阅读说明：本技术 一种飞机壁板的在线超声测量方法及加工方法 (Online ultrasonic measurement method and processing method of airplane wallboard ) 是由 甘露 张为民 于 2021-01-04 设计创作，主要内容包括：本发明涉及一种飞机壁板的在线超声测量方法及加工方法,一种飞机壁板的在线超声测量方法,包括以下步骤：在线超声测量,超声泛能量分析与嵌入式信息融合单元控制超声在线测量数控装置对待测飞机壁板的厚度及反射的超声能量进行在线测量和能量采集,同步地得到测厚数据和超声反射能量,所述超声反射能量包括不具有鲜明反射回波特征的第一超声能量和具有鲜明反射回波特征的第二超声波能量；数据处理,所述超声反射能量被反馈给超声泛能量分析与嵌入式信息融合单元进行处理。本发明还提供了一种飞机壁板的加工方法。本发明可应用于车、船、航空制造技术等领域。(The invention relates to an online ultrasonic measurement method and a processing method of an aircraft panel, and the online ultrasonic measurement method of the aircraft panel comprises the following steps: the method comprises the steps of online ultrasonic measurement, wherein an ultrasonic general energy analysis and embedded information fusion unit controls an ultrasonic online measurement numerical control device to perform online measurement and energy acquisition on the thickness and reflected ultrasonic energy of a wallboard of the airplane to be measured, and thickness measurement data and ultrasonic reflection energy are synchronously obtained, wherein the ultrasonic reflection energy comprises first ultrasonic energy without a distinct reflection echo characteristic and second ultrasonic energy with a distinct reflection echo characteristic; and data processing, wherein the ultrasonic reflection energy is fed back to the ultrasonic general energy analysis and embedded information fusion unit for processing. The invention also provides a processing method of the aircraft wall plate. The invention can be applied to the fields of vehicle, ship, aviation manufacturing technology and the like.)

1. An on-line ultrasonic measurement method for an aircraft wall plate is characterized by comprising the following steps:

the method comprises the steps that on-line ultrasonic measurement is carried out, an ultrasonic general energy analysis and embedded information fusion unit sends a measurement instruction and a control instruction to an ultrasonic on-line measurement device, the ultrasonic on-line measurement device carries out on-line thickness measurement and ultrasonic reflection energy information acquisition on a to-be-measured airplane wall plate, thickness measurement data and ultrasonic reflection energy are synchronously obtained, and the ultrasonic reflection energy comprises first ultrasonic energy without a vivid reflection echo characteristic and second ultrasonic energy with a vivid reflection echo characteristic;

the ultrasonic reflected energy is fed back to an ultrasonic general energy analysis and embedded information fusion unit, the first ultrasonic energy is processed into first ultrasonic data in the form of dark information or grey information, and the second ultrasonic energy is processed into second ultrasonic data; and the first ultrasonic data and the second ultrasonic data are respectively fed back to the ultrasonic general 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 concave-convex platform in the inner shape of the aircraft wall plate are obtained by data processing and combining the coordinate position information of the numerical control measuring platform.

2. The on-line ultrasonic measurement method of the aircraft wall panel according to claim 1, wherein in the on-line ultrasonic measurement step, the ultrasonic flood energy 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 of the thickness and information acquisition of ultrasonic reflection energy on the aircraft wall panel to synchronously obtain thickness measurement data and ultrasonic reflection energy within a specified time range.

3. The aircraft panel measurement method according to claim 1, wherein in the online measurement step, the ultrasonic measurement transducer at the aircraft panel measurement position is filled with the water-based couplant through a quantitative filling device when a preset time or preset conditions are triggered in the measurement state.

4. The on-line ultrasonic measurement method of the aircraft wall plate according to claim 3, wherein an electromagnetic insulation device is arranged between the ultrasonic measurement transducer and the ultrasonic flood energy analysis and embedded information fusion unit.

5. A method for processing an aircraft panel is characterized by comprising the following steps:

measuring the wall thickness of the aircraft wall and acquiring ultrasonic reflection energy, measuring the wall thickness of the aircraft wall by adopting the aircraft wall measuring method as claimed in claims 1-4, and acquiring the ultrasonic reflection energy within a specified time;

and processing the aircraft wall plate, wherein the ultrasonic flood energy analysis and embedded information fusion unit sends the wall thickness data and the ultrasonic reflection energy intensity data of the aircraft wall plate to the numerical control platform, and the numerical control platform processes the unfinished aircraft wall plate into a finished aircraft wall plate according to the received wall thickness data and the ultrasonic reflection energy intensity data of the aircraft wall plate.

6. The aircraft wall panel processing method according to claim 5, wherein in the aircraft wall panel processing step, the ultrasonic flood energy analysis and embedded information fusion unit sends the aircraft wall panel wall thickness data and the ultrasonic reflected energy intensity data to the numerical control platform through field correlation information.

7. The method of processing an aircraft panel according to claim 5, wherein in the step of processing an aircraft panel, the numerical control platform remotely controls the processing of the aircraft panel by a computer.

8. The method of processing an aircraft panel according to claim 7 wherein the computer processes the aircraft panel by remotely associating information with a remotely controlled numerically controlled platform.

Technical Field

The invention relates to the technical field of vehicle, ship and aviation manufacturing, in particular to an online ultrasonic measurement method and a processing method for an aircraft panel.

Background

When the parts such as the wall plates of the airplane are machined, ultrasonic measurement needs to be carried out on the machined parts. For example, in the measurement and processing of aircraft plate parts, in the prior art, the methods of ultrasonic measurement and processing are divided into two categories: in the first type of measuring and processing method, the adopted digital processing and assembling equipment of the aircraft wallboard parts of the aircraft does not have an automatic online ultrasonic measuring device and cannot carry out online ultrasonic measurement; the measurement and the positioning of the edge position of the inner-shaped boss of the aircraft panel require a complex positioning tool to be arranged on processing equipment. The whole measuring and positioning process is completely completed by manual operation by means of handheld measuring equipment. The measurement positioning mode intervened by manual intervention not only has long time consumption and low efficiency, but also greatly reduces the accuracy and reliability of measured data in the links of acquisition, recording, storage, transmission and the like, thereby causing the working efficiency and the processing quality of a post-compensation, processing and assembly system to be seriously adversely affected.

In the second type of measuring and processing method, the digital processing and assembling equipment for the aircraft wallboard parts of the aircraft is provided with a traditional ultrasonic thickness measuring device, but the position of the inner-shaped boss edge of the aircraft wallboard can be judged only by a simple direct thickness measuring method. Referring to fig. 1, as shown in fig. 1, a method for calculating the thickness of an aircraft panel includes:

where d is the aircraft panel thickness, c is the material sound velocity, t₀Is the peak time position, t, of the incident wave₁Is the peak time position of the reflected wave on the bottom surface of the wall plate of the airplane.

Referring to fig. 2, a schematic diagram of ultrasonic measurement points in a critical area of aircraft panel thickness variation is shown in fig. 2. In the second type of measurement and processing method, since the thickness measurement of the aircraft panel can be performed only by simply relying on the ultrasonic energy having the characteristic of the sharp reflection echo, it is difficult to perform an effective thickness measurement for the critical region of thickness variation, i.e., the ultrasonic energy diffusion surface, in which the sharp reflection echo cannot be formed as shown in fig. 2. The method is reflected in the measurement and positioning of the edge position of the inner-shaped boss of the aircraft panel, and the confusion of measurement information, larger data error and instability in positioning accuracy are caused. The measurement results are shown in fig. 3a and 3 b. Therefore, the integrated application of the online ultrasonic measurement and accurate positioning technology of the inner shape of the aircraft wall plate is greatly limited; further, the precision, speed, efficiency and quality of the aircraft wall plate parts in the digital processing and assembling process are difficult to improve.

In the prior art, no matter a complicated positioning tool is set, and then manual operation is carried out by holding a measuring device; the method is a measurement positioning technology which is based on the ultrasonic thickness measurement principle and carries out qualitative evaluation according to the thickness data of the aircraft panel. The measurement of the edge position of the female boss of an aircraft panel presents serious accuracy and data stability problems due to the invisibility of the female feature and the existence of the ultrasonic energy diffusion surface near the measured position. For the first kind of measuring and processing method, not only is the time consumption long and the efficiency low, but also the accuracy and the reliability of the measured data in the links of collection, recording, storage, transmission and the like are greatly reduced. For the second kind of measurement and processing method, because the diffusion surface of the ultrasonic energy and the probe surface of the ultrasonic transducer are not parallel or normal to different axes, 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, the digital processing and assembly of aircraft panel-like components is often carried out in a vertically suspended position. This makes it difficult for conventional ultrasonic thickness measurement methods to ensure good and continuous contact (water flowing down) between the water-based couplant and the ultrasonic thickness measurement probe on the aircraft wallboard-like parts, which further affects the stability of the ultrasonic measurement result.

Therefore, the inventor provides an online ultrasonic measuring method and a processing method which can accurately measure and position the wall plate of the airplane.

Disclosure of Invention

(1) Technical problem to be solved

The embodiment of the invention provides an on-line ultrasonic measurement method and a processing method of an aircraft panel, and not only can second ultrasonic energy with a distinct reflection echo characteristic be acquired, but also first ultrasonic energy without the distinct reflection echo characteristic can be acquired by creatively introducing an ultrasonic flood energy analysis method. By means of the ultrasonic universal energy analysis and embedded information fusion unit, the ultrasonic measurement information, the real-time online motion control information and the digital model information of the processed aircraft wall plate can be sensed and subjected to deep data fusion to obtain the wall thickness information of the aircraft wall plate and the data information of the edge position of the concave-convex platform of the inner shape of the aircraft wall plate, so that the online ultrasonic measurement and accurate positioning of the inner shape of the aircraft wall plate are realized, and the quality, the precision and the efficiency of the digital processing and assembling of aircraft wall plate parts of an aircraft are improved.

(2) Technical scheme

In a first aspect, an embodiment of the present invention provides an online ultrasonic measurement method for an aircraft panel, including the following steps:

the online ultrasonic measurement, the ultrasonic general energy analysis and embedded information fusion unit sends a measurement instruction and a control instruction to an ultrasonic online measurement device, the ultrasonic online measurement device carries out online measurement and ultrasonic reflection energy information acquisition on the thickness and reflected ultrasonic energy of the wall plate of the airplane to be measured, and thickness measurement data and ultrasonic reflection energy are synchronously obtained; the ultrasonic energy comprises first ultrasonic energy exhibiting diffuse reflectance and second ultrasonic energy characterized by distinct echogenicity;

and data processing, wherein the ultrasonic reflection energy is fed back to the ultrasonic general energy analysis and embedded information fusion unit, the first ultrasonic energy is processed into first ultrasonic data in a dark information or grey information mode, 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 general 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 concave-convex platform in the inner shape of the aircraft wall plate can be obtained through data processing and combining with the coordinate position information of the numerical control measuring platform.

Further, in the online ultrasonic measurement step, the ultrasonic general energy analysis and embedded information fusion unit sends a measurement instruction and a control instruction to the ultrasonic online measurement device, and the ultrasonic online measurement device performs online thickness measurement and comprehensive acquisition of ultrasonic reflection energy on the aircraft wall plate to obtain thickness measurement data and ultrasonic reflection energy within a specified time range at the same time.

Further, in the online measurement step, in the measurement state, when the preset time or the preset condition is triggered, the ultrasonic measurement transducer at the measurement position of the aircraft panel is filled with the water-based couplant through the quantitative filling device.

Furthermore, an electromagnetic insulating device is arranged between the ultrasonic measurement transducer and the ultrasonic extensive 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 online ultrasonic measurement of an aircraft panel of the first aspect, comprising the steps of:

measuring the wall thickness of the aircraft wall plate and collecting ultrasonic reflection energy, measuring the wall thickness of the aircraft wall plate by adopting the aircraft wall plate measuring method and obtaining the ultrasonic reflection energy within a specified time;

and processing the aircraft wall plate, wherein the ultrasonic flood energy analysis and embedded information fusion unit sends the wall thickness data and the ultrasonic reflection energy intensity data of the aircraft wall plate to the numerical control platform, and the numerical control platform processes the unfinished aircraft wall plate into a finished aircraft wall plate according to the received wall thickness data and the ultrasonic reflection energy intensity data of the aircraft wall plate.

Further, in the step of processing the aircraft wall plate, the ultrasonic flood energy analysis and embedded information fusion unit sends the wall thickness data and the ultrasonic reflection energy intensity data of the aircraft wall plate to the numerical control platform through the site correlation information.

Further, in the step of processing the aircraft panel, the numerical control platform remotely controls the processing of the aircraft panel through a computer.

Further, the computer remotely controls the numerical control platform to process the aircraft wall plate through remote associated information.

(3) Advantageous effects

Compared with the first type of measurement and processing method and the second type of measurement and processing method in the prior art, the online ultrasonic measurement method for the aircraft wall plate can accurately obtain the 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 of the inner-shaped boss and other positions of the aircraft wall plate. The method not only can carry out simple inner shape outline judgment and measurement according to thickness measurement data, but also can carry out identification, positioning and measurement of complex inner shape outlines of the aircraft wall panels by acquiring first ultrasonic energy and second ultrasonic energy and analyzing intensity distribution and variation trend of the first ultrasonic energy and the second ultrasonic energy. The aircraft wall plate measuring method of the invention effectively solves the problem of measurement and positioning data turbulence caused by the non-parallelism of the diffusion surface of the ultrasonic wave and the ultrasonic probe surface or the normal non-coaxiality thereof. The on-line ultrasonic measurement method of the aircraft wall plate can be widely applied to the manufacturing fields of high-speed rails, automobiles, ships and warships and the like.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used 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 it is obvious for those skilled in the art to further develop other drawings based on the drawings without creative efforts.

FIG. 1 is a schematic diagram of the principle of ultrasonic thickness measurement;

FIG. 2 is a schematic diagram of ultrasonic measurement points in a critical area of aircraft panel thickness variation;

FIG. 3a is a schematic diagram of the measurement point signals forming distinct reflected echoes in a second type of measurement and processing method of the background art;

FIG. 3b is a schematic diagram of the measurement point signals where it is difficult to form sharp reflection echoes in the second type of measurement and processing method of the background art; (ii) a

FIG. 4 is a schematic diagram of a method for on-line ultrasonic measurement of an aircraft panel in accordance with an embodiment of the present invention;

FIG. 5 is a schematic diagram of ultrasonic echo energy distribution during ultrasonic measurement of the inner shape of an aircraft panel according to an embodiment of the present invention;

fig. 6 is a schematic diagram of a method of processing an aircraft panel according to an embodiment of the invention.

Detailed Description

The embodiments of the present invention will be described in further detail with reference to the 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, alterations, and improvements in the parts, components, and connections without departing from the spirit of the invention.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

An on-line ultrasonic measurement method for an aircraft panel comprises the following steps:

the online ultrasonic measurement, the ultrasonic general energy analysis and embedded information fusion unit sends a measurement instruction and a control instruction to an ultrasonic online measurement device, the ultrasonic online measurement device carries out online measurement and energy acquisition on the thickness of the wall plate of the airplane to be measured and reflected ultrasonic energy, and thickness measurement data and ultrasonic reflection energy are synchronously obtained; the ultrasonic energy comprises first ultrasonic energy exhibiting diffuse reflectance and second ultrasonic energy characterized by distinct echogenicity;

and data processing, wherein the ultrasonic reflection energy is fed back to the ultrasonic general energy analysis and embedded information fusion unit, the first ultrasonic energy is processed into first ultrasonic data in a dark information or grey information mode, 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 general 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 concave-convex platform in the inner shape of the aircraft wall plate can be obtained through data processing and combining with the coordinate position information of the numerical control measuring platform.

The online ultrasonic measurement method for the aircraft wall plate creatively introduces the idea of ultrasonic flood energy analysis on the basis of the traditional second type measurement and processing method. Namely, the diffuse reflection first ultrasonic energy which is existed in the traditional ultrasonic measurement and is considered to be invalid is incorporated into the sensing system of the ultrasonic measurement in the form of dark information or gray information, so that the ultrasonic extensive energy analysis and embedded information fusion unit which takes the embedded system as the main body can collect not only the second ultrasonic energy which has the characteristic of a sharp reflection echo, namely the thickness measurement data. But also can collect first ultrasonic energy without distinct reflection echo characteristics, namely ultrasonic diffuse reflection energy caused by the fact that the surface of the material to be detected is not parallel to the surface of the ultrasonic transducer measuring head or the normal direction of the material is not coaxial. In the online ultrasonic measurement method of the aircraft wall plate of the embodiment, taking the measurement of the aircraft wall plate as an example, specifically, as shown in fig. 4, for the online ultrasonic measurement and accurate positioning of the edge position of the inner-shaped boss of the aircraft wall plate shown in fig. 4, the traditional solution idea is to obtain the thickness change data of the aircraft wall plate through simple thickness measurement operation, and judge the edge position of the inner-shaped boss of the aircraft wall plate by directly comparing the thickness measurement data. Although the method seems feasible, the method has the problems of large errors in measurement and instability in positioning accuracy. The reason is that when the ultrasonic measurement device in fig. 4 acquires the thickness variation data of the aircraft wall plate, whether the measurement is carried out in the positive spanwise movement or the negative spanwise movement, in order to try to obtain the key data which is enough to judge the edge position of the inner-shaped boss of the aircraft wall plate, a measurement process from thin to thick or from thick to thin near the inner-shaped boss of the aircraft wall plate must be completed. It is this change in internal profile thickness of the aircraft panel that creates a diffuse surface of ultrasonic energy as shown in figure 4. The diffusion surface reflecting the first ultrasonic energy is seriously unparallel to the ultrasonic transducer measuring head surface or the normal direction thereof is not coaxial, thereby undoubtedly causing the disorder error of the thickness measurement data and even completely losing the thickness measurement information; therefore, the ultrasonic measurement of the edge position of the inner-shaped boss of the aircraft panel has serious problems of precision and stability. The difference of this embodiment lies in that, when the aircraft panel is processed on the numerical control platform, by embedding the ultrasonic general 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-shaped boss of the aircraft panel, but also reflected ultrasonic energy (including ultrasonic reflection energy from the regular reflection surface and the diffuse reflection surface) is acquired, analyzed, processed and evaluated, and especially the first ultrasonic energy of the diffuse ultrasonic energy surface in fig. 4 is analyzed and processed. Based on the intensity of ultrasonic energy reflected by the measured profile, on the diffusion surface of the ultrasonic energy, due to energy diffusion, the ultrasonic measuring transducer is difficult to acquire echo information enough for determining the measured thickness; but on the whole diffusion surface of the ultrasonic energy, the intensity of the ultrasonic energy collected by the ultrasonic measuring transducer is changed along with the curvature of the diffusion surface, so that the digitalized grey 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 thickness variation region of the aircraft panel shown in fig. 2 is shown in fig. 5. The five ultrasonic energy feedback positions shown in the figure have clear ultrasonic thickness measuring echo feedback signals at other positions except the position 3, and the position 3 is just on the critical line of the change of the inner shape thickness. Although no clear thickness measurement information can be obtained at this position, the reflected energy of the ultrasonic wave can still be acquired despite its great attenuation due to scattering. Experiments prove that when the measurement positioning process shown in fig. 4 is carried out in the forward extending direction, the high point position of the edge of the inner-shaped boss of the aircraft panel to be obtained is exactly positioned at the inflection point position where the ultrasonic reflection energy intensity collected by the ultrasonic measurement transducer is suddenly increased from the strength gradually decreased. When the measurement and positioning process shown in fig. 4 is performed in the negative extension 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 where the intensity of the ultrasonic reflection energy changes from strong to weak. The analysis and processing results of the ultrasonic extensive energy are fused with the high-precision positioning information of the numerical control motion platform, so that the online ultrasonic measurement and the accurate positioning of the inner shape contour position of the aircraft wall plate can be realized.

Compared with the first type of measurement and processing method and the second type of measurement and processing method in the prior art, the online ultrasonic measurement method for the aircraft wall plate can accurately obtain the thickness data of the aircraft wall plate, can acquire the ultrasonic reflection energy information of the aircraft wall plate in real time, and can realize accurate online measurement and accurate positioning of the inner-shaped boss and other positions of the aircraft wall plate. The method not only can carry out simple inner shape outline judgment and measurement according to thickness measurement data, but also can carry out identification, positioning and measurement of complex inner shape outlines of the aircraft wall panels by acquiring first ultrasonic energy and second ultrasonic energy and analyzing intensity distribution and variation trend of the first ultrasonic energy and the second ultrasonic energy. The online ultrasonic measurement method for the aircraft wall plate effectively solves the problem of measurement and positioning data turbulence caused by the fact that the diffusion surface of ultrasonic waves is not parallel to the surface of the ultrasonic probe or the normal direction of the diffusion surface of the ultrasonic probe is not coaxial. The online ultrasonic measurement method of the aircraft wall plate 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 electromagnetic ultrasonic measurement device may be further used for online electromagnetic ultrasonic measurement. Because the electromagnetic ultrasonic measurement is an ultrasonic measurement mode which can be carried out in a non-contact way, the complicated and heavy water-based coupling agent supply and recovery system which is attached to the traditional online ultrasonic measurement can be completely abandoned, so that the online ultrasonic measurement and accurate positioning system is lighter. In addition, due to the characteristic of inclination redundancy, when the ultrasonic measurement device is used for online automatic measurement, even if a part to be measured has certain deformation and limited deviation occurs between the measured contact position and the contact normal direction, the ultrasonic reflection energy and the accurate positioning information of the inner-shaped boss of the aircraft wall plate can be accurately acquired, so that the reliability and the stability of online ultrasonic measurement and accurate positioning of the inner shape of the aircraft wall plate can be further ensured.

In order to solve the problem of poor contact of the water-based couplant when ultrasonic measurement is performed on aircraft wallboard parts in a vertical suspension posture, in the embodiment, as a further improvement of the technical scheme, in the online measurement step, the water-based couplant is filled into the ultrasonic measurement transducer at the aircraft wallboard measurement position through a quantitative filling device when preset time or preset conditions are triggered in a measurement state. And technical measures such as adding water absorbing or water retaining materials and the like are added to the ultrasonic measuring transducer to ensure that the water-based coupling effect of the water-based coupling agent filled each time is enough to complete a complete process of ultrasonic online measurement and accurate positioning of the aircraft wall plate. In the online ultrasonic measurement method of the aircraft wall plate, an online ultrasonic measurement tool which enables the numerical control platform and the ultrasonic measurement transducer to be combined and has stretching and guiding functions is additionally designed, so that the normal contact effect between the aircraft wall plate and the ultrasonic measurement transducer in the ultrasonic measurement and positioning process is ensured. Thereby being beneficial to improving the accuracy of online measurement and positioning of the inner shape of the wall plate of the airplane.

In this embodiment, as a further improvement of the above technical solution, an electromagnetic insulating device is disposed between the ultrasonic measurement transducer and the ultrasonic flood energy analysis and embedded information fusion unit, so as to prevent electromagnetic interference in a numerical control manufacturing site from adversely affecting measurement and positioning accuracy through a water-based coupling.

In a second aspect, the invention also provides a processing method of the aircraft wall panel, which adopts the following technical scheme:

a method for processing an aircraft panel comprises the following steps:

measuring the wall thickness of the aircraft wall plate and collecting ultrasonic reflection energy, and obtaining the wall thickness of the aircraft wall plate and the ultrasonic reflection energy within a specified time by adopting the online ultrasonic measurement method of the aircraft wall plate;

and processing the aircraft wall plate, wherein the ultrasonic flood energy analysis and embedded information fusion unit sends the wall thickness data and the ultrasonic reflection energy intensity data of the aircraft wall plate to the numerical control platform, and the numerical control platform processes the unfinished aircraft wall plate into a finished aircraft wall plate according to the received wall thickness data of the aircraft wall plate. In the specific embodiment of processing the aircraft panel, the numerical control platform is called an aircraft panel processing and assembling motion control platform, and the computer is called a remote data information processor (a general-purpose computer directly networked with a field system).

The steps of measuring the wall thickness of the aircraft panel and acquiring the ultrasonic reflected energy intensity data in the method for processing the aircraft panel according to the embodiment also have the advantages, and are not described herein again. On the basis of obtaining accurate wall thickness data and ultrasonic reflection energy intensity data of the aircraft wall panel, the numerical control platform can process finished aircraft wall panels with higher precision.

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 field-related information.

In this embodiment, as a further improvement of the above technical solution, in the step of processing the aircraft panel, the numerical control platform remotely controls the processing of 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 machine the aircraft panel through the remote associated information. And fusing the online acquired thickness information of the inner profile of the aircraft panel part, the ultrasonic reflected energy intensity data and the accurate positioning information with the site associated information through the remote associated information. The ultrasonic flooding energy analysis and embedded information fusion unit can carry out depth data processing on sensed thickness information and ultrasonic reflection energy intensity data of the inner shape of the aircraft panel, edge position information obtained through ultrasonic flooding energy analysis, and gray information or dark information from an ultrasonic diffusion surface and formed by ultrasonic reflection energy with variable changes. And finally determining the ultrasonic measurement result of the inner shape of the aircraft panel by comparing, analyzing and evaluating the inner shape with the existing machining data model. And under the control of a computer, processing the unfinished aircraft wallboard into a finished aircraft wallboard through a numerical control platform.

Based on the combination of the above embodiments, referring to fig. 6 again, the method for processing the aircraft panel according to this embodiment is shown in fig. 6. The ultrasonic flooding 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 internal shape of the aircraft panel, the core unit determines an online ultrasonic measurement method (comprising the relationship between motion control information and measurement control instructions, the rhythm and step pitch for acquiring ultrasonic measurement information, equivalent and time for supplementing coupling agents, matching feedback thickness measurement data and ultrasonic energy and the like) of the aircraft panel according to field associated information, remote associated information (comprising operation control information, system state information and the like) and self software and hardware state information from a numerical control system and a remote computer for processing and assembling the aircraft panel. And the numerical control programming system performs on-line numerical control ultrasonic measurement track programming on the aircraft wall plate according to the existing design data model. The numerical control platform runs according to a programming track, and acquires thickness information of the inner shape profile of the aircraft wall plate, ultrasonic reflection energy intensity data and accurately positioned sensing information in real time on line. By means of a data correlation network and a remote data information processing system, the online ultrasonic measurement system shown in fig. 6 fuses sensed thickness information of the inner contour of the aircraft panel, edge position information obtained through ultrasonic general energy analysis, and gray information or dark information from an ultrasonic diffusion surface and formed by variable ultrasonic reflection energy with control information of a numerical control platform, and carries out comprehensive data processing of depth. And obtaining a digital ultrasonic measurement result of the inner shape of the aircraft panel on the basis of comparison, analysis and evaluation of the existing processing data model.

It should be clear that the embodiments in this specification are described in a progressive manner, and the same or similar parts in the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known process techniques is omitted herein for the sake of brevity.

The above description is only an example of the present application and is not limited to the present application. Various modifications and alterations to this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.