CN114994174B - Method, device, equipment and medium for processing crack data of airplane windshield - Google Patents
Method, device, equipment and medium for processing crack data of airplane windshield Download PDFInfo
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Abstract
The application discloses a method, a device, equipment and a medium for processing crack data of an airplane windshield. The method comprises the steps of obtaining first echo time data for detecting an aircraft windshield by using an ultrasonic probe; establishing a corresponding relation between the first echo time data and each position point on the aircraft windshield through an augmented reality technology; according to the model information of the aircraft, standard echo time data are obtained in a pre-established echo time database; comparing the first echo time data corresponding to the same position point with the standard echo time data; when the difference value of the first echo time data and the standard echo time data is larger than a preset threshold value, determining a position point corresponding to the first echo time data as a target position point; and obtaining a crack detection result of the aircraft windshield according to the communication area formed by the target position point. The method utilizes ultrasonic equipment to replace visual inspection, can effectively improve the detection reliability and reduce the influence of human factors. The application can be widely applied to the technical field of aircrafts.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to an aircraft windshield crack data processing method, an aircraft windshield crack data processing device, an aircraft windshield crack data processing equipment and an aircraft windshield crack data processing medium.
Background
When the aircraft enters the cruising altitude, the aircraft windshield bears the pressure difference between the inside and the outside of the cabin and also bears the thermal stress caused by the temperature difference between the heating resistor and the outside of the aircraft, so that the stress structure of the windshield can be destroyed once a certain microcrack exists on the aircraft windshield, the microcrack of the aircraft windshield is enlarged to shield the sight of a pilot when the aircraft windshield is light, and the aircraft windshield is burst and falls off when the aircraft windshield is heavy to directly influence the flight safety.
Currently, aircraft windshield cracks are generally detected by visual inspection, finger touch and other methods. Due to illumination and human factors, the reliability of detection is reduced, and the light is seriously insufficient at night, and illumination is also required to reduce the influence on the result of visual detection. Moreover, the manual inspection mode can further reduce the detection reliability due to the overlong working time, eye fatigue and other factors, so that the potential safety hazard of operation still exists.
In view of the foregoing, there is a need for solving the technical problems in the related art.
Disclosure of Invention
The present application aims to solve at least one of the technical problems existing in the related art to a certain extent.
It is therefore an object of embodiments of the present application to provide a method for processing aircraft windshield crack data.
It is another object of an embodiment of the present application to provide an aircraft windshield crack data processing apparatus.
In order to achieve the technical purpose, the technical scheme adopted by the embodiment of the application comprises the following steps:
in a first aspect, an embodiment of the present application provides a method for processing aircraft windshield crack data, the method including the steps of:
Acquiring first echo time data for detecting an aircraft windshield using an ultrasonic probe;
establishing a corresponding relation between the first echo time data obtained in the process of detecting the windshield of the aircraft by the ultrasonic probe and each position point on the windshield of the aircraft through an augmented reality technology;
According to the model information of the aircraft, standard echo time data are obtained in a pre-established echo time database;
Comparing the first echo time data corresponding to the same position point with the standard echo time data according to the corresponding relation with each position point on the airplane windshield;
when the difference value of the first echo time data and the standard echo time data is larger than a preset threshold value, determining a position point corresponding to the first echo time data as a target position point;
And obtaining a crack detection result of the aircraft windshield according to the communication area formed by the target position point.
In addition, the method for processing the data of the windshield cracks of the airplane according to the embodiment of the application can also have the following additional technical characteristics:
further, in one embodiment of the application, the echo time database is built up by:
according to the model information of the airplane, acquiring a 3D model and structural information of an airplane windshield of the airplane;
according to the structural information, determining the time length required by reflecting the ultrasonic waves at each position point of the aircraft windshield;
And establishing an echo time database according to the 3D model and the time length required by reflecting the ultrasonic waves at each position point of the airplane windshield.
Further, in one embodiment of the application, the structural information includes the number of layers, material and thickness of each layer of the aircraft windshield; the method for determining the time length required by reflecting the ultrasonic waves at each position point of the airplane windshield according to the structural information comprises the following steps:
calculating the sub-time length required by the propagation of the ultrasonic wave in each layer of the material according to the thickness;
And accumulating the sub-time length to obtain the time length required by reflecting the ultrasonic wave on the windshield of the aircraft.
Further, in an embodiment of the present application, comparing the first echo time data corresponding to the same location point with the standard echo time data according to the correspondence relation with each location point on the wind shield of the aircraft includes:
matching a first position point in a 3D model corresponding to the currently detected airplane windshield and the currently detected airplane windshield through an augmented reality technology;
And acquiring and comparing the first echo time data corresponding to the first position point with the standard echo time data.
Further, in an embodiment of the present application, when the difference value between the first echo time data and the standard echo time data is greater than a preset threshold, determining the location point corresponding to the first echo time data as the target location point includes:
Calculating a difference value between the first echo time data and the standard echo time data, and determining a position point corresponding to the first echo time data as a target position point when the difference value is larger than a first preset threshold value; or alternatively
And calculating a difference value between the first echo time data and the standard echo time data, and determining a position point corresponding to the first echo time data as a target position point when the proportion of the difference value to the standard echo time data is larger than a second preset threshold value.
Further, in one embodiment of the present application, the method further comprises the steps of:
And sending the crack detection result and the model information of the aircraft to a background database for storage.
In a second aspect, an embodiment of the present application provides an aircraft windshield crack data processing apparatus, the control apparatus including:
The acquisition module is used for acquiring first echo time data of an aircraft windshield detected by using the ultrasonic probe;
The building module is used for building the corresponding relation between the first echo time data obtained in the process of detecting the airplane windshield by the ultrasonic probe and each position point on the airplane windshield through an augmented reality technology;
the inquiring module is used for obtaining standard echo time data from a pre-established echo time database according to the model information of the aircraft;
The comparison module is used for comparing the first echo time data and the standard echo time data corresponding to the same position point according to the corresponding relation with each position point on the aircraft windshield;
The processing module is used for determining a position point corresponding to the first echo time data as a target position point when the difference value of the first echo time data and the standard echo time data is larger than a preset threshold value;
and the output module is used for obtaining a crack detection result of the aircraft windshield according to the communication area formed by the target position point.
In a third aspect, an embodiment of the present application provides a terminal device, including:
at least one processor;
At least one memory for storing at least one program;
The at least one program, when executed by the at least one processor, causes the at least one processor to implement the aircraft windshield crack data processing method of the first aspect.
In a fourth aspect, embodiments of the present application also provide a computer readable storage medium having stored therein a processor executable program which when executed by a processor is for implementing the aircraft windshield crack data processing method of the first aspect.
The advantages and benefits of the application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the application.
The embodiment of the application provides a method for processing crack data of an aircraft windshield, which comprises the steps of obtaining first echo time data for detecting the aircraft windshield by using an ultrasonic probe; establishing a corresponding relation between the first echo time data obtained in the process of detecting the windshield of the aircraft by the ultrasonic probe and each position point on the windshield of the aircraft through an augmented reality technology; according to the model information of the aircraft, standard echo time data are obtained in a pre-established echo time database; comparing the first echo time data corresponding to the same position point with the standard echo time data according to the corresponding relation with each position point on the airplane windshield; when the difference value of the first echo time data and the standard echo time data is larger than a preset threshold value, determining a position point corresponding to the first echo time data as a target position point; and obtaining a crack detection result of the aircraft windshield according to the communication area formed by the target position point. The method utilizes ultrasonic equipment to replace visual inspection, can effectively improve the detection reliability and reduce the influence of human factors.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following description is made with reference to the accompanying drawings of the embodiments of the present application or the related technical solutions in the prior art, and it should be understood that the drawings in the following description are only for convenience and clarity of describing some embodiments in the technical solutions of the present application, and other drawings may be obtained according to these drawings without the need of inventive labor for those skilled in the art.
FIG. 1 is a schematic view of an environment for implementing a method for processing data of cracks in an aircraft windshield according to an embodiment of the present application;
FIG. 2 is a schematic flow chart of a method for processing data of cracks in an aircraft windshield according to an embodiment of the present application;
FIG. 3 is a schematic structural view of an aircraft windshield crack data processing apparatus according to an embodiment of the present application;
Fig. 4 is a schematic structural diagram of a terminal device according to an embodiment of the present application.
Detailed Description
Embodiments of the present application are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the application. The step numbers in the following embodiments are set for convenience of illustration only, and the order between the steps is not limited in any way, and the execution order of the steps in the embodiments may be adaptively adjusted according to the understanding of those skilled in the art.
When the aircraft enters the cruising altitude, the aircraft windshield bears the pressure difference between the inside and the outside of the cabin and also bears the thermal stress caused by the temperature difference between the heating resistor and the outside of the aircraft, so that the stress structure of the windshield can be destroyed once a certain microcrack exists on the aircraft windshield, the microcrack of the aircraft windshield is enlarged to shield the sight of a pilot when the aircraft windshield is light, and the aircraft windshield is burst and falls off when the aircraft windshield is heavy to directly influence the flight safety.
Currently, aircraft windshield cracks are generally detected by visual inspection, finger touch and other methods. Due to illumination and human factors, the reliability of detection is reduced, and the light is seriously insufficient at night, and illumination is also required to reduce the influence on the result of visual detection. Moreover, the manual inspection mode can further reduce the detection reliability due to the overlong working time, eye fatigue and other factors, so that the potential safety hazard of operation still exists.
In view of this, the embodiment of the application provides a method for processing crack data of an aircraft windshield, which is mainly applied to the technical field of aircraft. The method can replace visual inspection by using ultrasonic equipment, can effectively improve the reliability of detection and reduce the influence of human factors; and moreover, the obtained crack detection result of the aircraft windshield can be used for constructing a database by using the Internet +' so as to improve the analysis value of the crack data of the aircraft windshield, be beneficial to finding out the commonality of the crack of the aircraft windshield and be helpful to find out the defects of the windshield design in advance or be used for aviation accident investigation.
First, referring to fig. 1, fig. 1 is a schematic view of an implementation environment of an aircraft windshield crack data processing method according to an embodiment of the application. Referring to fig. 1, the main body of the implementation environment mainly includes a terminal device 110, a server 120 and an aircraft 130, where the terminal device 110 is communicatively connected to the server 120, and the terminal device 110 may obtain data related to the aircraft 130. The method for processing the windshield crack data of the aircraft may be performed based on the interaction between the terminal device 110 and the server 120, however, in some embodiments, the method for processing the windshield crack data of the aircraft may also be performed based on the terminal device 110 alone, and may be appropriately selected according to the actual application, which is not limited in the embodiment of the present application.
Specifically, the terminal device 110 in the present application may be a computer, a smart phone, a PDA device, etc. The server 120 may be an independent physical server, a server cluster or a distributed system formed by a plurality of physical servers, or a cloud server providing cloud services, cloud databases, cloud computing, cloud functions, cloud storage, network services, cloud communication, middleware services, domain name services, security services, CDNs (Content Delivery Network, content delivery networks), basic cloud computing services such as big data and artificial intelligent platforms, and the like. The communication connection between the terminal device 110 and the server 120 may be established through a wireless network or a wired network using standard communication techniques and/or protocols, which may be configured as the internet, or any other network including, but not limited to, a local area network (Local Area Network, LAN), a metropolitan area network (Metropolitan Area Network, MAN), a wide area network (Wide Area Network, WAN), a mobile, wired or wireless network, a private network, or any combination of virtual private networks, for example.
In the following, an aircraft windshield crack data processing method provided in an embodiment of the present application is described and illustrated with reference to the implementation environment shown in fig. 1. Referring to fig. 2, fig. 2 is a schematic diagram of an aircraft windshield crack data processing method according to an embodiment of the application, where the aircraft windshield crack data processing method includes, but is not limited to:
Step 210, acquiring first echo time data of an aircraft windshield detected by using an ultrasonic probe;
in this step, an ultrasonic probe is used to detect the aircraft windshield, and the obtained data is recorded as first echo time data. In the embodiment of the application, the ultrasonic probe is used for detecting the windshield of the aircraft, and the ultrasonic thickness measuring technical principle is utilized. The ultrasonic thickness measurement technology principle is similar to the light wave measurement principle, and when ultrasonic pulses emitted by the ultrasonic probe pass through a measured object to reach a material interface, the pulses are reflected back to the ultrasonic probe. By accurately measuring the time of propagation of ultrasonic waves in the material, the thickness of the measured material can be determined. Various materials that enable ultrasonic waves to propagate inside them at a constant velocity can be measured using this principle. The ultrasonic thickness measuring technology has the characteristics of wide measuring range, high precision, low cost and the like. Based on the characteristics of the ultrasonic thickness measurement technology and the characteristic of fixed layer number of the airplane windshield, the technology can be used for flaw detection, namely crack detection, for example, the actual echo time and the theoretical echo time can be compared, and if cracks exist at the detection position, the actual echo time is necessarily smaller than the theoretical time.
220, Establishing a corresponding relation between the first echo time data obtained in the process of detecting the windshield of the aircraft by the ultrasonic probe and each position point on the windshield of the aircraft through an augmented reality technology;
Since the actual echo time and the theoretical echo time need to be compared as much as possible (different materials or thicknesses are possible to be different) in the same position, the first echo time data measured on the windshield of the aircraft need to be in one-to-one correspondence with the detected position points, and thus the accuracy of subsequent comparison is relatively reliable.
Specifically, in this step, the augmented reality technology, also called AR technology (augmented reality), is a technology that calculates the position and angle of the camera image in real time and adds the corresponding image, and is a new technology that integrates the real world information and the virtual world information in a "seamless" manner, and this technology can cover the virtual world around the real world on the screen and interact with each other. By utilizing the technology, the corresponding relation between the first echo time data and the detected position point can be conveniently established, so that the position of the crack can be accurately positioned later.
Step 230, obtaining standard echo time data in a pre-established echo time database according to the model information of the aircraft;
In this step, as described above, the actual echo time and the theoretical echo time are compared, and if a crack exists at the detection site, the actual echo time is necessarily smaller than the theoretical time. Therefore, the theoretical time of the echo needs to be determined during comparison, and the theoretical time of the echo is recorded as standard echo time data, which can be obtained through test detection or theoretical calculation in advance and is stored in an echo time database, so that the subsequent call is convenient. Specifically, since different aircraft models may differ in materials and the like, and the same model is generally identical in structural configuration, in the established echo time database, corresponding standard echo time data may be stored in accordance with model information. When standard echo time data comparison needs to be called, inquiring and acquiring can be performed according to model information.
Specifically, in some embodiments, the echo time database is built by:
according to the model information of the airplane, acquiring a 3D model and structural information of an airplane windshield of the airplane;
according to the structural information, determining the time length required by reflecting the ultrasonic waves at each position point of the aircraft windshield;
And establishing an echo time database according to the 3D model and the time length required by reflecting the ultrasonic waves at each position point of the airplane windshield.
In the embodiment of the application, when the echo time database is established, the 3D model and the structural information of the airplane windshield of the airplane can be obtained according to the airplane type information of the airplane. The 3D model is used for matching the position of the detection point subsequently, and the structural information is used for determining the duration required by reflection of each position point of the aircraft windshield, namely the standard echo time data. In some more detailed embodiments, the structural information herein may include the number of layers, material and thickness of each layer of the aircraft windshield. For example, taking a common three-layer glass and two-layer adhesive aircraft windshield as an example, the aircraft windshield has five layers in total, and the length of time required for ultrasonic waves to travel once in the layer of material can be determined according to the thickness of each layer and the transmission speed of the ultrasonic waves in the layer of material, and the length is recorded as the sub-length by the application. And then accumulating the sub-lengths corresponding to the materials of each layer to obtain the time length required by reflecting the ultrasonic waves on the windshield of the aircraft.
In the 3D model, since the structural information of each location point is known, standard echo time data corresponding to each location point in the 3D model can be determined through the above procedure. Then, according to the 3D model and the time length required by the reflection of the ultrasonic wave at each position point of the airplane windshield, an echo time database of various airplane models can be built.
Step 240, comparing the first echo time data corresponding to the same position point with the standard echo time data according to the corresponding relation with each position point on the airplane windshield;
In this step, according to the correspondence relation with each position point on the aircraft windshield, the first echo time data corresponding to the same position point and the standard echo time data can be compared, so as to determine whether the position point is at the position where the crack is located. Specifically, in the embodiment of the present application, a first location point (the first location point may be a current detected location point) may be first matched in a 3D model corresponding to a current detected aircraft windshield and a current detected aircraft windshield by using an augmented reality technology, and then first echo time data and standard echo time data corresponding to the first location point are acquired and compared, and the data comparison of each location point may be implemented by performing a cyclic reciprocating operation in this way.
It can be understood that in the embodiment of the application, based on the characteristic that real world information and virtual world information can be integrated in a seamless manner by the AR technology, the surface crack of the aircraft windshield with variable thickness can be detected by aiming at the characteristic that a part of the aircraft windshield has a certain radian. By selecting model information, positioning the position detected by the ultrasonic probe by using an AR technology, and then adjusting out a 3D model of the plane windshield of the curved surface in the echo time database, overlapping matching of the positions can be realized, so that the theoretical echo time length corresponding to the position detected by the ultrasonic probe is determined, and the detection accuracy can be improved.
Step 250, determining a location point corresponding to the first echo time data as a target location point when the difference value between the first echo time data and the standard echo time data is greater than a preset threshold value;
In this step, whether or not the aircraft windshield has a crack can be determined by comparing the actual time (first echo time data) at which the ultrasonic wave propagates back and forth in the aircraft windshield with the theoretical time (first echo time data). Specifically, a difference value of the two may be calculated, and then the difference value is compared with a preset threshold value, and when the difference value is greater than the preset threshold value, it is explained that there is a high possibility that a crack is present here, so that it may be determined that the location point corresponding to the current first echo time data is determined as the target location point. Here, in some embodiments, the difference value may be a specific difference value of the time data, for example, a first preset threshold may be set as a specific time value, a difference value between the first echo time data and the standard echo time data is calculated, and if the difference value is greater than the first preset threshold, a location point corresponding to the first echo time data is determined to be a target location point; in some embodiments, the difference value may be a ratio of the calculated difference value to the standard echo time data, at this time, a second preset threshold may be set as a specific ratio value, and if the ratio of the difference value to the standard echo time data is greater than the second preset threshold, the location point corresponding to the first echo time data is determined as the target location point.
And 260, obtaining a crack detection result of the aircraft windshield according to the communication area formed by the target position point.
In the step, after obtaining each target position point belonging to the position of the crack, the crack detection result of the aircraft windshield can be obtained according to the communication area formed by the target position points.
In some embodiments, the method further comprises the steps of:
And sending the crack detection result and the model information of the aircraft to a background database for storage.
In the embodiment of the application, a related database can be constructed by using the Internet +' and then the crack detection result obtained by detection can be stored in a background database which is transmitted together with the model information of the corresponding airplane. Therefore, the value of the detection of the windshield cracks of the airplane can be effectively improved, the commonality of the generation of the windshield cracks of the airplane can be found, and the windshield design defects can be found in advance or used for the investigation of aviation accidents.
An aircraft windshield crack data processing apparatus according to an embodiment of the present application is described below with reference to the accompanying drawings.
Referring to fig. 3, an aircraft windshield crack data processing apparatus according to an embodiment of the present application includes:
an acquisition module 201 for acquiring first echo time data for detecting an aircraft windshield using an ultrasonic probe;
The establishing module 202 is configured to establish, by using an augmented reality technology, a correspondence between the first echo time data obtained in the process of detecting an aircraft windshield by using the ultrasonic probe and each position point on the aircraft windshield;
the query module 203 is configured to obtain standard echo time data from a pre-established echo time database according to model information of the aircraft;
A comparison module 204, configured to compare the first echo time data and the standard echo time data corresponding to the same location point according to the correspondence relation with each location point on the aircraft windshield;
the processing module 205 is configured to determine, as a target location point, a location point corresponding to the first echo time data when a difference value between the first echo time data and the standard echo time data is greater than a preset threshold;
And the output module 206 is used for obtaining the crack detection result of the aircraft windshield according to the communication area formed by the target position point.
It can be understood that the content in the above method embodiment is applicable to the embodiment of the present device, and the specific functions implemented by the embodiment of the present device are the same as those of the embodiment of the above method, and the achieved beneficial effects are the same as those of the embodiment of the above method.
Referring to fig. 4, an embodiment of the present application provides a terminal device, including:
at least one processor 301;
At least one memory 302 for storing at least one program;
The at least one program, when executed by the at least one processor 301, causes the at least one processor 301 to implement an aircraft windshield crack data processing method.
Similarly, the content in the above method embodiment is applicable to the embodiment of the present terminal device, and the functions specifically implemented by the embodiment of the present terminal device are the same as those of the embodiment of the above method, and the beneficial effects achieved by the embodiment of the above method are the same as those achieved by the embodiment of the above method.
The embodiment of the present application also provides a computer-readable storage medium in which a program executable by the processor 301 is stored, the program executable by the processor 301 being for performing the above-described aircraft windshield crack data processing method when executed by the processor 301.
Similarly, the content in the above method embodiment is applicable to the present computer-readable storage medium embodiment, and the functions specifically implemented by the present computer-readable storage medium embodiment are the same as those of the above method embodiment, and the beneficial effects achieved by the above method embodiment are the same as those achieved by the above method embodiment.
In some alternative embodiments, the functions/acts noted in the block diagrams may occur out of the order noted in the operational illustrations. For example, two blocks shown in succession may in fact be executed substantially concurrently or the blocks may sometimes be executed in the reverse order, depending upon the functionality/acts involved. Furthermore, the embodiments presented and described in the flowcharts of the present application are provided by way of example in order to provide a more thorough understanding of the technology. The disclosed methods are not limited to the operations and logic flows presented herein. Alternative embodiments are contemplated in which the order of various operations is changed, and in which sub-operations described as part of a larger operation are performed independently.
Furthermore, while the application is described in the context of functional modules, it should be appreciated that, unless otherwise indicated, one or more of the functions and/or features may be integrated in a single physical device and/or software module or may be implemented in separate physical devices or software modules. It will also be appreciated that a detailed discussion of the actual implementation of each module is not necessary to an understanding of the present application. Rather, the actual implementation of the various functional modules in the apparatus disclosed herein will be apparent to those skilled in the art from consideration of their attributes, functions and internal relationships. Accordingly, one of ordinary skill in the art can implement the application as set forth in the claims without undue experimentation. It is also to be understood that the specific concepts disclosed are merely illustrative and are not intended to be limiting upon the scope of the application, which is to be defined in the appended claims and their full scope of equivalents.
The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present application may be embodied essentially or in a part contributing to the prior art or in a part of the technical solution in the form of a software product stored in a storage medium, comprising several instructions for causing a device (which may be a personal computer, a server, a network device, etc.) to perform all or part of the steps of the method of the embodiments of the present application. And the aforementioned storage medium includes: a usb disk, a removable hard disk, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a magnetic disk, or an optical disk, or other various media capable of storing program codes.
Logic and/or steps represented in the flowcharts or otherwise described herein, e.g., a ordered listing of executable instructions for implementing logical functions, can be embodied in any computer-readable medium for use by or in connection with an instruction execution system, apparatus, or device, such as a computer-based system, processor-containing system, or other system that can fetch the instructions from the instruction execution system, apparatus, or device and execute the instructions. For the purposes of this description, a "computer-readable medium" can be any means that can contain, store, communicate, propagate, or transport the program for use by or in connection with the instruction execution system, apparatus, or device.
More specific examples (a non-exhaustive list) of the computer-readable medium would include the following: an electrical connection (electronic device) having one or more wires, a portable computer diskette (magnetic device), a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber device, and a portable compact disc read-only memory (CDROM). Additionally, the computer-readable medium may even be paper or other suitable medium upon which the program is printed, as the program may be electronically captured, via, for instance, optical scanning of the paper or other medium, then compiled, interpreted or otherwise processed in a suitable manner, if necessary, and then stored in a computer memory.
It is to be understood that portions of the present application may be implemented in hardware, software, firmware, or a combination thereof. In the above-described embodiments, the various steps or methods may be implemented in software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, may be implemented using any one or combination of the following techniques, as is well known in the art: discrete logic circuits having logic gates for implementing logic functions on data signals, application specific integrated circuits having suitable combinational logic gates, programmable Gate Arrays (PGAs), field Programmable Gate Arrays (FPGAs), and the like.
In the foregoing description of the present specification, reference has been made to the terms "one embodiment/example", "another embodiment/example", "certain embodiments/examples", and the like, means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the application. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the present application have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the spirit and principles of the application, the scope of which is defined by the claims and their equivalents.
While the preferred embodiment of the present application has been described in detail, the present application is not limited to the embodiments, and those skilled in the art can make various equivalent modifications or substitutions without departing from the spirit of the present application, and the equivalent modifications or substitutions are intended to be included in the scope of the present application as defined in the appended claims.
Claims (7)
1. An aircraft windshield crack data processing method, comprising the steps of:
Acquiring first echo time data for detecting an aircraft windshield using an ultrasonic probe;
establishing a corresponding relation between the first echo time data obtained in the process of detecting the windshield of the aircraft by the ultrasonic probe and each position point on the windshield of the aircraft through an augmented reality technology;
According to the model information of the aircraft, standard echo time data are obtained in a pre-established echo time database;
Comparing the first echo time data corresponding to the same position point with the standard echo time data according to the corresponding relation with each position point on the airplane windshield;
when the difference value of the first echo time data and the standard echo time data is larger than a preset threshold value, determining a position point corresponding to the first echo time data as a target position point;
Obtaining a crack detection result of the aircraft windshield according to the communication area formed by the target position point;
The echo time database is built by the following steps:
According to the model information of the airplane, acquiring a 3D model and structural information of an airplane windshield of the airplane; the structural information comprises the number of layers of the aircraft windshield, and the material and thickness of each layer;
calculating the sub-time length required by the propagation of the ultrasonic wave in each layer of the material according to the thickness;
Accumulating the sub-periods to determine the period required by the reflection of the ultrasonic waves at each position point of the aircraft windshield;
And establishing an echo time database according to the 3D model and the time length required by reflecting the ultrasonic waves at each position point of the airplane windshield.
2. The method for processing aircraft windshield crack data according to claim 1, wherein comparing the first echo time data corresponding to the same location point with the standard echo time data according to the correspondence relation with each location point on the aircraft windshield, comprises:
matching a first position point in a 3D model corresponding to the currently detected airplane windshield and the currently detected airplane windshield through an augmented reality technology;
And acquiring and comparing the first echo time data corresponding to the first position point with the standard echo time data.
3. The method for processing aircraft windshield crack data according to claim 1, wherein determining the location point corresponding to the first echo time data as the target location point when the difference value between the first echo time data and the standard echo time data is greater than a preset threshold value comprises:
Calculating a difference value between the first echo time data and the standard echo time data, and determining a position point corresponding to the first echo time data as a target position point when the difference value is larger than a first preset threshold value; or alternatively
And calculating a difference value between the first echo time data and the standard echo time data, and determining a position point corresponding to the first echo time data as a target position point when the proportion of the difference value to the standard echo time data is larger than a second preset threshold value.
4. The aircraft windshield crack data processing method of claim 1, further comprising the steps of:
And sending the crack detection result and the model information of the aircraft to a background database for storage.
5. An aircraft windshield crack data processing apparatus, the apparatus comprising:
The acquisition module is used for acquiring first echo time data of an aircraft windshield detected by using the ultrasonic probe;
The building module is used for building the corresponding relation between the first echo time data obtained in the process of detecting the airplane windshield by the ultrasonic probe and each position point on the airplane windshield through an augmented reality technology;
the inquiring module is used for obtaining standard echo time data from a pre-established echo time database according to the model information of the aircraft;
The comparison module is used for comparing the first echo time data and the standard echo time data corresponding to the same position point according to the corresponding relation with each position point on the aircraft windshield;
The processing module is used for determining a position point corresponding to the first echo time data as a target position point when the difference value of the first echo time data and the standard echo time data is larger than a preset threshold value;
The output module is used for obtaining a crack detection result of the aircraft windshield according to the communication area formed by the target position point;
The apparatus further comprises:
a database construction module for:
According to the model information of the airplane, acquiring a 3D model and structural information of an airplane windshield of the airplane; the structural information comprises the number of layers of the aircraft windshield, and the material and thickness of each layer;
calculating the sub-time length required by the propagation of the ultrasonic wave in each layer of the material according to the thickness;
Accumulating the sub-periods to determine the period required by the reflection of the ultrasonic waves at each position point of the aircraft windshield;
And establishing an echo time database according to the 3D model and the time length required by reflecting the ultrasonic waves at each position point of the airplane windshield.
6. A terminal device, comprising:
at least one processor;
At least one memory for storing at least one program;
the at least one program, when executed by the at least one processor, causes the at least one processor to implement the aircraft windshield crack data processing method of any of claims 1-4.
7. A computer-readable storage medium having stored therein a program executable by a processor, characterized in that: the processor executable program when executed by a processor is for implementing the aircraft windshield crack data processing method of any one of claims 1-4.
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| CN117864414B (en) * | 2023-11-07 | 2024-06-11 | 广州民航职业技术学院 | Method, system, equipment and storage medium for detecting damage of airplane windshield |
| CN117874905B (en) * | 2023-12-14 | 2024-07-30 | 广州民航职业技术学院 | Method, system, equipment and storage medium for predicting damage of airplane windshield |
| CN119129398B (en) * | 2024-08-26 | 2025-05-27 | 广州民航职业技术学院 | Aircraft windshield crack detection modeling method, device, equipment and storage medium |
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