be understood that the specific implementation methods described herein are only used to illustrate and explain the present disclosure, and are not used to limit the present disclosure.

[0024] like Figure 1 , Figure 2 The figure shows an exemplary embodiment of the present invention. The aircraft fuselage skin inspection device of the present invention comprises a trolley body 10, a lifting assembly 20 arranged in the middle of the trolley body 10, and a PTZ ball camera assembly 30 telescopically connected to the top of the lifting assembly 20;

[0025] The lifting assembly 20 includes a lifting base 21 arranged in the middle of the trolley body 10, a first DC motor 22 and a lifting bracket 23 arranged on the lifting base 21, the first DC motor 22 drives the lifting bracket 23 to rise and fall, and the PTZ ball camera assembly 30 includes a camera bracket 31 and a PTZ ball camera 32 installed at the bottom of the camera bracket 31, and the camera bracket 31 is installed on the top of the lifting bracket 23.

[0026] The aircraft fuselage skin detection device of the utility model is provided by installing a lifting assembly 20 in the middle of the trolley body 10, the lifting assembly 20 includes a lifting base 21, a lifting bracket 23 and a first DC motor 22, and the PTZ ball camera assembly 30 includes a camera bracket 31 and a PTZ ball camera 32, the camera bracket 31 is installed on the top of the lifting bracket 23, and the PTZ ball camera 32 is installed on the bottom of the camera bracket 31. The lifting bracket 23 is driven to rise or fall by the first DC motor 22, thereby driving the PTZ ball camera 32 to rise or fall, so that the PTZ ball camera 32 can change the current detection area and expand the detection range of the PTZ ball camera 32.

[0027] Specifically, Figure 3 As shown, the lifting component 20 includes a driving part and a first DC power supply, the driving part includes an embedded control board 80 and a dual H-bridge driving board 90, the first DC power supply is electrically connected to the embedded control board 80, the dual H-bridge driving board 90 and the first DC motor 22 respectively, the general input and output GPIO1 and the general input and output GPIO2 of the embedded control board 80 are respectively connected to the input terminal in1 and the input terminal in2 of the dual H-bridge driving board 90, the PWM output terminal of the embedded control board 80 is connected to the enable terminal ENA of the dual H-bridge driving board 90, and the output terminal out of the dual H-bridge driving board 90 is connected to the first DC motor 22.

[0028] The lifting assembly 20 of the aircraft fuselage skin detection device of the utility model is provided with a driving part, and the driving part includes an embedded control board 80 and a dual-channel H-bridge driving board 90. Preferably, the embedded control board 80 is an stm32 embedded chip, and the output end out of the dual-channel H-bridge driving board 90 is connected to the DC motor. Through the cooperation of the embedded control board 80 and the dual-channel H-bridge driving board 90, PWM modulation of the voltage is realized, and the PWM modulation voltage is used to control the first DC motor 22. PWM can adjust the magnitude of the output voltage by controlling the duty cycle, realize accurate control of the speed of the first DC motor 22, and make the motor run at different speeds. PWM modulation voltage can make the motor run smoother and reduce vibration and noise.

[0029] For example, Figure 2 As shown, the lifting assembly 20 also includes a pull-wire sensor 24 disposed at the bottom of the camera bracket 31 . The pull-wire sensor 24 is electrically connected to the embedded control board 80 , and the pull wire of the pull-wire sensor 24 is fixedly connected to the top surface of the lifting base 21 .

[0030] Specifically, Figure 3 As shown, a communication module is provided on the trolley body 10, and the communication module includes an RS485 communication serial port 110 and a conversion interface 100, the first DC power supply and the wire pulling sensor 24 are electrically connected, the UART1 communication serial port of the embedded control board 80 is connected to the communication serial port of the host computer, the UART2 communication serial port of the embedded control board 80 is connected to the input end of the conversion interface 100, the output end of the conversion interface 100 is connected to the input end of the RS485 communication serial port 110, and the output end out1 and the output end out2 of the wire pulling sensor 24 are respectively connected to the A signal end and the B signal end of the RS485 communication serial port 110.

[0031] In order to accurately control the rising or falling distance of the lifting assembly 20, the aircraft fuselage skin detection device of the utility model is equipped with a pull-wire sensor 24 at the bottom of the camera bracket 31. The pull wire of the pull-wire sensor 24 is fixedly connected to the top surface of the lifting base 21. The pull-wire sensor 24 is electrically connected to the embedded control board 80. The pull-wire sensor 24 can feed back the current pull-wire length to the embedded control board 80. The embedded control board 80 receives the feedback of the pull-wire sensor 24 and saves the pull-wire length value.

[0032] For example, in an exemplary embodiment of the present disclosure, when the lifting assembly 20 of the aircraft fuselage skin inspection device of the present invention is located at the lowest point, the horizontal height of the PTZ ball camera 32 is not higher than the height of the front of the trolley body 10 .

[0033] In this way, when the trolley body 10 travels on the belly of an aircraft, it can be ensured that the PTZ ball camera 32 will not collide with the aircraft body, so that the belly skin of the aircraft can be inspected normally.

[0034] For example, Figure 1 , Figure 2 As shown, the aircraft fuselage skin detection device of the utility model also includes an anti-collision component 40 arranged on the front and rear sides of the trolley body 10, the anti-collision component 40 includes an anti-collision rod 41 and a collision sensor 42, the anti-collision rod 41 is elastically connected to the collision sensor 42, the trolley body 10 is provided with a collision detection module, and the collision detection module is connected to the collision sensor 42 signal.

[0035] The collision detection module provided on the trolley body 10 includes an indicator light 120, a buzzer 130 and a collision detection circuit. The collision detection circuit is electrically connected to the collision sensor 42. When the anti-collision bar 41 collides with an external object, the collision sensor 42 receives a collision signal, at which time the collision detection circuit is closed to form a path, the indicator light 120 lights up, and the buzzer 130 sounds an alarm, thereby notifying the staff of the collision.

[0036] For example, Figure 2 As shown, the aircraft fuselage skin detection device of the utility model is provided with a computer inside the trolley body 10, the communication serial port of the computer is connected to the UART1 of the embedded control board 80, and the computer is provided with an LCD touch screen 50. A laser radar 60 is provided at the front of the trolley body 10, and GNSS antennas 70 are provided on the left and right sides of the front of the trolley body 10, and both the laser radar 60 and the GNSS antenna 70 are connected to the computer signal.

[0037] The trolley body 10 is equipped with a computer with an LCD touch screen 50, which is convenient for the PTZ camera to transmit the aircraft fuselage skin related data scanned back by the detection to the computer, and the computer is used for evaluation to obtain the detection results. The trolley body 10 has an activated radar at the front position, which can be used to obtain the three-dimensional point cloud data of the current environment, and the GNSS antenna 70 can obtain positioning information. The two are connected to the computer on the trolley body 10 for communication, and can better cooperate with the aircraft fuselage skin detection device to complete the aircraft fuselage skin detection task.

[0038] The preferred embodiments of the present disclosure are described in detail above in conjunction with the accompanying drawings; however, the present disclosure is not limited to the specific details in the above embodiments. Within the technical concept of the present disclosure, a variety of simple modifications can be made to the technical solution of the present disclosure, and these simple modifications all fall within the protection scope of the present disclosure.

[0039] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, the present disclosure will not further describe various possible combinations.

[0040] In addition, various embodiments of the present disclosure may be arbitrarily combined, and as long as they do not violate the concept of the present disclosure, they should also be regarded as the contents disclosed by the present disclosure.

Claims

1. An aircraft fuselage skin detection device, characterized in that: It includes a trolley body, a lifting assembly arranged in the middle of the trolley body, and a PTZ ball camera assembly telescopically connected to the top of the lifting assembly; The lifting assembly includes a lifting base arranged in the middle of the trolley body, a first DC motor and a lifting bracket arranged on the lifting base, the first DC motor drives the lifting bracket to rise and fall, the PTZ ball camera assembly includes a camera bracket and a PTZ ball camera installed at the bottom of the camera bracket, and the camera bracket is installed on the top of the lifting bracket.

2. The aircraft fuselage skin detection device according to claim 1, characterized in that: The lifting component includes a driving unit and a first DC power supply. The driving unit includes an embedded control board and a dual H-bridge driving board. The first DC power supply is electrically connected to the embedded control board, the dual H-bridge driving board and the first DC motor respectively. The general input and output GPIO1 and the general input and output GPIO2 of the embedded control board are respectively connected to the input terminal in1 and the input terminal in2 of the dual H-bridge driving board. The PWM output terminal of the embedded control board is connected to the enable terminal ENA of the dual H-bridge driving board. The output terminal out of the dual H-bridge driving board is connected to the first DC motor.

3. The aircraft fuselage skin detection device according to claim 2, characterized in that: The lifting assembly also includes a pull-wire sensor arranged at the bottom of the camera bracket, the pull-wire sensor is electrically connected to the embedded control board, and the pull wire of the pull-wire sensor is fixedly connected to the top surface of the lifting base.

4. The aircraft fuselage skin detection device according to claim 3, characterized in that: A communication module is provided on the trolley body, and the communication module includes an RS485 communication serial port and a conversion interface. The first DC power supply is electrically connected to the pull-wire sensor, the UART1 communication serial port of the embedded control board is connected to the communication serial port of the host computer, the UART2 communication serial port of the embedded control board is connected to the input end of the conversion interface, the output end of the conversion interface is connected to the input end of the RS485 communication serial port, and the output end out1 and the output end out2 of the pull-wire sensor are respectively connected to the A signal end and the B signal end of the RS485 communication serial port.

5. The aircraft fuselage skin detection device according to claim 1, characterized in that: When the lifting assembly is at the lowest point, the horizontal height of the PTZ ball camera is not higher than the height of the front of the trolley body.

6. The aircraft fuselage skin detection device according to claim 1, characterized in that: It also includes an anti-collision component arranged on the front and rear sides of the trolley body, the anti-collision component includes an anti-collision rod and a collision sensor, the anti-collision rod is elastically connected to the collision sensor, the trolley body is provided with a collision detection module, and the collision detection module is connected to the collision sensor signal.

7. The aircraft fuselage skin detection device according to claim 2, characterized in that: A computer is arranged inside the trolley body, a communication serial port of the computer is communicatively connected with the UART1 of the embedded control board, and the computer is provided with an LCD touch screen.

8. The aircraft fuselage skin detection device according to claim 7, characterized in that: A laser radar is arranged at the front of the vehicle body, and GNSS antennas are arranged on the left and right sides of the front of the vehicle body. Both the laser radar and the GNSS antennas are connected to the computer signal.

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