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

Abstract

The invention discloses an aircraft damage detection method, device and equipment based on an intelligent coating system, and the method comprises the steps: building a standard signal matrix according to the deployment position points of each group of matched signal transmitters and signal receivers; wherein the standard signal matrix is used for recording signal transmission links between each group of matched signal transmitters and signal receivers; starting each signal transmitter, and detecting response information of each signal receiver; wherein the response information is used for representing whether the signal receiver receives a signal sent by the matched signal transmitter; and according to the response information of each signal receiver, determining a skin damage area on the surface of the aircraft. According to the method, professional equipment does not need to be used for detecting all position points on the aircraft skin one by one, the damage detection efficiency and accuracy can be greatly improved, and the overall implementation cost is low. The method can be widely applied to the technical field of airplanes.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, 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 aircraft that can fly in the atmosphere, usually relying on the lift generated by its wings to support the weight of the fuselage, and moving forward through the thrust or pull provided by the engine. Aircraft skin refers to the thin shell covering the outer surface of the aircraft frame, which is crucial to the safe operation of the aircraft.

[0003] In the related technology, in order to ensure the safe operation of the aircraft, it is often necessary to perform damage detection on the aircraft skin. At present, when performing damage detection on the aircraft skin, the staff generally uses professional detection equipment to detect the situation of each location. This implementation method takes a long time, has high labor costs, and is prone to omissions and negligence, resulting in low detection accuracy, which affects the safety of aircraft operation. Summary of the invention

[0004] The purpose of this application is to solve one of the technical problems existing in the related art to at least a certain extent.

[0005] To this end, one purpose 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] In order to achieve the above technical objectives, the technical solutions adopted by 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 coating system, wherein the intelligent coating system includes an electromagnetically controlled sensor array and a composite paint surface laid on the surface of the aircraft, wherein 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 of the aircraft surface; the electromagnetically controlled sensor array includes a plurality of sets of matching signal transmitters and signal receivers, wherein each set of matching signal transmitters and signal receivers are arranged in a horizontally and vertically staggered manner, and the signal transmitters and the signal receivers are connected to the magnetic fluid coating;

[0008] The aircraft damage detection method comprises:

[0009] A standard signal matrix is ​​established according to the deployment positions of the signal transmitters and the signal receivers of each group; wherein the standard signal matrix is ​​used to record the signal transmission links between the signal transmitters and the signal receivers of each group;

[0010] Starting each of the signal transmitters and detecting 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 matching signal transmitter;

[0011] The skin damage area on the aircraft surface is determined according to the response information of each of the signal receivers.

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

[0013] Furthermore, in one embodiment of the present application, determining the skin damage area on the aircraft surface according to the response information of each of the signal receivers includes:

[0014] If the signal receiver does not receive the signal sent by the matching signal transmitter, the signal transmission link between the signal receiver and the matching signal transmitter is determined as a signal interruption link;

[0015] The skin damage area on the aircraft surface is determined by using the area cross-covered by each of the signal interruption links.

[0016] Furthermore, in one embodiment of the present application, determining the skin damage area on the aircraft surface according to the response information of each of the signal receivers includes:

[0017] Determine a standard signal intersection point according to the signal transmission links in the standard signal matrix; wherein the standard signal intersection point is the intersection point of any two signal transmission links;

[0018] Determining a signal detection link according to response information of each of the signal receivers;

[0019] Determine a standard signal intersection point through which the signal detection link passes as a detection signal intersection point;

[0020] The skin damage area on the aircraft surface is determined according to the intersection points of the detection signals.

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

[0022] If the signal receiver receives a signal sent by the matching signal transmitter, a signal transmission link between the signal receiver and the matching signal transmitter is determined as a signal detection link;

[0023] Alternatively, if the signal receiver does not receive the signal sent by the matching signal transmitter, the signal of the matching signal transmitter is tracked and analyzed to determine the signal detection link corresponding to the matching signal transmitter.

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

[0025] Taking each of the detection signal intersections and the deployment location points as endpoints, a plurality of minimum rectangular units are determined on the aircraft surface; wherein the interior and the sides of the minimum rectangular units do not include the detection signal intersections and the deployment location points;

[0026] An area on the aircraft surface except the minimum rectangular unit is determined as a skin damage area.

[0027] Furthermore, in one embodiment of the present application, the protective paint layer adopts a high-transmittance protective paint layer.

[0028] Furthermore, in one embodiment of the present application, the method further includes:

[0029] If all of the signal receivers receive the signal sent by the matching signal transmitter, it is determined that there is no skin damage area on the surface of the aircraft.

[0030] On the other hand, an embodiment of the present application provides an aircraft damage detection device based on an intelligent coating system, wherein the intelligent coating system includes an electromagnetically controlled sensor array and a composite paint surface laid on the surface of the aircraft, wherein 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 of the aircraft surface; the electromagnetically controlled sensor array includes a plurality of sets of matching signal transmitters and signal receivers, wherein each set of matching signal transmitters and signal receivers are arranged in a horizontally and vertically staggered manner, and the signal transmitters and the signal receivers are connected to the magnetic fluid coating;

[0031] The aircraft damage detection device comprises:

[0032] An establishing unit, used to establish a standard signal matrix according to the deployment position points of each group of the signal transmitters and the signal receivers; wherein the standard signal matrix is ​​used to record the signal transmission links between each group of the signal transmitters and the signal receivers;

[0033] A start-up unit, used to start each of the signal transmitters and detect 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 matching signal transmitter;

[0034] A processing unit is used to determine 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 the intelligent painting system.

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

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

[0041] The embodiment of the present application discloses an aircraft damage detection method based on an intelligent coating system, which establishes a standard signal matrix according to the deployment position points of each group of matching signal transmitters and signal receivers; wherein the standard signal matrix is ​​used to record the signal transmission link between each group of matching signal transmitters and signal receivers; each signal transmitter is started to detect the response information of each signal receiver; wherein the response information is used to characterize whether the signal receiver has received the signal sent by the matching signal transmitter; and according to the response information of each signal receiver, the skin damage area on the surface of the aircraft is determined. This method does not require the use of professional equipment to detect each position point on the aircraft skin one by one. Through the electromagnetic control sensor array and the magnetic fluid coating in the intelligent coating system, it is convenient to determine which areas have been damaged. In this way, the efficiency and accuracy of damage detection can be greatly improved, and the overall implementation cost is low. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following introduction is made to the drawings of the embodiments of the present application or the related technical solutions in the prior art. It should be understood that the drawings introduced below are only for the convenience of clearly describing some embodiments of the technical solutions of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without paying any creative work.

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

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

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

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

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

[0048] Figure 6 A schematic diagram of the structure of a computer device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0049] The present application is further described below in conjunction with the accompanying drawings and specific embodiments. The described embodiments should not be regarded as limiting the present application, and all other embodiments obtained by ordinary technicians in this field without creative work are 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, but it will be understood that “some embodiments” may be the same subset or different subsets of all possible embodiments and may be combined with each other without conflict.

[0051] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art 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, usually relying on the lift generated by its wings to support the weight of the fuselage, and moving forward through the thrust or pull provided by the engine. Aircraft skin refers to the thin shell covering the outer surface of the aircraft frame, which is crucial to the safe operation of the aircraft.

[0053] In the related technology, in order to ensure the safe operation of the aircraft, it is often necessary to perform damage detection on the aircraft skin. At present, when performing damage detection on the aircraft skin, the staff generally uses professional detection equipment to detect the situation of each location. This implementation method takes a long time, has high labor costs, and is prone to omissions and negligence, resulting in low detection accuracy, which affects the safety of aircraft operation.

[0054] In view of this, an aircraft damage detection method based on an intelligent coating system is provided in an embodiment of the present application. A standard signal matrix is ​​established according to the deployment position points of each group of matching signal transmitters and signal receivers; wherein the standard signal matrix is ​​used to record the signal transmission link between each group of matching signal transmitters and signal receivers; each signal transmitter is started to detect the response information of each signal receiver; wherein the response information is used to characterize whether the signal receiver has received the signal sent by the matching signal transmitter; and according to the response information of each signal receiver, the skin damage area on the surface of the aircraft is determined. This method does not require the use of professional equipment to detect each position point on the aircraft skin one by one. Through the electromagnetic control sensor array and the magnetic fluid coating in the intelligent coating system, it is convenient to determine which areas have been damaged. In this way, the efficiency and accuracy of damage detection can be greatly improved, and the overall implementation cost is low.

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

[0056] In the embodiment of the present application, the intelligent coating system includes an electromagnetically controlled sensor array and a composite paint surface laid on the surface of the aircraft. Figure 1 , Figure 1 A schematic diagram of a composite paint surface of an intelligent coating system provided in an embodiment of the present application is shown. For the composite paint surface, it includes an insulating primer layer, a magnetic fluid coating and a protective paint layer sequentially laid on the skin of the aircraft surface. The insulating primer layer is laid directly on the skin of the aircraft surface, the magnetic fluid coating is laid on the insulating primer layer, and the protective paint layer is laid on the magnetic fluid coating. In some embodiments, the protective paint layer can adopt a high-transmittance protective paint layer. The high-transmittance protective paint layer generally refers to a coating material applied to the surface to provide protection and increase transparency. This coating is widely used in various fields, such as automobiles, electronic products, furniture, artwork protection, etc., has a good protective effect, and has good transparency and is easy to clean.

[0057] In the embodiment of the present application, the electromagnetic control sensor array includes a plurality of sets of matching signal transmitters and signal receivers. Figure 2 , Figure 2A schematic diagram of an electromagnetic control sensor array provided in an embodiment of the present application is shown. In the electromagnetic control sensor array, each group of matching signal transmitters and signal receivers can be arranged in a horizontally and vertically staggered manner, and both the signal transmitters and signal receivers can be connected to the magnetic fluid coating.

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

[0059] In the electromagnetic control sensor array, the matching signal transmitter and signal receiver are connected to the magnetic fluid coating. The signal generator transmits signals to the corresponding signal receiver in a directional manner. When the signal emitted by the signal transmitter passes through the magnetic fluid material, under ideal conditions, the signal will be received and recognized by the corresponding signal receiver. When the skin on the surface of the aircraft is damaged, due to the destruction of the magnetic fluid coating, some signal receivers will not be able to receive signals normally. Based on this feature, aircraft damage detection can be achieved.

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

[0061] Step 310: Establish a standard signal matrix according to the deployment locations of the signal transmitters and signal receivers of each group; wherein the standard signal matrix is ​​used to record the signal transmission links between the signal transmitters and signal receivers of each group;

[0062] Step 320: start each of the signal transmitters and detect 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 matching signal transmitter;

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

[0064] In an embodiment of the present application, a method for detecting damage to an aircraft based on an intelligent painting system is provided. Based on the intelligent painting system provided above, the detection method can realize damage detection for the aircraft skin.

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

[0066] When performing damage detection on the aircraft skin, each signal transmitter can be started, 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 matching signal transmitter. Exemplarily, in some embodiments, the response information can be represented by 0 or 1 signals. If the signal receiver receives the signal sent by the matching 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 matching 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] Based on the response information of each signal receiver, it can be determined which signal receivers have not received the signal sent by the corresponding signal transmitter. Therefore, it can be determined which signal transmission links in the standard signal matrix are cut off, thereby determining the skin damage area on the aircraft surface.

[0068] It is understandable that the aircraft damage detection method provided in the embodiment of the present application 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 magnetic fluid coating in the intelligent coating system, it is convenient to determine which areas have been damaged. In this way, the efficiency and accuracy of damage detection can be greatly improved, and the overall implementation cost is low.

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

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

[0071] The skin damage area on the aircraft surface is determined by using the area cross-covered by each of the signal interruption links.

[0072] In the embodiment of the present application, when determining the skin damage area on the aircraft surface according to the response information, in some embodiments, it is possible to determine which signal receivers have not received the signal sent by the matching signal transmitter according to the response information, and determine the signal transmission link between the signal receiver and the signal transmitter as a signal interruption link. It is understandable that the interruption of the signal interruption link indicates that there is skin damage on its path. Therefore, in the embodiment of the present application, the skin damage area on the aircraft surface can be determined according to each signal interruption link.

[0073] For details, please refer to Figure 4 , Figure 4 A schematic diagram of determining the skin damage area on the surface of an aircraft provided in an embodiment of the present application is shown. Figure 4 As shown, when the aircraft skin is damaged, part of the signal transmission link cannot be transmitted normally and becomes a signal interruption link (shown by the dotted line). Figure 4 In the embodiment of the present invention, when the aircraft skin is damaged, the signal transmission links corresponding to the signal transmitters numbered 1, 2, 3, B, and C are determined to be signal interruption links. In the embodiment of the present application, the area cross-covered by these signal interruption links can be determined, and this area is the skin damage area on the aircraft surface.

[0074] It can be understood that in the embodiment of the present application, when the above-mentioned method is used to determine the skin damage area on the aircraft surface, the determination accuracy is related to the density of 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 of the signal receivers includes:

[0076] Determine a standard signal intersection point according to the signal transmission links in the standard signal matrix; wherein the standard signal intersection point is the intersection point of any two signal transmission links;

[0077] Determining a signal detection link according to response information of each of the signal receivers;

[0078] Determine a standard signal intersection point through which the signal detection link passes as a detection signal intersection point;

[0079] The skin damage area on the aircraft surface is determined according to the intersection points of the detection signals.

[0080] In the embodiment of the present application, when detecting the skin damage area on the surface of the aircraft, the detection can also be implemented based on the signal intersection point. Specifically, first, the standard signal intersection point can be determined based on the signal transmission link in the standard signal matrix. Here, the standard signal intersection point is the intersection point of any two signal transmission links, such as Figure 2 The intersections of the various signal transmission links shown can all be identified as standard signal intersections. Then, in the actual detection process, the signal detection link can be determined based on the response information of each signal receiver. Specifically, if the signal receiver receives a signal sent by a matching signal transmitter, the signal transmission link between the signal receiver and the matching signal transmitter can be determined as a signal detection link; and if the signal receiver does not receive a signal sent by a matching signal transmitter, the signal of the matching signal transmitter can be tracked and analyzed to determine the signal detection link corresponding to the matching signal transmitter. In an embodiment of the present application, the signal of the signal transmitter is tracked and analyzed, that is, it is determined where the signal transmission of the signal transmitter is interrupted, and based on the location of the interruption and the deployment location of the signal transmitter, the signal detection link corresponding to the signal transmitter can be determined.

[0081] Next, in an embodiment of the present application, a standard signal intersection point through which a signal detection link passes can be determined as a detection signal intersection point, and then, based on the detection signal intersection point, a skin damage area on the aircraft surface can be determined.

[0082] Specifically, determining the skin damage area on the aircraft surface according to the intersection of the detection signals includes:

[0083] Taking each of the detection signal intersections and the deployment location points as endpoints, a plurality of minimum rectangular units are determined on the aircraft surface; wherein the interior and the sides of the minimum rectangular units do not include the detection signal intersections and the deployment location points;

[0084] An area on the aircraft surface except the minimum rectangular unit is determined as a skin damage area.

[0085] Reference Figure 5 , Figure 5A schematic diagram of determining the skin damage area on the aircraft surface by detecting the intersection of signals in an embodiment of the present application is shown. In the embodiment of the present application, after determining the intersection of the detection signals, several minimum rectangular units can be determined on the aircraft surface with the intersection of the detection signals and the deployment position point as endpoints. The so-called minimum rectangular unit is a rectangular unit that does not have other rectangular units with the intersection of signals and the deployment position point as endpoints, that is, the interior and sides of the minimum rectangular unit do not include the intersection of detection signals and the deployment position point. The areas covered by these minimum rectangular units are all areas where the signal link can be transmitted. Therefore, in the embodiment of the present application, the areas on the aircraft surface other than these minimum rectangular units can be determined as skin damage areas. Compared with the aforementioned method of determining the skin damage area based on the signal interruption link, in the embodiment of the present application, the skin damage area determined based on the intersection of detection signals has a higher accuracy.

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

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

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

[0089] The present application also provides an aircraft damage detection device based on an intelligent painting system, the device comprising:

[0090] An establishing unit, used to establish a standard signal matrix according to the deployment position points of each group of the signal transmitters and the signal receivers; wherein the standard signal matrix is ​​used to record the signal transmission links between each group of the signal transmitters and the signal receivers;

[0091] A start-up unit, used to start each of the signal transmitters and detect 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 matching signal transmitter;

[0092] A processing unit is used to determine the skin damage area on the aircraft surface according to the response information of each of the signal receivers.

[0093] Understandably, Figure 3The contents of the embodiment of the aircraft damage detection method based on the intelligent painting system shown in the figure are applicable to the embodiment of the aircraft damage detection device based on the intelligent painting system. The functions specifically implemented by the embodiment of the aircraft damage detection device based on the intelligent painting system are the same as those of the embodiment of the aircraft damage detection method based on the intelligent painting system. Figure 3 The aircraft damage detection method based on the intelligent coating system shown in the embodiment is the same as that of the embodiment shown in the embodiment, and the beneficial effects achieved are the same as those achieved in the embodiment shown in the embodiment. Figure 3 The beneficial effects achieved by the embodiment of the aircraft damage detection method based on the intelligent painting system shown are also the same.

[0094] Reference Figure 6 , the embodiment of the present application further discloses a computer device, including:

[0095] at least one processor 601;

[0096] At least one memory 602, used to store 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 following Figure 3 An embodiment of an aircraft damage detection method based on an intelligent painting system is shown.

[0098] It is understandable that if Figure 3 The contents of the embodiment of an aircraft damage detection method based on an intelligent coating system shown in FIG. 1 are applicable to the computer device embodiment. The functions specifically implemented by the computer device embodiment are similar to those in FIG. Figure 3 The aircraft damage detection method based on the intelligent coating system shown in the embodiment is the same as that shown in the embodiment of the invention, and the beneficial effects achieved are the same as those of the embodiment of the invention. Figure 3 The beneficial effects achieved by the embodiment of the aircraft damage detection method based on the intelligent painting system shown are also the same.

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

[0100] It is understandable that if Figure 3 The contents of the embodiment of an aircraft damage detection method based on an intelligent painting system shown in the figure are applicable to the embodiment of this computer-readable storage medium. The functions specifically implemented by this computer-readable storage medium embodiment are similar to those in the embodiment of the present invention. Figure 3 The aircraft damage detection method based on the intelligent coating system shown in the embodiment is the same as that shown in the embodiment of the invention, and the beneficial effects achieved are the same as those of the embodiment of the invention. Figure 3 The beneficial effects achieved by the embodiment of the aircraft damage detection method based on the intelligent painting system shown are also the same.

[0101] In some selectable embodiments, the function / operation mentioned in the block diagram may not occur in the order mentioned in the operation diagram. For example, depending on the function / operation involved, the two boxes shown in succession can actually be executed substantially simultaneously or the boxes can sometimes be executed in reverse order. In addition, the embodiment presented and described in the flow chart of the application is provided by way of example, for the purpose of providing a more comprehensive understanding of technology. The disclosed method is not limited to the operation and logic flow presented herein. Selectable embodiments are expected, wherein the order of various operations is changed and the sub-operation of a part described as a larger operation is performed independently.

[0102] In addition, although the present application is described in the context of functional modules, it should be understood that, unless otherwise specified, one or more of the functions and / or features can be integrated into a single physical system and / or software module, or one or more functions and / or features can be implemented in a separate physical system or software module. It can also be understood that a detailed discussion of the actual implementation of each module is unnecessary for understanding the present application. More specifically, in view of the properties, functions and internal relationships of the various functional modules in the system disclosed herein, the actual implementation of the module will be understood within the conventional techniques of engineers. Therefore, those skilled in the art can implement the present application set forth in the claims without excessive experimentation using ordinary techniques. It can 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 attached claims and their equivalents.

[0103] If the 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 this understanding, the technical solution of the present application, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, which is stored in a storage medium and includes several instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the various embodiments of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, and other media that can store program codes.

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

[0105] More specific examples of computer-readable media (a non-exhaustive list) include the following: an electrical connection with one or more wires (electronic systems), a portable computer disk case (magnetic systems), a random access memory (RAM), a read-only memory (ROM), an erasable and programmable read-only memory (EPROM or flash memory), a fiber optic system, and a portable compact disk read-only memory (CDROM). In addition, the computer-readable medium may even be a paper or other suitable medium on which the program is printed, since the program may be obtained electronically, for example, by optically scanning the paper or other medium, followed by editing, deciphering or, if necessary, processing in another suitable manner, and then stored in a computer memory.

[0106] It should be understood that the various parts of the present application can be implemented by hardware, software, firmware or a combination thereof. In the above-mentioned embodiments, multiple steps or methods can be implemented by software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented by hardware, as in another embodiment, it can be implemented by any one of the following technologies known in the art or their combination: a discrete logic circuit having a logic gate circuit for implementing a logic function for a data signal, a dedicated integrated circuit having a suitable combination of logic gate circuits, a programmable gate array (PGA), a field programmable gate array (FPGA), etc.

[0107] In the above description of this specification, the description with reference to the terms "one embodiment / example", "another embodiment / example" or "certain embodiments / examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may 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 skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present application, and that the scope of the present application is defined by the claims and their equivalents.

[0109] The above is a specific description of the preferred implementation of the present application, but the present application is not limited to the embodiments. Those skilled in the art can make various equivalent modifications or substitutions without violating the spirit of the present application. These equivalent modifications or substitutions are all included in the scope defined by the claims of the present application.

[0110] In the description of this specification, the description with reference to the terms "one embodiment", "another embodiment" or "certain embodiments" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiments or examples are included in at least one embodiment or example of the present application. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may 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 skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present application, and that 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 coating system includes an electromagnetic control sensor array and a composite paint surface laid on the surface of the aircraft, wherein 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 of the aircraft surface; the electromagnetic control sensor array includes a plurality of sets of matching signal transmitters and signal receivers, wherein each set of matching signal transmitters and signal receivers are arranged in a horizontally and vertically staggered manner, and the signal transmitters and signal receivers are connected to the magnetic fluid coating; The aircraft damage detection method comprises: A standard signal matrix is ​​established according to the deployment positions of the signal transmitters and the signal receivers of each group; wherein the standard signal matrix is ​​used to record the signal transmission links between the signal transmitters and the signal receivers of each group; Starting each of the signal transmitters and detecting 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 matching signal transmitter; The skin damage area on the aircraft surface is determined according to the response information of each of the signal receivers.

2. The aircraft damage detection method based on the intelligent painting system according to claim 1 is characterized in that: Determining the skin damage area on the aircraft surface according to the response information of each of the signal receivers includes: If the signal receiver does not receive the signal sent by the matching signal transmitter, the signal transmission link between the signal receiver and the matching signal transmitter is determined as a signal interruption link; The skin damage area on the aircraft surface is determined by using the area cross-covered by each of the signal interruption links.

3. The aircraft damage detection method based on the intelligent painting system according to claim 1 is characterized in that: Determining the skin damage area on the aircraft surface according to the response information of each of the signal receivers includes: Determine a standard signal intersection point according to the signal transmission links in the standard signal matrix; wherein the standard signal intersection point is the intersection point of any two signal transmission links; Determining a signal detection link according to response information of each of the signal receivers; Determine a standard signal intersection point through which the signal detection link passes as a detection signal intersection point; The skin damage area on the aircraft surface is determined according to the intersection points of the detection signals.

4. The aircraft damage detection method based on the intelligent painting system according to claim 3 is characterized in that: The step of determining a signal detection link according to the response information of each of the signal receivers includes: If the signal receiver receives a signal sent by the matching signal transmitter, a signal transmission link between the signal receiver and the matching signal transmitter is determined as a signal detection link; Alternatively, if the signal receiver does not receive the signal sent by the matching signal transmitter, the signal of the matching signal transmitter is tracked and analyzed to determine the signal detection link corresponding to the matching signal transmitter.

5. The aircraft damage detection method based on the intelligent painting system according to claim 4 is characterized in that: Determining the skin damage area on the aircraft surface according to the intersection of the detection signals includes: Taking each of the detection signal intersections and the deployment location points as endpoints, a plurality of minimum rectangular units are determined on the aircraft surface; wherein the interior and the sides of the minimum rectangular units do not include the detection signal intersections and the deployment location points; An area on the aircraft surface except the minimum rectangular unit is determined as a skin damage area.

6. An aircraft damage detection method based on an intelligent painting system according to any one of claims 1 to 5, characterized in that: The protective paint layer is a high-transmittance protective paint layer.

7. The aircraft damage detection method based on the intelligent painting system according to claim 1 is characterized in that: The method further comprises: If all of the signal receivers receive the signal sent by the matching signal transmitter, it is determined that there is no skin damage area on the surface of the aircraft.

8. An aircraft damage detection device based on an intelligent painting system, characterized in that: The intelligent coating system includes an electromagnetic control sensor array and a composite paint surface laid on the surface of the aircraft, wherein 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 of the aircraft surface; the electromagnetic control sensor array includes a plurality of sets of matching signal transmitters and signal receivers, wherein each set of matching signal transmitters and signal receivers are arranged in a horizontally and vertically staggered manner, and the signal transmitters and signal receivers are connected to the magnetic fluid coating; The aircraft damage detection device comprises: An establishing unit, used to establish a standard signal matrix according to the deployment position points of each group of the signal transmitters and the signal receivers; wherein the standard signal matrix is ​​used to record the signal transmission links between each group of the signal transmitters and the signal receivers; A start-up unit, used to start each of the signal transmitters and detect 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 matching signal transmitter; A processing unit is used to determine the skin damage area on the aircraft surface according to the response information of each of the signal receivers.

9. A computer device, characterized in that: include: 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 based on an intelligent painting system as described in any one of claims 1 to 7.

10. A computer-readable storage medium storing a program executable by a processor, characterized in that: The processor-executable program is used to implement an aircraft damage detection method based on an intelligent painting system as described in any one of claims 1 to 7 when executed by the processor.

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