Aircraft damage detection method, device and equipment based on intelligent painting system

Abstract

The present application discloses an aircraft damage detection method, device and equipment based on an intelligent painting system. A standard signal matrix is established according to the deployment position points of each set of supporting signal transmitters and signal receivers; wherein, the standard signal matrix is used to record the signal transmission links between each set of supporting signal transmitters and signal receivers. Each signal transmitter is activated to detect the response information of each signal receiver; wherein, the response information is used to characterize whether the signal receiver receives the signal sent by the supporting signal transmitter. According to the response information of each signal receiver, the skin damage area on the aircraft surface is determined. This method does not need to use professional equipment to detect each position point on the aircraft skin one by one, which can greatly improve the efficiency and accuracy of damage detection, and the overall implementation cost is relatively low. The present application can be widely applied in the field of aircraft technology.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft, and in particular to an aircraft damage detection method, device and equipment based on an intelligent painting system. Background Art

[0002] An aircraft is an aerial vehicle capable of flying in the atmosphere. It usually relies on the lift generated by its wings to support the weight of the fuselage and moves forward through the thrust or pull provided by the engine. The aircraft skin refers to the thin shell layer covering the outer surface of the aircraft skeleton, which is crucial for the safe operation of the aircraft.

[0003] In the related art, in order to ensure the safe operation of the aircraft, it is often necessary to detect the damage of the aircraft skin. Currently, when detecting the damage of the aircraft skin, generally, staff use professional detection equipment to detect the conditions of each site. This implementation method requires a long time-consuming, high labor cost, and is prone to omissions and negligence, resulting in low detection accuracy and affecting the operation safety of the aircraft. Summary of the Invention

[0004] An object of the present application is to solve at least to some extent one of the technical problems existing in the related art.

[0005] To this end, an object of an embodiment of the present application is to provide an aircraft damage detection method, device and equipment based on an intelligent painting system.

[0006] To achieve the above technical object, the technical solutions adopted in the embodiments of the present application include:

[0007] On the one hand, an embodiment of the present application provides an aircraft damage detection method based on an intelligent painting system. The intelligent painting system includes an electromagnetic control sensor array and a composite paint surface laid on the aircraft surface. The composite paint surface includes an insulating primer layer, a magnetorheological fluid coating and a protective paint layer laid in sequence. Among them, the insulating primer layer is in contact with the skin on the aircraft surface; the electromagnetic control sensor array includes several sets of supporting signal transmitters and signal receivers. The supporting signal transmitters and signal receivers in each set are arranged in a vertical and horizontal staggered manner, and the signal transmitters and signal receivers are connected to the magnetorheological fluid coating;

[0008] The aircraft damage detection method includes:

[0009] According to the deployment position points of the supporting signal transmitters and signal receivers in each set, a standard signal matrix is established; wherein, the standard signal matrix is used to record the signal transmission link between the supporting signal transmitters and signal receivers in each set;

[0010] Activate each of the signal transmitters and detect the response information of each of the signal receivers; wherein, the response information is used to indicate whether the signal receiver has received the signal sent by the supporting signal transmitter.

[0011] Determine the skin damage area on the surface of the aircraft based on the response information of each of the signal receivers.

[0012] In addition, according to the aircraft damage detection method based on the intelligent painting system in the above embodiments of the present application, the following additional technical features may also be included:

[0013] Further, in an embodiment of the present application, the determining the skin damage area on the surface of the aircraft based on the response information of each of the signal receivers includes:

[0014] If the signal receiver does not receive the signal sent by the supporting signal transmitter, determine the signal transmission link between the signal receiver and the supporting signal transmitter as a signal interruption link.

[0015] Determine the area covered by the intersections of each of the signal interruption links as the skin damage area on the surface of the aircraft.

[0016] Further, in an embodiment of the present application, the determining the skin damage area on the surface of the aircraft based on the response information of each of the signal receivers includes:

[0017] Determine standard signal intersection points according to the signal transmission links in the standard signal matrix; wherein, the standard signal intersection points are the intersection points of any two signal transmission links.

[0018] Determine signal detection links according to the response information of each of the signal receivers.

[0019] Determine the standard signal intersection points passed by the signal detection links as detection signal intersection points.

[0020] Determine the skin damage area on the surface of the aircraft according to the detection signal intersection points.

[0021] Further, in an embodiment of the present application, the determining the signal detection links according to the response information of each of the signal receivers includes:

[0022] If the signal receiver receives the signal sent by the supporting signal transmitter, determine the signal transmission link between the signal receiver and the supporting signal transmitter as a signal detection link.

[0023] Alternatively, if the signal receiver does not receive the signal sent by the supporting signal transmitter, trace and analyze the signal of the supporting signal transmitter to determine the signal detection link corresponding to the supporting signal transmitter.

[0024] Further, in an embodiment of the present application, the determining the skin damage area on the aircraft surface according to the detection signal intersection points includes:

[0025] Taking each of the detection signal intersection points and the deployment position points as endpoints, determine a number of minimum rectangular units on the aircraft surface; wherein, the inside and edges of the minimum rectangular unit do not include the detection signal intersection points and the deployment position points;

[0026] Determine the area other than the minimum rectangular units on the aircraft surface as the skin damage area.

[0027] Further, in an embodiment of the present application, the protective paint layer adopts a high-transparency protective paint layer.

[0028] Further, in an embodiment of the present application, the method further includes:

[0029] If all the signal receivers receive the signals sent by the supporting signal transmitters, determine that there is no skin damage area on the aircraft surface.

[0030] On the other hand, an embodiment of the present application provides an aircraft damage detection device based on an intelligent painting system. The intelligent painting system includes an electromagnetic control sensor array and a composite paint surface laid on the aircraft surface. The composite paint surface includes an insulating primer layer, a magnetic fluid coating, and a protective paint layer laid in sequence, wherein the insulating primer layer is in contact with the skin on the aircraft surface; the electromagnetic control sensor array includes a number of sets of supporting signal transmitters and signal receivers, and each set of supporting signal transmitters and signal receivers are arranged in a horizontal and vertical staggered manner, and the signal transmitters and signal receivers are connected to the magnetic fluid coating;

[0031] The aircraft damage detection device includes:

[0032] A establishing unit, configured to establish a standard signal matrix according to the deployment position points of each set of supporting signal transmitters and signal receivers; wherein, the standard signal matrix is used to record the signal transmission link between each set of supporting signal transmitters and signal receivers;

[0033] A starting unit, configured to start each of the signal transmitters and detect the response information of each of the signal receivers; wherein, the response information is used to indicate whether the signal receiver receives the signal sent by the supporting signal transmitter;

[0034] A processing unit for determining the skin damage area on the aircraft surface according to the response information of each of the signal receivers.

[0035] On the other hand, an embodiment of the present application provides a computer device, including:

[0036] At least one processor;

[0037] At least one memory for storing at least one program;

[0038] When the at least one program is executed by the at least one processor, the at least one processor implements the above-mentioned aircraft damage detection method based on an intelligent painting system.

[0039] On the other hand, an embodiment of the present application further provides a computer-readable storage medium, in which a program executable by a processor is stored, and the program executable by the processor is used to implement the above-mentioned aircraft damage detection method based on an intelligent painting system when executed by the processor.

[0040] The advantages and beneficial effects of the present application will be partially given in the following description, partially will become obvious from the following description, or will be understood through the practice of the present application:

[0041] An aircraft damage detection method based on an intelligent painting system disclosed in an embodiment of the present application establishes a standard signal matrix according to the deployment position points of each set of supporting signal transmitters and signal receivers; wherein, the standard signal matrix is used to record the signal transmission link between each set of supporting signal transmitters and signal receivers; start each signal transmitter and detect the response information of each signal receiver; wherein, the response information is used to characterize whether the signal receiver receives the signal sent by the supporting signal transmitter; determine the skin damage area on the aircraft surface according to the response information of each signal receiver. This method does not need to use professional equipment to detect each position point on the aircraft skin one by one. Through the electromagnetic control sensor array and the magnetorheological fluid coating in the intelligent painting system, it is convenient to determine which areas are damaged. In this way, the efficiency and accuracy of damage detection can be greatly improved, and the overall implementation cost is relatively low. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following introduces the drawings related to the technical solutions in the embodiments of the present application or the prior art. It should be understood that the drawings introduced below are only for clearly expressing some embodiments of the technical solutions in the present invention, and those skilled in the art can obtain other drawings based on these drawings without creative efforts.

[0043] Figure 1 Schematic diagram of a composite paint surface of an intelligent painting system provided in an embodiment of the present application;

[0044] Figure 2 Schematic diagram of an electromagnetic control sensor array provided in an embodiment of the present application;

[0045] Figure 3 Schematic flow diagram of an aircraft damage detection method based on an intelligent painting system provided in an embodiment of the present application;

[0046] Figure 4 Schematic diagram of determining a skin damage area on the surface of an aircraft provided in an embodiment of the present application;

[0047] Figure 5 Schematic diagram of determining a skin damage area on the surface of an aircraft by detecting signal intersection points provided in an embodiment of the present application;

[0048] Figure 6 Schematic diagram of the structure of a computer device provided in an embodiment of the present application. Detailed implementation manners

[0049] The present application will be further described below in conjunction with the accompanying drawings of the specification and specific embodiments. The described embodiments should not be regarded as limitations on the present application. All other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present application.

[0050] In the following description, reference is made to "some embodiments", which describe a subset of all possible embodiments. However, it can be understood that "some embodiments" can be the same subset or different subsets of all possible embodiments, and can be combined with each other without conflict.

[0051] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill in the technical field to which this application belongs. The terms used herein are only for the purpose of describing the embodiments of this application and are not intended to limit this application.

[0052] An aircraft is an aircraft that can fly in the atmosphere. It usually relies on the lift generated by its wings to support the weight of the fuselage and moves forward through the thrust or pull provided by the engine. The aircraft skin refers to the thin shell layer covering the outer surface of the aircraft skeleton, which is crucial for the safe operation of the aircraft.

[0053] In the related art, in order to ensure the safe operation of an aircraft, it is often necessary to detect damage to the aircraft skin. Currently, when detecting damage to the aircraft skin, generally, staff use professional detection equipment to detect the conditions of each position point. This implementation method requires a long time-consuming, high labor cost, and is prone to omissions and oversights, resulting in low detection accuracy and affecting the operation safety of the aircraft.

[0054] In view of this, in the embodiments of the present application, an aircraft damage detection method based on an intelligent painting system is provided. According to the deployment position points of each set of supporting signal transmitters and signal receivers, a standard signal matrix is established; wherein, the standard signal matrix is used to record the signal transmission links between each set of supporting signal transmitters and signal receivers; each signal transmitter is started, and the response information of each signal receiver is detected; wherein, the response information is used to indicate whether the signal receiver has received the signal sent by the supporting signal transmitter; according to the response information of each signal receiver, the damaged area of the aircraft skin surface is determined. This method does not require using professional equipment to detect each position point on the aircraft skin one by one. Through the electromagnetic control sensor array and the magnetorheological fluid coating in the intelligent painting system, it is convenient to determine which areas are damaged. In this way, the efficiency and accuracy of damage detection can be greatly improved, and the overall implementation cost is relatively low.

[0055] Before introducing the aircraft damage detection method provided in the embodiments of the present application, first, an intelligent painting system provided in the embodiments of the present application is introduced and described.

[0056] In the embodiments of the present application, the intelligent painting system includes an electromagnetic control sensor array and a composite paint surface laid on the aircraft surface. Among them, please refer to Figure 1 , Figure 1 shows a schematic diagram of the composite paint surface of an intelligent painting system provided in the embodiments of the present application. For this composite paint surface, it includes an insulating primer layer 3, a magnetorheological fluid coating 2, and a protective paint layer 1 that are sequentially laid on the skin 4 of the aircraft surface. The insulating primer layer 3 is directly laid on the skin 4 of the aircraft surface, the magnetorheological fluid coating 2 is laid on the insulating primer layer 3, and the protective paint layer 1 is laid on the magnetorheological fluid coating 2. In some embodiments, the protective paint layer 1 can adopt a high-transparency protective paint layer. A high-transparency protective paint layer generally refers to a coating material applied to the surface to provide protection and increase transparency. This kind of coating is widely used in various fields, such as automobiles, electronic products, furniture, art protection, etc., and has good protection effects, good transparency, and is easy to clean.

[0057] In the embodiments of the present application, the electromagnetic control sensor array includes several sets of supporting signal transmitters and signal receivers. Exemplarily, please refer to Figure 2 , Figure 2It shows a schematic diagram of an electromagnetic control sensor array provided in an embodiment of the present application. In the electromagnetic control sensor array, groups of supporting signal transmitters and signal receivers can be arranged in a horizontal and vertical staggered manner, and moreover, both the signal transmitters and the signal receivers can be connected to the magnetorheological fluid coating.

[0058] In the embodiment of the present application, the overall operation principle of the intelligent painting system is as follows:

[0059] Inside the electromagnetic control sensor array, the supporting signal transmitters and signal receivers are connected to the magnetorheological fluid paint. The signal generator emits signals in a targeted manner to the corresponding signal receivers. When the signal emitted by the signal transmitter passes through the magnetorheological fluid substance, under ideal conditions, the signal will be received and recognized by the corresponding signal receiver. When the skin of the aircraft surface is damaged, since the magnetorheological fluid coating is damaged, it will cause some signal receivers to be unable to receive signals normally. Based on this feature, damage detection of the aircraft can be achieved.

[0060] Please refer to Figure 3 , Figure 3 is a schematic flow chart of an aircraft damage detection method based on an intelligent painting system provided in an embodiment of the present application. Referring to Figure 3 , the aircraft damage detection method based on an intelligent painting system includes but is not limited to:

[0061] Step 310: Establish a standard signal matrix according to the deployment position points of each group of supporting signal transmitters and signal receivers; wherein, the standard signal matrix is used to record the signal transmission link between each group of supporting signal transmitters and signal receivers;

[0062] Step 320: Start each signal transmitter and detect the response information of each signal receiver; wherein, the response information is used to indicate whether the signal receiver has received the signal sent by the supporting signal transmitter.

[0063] Step 330: Determine the skin damage area on the aircraft surface according to the response information of each signal receiver.

[0064] In the embodiment of the present application, an aircraft damage detection method based on an intelligent painting system is provided. Based on the intelligent painting system provided above, this detection method can achieve damage detection of the aircraft skin.

[0065] Specifically, in the embodiments of the present application, a standard signal matrix can be established according to the deployment location points of the supporting signal transmitters and signal receivers in each group. The standard signal matrix can be used to record the signal transmission links between the supporting signal transmitters and signal receivers in each group. It can be understood that when the aircraft skin itself is intact, each signal receiver can receive signals, and each signal transmission link will also be complete.

[0066] When detecting damage to the aircraft skin, each signal transmitter can be activated, and then the response information of each signal receiver can be detected. Here, the response information can be used to characterize whether each signal receiver has received the signal sent by the supporting signal transmitter. Exemplarily, in some embodiments, the response information can be represented by 0 and 1 signals. If the signal receiver receives the signal sent by the supporting signal transmitter, the corresponding response information can be fed back as 1. Conversely, if the signal receiver does not receive the signal sent by the supporting signal transmitter, the corresponding response information can be fed back as 0. Of course, in the embodiments of the present application, the specific setting method of the response information can be flexibly set according to actual needs, and the present application does not limit this.

[0067] According to the response information of each signal receiver, it can be determined which signal receivers have not received the signal sent by the supporting signal transmitter. Thus, it can be determined which signal transmission links in the standard signal matrix are cut off, and then the damaged area of the aircraft skin surface can be determined.

[0068] It can be understood that the aircraft damage detection method provided in the embodiments of the present application does not require using professional equipment to detect each position point on the aircraft skin one by one. Through the electromagnetic control sensor array and the magnetorheological fluid coating in the intelligent painting system, it can be conveniently determined which areas are damaged. In this way, the efficiency and accuracy of damage detection can be greatly improved, and the overall implementation cost is relatively low.

[0069] Specifically, in some embodiments, the determining the damaged area of the aircraft skin surface according to the response information of each signal receiver includes:

[0070] If the signal receiver does not receive the signal sent by the supporting signal transmitter, determine the signal transmission link between the signal receiver and the supporting signal transmitter as a signal interruption link;

[0071] Determine the area covered by the intersection of each signal interruption link as the damaged area of the aircraft skin surface.

[0072] In the embodiments of the present application, when determining the skin damage area on the aircraft surface based on the response information, in some embodiments, it is possible to determine, based on the response information, which signal receivers do not receive the signals sent by the supporting signal transmitters, and determine the signal transmission link between the signal receiver and the signal transmitter as a signal interruption link. It can be understood that the reason for the interruption of the signal interruption link indicates that there is a situation of skin damage on its path. Therefore, in the embodiments of the present application, the skin damage area on the aircraft surface can be determined based on each signal interruption link.

[0073] Specifically, please refer to Figure 4 , Figure 4 which shows a schematic diagram of a method for determining the skin damage area on the aircraft surface provided in the embodiments of the present application. As Figure 4 shown, in the case of skin damage on the aircraft skin, part of the signal transmission link cannot be normally transmitted and becomes a signal interruption link (shown by the dotted line). Figure 4 In it, when there is skin damage on the aircraft skin, the signal transmission links corresponding to the signal transmitters numbered 1, 2, 3, B, and C are determined as signal interruption links. In the embodiments of the present application, it is possible to determine the area covered by the intersection of these signal interruption links, and this area is the skin damage area on the aircraft surface.

[0074] It can be understood that in the embodiments of the present application, when determining the skin damage area on the aircraft surface in the above-mentioned manner, the determination accuracy is related to the density of the signal transmitters and signal receivers set in the electromagnetic control sensor array. The smaller the distance between adjacent devices in the electromagnetic control sensor array, the higher the detection accuracy.

[0075] Specifically, in some embodiments, determining the skin damage area on the aircraft surface according to the response information of each signal receiver includes:

[0076] Determining standard signal intersection points according to the signal transmission links in the standard signal matrix; wherein, the standard signal intersection points are the intersection points of any two signal transmission links;

[0077] Determining signal detection links according to the response information of each signal receiver;

[0078] Determining the standard signal intersection points passed by the signal detection links as detection signal intersection points;

[0079] Determining the skin damage area on the aircraft surface according to the detection signal intersection points.

[0080] In the embodiments of the present application, when detecting the skin damage area on the surface of an aircraft, detection can also be achieved based on signal intersection points. Specifically, first, the standard signal intersection points can be determined according to the signal transmission links in the standard signal matrix. Here, the standard signal intersection point is the intersection point of any two signal transmission links. For example, Figure 2 the intersection points of the respective signal transmission links shown can all be identified as standard signal intersection points. Then, during the actual detection process, the signal detection links can be determined according to the response information of each signal receiver. Specifically, if a signal receiver receives the signal sent by the supporting signal transmitter, the signal transmission link between the signal receiver and the supporting signal transmitter can be determined as the signal detection link; if the signal receiver does not receive the signal sent by the supporting signal transmitter, then the signal of the supporting signal transmitter can be traced and analyzed to determine the signal detection link corresponding to the supporting signal transmitter. In the embodiments of the present application, tracing and analyzing the signal of the signal transmitter means determining where the signal transmission of the signal transmitter is interrupted. Based on the interruption position point and the deployment position point of the signal transmitter, the signal detection link corresponding to the signal transmitter can be determined.

[0081] Next, in the embodiments of the present application, the standard signal intersection points passed by the signal detection links can be determined as the detected signal intersection points, and then, based on the detected signal intersection points, the skin damage area on the surface of the aircraft can be determined.

[0082] Specifically, determining the skin damage area on the surface of the aircraft based on the detected signal intersection points includes:

[0083] Taking each of the detected signal intersection points and the deployment position point as endpoints, a number of minimum rectangular units are determined on the surface of the aircraft; wherein, the inside and on the sides of the minimum rectangular unit do not include the detected signal intersection points and the deployment position point;

[0084] The area on the surface of the aircraft other than the minimum rectangular unit is determined as the skin damage area.

[0085] Refer to Figure 5 , Figure 5The figure shows a schematic diagram of determining the skin damage area on the aircraft surface by detecting signal intersection points in the embodiments of the present application. In the embodiments of the present application, after determining the signal intersection points, several minimum rectangular units can be determined on the aircraft surface with the signal intersection points and the deployment position points as endpoints. The so-called minimum rectangular unit is a rectangular unit that does not have other rectangular units with the signal intersection points and the deployment position points as endpoints inside, that is, the inside and sides of the minimum rectangular unit do not include the signal intersection points and the deployment position points. The areas covered by these minimum rectangular units are all areas where the signal link can transmit. Therefore, in the embodiments of the present application, the areas on the aircraft surface other than these minimum rectangular units can be determined as the skin damage areas. Compared with the method of determining the skin damage area according to the signal interruption link described above, in the embodiments of the present application, the accuracy of the skin damage area determined according to the signal intersection points is higher.

[0086] Specifically, in some embodiments, the method further includes:

[0087] If all the signal receivers receive the signals sent by the supporting signal transmitters, it is determined that there is no skin damage area on the aircraft surface.

[0088] In the embodiments of the present application, if all the signal receivers receive the signals sent by the supporting signal transmitters, it means that each signal transmission link is complete and not damaged. Therefore, it can be determined that there is no skin damage area on the aircraft surface.

[0089] The embodiments of the present application further provide an aircraft damage detection device based on an intelligent painting system. The device includes:

[0090] A building unit, configured to build a standard signal matrix according to the deployment position points of each group of supporting signal transmitters and signal receivers; wherein, the standard signal matrix is used to record the signal transmission links between each group of supporting signal transmitters and signal receivers;

[0091] A starting unit, configured to start each signal transmitter and detect the response information of each signal receiver; wherein, the response information is used to indicate whether the signal receiver receives the signal sent by the supporting signal transmitter;

[0092] A processing unit, configured to determine the skin damage area on the aircraft surface according to the response information of each signal receiver.

[0093] It can be understood that Figure 3The content in the embodiment of the aircraft damage detection method based on the intelligent painting system shown is applicable to the embodiment of the aircraft damage detection device based on the intelligent painting system. The functions specifically implemented in the embodiment of the aircraft damage detection device based on the intelligent painting system are the same as those in Figure 3 the embodiment of the aircraft damage detection method based on the intelligent painting system shown, and the beneficial effects achieved are the same as those in Figure 3 the embodiment of the aircraft damage detection method based on the intelligent painting system shown.

[0094] Referring to Figure 6 , an embodiment of the present application also discloses a computer device, including:

[0095] At least one processor 601;

[0096] At least one memory 602 for storing at least one program;

[0097] When at least one program is executed by at least one processor 601, at least one processor 601 implements the embodiment of the aircraft damage detection method based on the intelligent painting system as shown in Figure 3 .

[0098] It can be understood that the content in the embodiment of the aircraft damage detection method based on the intelligent painting system as shown in Figure 3 is applicable to the embodiment of this computer device. The functions specifically implemented in the embodiment of this computer device are the same as those in the embodiment of the aircraft damage detection method based on the intelligent painting system as shown in Figure 3 , and the beneficial effects achieved are the same as those in the embodiment of the aircraft damage detection method based on the intelligent painting system as shown in Figure 3 .

[0099] An embodiment of the present application also discloses a computer-readable storage medium, in which a program executable by a processor is stored. The program executable by the processor is used to implement the embodiment of the aircraft damage detection method based on the intelligent painting system as shown in Figure 3 .

[0100] It can be understood that the content in the embodiment of the aircraft damage detection method based on the intelligent painting system as shown in Figure 3 is applicable to the embodiment of this computer-readable storage medium. The functions specifically implemented in the embodiment of this computer-readable storage medium are the same as those in the embodiment of the aircraft damage detection method based on the intelligent painting system as shown in Figure 3 , and the beneficial effects achieved are the same as those in the embodiment of the aircraft damage detection method based on the intelligent painting system as shown in Figure 3 .

[0101] In some alternative embodiments, the functions / operations recited in the block diagrams may not occur in the order presented in the operational illustrations. For example, depending on the functions / operations involved, two consecutive blocks shown may actually be executed substantially simultaneously or the blocks may sometimes be executed in reverse order. Further, the embodiments presented and described in the flowcharts of the present application are provided by way of example for the purpose of providing a more comprehensive understanding of the technology. The disclosed methods are not limited to the operations and logical flows presented herein. Alternative embodiments are contemplated in which the order of various operations is altered and in which sub-operations described as part of a larger operation are performed independently.

[0102] Moreover, although the present application has been described in the context of functional modules, it should be understood that, unless otherwise stated to the contrary, one or more of the functions and / or features may be integrated in a single physical system and / or software module, or one or more functions and / or features may be implemented in separate physical systems or software modules. It should also be understood that a detailed discussion of the actual implementation of each module is not necessary for an understanding of the present application. Rather, given the attributes, functions, and internal relationships of the various functional modules in the system disclosed herein, the actual implementation of the modules will be understood within the ordinary skill of an engineer. Thus, those skilled in the art can implement the present application as set forth in the claims without undue experimentation. It should also be understood that the specific concepts disclosed are merely illustrative and are not intended to limit the scope of the present application, which is determined by the full scope of the appended claims and their equivalents.

[0103] If a function is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on such understanding, the technical solution of the present application, in essence, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product stored in a storage medium, including several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods of the various embodiments of the present application. The foregoing storage medium includes: various media that can store program codes, such as a USB flash drive, a portable hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disc.

[0104] The logic and / or steps represented in the flowchart or otherwise described herein, for example, can be considered as a definitional sequence list of executable instructions for implementing logical functions, and can be specifically implemented in any computer-readable medium for use by an instruction execution system, system, or device (such as a computer-based system, a system including a processor, or other systems that can fetch and execute instructions from the instruction execution system, system, or device), or used in conjunction with these instruction execution systems, systems, or devices. For the purposes of this specification, a "computer-readable medium" can be any system that can contain, store, communicate, propagate, or transport a program for use by or in conjunction with an instruction execution system, system, or device.

[0105] More specific examples (a non-exhaustive list) of computer-readable media include the following: an electrical connection portion (electronic system) having one or more wirings, a portable computer diskette (magnetic system), a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber system, and a portable compact disc read-only memory (CDROM). Additionally, a computer-readable medium can even be paper or other suitable media on which a program can be printed, because the program can be obtained electronically, for example, by optically scanning the paper or other media, followed by editing, interpretation, or otherwise processing as appropriate, and then stored in a computer memory.

[0106] It should be understood that various parts of the present application can be implemented using hardware, software, firmware, or a combination thereof. In the above-described embodiments, multiple steps or methods can be implemented using software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented using hardware, as in another embodiment, any one or a combination of the following techniques well known in the art can be used: discrete logic circuits having logic gate circuits for implementing logical functions on data signals, application specific integrated circuits having appropriate combinational logic gate circuits, programmable gate arrays (PGAs), field programmable gate arrays (FPGAs), etc.

[0107] In the above description of this specification, the description with reference to terms such as "one embodiment / Example", "another embodiment / Example", or "certain embodiments / Examples", etc., means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0108] Although the embodiments of the present application have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present application. The scope of the present application is defined by the claims and their equivalents.

[0109] The above has specifically described the preferred embodiments of the present application, but the present application is not limited to the embodiments. Those skilled in the art can make various equivalent deformations or substitutions without departing from the spirit of the present application, and these equivalent deformations or substitutions are all included within the scope defined by the claims of the present application.

[0110] In the description of this specification, the description with reference to terms such as "one embodiment", "another embodiment", or "certain embodiments" means that the specific features, structures, materials, or characteristics described in connection with the embodiments or examples are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0111] Although the embodiments of the present application have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present application. The scope of the present application is defined by the claims and their equivalents.

Claims

1. An aircraft damage detection method based on an intelligent painting system, characterized in that, The intelligent painting system includes an electromagnetic control sensor array and a composite paint surface laid on the surface of the aircraft. The composite paint surface includes an insulating primer layer, a magnetorheological fluid coating, and a protective paint layer laid in sequence. Among them, the insulating primer layer is in contact with the skin on the surface of the aircraft; the electromagnetic control sensor array includes several sets of supporting signal transmitters and signal receivers. The supporting signal transmitters and signal receivers in each set are arranged in a horizontal and vertical staggered manner, and the signal transmitters and signal receivers are connected to the magnetorheological fluid coating; The aircraft damage detection method includes: Establish a standard signal matrix according to the deployment position points of the supporting signal transmitters and signal receivers in each set; among them, the standard signal matrix is used to record the signal transmission link between the supporting signal transmitters and signal receivers in each set; Start each of the signal transmitters and detect the response information of each of the signal receivers; among them, the response information is used to indicate whether the signal receiver has received the signal sent by the supporting signal transmitter; Determine the damaged area of the skin on the surface of the aircraft according to the response information of each of the signal receivers; The determining the damaged area of the skin on the surface of the aircraft according to the response information of each of the signal receivers includes: If the signal receiver does not receive the signal sent by the supporting signal transmitter, determine the signal transmission link between the signal receiver and the supporting signal transmitter as a signal interruption link; Determine the area covered by the intersection of each of the signal interruption links as the damaged area of the skin on the surface of the aircraft.

2. The aircraft damage detection method based on an intelligent painting system according to claim 1, characterized in that, The determining the damaged area of the skin on the surface of the aircraft according to the response information of each of the signal receivers includes: Determine standard signal intersection points according to the signal transmission links in the standard signal matrix; among them, the standard signal intersection points are the intersection points of any two signal transmission links; Determine signal detection links according to the response information of each of the signal receivers; Determine the standard signal intersection points passed by the signal detection links as detection signal intersection points; Determine the damaged area of the skin on the surface of the aircraft according to the detection signal intersection points.

3. The aircraft damage detection method based on an intelligent painting system according to claim 2, characterized in that The determining the signal detection links according to the response information of each of the signal receivers includes: If the signal receiver receives the signal sent by the supporting signal transmitter, determine the signal transmission link between the signal receiver and the supporting signal transmitter as a signal detection link; Or, if the signal receiver does not receive the signal sent by the supporting signal transmitter, perform a trace analysis on the signal of the supporting signal transmitter to determine the signal detection link corresponding to the supporting signal transmitter.

4. The aircraft damage detection method based on an intelligent painting system according to claim 3, characterized in that, The determining the damaged area of the skin on the surface of the aircraft according to the detection signal intersection points includes: Take each of the detection signal intersection points and the deployment position points as endpoints, and determine several minimum rectangular units on the surface of the aircraft; among them, the inside and edges of the minimum rectangular unit do not include the detection signal intersection points and the deployment position points; Determine the area on the surface of the aircraft other than the smallest rectangular unit as the skin damage area.

5. A method for aircraft damage detection based on an intelligent painting system according to any one of claims 1-4, characterized in that, The protective paint layer uses a high-transparency protective paint layer.

6. The aircraft damage detection method based on an intelligent painting system according to claim 1, characterized in that, The method further includes: If all the signal receivers receive the signals sent by the supporting signal transmitters, it is determined that there is no skin damage area on the surface of the aircraft.

7. An aircraft damage detection device based on an intelligent painting system, characterized in that, The intelligent painting system includes an electromagnetic control sensor array and a composite paint surface laid on the surface of the aircraft. The composite paint surface includes an insulating primer layer, a magnetorheological fluid coating, and a protective paint layer laid in sequence. Among them, the insulating primer layer is in contact with the skin on the surface of the aircraft; the electromagnetic control sensor array includes several sets of supporting signal transmitters and signal receivers. Each set of supporting signal transmitters and signal receivers are arranged in a horizontal and vertical staggered manner, and the signal transmitters and signal receivers are connected to the magnetorheological fluid coating; The aircraft damage detection device includes: A building unit, configured to build a standard signal matrix according to the deployment position points of each set of supporting signal transmitters and signal receivers; wherein, the standard signal matrix is used to record the signal transmission link between each set of supporting signal transmitters and signal receivers; A starting unit, configured to start each of the signal transmitters and detect the response information of each of the signal receivers; wherein, the response information is used to indicate whether the signal receiver receives the signal sent by the supporting signal transmitter; A processing unit, configured to determine the skin damage area on the surface of the aircraft according to the response information of each of the signal receivers; Specifically, the processing unit is configured to: If the signal receiver does not receive the signal sent by the supporting signal transmitter, determine the signal transmission link between the signal receiver and the supporting signal transmitter as a signal interruption link; Determine the area covered by the intersection of each of the signal interruption links as the skin damage area on the surface of the aircraft.

8. A computer device, characterized in that, Includes: At least one processor; At least one memory for storing at least one program; When the at least one program is executed by the at least one processor, the at least one processor implements an aircraft damage detection method according to any one of claims 1-6.

9. A computer-readable storage medium storing a program executable by a processor, characterized in that: The program executable by the processor, when executed by the processor, is used to implement an aircraft damage detection method according to any one of claims 1-6.

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