CN112731405B - Online ultrasonic measurement method and processing method for aircraft wall panel - Google Patents
Online ultrasonic measurement method and processing method for aircraft wall panel Download PDFInfo
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Abstract
The invention relates to an on-line ultrasonic measuring method and a processing method of an aircraft wallboard, and the on-line ultrasonic measuring method of the aircraft wallboard comprises the following steps: on-line ultrasonic measurement, ultrasonic energy-spreading analysis and embedded information fusion unit control ultrasonic on-line measurement numerical control device to conduct on-line measurement and energy collection on thickness of an aircraft panel to be measured and reflected ultrasonic energy, thickness measurement data and ultrasonic reflection energy are synchronously obtained, and the ultrasonic reflection energy comprises first ultrasonic energy without sharp reflection echo characteristics and second ultrasonic energy with sharp reflection echo characteristics; and (3) data processing, wherein the ultrasonic reflection energy is fed back to an ultrasonic energy analysis and embedded information fusion unit for processing. The invention also provides a processing method of the aircraft panel. The invention can be applied to the fields of vehicles, ships, aviation manufacturing technology and the like.
Description
Technical Field
The invention relates to the technical field of vehicle, ship and aviation manufacturing, in particular to an on-line ultrasonic measurement method and a processing method of an aircraft wallboard.
Background
When the aircraft panel parts are processed, ultrasonic measurement is required to be carried out on the processed parts. In the prior art, methods of ultrasonic measurement and processing are divided into two categories, such as in the measurement and processing of aircraft board type parts: in the first type of measuring and processing method, the adopted digital processing and assembling equipment for aircraft panel parts is not provided with an automatic online ultrasonic measuring device and cannot carry out online ultrasonic measurement; the measurement and positioning of the edge position of the inner-shaped boss of the aircraft panel requires complex positioning tools on processing equipment. The whole measuring and positioning process is completed by manual operation completely by means of a handheld measuring device. The manual intervention measurement positioning mode is long in time consumption and low in efficiency, and the accuracy and reliability of measurement data in the links of acquisition, recording, storage, transmission and the like are greatly reduced, so that the working efficiency and the processing quality of a post-compensation and processing and assembling system are seriously adversely affected.
In the second type of measuring and processing method, the digital processing and assembling equipment of the aircraft panel parts is provided with a traditional ultrasonic thickness measuring device, but the position of the edge of the inner-shaped boss of the aircraft panel can be judged only by a simple direct thickness measuring method. Referring to fig. 1, as shown in fig. 1, the method for calculating the thickness of the aircraft panel includes:
where d is aircraft panel thickness, c is material sonic velocity, t 0 Is the peak time position of the incident wave, t 1 Is the peak time position of the reflected wave at the bottom surface of the aircraft panel.
Referring to fig. 2, an ultrasonic measurement point of the critical area of the thickness variation of the aircraft panel is schematically shown in fig. 2. In the second type of measurement and processing method, since the thickness measurement of the aircraft panel can be performed simply by relying on ultrasonic energy having a characteristic of a sharp reflection echo, it is difficult to perform an effective thickness measurement for a critical area of thickness variation, i.e., an ultrasonic energy diffusion surface, where a sharp reflection echo cannot be formed as shown in fig. 2. The reaction is on the measurement and the location of the edge position of the inner-shaped boss of the aircraft panel, thereby causing confusion and larger data errors of measurement information and instability in positioning accuracy. The measurement results are shown in fig. 3a and 3 b. Therefore, the integrated application of the on-line ultrasonic measurement and the accurate positioning technology of the inner shape of the aircraft panel is greatly limited; and the precision, speed, efficiency and quality of the aircraft panel parts in the digital processing and assembling process are difficult to improve.
In the prior art, no matter how to rely on setting a complex positioning tool, and then manually operating the tool by using a handheld measuring device; and also based on the ultrasonic thickness measurement principle, the measurement and positioning technology for carrying out qualitative evaluation according to the thickness data of the aircraft panel. The measurement of the edge position of an interior boss of an aircraft panel presents serious accuracy and data stability problems due to the invisibility of the interior shape feature and the presence of a diffusing surface of ultrasonic energy in the vicinity of the measured position. For the first type of measurement and processing method, the time consumption is long, the efficiency is low, and the accuracy and the reliability of measurement data in the links of acquisition, recording, storage, transmission and the like are greatly reduced. For the second type of measurement and processing method, because the diffusion surface of the ultrasonic energy is seriously non-parallel to the probe surface of the ultrasonic transducer or the normal direction of the diffusion surface is not coaxial with the probe surface of the ultrasonic transducer, the thickness measurement data is disturbed and the thickness measurement information is completely lost, so that the acquired data is often insufficient to obtain an accurate positioning evaluation result. Furthermore, for convenience of operation and space saving, digital processing and assembly of aircraft panel parts are often performed in a vertical hanging posture. This makes it difficult to ensure good and consistent contact (water flowing down) between the water-based couplant and the ultrasonic thickness probe on aircraft panel parts by conventional ultrasonic thickness measurement methods, which further affects the stability of the ultrasonic measurement results.
Accordingly, the inventors provide an on-line ultrasonic measurement method and processing method that enables accurate measurement and positioning of aircraft panels.
Disclosure of Invention
(1) Technical problem to be solved
The embodiment of the invention provides an online ultrasonic measurement method and a processing method of an aircraft panel, which can collect second ultrasonic energy with vivid reflection echo characteristics and collect first ultrasonic energy without vivid reflection echo characteristics by creatively introducing an ultrasonic energy analysis method. The ultrasonic energy analysis and embedded information fusion unit can fuse the perceived ultrasonic measurement information, the real-time online motion control information and the digital model information of the processed aircraft wall plate with the depth data to obtain the wall thickness information of the aircraft wall plate and the data information of the edge position of the inner-shape convex-concave table of the aircraft wall plate, thereby realizing the online ultrasonic measurement and accurate positioning of the inner shape of the aircraft wall plate and improving the quality, precision and efficiency of the digital processing and assembly of the aircraft wall plate parts of the aircraft.
(2) Technical proposal
In a first aspect, an embodiment of the present invention provides an on-line ultrasonic measurement method for an aircraft panel, including the steps of:
the method comprises the steps of on-line ultrasonic measurement, an ultrasonic energy-spreading analysis and embedded information fusion unit sends a measurement instruction and a control instruction to an ultrasonic on-line measurement device, and the ultrasonic on-line measurement device performs on-line measurement and information acquisition of ultrasonic reflection energy on the thickness of an aircraft panel to be measured and the reflected ultrasonic energy to synchronously obtain thickness measurement data and ultrasonic reflection energy; the ultrasonic energy includes a first ultrasonic energy exhibiting diffuse reflection and a second ultrasonic energy having a characteristic of sharp echo reflection;
and (3) data processing, wherein the ultrasonic reflected energy is fed back to an ultrasonic energy analysis and embedded information fusion unit, the first ultrasonic energy is processed into first ultrasonic data in the form of dark information or gray information, and the second ultrasonic energy is processed into second ultrasonic data, namely thickness measurement data. The first ultrasonic data and the second ultrasonic data are respectively fed back to the ultrasonic energy analysis and embedded information fusion unit for data processing, and the wall thickness information of the aircraft panel and the data information of the edge position of the inner-shaped convex-concave table of the aircraft panel can be obtained by combining the coordinate position information of the numerical control measurement platform through data processing.
Further, in the step of online ultrasonic measurement, the ultrasonic energy analysis and embedded information fusion unit sends measurement instructions and control instructions to an ultrasonic online measurement device, and the ultrasonic online measurement device performs online measurement of the thickness of the aircraft panel and comprehensive collection of ultrasonic reflection energy so as to obtain thickness measurement data and ultrasonic reflection energy in a specified time range at the same time.
Further, in the on-line measuring step, when a preset time or a preset condition is triggered in a measuring state, the water-based coupling agent is poured into the ultrasonic measuring transducer at the measuring position of the aircraft panel through the quantitative pouring device.
Further, an electromagnetic insulation device is arranged between the ultrasonic measuring transducer and the ultrasonic energy analysis and embedded information fusion unit.
In a second aspect, there is provided a method of processing an aircraft panel using the method of on-line ultrasonic measurement of an aircraft panel of the first aspect, comprising the steps of:
measuring the wall thickness of the aircraft wall panel and collecting ultrasonic reflection energy, measuring the wall thickness of the aircraft wall panel by adopting the aircraft wall panel measuring method, and obtaining the ultrasonic reflection energy in a specified time;
and the ultrasonic energy analysis and embedded information fusion unit sends the wall thickness data of the aircraft wall and the ultrasonic reflection energy intensity data to the numerical control platform, and the numerical control platform processes the unfinished aircraft wall into a finished aircraft wall according to the received wall thickness data of the aircraft wall and the ultrasonic reflection energy intensity data.
Further, in the step of processing the aircraft panel, the ultrasonic energy analysis and embedded information fusion unit transmits the wall thickness data and the ultrasonic reflection energy intensity data of the aircraft panel to the numerical control platform through site association information.
Further, in the step of processing the aircraft panel, the numerical control platform is used for processing the aircraft panel through computer remote control.
Further, the computer remotely controls the numerical control platform to process the aircraft panel through remote association information.
(3) Advantageous effects
In summary, compared with the first type measurement and processing method and the second type measurement and processing method in the prior art, the method for performing online ultrasonic measurement on the aircraft wall plate can accurately obtain thickness data of the aircraft wall plate, can acquire ultrasonic reflection energy information of the aircraft wall plate in real time, and can realize accurate online measurement and accurate positioning on the positions of the inner boss and the like of the aircraft wall plate. The method not only can carry out simple inner shape contour judgment measurement according to thickness measurement data, but also can carry out complex identification positioning and measurement of the inner shape contour of the aircraft panel by collecting the first ultrasonic energy and the second ultrasonic energy and analyzing the intensity distribution and the change trend of the first ultrasonic energy and the second ultrasonic energy. The aircraft panel measuring method of the invention can effectively solve the problem of disturbance of measuring and positioning data caused by non-parallel or normal non-coaxial ultrasonic diffuse surface and ultrasonic probe surface. The on-line ultrasonic measuring method of the aircraft wall panel can be widely applied to the manufacturing fields of high-speed rails, automobiles, ships and the like.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and other drawings may be obtained according to the evolution of these drawings without the need of creative efforts for a person skilled in the art.
FIG. 1 is a schematic diagram of the principle of ultrasonic thickness measurement;
FIG. 2 is a schematic illustration of ultrasonic measurement points of critical areas of aircraft panel thickness variation;
FIG. 3a is a schematic diagram of a measurement point signal forming a sharp reflection echo in a second type of measurement and processing method of the background art;
FIG. 3b is a schematic diagram of a measurement point signal that is difficult to form a sharp reflection echo in a second type of measurement and processing method of the background art; the method comprises the steps of carrying out a first treatment on the surface of the
FIG. 4 is a schematic illustration of an on-line ultrasonic measurement method of an aircraft panel according to an embodiment of the invention;
FIG. 5 is a schematic view of ultrasonic echo energy distribution during ultrasonic measurement of an aircraft panel geometry in accordance with an embodiment of the present invention;
fig. 6 is a schematic view of a method of processing aircraft panels according to an embodiment of the invention.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention and are not intended to limit the scope of the invention, i.e., the invention is not limited to the embodiments described, but covers any modifications, substitutions and improvements in parts, components and connections without departing from the spirit of the invention.
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The present application will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
An on-line ultrasonic measurement method for aircraft panels, comprising the steps of:
the method comprises the steps of on-line ultrasonic measurement, an ultrasonic energy-spreading analysis and embedded information fusion unit sends a measurement instruction and a control instruction to an ultrasonic on-line measurement device, and the ultrasonic on-line measurement device performs on-line measurement and energy acquisition on the thickness of an aircraft panel to be measured and reflected ultrasonic energy to synchronously obtain thickness measurement data and ultrasonic reflected energy; the ultrasonic energy includes a first ultrasonic energy exhibiting diffuse reflection and a second ultrasonic energy having a characteristic of sharp echo reflection;
and (3) data processing, wherein the ultrasonic reflected energy is fed back to an ultrasonic energy analysis and embedded information fusion unit, the first ultrasonic energy is processed into first ultrasonic data in the form of dark information or gray information, and the second ultrasonic energy is processed into second ultrasonic data, namely thickness measurement data. The first ultrasonic data and the second ultrasonic data are respectively fed back to the ultrasonic energy analysis and embedded information fusion unit for data processing, and the wall thickness information of the aircraft panel and the data information of the edge position of the inner-shaped convex-concave table of the aircraft panel can be obtained by combining the coordinate position information of the numerical control measurement platform through data processing.
The on-line ultrasonic measuring method of the aircraft panel of the embodiment creatively introduces the idea of ultrasonic energy analysis based on the traditional second-class measuring and processing method. That is, the diffusely reflected first ultrasonic energy which is considered to be ineffective and exists in the traditional ultrasonic measurement is included in the perception system of the ultrasonic measurement in the form of dark information or gray information, so that the ultrasonic energy analysis and embedded information fusion unit mainly comprises an embedded system can collect the second ultrasonic energy with the characteristic of vivid reflection echo, namely thickness measurement data. And the first ultrasonic energy without the characteristic of clear reflection echo, namely the diffuse reflection energy of the ultrasonic wave caused by the fact that the surface of the measured material is not parallel to the head surface of the ultrasonic transducer or the normal direction of the ultrasonic transducer is not coaxial with the head surface of the ultrasonic transducer, can be acquired. In the on-line ultrasonic measurement method of the aircraft panel of the embodiment, taking the measurement of the aircraft panel as an example, specifically, as shown in fig. 4, for on-line ultrasonic measurement and accurate positioning of the edge position of the inner boss of the aircraft panel shown in fig. 4, the conventional solution thinking is to obtain thickness variation data of the aircraft panel by simple thickness measurement operation, and judge the edge position of the inner boss of the aircraft panel by a method of directly comparing the thickness measurement data. Although the method seems to be feasible, the method has the problems of larger error in measurement and instability in positioning accuracy. The reason for this is that the ultrasonic measuring device in fig. 4 must perform a thin-to-thick or thick-to-thin measurement of the vicinity of the inner boss of the panel in order to obtain critical data sufficient to determine the edge position of the inner boss of the panel when acquiring the thickness variation data of the panel, whether measured in the positive spanwise direction or in the negative spanwise direction. It is this variation in the thickness of the interior shape of the aircraft panel that forms the diffusing surface for ultrasonic energy as shown in fig. 4. The diffusion surface reflecting the first ultrasonic energy is seriously non-parallel to the head surface of the ultrasonic transducer or the normal direction of the diffusion surface is not coaxial with the head surface of the ultrasonic transducer, so that the turbulence error of the thickness measurement data is definitely caused, and even the thickness measurement information is completely lost; in this way, serious problems of precision and stability can occur in ultrasonic measurement of the edge position of the inner-shaped boss of the aircraft panel. The difference between this embodiment is that, when the numerical control platform processes the aircraft panel, by embedding the ultrasonic energy analysis and embedded information fusion unit in the numerical control platform, not only the thickness measurement data of the aircraft panel is obtained in the process of online ultrasonic measurement and accurate positioning of the edge position of the inner boss of the aircraft panel, but also the reflected ultrasonic energy (including the ultrasonic reflected energy from the specular reflection surface and the diffuse reflection surface) is collected, analyzed, processed and evaluated, and in particular, the first ultrasonic energy of the ultrasonic energy diffusion surface in fig. 4 is analyzed and processed. On the diffuse surface of ultrasonic energy, it is difficult for the ultrasonic measuring transducer to acquire echo information sufficient to determine the measured thickness due to energy diffusion in terms of the intensity of ultrasonic energy reflected by the measured surface; however, the intensity of the ultrasonic energy collected by the ultrasonic measuring transducer on the whole diffusion surface of the ultrasonic energy is changed in intensity according to the curvature of the diffusion surface, so that the digital gray information and the dark information marked by the intensity of the ultrasonic energy are formed. The ultrasonic echo energy distribution corresponding to the ultrasonic measurement process of the aircraft panel thickness variation region shown in fig. 2 is shown in fig. 5. The five ultrasonic energy feedback positions are shown as well as position 3, and other positions have clear ultrasonic thickness measurement echo feedback signals, and position 3 is located on the critical line of the thickness change of the inner shape. Although clear thickness measurement information cannot be obtained at this position, the reflected energy of the ultrasonic wave is acquired although it is greatly attenuated due to scattering. Experiments prove that when the measurement positioning process shown in fig. 4 is carried out in the forward direction, the high point position of the edge of the inner-shaped boss of the aircraft panel is just at the inflection point position where the intensity of ultrasonic reflection energy acquired by the ultrasonic measurement transducer is suddenly enhanced from strong to weak. When the measuring and positioning process shown in fig. 4 is performed according to the negative spanwise direction, the high point position of the edge of the inner-shaped boss of the aircraft panel to be obtained is located at the inflection point position of the intensity of ultrasonic reflection energy from strong to weak. The analysis and processing results of ultrasonic energy are fused with the high-precision positioning information of the numerical control motion platform, so that the on-line ultrasonic measurement and the accurate positioning of the inner shape outline position of the aircraft panel can be realized.
Compared with the first type of measuring and processing method and the second type of measuring and processing method in the prior art, the method for performing online ultrasonic measurement on the aircraft wall plate can accurately obtain thickness data of the aircraft wall plate, can acquire ultrasonic reflection energy information of the aircraft wall plate in real time, and can accurately perform online measurement and accurate positioning on the inner boss and other positions of the aircraft wall plate. The method not only can carry out simple inner shape contour judgment measurement according to thickness measurement data, but also can carry out complex identification positioning and measurement of the inner shape contour of the aircraft panel by collecting the first ultrasonic energy and the second ultrasonic energy and analyzing the intensity distribution and the change trend of the first ultrasonic energy and the second ultrasonic energy. The on-line ultrasonic measuring method for the aircraft panel of the embodiment can effectively solve the problem of disturbance of measuring and positioning data caused by non-parallel or normal non-coaxial ultrasonic diffusion surfaces and ultrasonic probe surfaces. The on-line ultrasonic measuring method of the aircraft wall panel can be widely applied to the manufacturing fields of high-speed rails, automobiles, ships and the like.
In this embodiment, as a further improvement of the above technical solution, in the online measurement step, the present solution may further use an electromagnetic ultrasonic measurement device to perform online electromagnetic ultrasonic measurement. Because electromagnetic ultrasonic measurement is an ultrasonic measurement mode which can be carried out in a non-contact way, the system can thoroughly discard a complex and heavy water-based couplant supply and recovery system attached to the traditional online ultrasonic measurement, and the online ultrasonic measurement and accurate positioning system is lighter. In addition, due to the fact that the device has the characteristic of inclination redundancy, when in online automatic measurement, even if a part to be measured has certain deformation, the measured contact position and the contact normal direction are subjected to limited deviation, ultrasonic reflection energy and accurate positioning information of an inner boss of an aircraft wallboard can be accurately acquired, and accordingly reliability and stability of online ultrasonic measurement and accurate positioning of the inner boss of the aircraft wallboard can be further guaranteed.
In order to solve the problem of poor contact of the water-based couplant when the vertical suspension posture is used for ultrasonic measurement of aircraft panel parts of an aircraft, in the embodiment, as a further improvement of the technical scheme, in the online measurement step, when the preset time or the preset condition is triggered in the measurement state, the water-based couplant is poured into the ultrasonic measurement transducer at the measurement position of the aircraft panel through the quantitative pouring device. The ultrasonic measuring transducer is additionally provided with technical measures such as water absorbing or water retaining materials and the like so as to ensure that the water-based coupling effect of the water-based coupling agent poured each time is enough to complete a complete process of ultrasonic on-line measurement and accurate positioning of the aircraft panel. In the on-line ultrasonic measuring method of the aircraft panel, an on-line ultrasonic measuring tool which combines the numerical control platform and the ultrasonic measuring transducer and has the functions of extension and guide is additionally designed, so that the normal contact effect between the aircraft panel and the ultrasonic measuring transducer in the ultrasonic measuring and positioning process is ensured. Thereby being beneficial to improving the precision of on-line measurement and positioning of the inner shape of the aircraft panel.
In this embodiment, as a further improvement of the above technical solution, an electromagnetic insulation device is disposed between the ultrasonic measurement transducer and the ultrasonic energy analysis and embedded information fusion unit, so as to prevent electromagnetic interference in the numerical control manufacturing site from adversely affecting measurement and positioning accuracy through a water-based coupling object.
In a second aspect, the invention also provides a processing method of the aircraft panel, which adopts the following technical scheme:
a method of processing aircraft panels comprising the steps of:
measuring the wall thickness of the aircraft wall panel and collecting ultrasonic reflection energy, and obtaining the wall thickness of the aircraft wall panel and ultrasonic reflection energy in a specified time by adopting the online ultrasonic measurement method of the aircraft wall panel;
and processing the aircraft panel, wherein the ultrasonic energy analysis and embedded information fusion unit transmits the wall thickness data of the aircraft panel and the ultrasonic reflection energy intensity data to the numerical control platform, and the numerical control platform processes the unfinished aircraft panel into a finished aircraft panel according to the received wall thickness data of the aircraft panel. In the specific embodiment of machining aircraft panels, the numerically controlled platform is collectively referred to as an aircraft panel machining and assembly motion control platform, and the computer is collectively referred to as a telematics processor (a general purpose computer that is directly networked with an on-site system).
The steps of measuring the wall thickness of the aircraft panel and collecting the ultrasonic reflection energy intensity data in the method for processing the aircraft panel of the embodiment also have the advantages, and are not described herein. Based on accurate wall thickness data and ultrasonic reflection energy intensity data of the aircraft wall plate, the numerical control platform can process finished aircraft wall plates with higher precision, and the processing method of the aircraft wall plates can be widely applied to the manufacturing fields of high-speed rails, automobiles, ships and the like.
In this embodiment, as a further improvement of the above technical solution, in the step of processing the aircraft panel, the embedded information fusion unit sends the wall thickness data of the aircraft panel and the ultrasonic reflection energy intensity data to the numerical control platform through the site association information.
In this embodiment, as a further improvement of the foregoing technical solution, in the step of processing the aircraft panel, the numerical control platform remotely controls to process the aircraft panel through a computer.
In this embodiment, as a further improvement of the above technical solution, the computer remotely controls the numerical control platform to process the aircraft panel through remote associated information. And fusing the on-line acquired inner shape contour thickness information of the aircraft panel part, ultrasonic reflection energy intensity data and accurate positioning information with on-site associated information through remote associated information. The ultrasonic energy analysis and embedded information fusion unit can process the perceived thickness information of the inner shape outline of the aircraft panel, ultrasonic reflection energy intensity data, edge position information obtained by ultrasonic energy analysis, and gray information or dark information formed by variable ultrasonic reflection energy from an ultrasonic diffusion surface. The ultrasonic measurements of the interior shape of the aircraft panel are ultimately determined by comparison, analysis and evaluation with existing process data models. Under the control of a computer, the unfinished aircraft panel is processed into a finished aircraft panel through a numerical control platform.
Based on the combination of the above embodiments, please refer to fig. 6 again, the processing method of the aircraft panel of this embodiment is shown in fig. 6. The ultrasonic energy analysis and embedded information fusion unit in fig. 6 is a core control processing device in the whole system. In the process of online ultrasonic measurement and accurate positioning of the inner shape of the aircraft wall panel, the core unit decides an online ultrasonic measurement method (comprising the relation between motion control information and measurement control instructions, the rhythm and step pitch of collecting ultrasonic measurement information, the supplement equivalent and time of a couplant, the matching of feedback thickness measurement data and ultrasonic energy and the like) of the aircraft wall panel according to site related information, remote related information (comprising operation control information, system state information and the like) and own software and hardware state information from a numerical control system and a remote computer for processing and assembling the aircraft wall panel. The numerical control programming system programs the track of the on-line numerical control ultrasonic measurement of the aircraft panel according to the existing design data model. The numerical control platform runs according to the programmed track, and acquires thickness information of the inner shape outline of the aircraft panel, ultrasonic reflection energy intensity data and accurate positioning perception information in real time on line. The on-line ultrasonic measuring system shown in fig. 6 fuses perceived inner shape contour thickness information of an aircraft panel, edge position information obtained through ultrasonic energy analysis, and gray information or dark information formed by variable ultrasonic reflection energy from an ultrasonic diffusion surface with control information of a numerical control platform by means of a data correlation network and a remote data information processing system, and performs comprehensive data processing of depth. And on the basis of comparison, analysis and evaluation of the existing processing data model, a digital ultrasonic measurement result of the inner shape of the aircraft panel is obtained.
It should be understood that, in the present specification, each embodiment is described in an incremental manner, and the same or similar parts between the embodiments are all referred to each other, and each embodiment is mainly described in a different point from other embodiments. The invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known method techniques is omitted here for the sake of brevity.
The foregoing is merely exemplary of the present application and is not limited thereto. Various modifications and alterations of this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modifications, equivalent substitutions, improvements, etc. which are within the spirit and principles of the present application are intended to be included within the scope of the claims of the present application.
Claims (8)
1. An on-line ultrasonic measurement method for an aircraft panel is characterized by comprising the following steps:
the method comprises the steps that online ultrasonic measurement is carried out, an ultrasonic energy-spreading analysis and embedded information fusion unit sends measurement instructions and control instructions to an ultrasonic online measurement device, the ultrasonic online measurement device carries out thickness online measurement and ultrasonic reflection energy information acquisition on an aircraft panel to be measured, thickness measurement data and ultrasonic reflection energy are synchronously obtained, and the ultrasonic reflection energy comprises first ultrasonic energy without sharp reflection echo characteristics and second ultrasonic energy with sharp reflection echo characteristics;
data processing, wherein the ultrasonic reflected energy is fed back to an ultrasonic energy analysis and embedded information fusion unit, the first ultrasonic energy is processed into first ultrasonic data in the form of dark information or gray information, and the second ultrasonic energy is processed into second ultrasonic data; the first ultrasonic data and the second ultrasonic data are respectively fed back to the ultrasonic energy analysis and embedded information fusion unit for data processing, and the wall thickness information of the aircraft wall plate and the data information of the edge position of the inner-shaped convex-concave table of the aircraft wall plate are obtained by combining the coordinate position information of the numerical control measurement platform through data processing.
2. The method for on-line ultrasonic measurement of an aircraft panel according to claim 1, wherein in the on-line ultrasonic measurement step, the ultrasonic energy-in-a-field analysis and embedded information fusion unit issues measurement instructions and control instructions to an ultrasonic on-line measurement device, and the ultrasonic on-line measurement device performs on-line measurement of thickness and information acquisition of ultrasonic reflection energy on the aircraft panel to synchronously obtain thickness measurement data and ultrasonic reflection energy within a specified time range.
3. The method for on-line ultrasonic measurement of an aircraft panel according to claim 1, wherein in the on-line measurement step, the ultrasonic measurement transducer at the aircraft panel measurement site is perfused with the water-based couplant by the quantitative perfusion device when a preset time or preset condition is triggered in the measurement state.
4. An on-line ultrasonic measurement method of aircraft panels according to claim 3, wherein electromagnetic insulation means are provided between the ultrasonic measurement transducer and the ultrasonic energy analysis and embedded information fusion unit.
5. A method of processing an aircraft panel, comprising the steps of:
measuring the wall thickness of the aircraft wall panel and collecting ultrasonic reflection energy, measuring the wall thickness of the aircraft wall panel by adopting the online ultrasonic measurement method of the aircraft wall panel according to any one of claims 1-4, and obtaining the ultrasonic reflection energy in a specified time;
and the ultrasonic energy analysis and embedded information fusion unit sends the wall thickness data of the aircraft wall and the ultrasonic reflection energy intensity data to the numerical control platform, and the numerical control platform processes the unfinished aircraft wall into a finished aircraft wall according to the received wall thickness data of the aircraft wall and the ultrasonic reflection energy intensity data.
6. The method according to claim 5, wherein in the step of processing the panel, the ultrasonic energy analysis and embedded information fusion unit transmits the panel wall thickness data and the ultrasonic reflected energy intensity data to the numerical control platform through field association information.
7. The method of claim 5, wherein in the step of machining the aircraft panel, the numerical control platform remotely controls machining of the aircraft panel by a computer.
8. The method of claim 7, wherein the computer remotely controls the numerical control platform to process the aircraft panel via remote associated information.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110002328.7A CN112731405B (en) | 2021-01-04 | 2021-01-04 | Online ultrasonic measurement method and processing method for aircraft wall panel |
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