A method and apparatus for in-situ composite wing cold cathode x-ray inspection

Abstract

The present application relates to a kind of wing composite material in situ cold cathode X-ray detection device and method, device includes base, liftable support frame, U-shaped fixing frame, clamping plate, cold cathode X-ray emitter, DR imaging plate, range camera and wireless controller, detection method is using the cold cathode X-ray detection device of above-mentioned intelligent shape to carry out the shape of wing beforehand, form detection path, when aircraft completes flight task and enters detection, through wireless control detection device, aircraft wing composite material is detected quickly automatically.By setting cold cathode X-ray detection device, the detection of aircraft wing composite material is carried out, the weakness of traditional thermal ray equipment, such as large size and strong radiation, is overcome, and the safety of detection is improved.By the setting of simulation detection path, the adjustment of control during detection is reduced, so that the detection process is more smooth, and the detection efficiency is improved.The reliability of detection result is improved by verifying simulation detection path by pre-detection.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aviation composite material detection, and particularly to a wing composite material in-situ cold cathode X-ray detection method and device. BACKGROUND

[0002] With the progress of social science and technology, the aircraft wing largely adopts composite materials with higher strength and lighter weight to replace the previous light aluminum alloy structure. However, due to the special manufacturing process of composite materials, the conventional ultrasonic and eddy current method cannot complete the rapid and reliable detection of the in-service in-situ wing composite material structure health condition. At present, the detection of the wing composite material mostly adopts infrared, terahertz and other optical methods, which can only perform limited detection and evaluation on the superficial skin peeling. The conventional hot cathode ray machine is bulky, has large radiation energy, is harmful to human body, and has a long start-up time, so it cannot quickly implement effective detection and evaluation of the in-service in-situ aircraft wing after the aircraft lands. Therefore, it is necessary to explore a method and device for rapidly detecting the in-service in-situ aircraft wing composite material structure health condition. SUMMARY

[0003] To solve the above problems, the present application provides a wing composite material in-situ cold cathode X-ray detection device, which is implemented as follows:

[0004] A wing composite material in-situ cold cathode X-ray detection device, comprising:

[0005] A base provided with an electrically driven walking mechanism;

[0006] A liftable support frame connected to the base, and an upper portion of the liftable support frame is provided with a U-shaped fixing frame;

[0007] Clamping plates including upper and lower clamping plates, the two clamping plates are respectively swingably connected to two arms of the U-shaped fixing frame through electrically controlled rotating connecting pieces, and the distance between the two arms of the U-shaped fixing frame is adjustable;

[0008] A cold cathode X-ray emitter and a DR imaging plate are respectively fixed on the inner side walls of the two clamping plates, the cold cathode X-ray emitter is arranged on the lower clamping plate and emits a cold cathode X-ray source upward;

[0009] A distance measuring camera is fixed on the corresponding clamping plate, and the distance between the detection device and the wing part to be detected is measured through the distance measuring camera;

[0010] A control module is wirelessly or wiredly connected to the electric walking mechanism, the lifting mechanism of the liftable support frame, the rotating mechanism of the U-shaped fixing frame, the electric control rotating connecting piece and the distance measuring camera, and controls the detection surface multidimensional adjustment to adapt to the wing shape.

[0011] The application further discloses a wing composite material in-situ cold cathode X-ray detection method.

[0012] The specific steps are as follows:

[0013] S1: a three-dimensional parameter model of the wing is established through a computer, the thickness, curvature and inclination angle of the composite material of different parts of the wing of the to-be-detected aircraft model are pre-detected, and the best detection model is formed; the electric control parameter model of the detection equipment is established according to the detection model, the detection of the wing composite material is simulated walking, the simulated detection path is formed, and the simulated detection path is saved in the control system;

[0014] S2: after the aircraft completes the flight task, the detection device is moved to the wing, pre-walking before detection is quickly performed according to the pre-stored detection path of the system, the distance from the cold cathode X-ray emitter and the DR imaging plate to the wing is measured by the distance measuring probe on the clamping plate, and the pre-detection data is fed back to the controller; if there is an error between the pre-detection result and the simulated detection path calculated according to the model, then the fine adjustment is performed on the basis of the simulated detection path according to the detection model;

[0015] S3: after the pre-detection path walking is completed and the path is adjusted, the first actual detection of the wing composite material is immediately performed, each part of the detection device is linked and adjusted, the walking is completed, and the detection result is obtained;

[0016] S4: the same part on the wing is detected multiple times in time sharing, the change of the composite material structure health state from the dynamic load to the static load of the aircraft is tracked and analyzed.

[0017] As a further improvement, the best detection model in the step S1 is simulated and calculated according to the shape contour of the wing, the distance from the cold cathode X-ray emitter to the lower surface of the wing, the distance from the DR imaging plate to the upper surface of the wing and the inclination angle of the two clamping plates corresponding to the inclined parts of the wing.

[0018] As a further improvement, the electric control parameter model in the step S1 includes the walking direction and speed of the electric control roller, the lifting height and speed of the liftable support frame, the lifting height and speed of the two arms of the U-shaped fixing frame, and the rotation angle and speed of the two electric control rotation connectors.

[0019] As a further improvement, the electric control parameter model further includes the control of the cold cathode X-ray emitter, and the corresponding cold cathode X-ray emission energy is set according to the wing composite material of different thicknesses.

[0020] As a further improvement, the time-sharing detection in the step S4 is divided into three times, i.e., 1-10 minutes, 10-20 minutes and 20-30 minutes of the approach of the airplane.

[0021] Compared with the prior art, the present application can obtain the following technical effects:

[0022] Firstly, the present application creates a new device and method for in-situ detection of the health state of the airplane wing composite material structure, adopts the cold cathode X-ray detection technology, detects the airplane wing composite material by setting the cold cathode X-ray detection device, overcomes the weaknesses of the traditional thermal ray device, such as large volume and strong radiation, not only improves the safety of detection, but also shortens the starting time of the device, and can better complete the in-situ detection of the wing composite material in the effective detection time, thereby solving the technical problem of the current in-situ rapid detection of the airplane wing composite material.

[0023] Secondly, the present application sets the mode of intelligent walking and automatic detection, the detection device can realize the accessibility in multiple dimensions, can move in any direction through the electric control walking mechanism, can adapt to the detection surface of different heights through the liftable support frame, can adapt to the wing composite material of different thicknesses through the adjustable distance between the U-shaped fixing frames, and can adapt to the non-planar structure on the wing through the overturning of the clamping plate. Through the operation of the wireless control device, manual detection is not needed, the detection efficiency is greatly improved, and the harm of the ray radiation to the human body is reduced.

[0024] Thirdly, the detection method of the present application pre-simulates the contour of the airplane wing through a computer, designs the best detection model, calculates the parameters of each electric control component to form an electric control parameter model, forms a simulated detection path, sets the simulated detection path, reduces the adjustment of the control in the detection process, makes the detection process more smooth, and improves the detection efficiency.

[0025] Four, the detection of the application includes a rapid verification process of the simulation detection path after the aircraft approach, namely designing two steps of pre-detection and actual detection, the pre-detection stage only needs to walk fast and start the equipment preparation at the same time, the pre-detection stage improves the reliability of the detection result, reasonably arranges the equipment starting time, saves the energy loss on the basis of not affecting the detection. BRIEF DESCRIPTION OF DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the application examples or the prior art or the descriptions needed in the prior art description, it is obvious that for ordinary skilled persons in the art, without creative labor, other drawings can also be obtained according to these drawings.

[0027] Figure 1 The detection state of the application is shown in the figure.

[0028] Figure 2 The structure of the detection device of the application is shown in the figure.

[0029] Figure 3 The Figure 2 The schematic view of another perspective.

[0030] Figure 4 The Figure 3 The enlarged schematic view of the A area.

[0031] Figure 5 The two clamping plates of the detection device of the application are shown in the figure.

[0032] Figure 6 The lifting change demonstration diagram of the detection device of the application is shown in the figure.

[0033] Figure 7 The flow chart of the detection method of the application is shown in the figure.

[0034] In the figure:

[0035] 10-base, 11-electric control roller;

[0036] 20-liftable support frame, 21-fixed part, 22-liftable part;

[0037] 30-U-shaped fixed frame;

[0038] 40-upper clamping plate, 41-lower clamping plate;

[0039] 50-cold cathode ray emitter;

[0040] 60-DR imaging plate;

[0041] 70-range-finding camera. DETAILED DESCRIPTION

[0042] In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the claimed present application, but only represents selected embodiments of the present application.

[0043] In the description of the present application, the terms "first", "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined with "first", "second" can be explicitly or implicitly included one or more of the features.

[0044] According to the development in recent years, the development of cold cathode ray machine DR display technology makes it possible to detect the composite material of the aircraft wing in situ, which overcomes the weaknesses of large volume and strong radiation, and is a new safe technology. A self-propelled or fully automatic cart is used, the cold cathode emitter is placed on the upper or lower surface of the cart, and the DR display screen is placed opposite to it, forming a face-to-face U-shaped structure, which is pushed by hand or carried by a power car. If necessary, the counterweight automatic driving mechanism is provided, so that it can avoid obstacles and undetectable areas according to different aircraft models and wing sizes, heights, and effectively, so as to realize the in-situ detection of the composite material of the aircraft wing, and improve the work efficiency and the safety factor of the aircraft.

[0045] Reference is made to the accompanying drawings Figures 1-7 On the basis of the prior art, the present application researches a kind of cold cathode X-ray detection device for wing composite material in situ, which carries out health detection of aircraft wing composite material in a fully automatic mode, comprising:

[0046] The lower surface of the base 10 is provided with electric control rollers 11, at least four electric control rollers 11, four electric control rollers 11 are provided with drivers, the direction and walking speed of the electric control rollers 11 are controlled wirelessly by the controller, the electric control rollers 11 can be universally adjusted, and the steering is flexible.

[0047] The liftable support frame 20 is arranged at the upper end of the base 10, including a fixed part 21 and a liftable part 22, and the end of the liftable support frame 20 away from the base 10 is provided with a U-shaped fixing frame 30, referring to the accompanying drawings Figure 1 The U-shaped fixing frame 30 is placed laterally, i.e. the open end of the U-shaped fixing frame 30 faces the wing to be detected.

[0048] The clamping plates include an upper clamping plate 40 and a lower clamping plate 41, which are kept parallel to each other, and are rotatably arranged on the two arms of the U-shaped fixing frame 30 through electrically controlled rotary connectors (not shown) arranged at the connection between the clamping plates and the U-shaped fixing frame.

[0049] The distance measuring camera 70 is arranged on the clamping plate, in particular, at the front end of the clamping plate, and is arranged on each of the two clamping plates, and the distance between the detection device and the part to be detected of the wing is measured through the distance measuring camera 70.

[0050] The controller can wirelessly control the electrically controlled rollers 11, the liftable support frame 20, the two arms of the U-shaped fixing frame, the electrically controlled rotary connectors and the distance measuring camera 70, control the movement of the electrically controlled rollers 11, control the lifting or lowering of the liftable support frame 20, control the rotation of the electrically controlled connectors by a corresponding angle, control the distance measuring camera 70 to measure the real-time distance, control the adjustment of the distance between the two arms of the U-shaped fixing frame 30, and the like. Figure 5 , attached Figure 6 , attached Figure 5 and attached Figure 6 are the demonstration diagrams of the lifting transformation or the clamping plate turning transformation of the device.

[0051] The device of the present application detects the composite material of the wing of the aircraft by setting the detection device using the cold cathode rays, overcomes the weakness of the large volume and strong radiation of the traditional thermal ray equipment, and improves the safety of the detection.

[0052] Further, in order to reduce the risk coefficient of the detection, the cold cathode ray emitter 50 is arranged on the lower clamping plate 41 and emits the cold cathode ray source upward. Referring to attached Figure 3 In the embodiment, the cold cathode ray emitter 50 and the DR imaging plate 60 are clamped on the clamping plate through the sliding groove, which is simple in structure but reliable and stable.

[0053] Further, the distance between the two arms of the U-shaped fixing frame 30 can be adjusted, and the thickness of different parts of the wing will be different. The design adjusts the distance between the two arms of the U-shaped fixing frame to adjust the distance between the cold cathode ray emitter and the DR imaging plate and the wing, and improves the reliability of the detection result.

[0054] The application further discloses a wing composite material in-situ cold cathode X-ray detection method, which is characterized by the following steps.

[0055] Further improvement, the specific steps of the detection method are as follows:

[0056] S1: a three-dimensional parameter model of the wing is established by a computer, the thickness, curvature, inclination angle and other contour parameters of the composite material at different positions of the wing of the to-be-detected aircraft type are calculated, and an optimal detection model is formed according to the characteristics of the cold cathode ray detection method; an electric control parameter model of the detection equipment is established according to the detection model, the detection of the wing composite material is simulated to form a simulated detection path, and the simulated detection path is saved in the control system;

[0057] S2: after the aircraft completes the task, the detection device is moved to the wing, and pre-walking before detection is performed according to the pre-stored detection path of the system, the simulated detection path is detected and corrected, the distance from the cold cathode ray emitter and the DR imaging plate to the wing is detected by the ranging camera on the clamping plate, and the pre-detection data is fed back to the controller; if there is an error between the pre-detection result and the optimal detection model calculated, the electric control parameter model is adjusted;

[0058] S3: after the pre-detection path walking is completed and the path is adjusted, the first actual detection of the wing composite material is performed immediately, and the detection result is obtained;

[0059] S4: the same part on the wing is detected multiple times in time-sharing mode, and the change of the composite material structure from landing to complete static load is tracked and analyzed.

[0060] Further, the optimal detection model in the step S1 is simulated and calculated according to the distance from the cold cathode ray emitter to the lower surface of the wing, the distance from the DR imaging plate to the upper surface of the wing and the inclination angle of the two clamping plates corresponding to the inclined position of the wing.

[0061] Further, the electric control parameter model in the step S1 includes the walking direction and speed of the electric control roller, the lifting height and speed of the liftable support frame, and the lifting height and speed of the two arms of the U-shaped fixing frame. The walking speed of the electric control roller is matched with the lifting speed of the liftable support frame and the lifting speed of the two arms of the U-shaped fixing frame. In order to ensure the stability of the detection, the pre-walking is performed, the parameters adjusted in the detection process are saved in the control system, and the parameters are taken as a complete walking program. After the aircraft approaches, the system controls the detection vehicle to quickly complete the in-situ cold cathode ray detection of the wing.

[0062] Further, the electric control parameter model further includes the control of the cold cathode ray emitter, and corresponding cold cathode ray emission energy is set for the wing composite material of different thicknesses, so as to ensure the reliability of the detection result.

[0063] By setting the intelligent walking and the automatic detection mode, the wireless control device is operated without manual pushing detection, so that the detection efficiency is greatly improved, and the harm of the ray radiation to the human body is reduced. The detection method pre-simulates the shape contour of the aircraft wing through the computer, calculates the parameters of each electric control component to form an electric control parameter model by designing the best detection model, forms a simulated detection path, sets the simulated detection path, reduces the adjustment of the control in the detection process, makes the detection process more smooth, and improves the detection efficiency. The detection includes a rapid verification process of the simulated detection path after the aircraft approaches, that is, two steps of design pre-detection and actual detection. The pre-detection stage only needs to quickly walk and start the equipment, the pre-detection stage improves the reliability of the detection result, reasonably arranges the equipment starting time, saves the energy loss without affecting the detection.

[0064] Further, the time-sharing detection of the step S4 is divided into three times, that is, 1-10 minutes, 10-20 minutes, and 20-30 minutes after the aircraft approaches. Through the time-sharing detection, complete detection samples are obtained, which is beneficial to analysis and comparison. Through the analysis and comparison of the detection results in different time periods, the composite material can be more effectively monitored.

[0065] The above only describes the preferred embodiments of the present application and is not used to limit the present application. For those skilled in the art, the present application can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An in-situ cold cathode X-ray inspection device for wing composite materials, characterized in that, include: A base, wherein the base is equipped with an electrically controlled walking mechanism; A liftable support frame is connected to the base, and a U-shaped fixing frame is provided on the upper part of the liftable support frame; The clamping plate includes an upper clamping plate and a lower clamping plate. The two clamping plates are swayably connected to the two arms of the U-shaped fixing frame through an electrically controlled rotating connector. The distance between the two arms of the U-shaped fixing frame is adjustable. A cold cathode X-ray emitter and a DR imaging plate are respectively fixed on the inner sidewalls of two clamping plates. The cold cathode X-ray emitter is set on the lower clamping plate and emits cold cathode X-ray sources upward. A ranging camera, which is fixed on a corresponding clamping plate, is used to measure the distance between the detection device and the part of the wing to be inspected. The control module is wirelessly or wired to the electrically controlled walking mechanism, the lifting mechanism of the liftable support frame, the rotating mechanism of the U-shaped fixed frame, the electrically controlled rotating connector, and the ranging camera, and the control detection surface is multidimensionally adjustable to adapt to the shape of the wing.

2. A method for in-situ cold cathode X-ray inspection of wing composite materials, employing the inspection device as described in claim 1, characterized in that, The aircraft wing shape is pre-shaped using a smart, mobile cold cathode X-ray inspection device, forming an inspection path that is pre-stored in the control system. When the aircraft completes its flight mission and enters the inspection area, the inspection device is wirelessly controlled to automatically and quickly inspect the composite material of the aircraft wing. The specific steps are as follows: S1: A three-dimensional parametric model of the wing is established by computer. The thickness, curvature, and tilt angle of the composite material in different parts of the wing of the aircraft to be tested are measured in advance to form the optimal testing model. Based on the testing model, an electronic control parameter model of the testing equipment is established to simulate the testing of the wing composite material, form a simulated testing path, and save the simulated testing path in the control system. S2: After the aircraft completes its flight mission, the detection device is moved to the wing. Based on the detection path stored in the system, a pre-detection process is quickly performed. The distance from the cold cathode X-ray emitter and DR imaging plate to the wing is calculated by the ranging probe on the clamping plate. The pre-detection data is fed back to the controller. If there is an error between the pre-detection result and the simulated detection path calculated by the model, fine adjustments are made based on the simulated detection path according to the detection model. S3: After the pre-detection path is completed and the path is adjusted, the first actual test of the wing composite material is carried out. The various parts of the detection device are adjusted in conjunction to complete the path and obtain the test results. S4: Perform multiple tests on the same part of the wing at different times to track and analyze the changes in the health status of the composite material structure as the aircraft transitions from dynamic load to static load.

3. The in-situ cold cathode X-ray detection method for wing composite materials according to claim 2, characterized in that, The optimal detection model in step S1 is calculated based on the outer contour of the wing to simulate the distance from the cold cathode X-ray emitter to the lower surface of the wing, the distance from the DR imaging plate to the upper surface of the wing, and the tilt angle of the two clamping plates corresponding to the tilted part of the wing.

4. The in-situ cold cathode X-ray detection method for wing composite materials according to claim 3, characterized in that, The electronic control parameter model in step S1 includes the walking direction and speed of the electronically controlled rollers, the lifting height and speed of the liftable support frame, the lifting height and speed of the two arms of the U-shaped fixed frame, and the rotation angle and speed of the two electronically controlled rotating connectors.

5. The in-situ cold cathode X-ray detection method for wing composite materials according to claim 4, characterized in that, The electronic control parameter model also includes the control of the cold cathode X-ray emitter, setting the corresponding cold cathode X-ray emission energy for different thicknesses of wing composite materials.

6. The in-situ cold cathode X-ray detection method for wing composite materials according to claim 5, characterized in that, The time-division detection in step S4 is divided into three stages: 1-10 minutes, 10-20 minutes, and 20-30 minutes during aircraft arrival.

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