A method and device for rapid detection of aircraft combat damage

Abstract

The present invention discloses a method and equipment for rapid detection of aircraft combat damage, wherein the method comprises: classifying the damage types of aircraft composite material-based stealth coatings; clarifying the in-situ detection method of composite material-based stealth coating damage. The detection method is: in the case of penetrating damage, a phased array detection method is used to detect the damaged part to be detected according to preset parameters, and the damage size of the layer around the hole in the damaged part to be detected is determined; in the case of non-penetrating damage, a high-frequency ultrasonic detection module with a preset excitation circuit is used to determine the damage depth of the damaged part to be detected, wherein the excitation circuit is used to control the sending and receiving of the signal of the high-frequency ultrasonic detection module. The method for rapid detection of aircraft combat damage provided by the present application can not only realize the in-situ measurement of the damage position, size and depth, but also realize multiple uses of one machine, meeting the requirements of portability, miniaturization and combination of field support.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a method and equipment for rapid detection of aircraft combat damage. Background Art

[0002] Aircraft combat damage repair is an important way to improve the dispatch capability of combat damaged aircraft, which requires three steps: combat damage detection, combat damage assessment, and combat damage repair. Therefore, aircraft combat damage detection is a prerequisite for combat damage repair. However, there are many aircraft combat damages, their distribution is random, and their damage patterns are diverse. It is very difficult to quickly detect all combat damages in a short period of time.

[0003] In order to reduce the weight of the aircraft and improve its stealth capability, stealth coatings are usually sprayed on the composite substrate of the aircraft. However, the composite substrate structure sprayed with coatings will produce various types of damage under low-speed and high-speed impacts. At present, infrared thermal imaging detection technology and terahertz detection technology are mainly used to detect possible damage such as delamination and shedding of the structure. However, the detection equipment is bulky and has poor environmental adaptability. It cannot meet the needs of field wartime detection, and the accuracy of the detection results is poor. Summary of the invention

[0004] The purpose of the embodiments of the present invention is to provide a method and device for rapid detection of aircraft combat damage, which can solve at least one of the above-mentioned problems existing in the prior art.

[0005] In order to solve the above technical problems, the present invention provides the following technical solutions:

[0006] An embodiment of the present invention provides a method for rapid detection of aircraft combat damage, wherein the method comprises:

[0007] Determine the damage type of the composite material-based stealth coating on the fuselage, where the damage type includes: penetrating damage and non-penetrating damage;

[0008] In the case of penetrating damage, the phased array detection method is used to detect the damaged area according to the preset parameters to determine the damage size of the layer around the hole in the damaged area; wherein the preset parameters include: detection frequency, scanning mode and imaging gate parameters;

[0009] In the case of non-penetrating damage, a high-frequency ultrasonic detection module with a preset excitation circuit is used to determine the damage depth of the detected damage, wherein the excitation circuit is used to control the sending and receiving of signals of the high-frequency ultrasonic detection module.

[0010] Optionally, in the case of penetrating damage, the step of using a phased array detection method to detect the detected damage according to preset parameters to determine the damage size of the layer around the hole at the detected damage includes:

[0011] In the case of penetrating damage, the change type of the bottom surface thickness of the detected damage is determined by the first scanning waveform obtained by pre-scanning; wherein the change types include: step change of the bottom surface thickness and gradual change of the bottom surface thickness, and the first scanning waveform is a detection signal perpendicular to the reinforcement direction or the thickness change direction;

[0012] Searching the system for a target detection method that matches the change type;

[0013] The detected damaged part is detected according to the target detection method and preset parameters to determine the damage size of the layer around the hole in the detected damaged part.

[0014] Optionally, the step of detecting the detected damaged part according to the target detection method and preset parameters to determine the damage size of the layer around the hole in the detected damaged part includes:

[0015] When the change type is a step change in bottom thickness, setting the detection range of the phased array probe to the maximum workpiece thickness;

[0016] The phased array probe is moved to perform linear scanning along the reinforcement direction to obtain a second scanning waveform diagram and / or a third scanning waveform diagram; wherein the second scanning waveform is a detection waveform of an intact reinforcement structure, and the third scanning waveform is a damage detection waveform of the reinforcement structure, and the preset parameters include a detection range, ultrasonic sound velocity, gate parameters, and a display mode; the linear scanning of the phased array probe is a linear arrangement of the first probe, the second probe, and the third probe;

[0017] The damage size of the delamination around the hole at the detected damage location is determined according to the second scanning waveform and / or the third scanning waveform.

[0018] Optionally, the step of detecting the detected damaged part according to the target detection method and preset parameters to determine the damage size of the layer around the hole in the detected damaged part includes:

[0019] When the change type is a gradual change in bottom thickness, setting the detection range of the phased array probe to the maximum workpiece thickness;

[0020] The phased array probe is moved to perform linear scanning perpendicular to the thickness gradient direction of the bottom surface to obtain a second scanning waveform and / or a third scanning waveform; wherein the second scanning waveform is a detection waveform of an intact structure, and the third scanning waveform is a detection waveform of a damaged structure; the preset parameters include detection range, ultrasonic sound velocity, gate parameters, and display mode;

[0021] The damage size of the delamination around the hole at the detected damage location is determined according to the second scanning waveform and / or the third scanning waveform.

[0022] Optionally, the imaging gate parameters are set in the following manner:

[0023] Pre-scanning the inspection object to determine the bottom wave corresponding to the bottom surface of the damaged part;

[0024] The front edge of the last reflected echo is collected within the bottom wave gate range as the bottom wave front edge, and the imaging gate is set to automatically track the bottom wave; wherein the imaging gate width is 0.1 mm.

[0025] Optionally, the ultrasonic sound velocity range is 2800 to 3000 m / s.

[0026] Optionally, the excitation circuit includes:

[0027] A loop consisting of a power supply, a first resistor, a first capacitor and a first switch connected in series in sequence;

[0028] The first switch is connected in parallel with a first branch circuit and a second branch circuit, wherein the first branch circuit is composed of a second capacitor and a second resistor connected in series, and the second branch circuit is composed of a first diode and a third resistor connected in series; the first end of the second capacitor is connected in series with the cathode of the first diode, and the anode of the first diode is connected in series with the third resistor to output a pulse signal;

[0029] The first end of the second resistor is connected in series with the first capacitor, and the second end of the second resistor is connected to the first end of the second capacitor, the cathode of the first diode, and a third branch circuit; wherein the third branch circuit is composed of a second switch and a second diode connected in series, the cathode of the second diode is connected to the second end of the second resistor, and the anode of the second diode is connected to the second switch;

[0030] The switch control end of the first switch is connected to a driver, and the driver is used to receive a pulse signal sent by a system control unit.

[0031] The embodiment of the present invention further provides a rapid aircraft combat damage detection device, wherein the device comprises: a processor, a phased array detection module and a high-frequency ultrasonic detection module;

[0032] The processor is used to determine the damage type of the composite material-based stealth coating on the fuselage, and call a matching detection module according to the damage type, wherein the damage type includes: penetrating damage and non-penetrating damage;

[0033] The phased array detection module is used to be called by the processor to detect the detected damage by using the phased array detection method according to preset parameters in the case of penetrating damage, and determine the damage size of the layer around the hole in the detected damage; wherein the preset parameters include: detection frequency, scanning mode and imaging gate parameters;

[0034] The high-frequency ultrasonic detection module is used to be called by the processor to detect the detected damaged area in the case of non-penetrating damage, and determine the damage depth of the detected damaged area based on the received signal, wherein, the high-frequency ultrasonic detection module is preset with an excitation circuit, and the excitation circuit is used to control the sending and receiving of the high-frequency ultrasonic detection module signal.

[0035] Optionally, the phased array detection module includes:

[0036] A damage type judgment submodule is used to judge the change type of the bottom surface thickness of the detected damage by the first scanning waveform obtained by the pre-scan when the damage type is penetrating damage; wherein the change types include: step change of the bottom surface thickness and gradual change of the bottom surface thickness, and the first scanning waveform is a detection signal perpendicular to the reinforcement direction or the thickness change direction;

[0037] A detection mode search submodule is used to search the system for a target detection mode that matches the change type;

[0038] The detection execution submodule is used to detect the detected damaged part according to the target detection method and preset parameters, and determine the damage size of the layer around the hole of the detected damaged part.

[0039] Optionally, the detection execution submodule is specifically used for:

[0040] When the change type is a step change in bottom thickness, setting the detection range of the phased array probe to the maximum workpiece thickness;

[0041] The phased array probe is moved to perform linear scanning along the reinforcement direction to obtain a second scanning waveform and / or a third scanning waveform; wherein the second scanning waveform is a detection waveform of an intact reinforcement structure, and the third scanning waveform is a damage detection waveform of the reinforcement structure, and the preset parameters include a detection range, ultrasonic sound velocity, gate parameters, and a display mode; the linear scanning of the phased array probe is a linear arrangement of the first probe, the second probe, and the third probe;

[0042] The damage size of the delamination around the hole at the detected damage location is determined according to the second scanning wave and / or the third scanning wave.

[0043] Optionally, the detection execution module is specifically used to:

[0044] When the change type is a step change in bottom thickness, setting the detection range of the phased array probe to the maximum workpiece thickness;

[0045] The phased array probe is moved to perform linear scanning along the reinforcement direction to obtain a second scanning waveform and / or a third scanning waveform; wherein the second scanning waveform is a detection waveform of an intact reinforcement structure, and the third scanning waveform is a damage detection waveform of the reinforcement structure, and the preset parameters include a detection range, ultrasonic sound velocity, gate parameters, and a display mode; the linear scanning of the phased array probe is a linear arrangement of the first probe, the second probe, and the third probe;

[0046] The damage size of the delamination around the hole at the detected damage location is determined according to the second scanning wave and / or the third scanning wave.

[0047] Optionally, the imaging gate parameters are set in the following manner:

[0048] Pre-scanning the inspection object to determine the bottom wave corresponding to the bottom surface of the damaged part;

[0049] The front edge of the last reflected echo is collected within the bottom wave gate range as the bottom wave front edge, and the imaging gate is set to automatically track the bottom wave; wherein the imaging gate width is 0.1 mm.

[0050] Optionally, the ultrasonic sound velocity range is 2800 to 3000 m / s.

[0051] Optionally, the excitation circuit includes:

[0052] A loop consisting of a power supply, a first resistor, a first capacitor and a first switch connected in series in sequence;

[0053] The first switch is connected in parallel with a first branch circuit and a second branch circuit, wherein the first branch circuit is composed of a second capacitor and a second resistor connected in series, and the second branch circuit is composed of a first diode and a third resistor connected in series; the first end of the second capacitor is connected in series with the cathode of the first diode, and the anode of the first diode is connected in series with the third resistor to output a pulse signal;

[0054] The first end of the second resistor is connected in series with the first capacitor, and the second end of the second resistor is connected to the first end of the second capacitor, the cathode of the first diode, and a third branch circuit; wherein the third branch circuit is composed of a second switch and a second diode connected in series, the cathode of the second diode is connected to the second end of the second resistor, and the anode of the second diode is connected to the second switch;

[0055] The switch control end of the first switch is connected to a driver, and the driver is used to receive a pulse signal sent by a system control unit.

[0056] The rapid detection scheme for aircraft combat damage provided by this application determines the damage type of the composite material-based stealth coating on the fuselage; in the case of penetrating damage, a phased array detection method is used to detect the damaged part according to preset parameters to determine the damage size of the layer around the hole in the damaged part; in the case of non-penetrating damage, a high-frequency ultrasonic detection module with a preset excitation circuit is used to determine the damage depth of the damaged part. The scheme provided by this application uses a processor to refine and distinguish the damage type, and different detection modules are used for detection of different damage types. It can not only achieve accurate measurement of the damage location, size and depth, but also realize multiple uses of one machine, meeting the requirements of portability, miniaturization and combination of field support. BRIEF DESCRIPTION OF THE DRAWINGS

[0057] Figure 1 is a flowchart showing the steps of a method for rapid detection of aircraft combat damage according to an embodiment of the present application;

[0058] Figure 2 It is a schematic diagram of the principle of penetrating damage detection of composite material-based stealth coating structure;

[0059] Figure 3 is a schematic diagram of a non-penetrating injury structure according to an embodiment of the present application;

[0060] Figure 4 is a schematic diagram showing different types of bottom thickness variation types of embodiments of the present application;

[0061] Figure 5 is a schematic diagram of an excitation circuit according to an embodiment of the present application;

[0062] Figure 6 It is a structural block diagram of an aircraft combat damage rapid detection device according to an embodiment of the present application. DETAILED DESCRIPTION

[0063] In order to make the technical problems, technical solutions and advantages to be solved by the present invention more clear, a detailed description will be given below with reference to the accompanying drawings and specific embodiments.

[0064] The present application provides a rapid detection scheme for aircraft combat damage, which can not only detect damage to the aircraft's composite material-based stealth coating, providing a basis for subsequent evaluation and repair, but also accurately measure the thickness of the composite material-based stealth coating, providing support for routine field maintenance and wartime emergency repairs. Not only that, the aircraft combat damage rapid detection scheme provided by the present application can also detect coating damage on other aircraft materials.

[0065] From the perspective of emergency repair, the solution provided in this application divides various types of damage to composite-based stealth coatings under low-speed and high-speed impacts into two categories: penetrating damage and non-penetrating damage. For penetrating damage detection, the purpose is to quickly determine the size of the damage, and innovative phased array detection technology is applied. Through multi-gate automatic identification and monitoring algorithms, the problem of rapid quantification of body damage is solved, avoiding the shortcomings of partition detection and the need to equip multiple types of detection probes. For non-penetrating damage detection, the purpose is to accurately determine the depth of damage. By integrating a high-frequency ultrasonic detection unit on the ultrasonic phased array detection equipment, the purpose of accurately locating the depth of damage in the field is achieved, avoiding complete removal and reducing the efficiency of emergency repair. At the same time, the solution can also accurately measure the thickness of the coating, realize multiple uses of one machine, and meet the requirements of portability, miniaturization, and combination of field support.

[0066] The aircraft combat damage rapid detection solution provided by the embodiment of the present application is described in detail below with reference to the accompanying drawings through specific embodiments and their application scenarios.

[0067] As attached Figure 1 As shown, the aircraft battle damage rapid detection method of the embodiment of the present application includes the following steps:

[0068] Step 101: Determine the type of damage to the composite-based stealth coating on the fuselage.

[0069] Among them, the injury types include: penetrating injury and non-penetrating injury.

[0070] The aircraft combat damage rapid detection method provided in the embodiment of the present application can be applied to electronic equipment, and the electronic equipment includes a processor, a phased array detection module (also referred to as a phased array ultrasonic detection module) and a high-frequency ultrasonic detection module. The processor stores a computer program related to damage detection of composite material-based stealth coatings, and the processor of the electronic device executes the computer program to control the phased array detection module and the high-frequency ultrasonic detection module to perform damage detection. In actual implementation, the aircraft combat damage rapid detection method provided in the embodiment of the present application can be used to visually inspect the aircraft combat damage according to the aircraft inspection route to understand the general damage of the aircraft.

[0071] The role of the processor in the embodiment of the present application is to coordinate the orderly operation of the conventional phased array detection module and the high-frequency ultrasonic detection module. In the embodiment of the present application, different modules such as analog front end, digital processing and phased array drive are integrated into a single system, while maintaining the miniaturization and low power consumption of the system. When designing the scheme of the present application, it is considered that the difference between the conventional phased array detection module and the high-frequency ultrasonic detection module in analog signals leads to the inability to integrate the circuit of the analog part, but it can be realized in the digital circuit part, and the digital circuit resources required for processing high-frequency signals and processing phased array signals are comprehensively evaluated, and the two share a set of digital circuits. Secondly, in terms of system control, the phased array detection module needs multiple excitations to obtain a detection result, and there are concepts of focusing law and sound line in it. The high-frequency ultrasonic detection module can get a detection result after one excitation. How to control the data flow of the two and ensure the correct output of the detection result is also crucial. The present application integrates high-frequency detection into phased array detection, and regards high-frequency detection as part of the phased array focusing law and as a special phased array sound line, so that the phased array produces a detection result and the high frequency synchronously outputs a result.

[0072] Schematic diagram of penetration damage detection principle of composite material based stealth coating structure Figure 2 As shown. Since the coating is a multi-interface thin layer structure, delamination, shedding and other damages may occur between the substrate and the primer, the primer and the intermediate layer, the surface layer, etc., and since the substrate is a composite material, the composite material will also have delamination damage around the hole under the impact load. Therefore, the detection of penetrating damage actually requires determining the size of the delamination damage around the hole.

[0073] like Figure 3 As shown in the schematic diagram of the non-penetrating damage structure, non-penetrating damage may be delamination damage existing inside the coating, or it may be non-penetrating damage caused by impacts such as fragments. When the substrate is not damaged and only delamination exists inside the coating, determining the precise depth of the delamination can reduce the workload of grinding, thereby reducing the number of times the coating is sprayed, performing precise repairs, and improving the efficiency of emergency repairs. When the substrate is also partially damaged, determining the damage depth can also reduce the amount of substrate removed.

[0074] Therefore, different damage types need to be implemented using different damage detection methods. It should be noted that in the embodiment of the present application, only two types of damage types, namely penetrating damage and non-penetrating damage, are used for illustration. In the actual implementation process, the damage types can also be divided into three or even more types.

[0075] Step 102: In the case of penetrating damage, a phased array detection method is used to detect the damaged area according to preset parameters to determine the damage size of the layer around the hole in the damaged area.

[0076] Among them, the preset parameters include: detection frequency, scanning mode, detection range, ultrasonic sound speed, imaging gate parameters and display mode, etc.

[0077] Considering both practicality and economy, the conventional phased array detection module recommends the use of a 64-chip water bag phased array detection probe, with a detection frequency of 10MHz, a delay rule set to simple linear scanning, and three imaging modes: A, B, and C. It is equipped with a one-dimensional linear scanner to detect the presence and size of defects in composite material-based stealth coatings. On this basis, in order to achieve rapid detection and quantification of battle damage in composite material-based stealth coatings with variable cross-sections and thicknesses, the following preferred methods can be used for detection:

[0078] Preferably, in the case of penetrating damage, a method of using a phased array detection method to detect the detected damage according to preset parameters to determine the damage size of the layer around the hole at the detected damage may include the following sub-steps:

[0079] Sub-step 1: in the case of penetrating damage, determine the type of change in the bottom surface thickness of the detected damage by using the first scanning waveform obtained by pre-scanning;

[0080] The types of changes include: step changes in bottom thickness, gradual changes in bottom thickness, etc. The first scanning waveform is a detection signal perpendicular to the reinforcement direction or the thickness change direction. Figure 4 is a schematic diagram showing different types of bottom thickness variation types of embodiments of the present application, Figure 4 (a) is a schematic diagram showing the gradual thickness change of the bottom surface. Figure 4 (b) is a schematic diagram showing the step change of the bottom thickness. The change type may also include other types, which indicate that the bottom thickness change is a small plane or a nearly plane area. For this type of change, the method of monitoring the bottom wave amplitude can be used to determine the defect.

[0081] The first scanning waveform is a detection signal perpendicular to the reinforcement direction or the thickness change direction.

[0082] Sub-step 2: Search the system for a target detection method that matches the change type;

[0083] In this preferred embodiment, in order to further realize automation, after the sound velocity of the detection object is calibrated, the matching target detection method is automatically searched or called according to the pre-scanned bottom surface thickness change type. The system can formulate the detection method comprehensive structure form and the scanning bottom surface thickness change range.

[0084] Sub-step 3: Detect the damaged area according to the target detection method and preset parameters to determine the damage size of the layer around the hole in the damaged area.

[0085] Specifically, a feasible method of detecting the detected damaged part according to the target detection method and preset parameters to determine the damage size of the layer around the hole of the detected damaged part can be as follows:

[0086] When the bottom surface thickness change type is a step change in the bottom surface thickness, the detection range of the phased array probe is set to the maximum workpiece thickness; the phased array probe is moved to perform linear scanning along the reinforcement direction to obtain a second scanning waveform and / or a third scanning waveform;

[0087] Among them, the second scanning waveform is the detection waveform of the intact reinforced structure, and the third scanning waveform is the damage detection waveform of the reinforced structure. The preset parameters include: detection range, ultrasonic sound velocity, gate parameters, and display mode; the linear scanning of the phased array probe is a linear arrangement of the first and second probes, the second probe, and the third probe; based on the second scanning waveform and / or the third scanning waveform, the damage size of the stratification around the hole at the damaged part under inspection is determined.

[0088] In the actual implementation process, refer to Figure 4 (b) For the area with step-change thickness on the bottom surface. First, perform a pre-scan to determine whether the inspected area is a step-change area. At this time, the detection range can be increased and judged by observing the A-scan waveform (i.e., the first scan waveform obtained by scanning with the first probe). Then set the detection range to the maximum workpiece thickness, perform a rectangular scan along the reinforcement direction, and make defect judgments by observing the B-scan image (i.e., the second scan waveform obtained by scanning with the second probe) or the C-scan image of the bottom wave (i.e., the third scan waveform obtained by scanning with the third probe).

[0089] Specifically, a feasible method of detecting the detected damaged part according to the target detection method and preset parameters to determine the damage size of the layer around the hole in the detected damaged part may include the following sub-steps:

[0090] S1: When the change type is the gradual change of the bottom thickness, set the detection range of the phased array probe to the maximum workpiece thickness;

[0091] S2: moving the phased array probe to perform linear scanning perpendicular to the thickness gradient direction of the bottom surface to obtain a second scanning waveform and / or a third scanning waveform;

[0092] The second scanning waveform is a detection waveform of an intact structure, and the third scanning waveform is a detection waveform of a damaged structure; the preset parameters include detection range, ultrasonic sound velocity, gate parameters, and display mode;

[0093] S3: Determine the damage size of the layer around the hole at the detected damage location according to the second scanning waveform and / or the third scanning waveform.

[0094] In the actual implementation process, refer to Figure 4(a) For the case of gradual thickness change of the bottom surface. First, determine whether the inspected part is a gradual change area through pre-scanning. At this time, the detection range can be increased. By observing the A-scan waveform (i.e., the first scanning waveform obtained by scanning with the first probe), it can be judged that the bottom surface echo continuously moves to the left or right, which is a gradual change structure. Then set the detection range to the maximum workpiece thickness, scan perpendicular to the gradual change direction, and judge the defects by observing the B-scan image (i.e., the second scanning waveform obtained by scanning with the second probe) or the C-scan image of the bottom wave (i.e., the third scanning waveform obtained by scanning with the third probe).

[0095] In an optional embodiment, the imaging gate parameters are set in the following manner:

[0096] The inspection object is pre-scanned to determine the bottom wave corresponding to the bottom surface of the damaged area; the front edge of the last reflected echo is collected within the bottom wave gate range as the bottom wave front edge, and the imaging gate is set to automatically track the bottom wave; wherein the imaging gate width is preferably set to 0.1 mm. It should be noted that the specific value of the imaging gate width can be flexibly set by those skilled in the art according to actual needs, and is not specifically limited in the embodiments of the present application.

[0097] Step 103: In the case of non-penetrating damage, a high-frequency ultrasonic detection module with a preset excitation circuit is used to determine the damage depth of the detected damage.

[0098] like Figure 3 As shown, non-penetrating damage may be stratified damage existing inside the coating, or it may be non-penetrating damage caused by impacts such as fragments. When the substrate is not damaged and only stratification exists inside the coating, determining the precise depth of the stratification can reduce the workload of grinding, thereby reducing the number of times the coating is sprayed, performing precise repairs, and improving the efficiency of emergency repairs. When part of the substrate is also damaged, determining the depth of damage can also reduce the amount of substrate removed. Since the thickness of the composite material layer is about 0.15mm, the thickness of the coating surface layer, primer layer, etc. is also about 0.15mm, so in order to accurately determine the damage depth, the detection accuracy must reach 0.1mm. Therefore, the detection frequency during high-frequency ultrasonic testing needs to reach 20MH or above, and it is preferred to set the detection frequency to 20MH-75MHz.

[0099] To realize the above-mentioned high-frequency ultrasonic detection, it is important to solve the two problems of signal excitation (i.e. transmission) and reception. It is necessary to integrate the phased array ultrasonic module and high-frequency ultrasonic detection, and meet the ultra-high precision requirement of 100μm for the positioning of the damage depth of this application. In the embodiment of this application, a new generation of high-speed semiconductor GaN switches are used to build a flyback half-bridge switching circuit to realize the design of an ultra-strong and ultra-fine ultrasonic excitation source. The complete excitation circuit includes a switching circuit, a DC-DC high-voltage source, a switch driver, and a zeroing circuit. .

[0100] An exemplary excitation circuit structure is shown in FIG. Figure 5 As shown:

[0101] The excitation circuit includes a power supply +HV connected in series out , first resistor R1, first capacitor C in and a loop consisting of a first switch M1;

[0102] The first switch M1 is connected in parallel with a first branch circuit and a second branch circuit, wherein the first branch circuit is composed of a second capacitor C1 and a second resistor R2 connected in series, and the second branch circuit is composed of a first diode D3 and a third resistor R3 connected in series; the first end of the second capacitor C1 is connected in series with the cathode of the first diode D3, and the anode of the first diode D3 is connected in series with the third resistor R3 to output a pulse signal (i.e., ultra-fine and ultra-strong pulse output);

[0103] The first end of the second resistor R2 is connected to the first capacitor C in The second end of the second resistor R2 is connected in series, the first end of the second capacitor C1, the cathode of the first diode D3 and the third branch circuit; wherein the third branch circuit is composed of a second switch M2 and a second diode D4 connected in series, the cathode of the second diode D4 is connected to the second end of the second resistor R2, and the anode of the second diode D4 is connected to the second switch M2;

[0104] The switch control end of the first switch M1 is connected to a driver, which is used to receive a pulse signal sent by the system control unit. The driver can be a GaN gallium nitride driver, but is not limited thereto and can also be any appropriate driver. PUL is a pulse sent to the driver, which is processed by the excitation circuit to output an ultra-fine and ultra-strong pulse.

[0105] Figure 5 The high-voltage power supply in the system is efficiently converted into a high-voltage DC power supply by the DC-DC processing module, providing an energy source for the entire transmitting circuit. During the off period of the high-speed switch M1, the capacitor C1 stores high-voltage energy through the resistor R1. The system control unit module generates a periodically repeated switching signal according to a certain rule, and combines a dedicated high-current driver to provide a sufficiently fast turn-on voltage for M1. After the switch is turned on, according to the principle that the voltage difference between the two ends of the capacitor cannot change suddenly, the output end of C1 will generate a negative high-voltage energy signal. At the moment when the control signal is about to be turned off, M2 is stimulated to make the transmission pulse rise quickly, so that an ultra-strong and ultra-fine negative square wave transmission pulse can be obtained at the output end. Since the transmission pulse width itself is very narrow, at the order of tens of nanoseconds, the control time of M1 and M2 is also required to be very precise, otherwise there may be a risk of transmission failure or even damage to the device. In the actual implementation process, a dedicated delay chip can be used for precise time difference control, and the control accuracy of the delay chip must reach the 1ns level.

[0106] For the reception and extraction of high-frequency signals, this part includes a broadband low-noise amplifier, a high-performance bridge limiting circuit, an AAD08Q0250 high-speed analog-to-digital conversion chip, etc. This part can be implemented by existing circuits or chips, and will not be described in detail here.

[0107] In the research on the fusion of phased array and high-frequency ultrasound in this application, a key challenge is how to effectively combine high-frequency ultrasonic detection with phased array ultrasonic detection. This requires research and solution from two aspects: circuit design and software design.

[0108] (1) Circuit design

[0109] High-frequency signal processing: As mentioned above, the frequency band of high-frequency ultrasound is 30MHz-100MHz, and it is necessary to design a circuit that can process 30MHz-100MHz high-frequency ultrasound signals to ensure accurate transmission and reception of signals. This includes the design and optimization of key components such as high-frequency amplifiers, filters, and analog-to-digital converters (ADCs).

[0110] Phased array drive: Design phased array drive circuit to achieve precise control of each unit in the phased array. This requires the circuit to provide precise timing and amplitude control to achieve fine adjustment of phase and amplitude. Secondly, each unit in the phased array requires analog amplification, filtering and analog-to-digital conversion channels. The number of channels designed for this project is 16-128, that is, there are 16 parallel analog channels. Highly integrated IC chips are required to reduce the area of ​​the circuit board to achieve portable detection.

[0111] Power management: As mentioned above, the phased array has 16 parallel analog channels, and its power consumption and heat generation are close to 16 times that of conventional single-channel devices. At the same time, due to its high digitization frequency, the high-speed ADC also has relatively high power consumption and heat generation. Therefore, power management and thermal management must be considered in circuit design. Reasonable power supply design and heat dissipation design are crucial to ensure system stability. Calculate the power consumption of each unit in the circuit in detail, refine the design of each power supply, and select a power supply solution with high conversion efficiency and low heat generation. Design an independent cooling system, refer to the cooling method of the notebook, collect the heat of the main heat-generating chips together through the heat pipe, and then use a turbo fan for air cooling.

[0112] System integration: Integrating different modules such as analog front-end, digital processing and phased array drive into a single system while maintaining the system's miniaturization and low power consumption is an important challenge in circuit design. The difference between the two in analog signals makes it impossible to integrate the analog circuit, but it can be realized in the digital circuit part. Comprehensively evaluate the digital circuit resources required for processing high-frequency signals and processing phased array signals, and the two share a set of digital circuits. Secondly, in terms of system control, the phased array requires multiple excitations to obtain a detection result, which involves the concepts of focal law and sound line. High-frequency ultrasonic excitation can obtain a detection result once, so how to control the data flow of the two and ensure the correct output of the detection result is also crucial. We integrate high-frequency detection into phased array detection, and use high-frequency detection as part of the phased array focal law and as a special phased array sound line, so that the phased array produces a detection result and the high frequency synchronously outputs a result.

[0113] Anti-interference design: Considering that high-frequency ultrasonic signals are susceptible to interference, circuit design needs to adopt effective anti-interference measures, such as differential signal processing, shielding, and the use of low-noise components.

[0114] The method for rapid detection of aircraft combat damage provided in the embodiment of the present application determines the damage type of the composite material-based stealth coating on the fuselage; in the case of penetrating damage, a phased array detection method is used to detect the detected damage according to preset parameters to determine the damage size of the layer around the hole in the detected damage; in the case of non-penetrating damage, a high-frequency ultrasonic detection module with a preset excitation circuit is used to determine the damage depth of the detected damage. The method provided by the present application uses a conventional phased array detection module for penetrating damage, and detects by monitoring the bottom wave to determine the size of the damage area; for non-penetrating damage, a conventional phased array is first used for preliminary inspection to determine the damage range, and then a high-frequency ultrasound is used to accurately detect the damage depth. The damage type is refined and distinguished by the processor, and different damage types are detected using different detection modules, which can not only realize the accurate measurement of the damage position, size and depth, but also realize multiple uses of one machine, meeting the requirements of portability, miniaturization and combination of field support.

[0115] Figure 6 A structural block diagram of a rapid aircraft combat injury detection device to implement the embodiment of the present application.

[0116] The aircraft battle damage rapid detection device provided in the embodiment of the present application includes: a processor 601, a phased array detection module 602 and a high-frequency ultrasonic detection module 603;

[0117] The processor 601 is used to determine the damage type of the composite material-based stealth coating on the fuselage, and call a matching detection module according to the damage type, wherein the damage type includes: penetrating damage and non-penetrating damage;

[0118] The phased array detection module 602 is used to be called by the processor to detect the detected damage by using the phased array detection method according to preset parameters in the case of penetrating damage, and determine the damage size of the layer around the hole in the detected damage; wherein the preset parameters include: detection frequency, scanning mode and imaging gate parameters;

[0119] The high-frequency ultrasonic detection module 603 is used to be called by the processor to detect the detected damaged area in the case of non-penetrating damage, and determine the damage depth of the detected damaged area based on the received signal, wherein, the high-frequency ultrasonic detection module is preset with an excitation circuit, and the excitation circuit is used to control the sending and receiving of the high-frequency ultrasonic detection module signal.

[0120] Optionally, the phased array detection module includes:

[0121] A damage type judgment submodule is used to judge the change type of the bottom surface thickness of the detected damage by the first scanning waveform obtained by the pre-scan when the damage type is penetrating damage; wherein the change types include: step change of the bottom surface thickness and gradual change of the bottom surface thickness, and the first scanning waveform is a detection signal perpendicular to the reinforcement direction or the thickness change direction;

[0122] A detection mode search submodule is used to search the system for a target detection mode that matches the change type;

[0123] The detection execution submodule is used to detect the detected damaged part according to the target detection method and preset parameters, and determine the damage size of the layer around the hole of the detected damaged part.

[0124] Optionally, the detection execution submodule is specifically used for:

[0125] When the change type is a step change in bottom thickness, setting the detection range of the phased array probe to the maximum workpiece thickness;

[0126] The phased array probe is moved to perform linear scanning along the reinforcement direction to obtain a second scanning waveform and / or a third scanning waveform; wherein the second scanning waveform is a detection waveform of an intact reinforcement structure, and the third scanning waveform is a damage detection waveform of the reinforcement structure, and the preset parameters include a detection range, ultrasonic sound velocity, gate parameters, and a display mode; the linear scanning of the phased array probe is a linear arrangement of the first probe, the second probe, and the third probe;

[0127] The damage size of the delamination around the hole at the detected damage location is determined according to the second scanning wave and / or the third scanning wave.

[0128] Optionally, the detection execution module is specifically used to:

[0129] When the change type is a step change in bottom thickness, setting the detection range of the phased array probe to the maximum workpiece thickness;

[0130] The phased array probe is moved to perform linear scanning along the reinforcement direction to obtain a second scanning waveform and / or a third scanning waveform; wherein the second scanning waveform is a detection waveform of an intact reinforcement structure, and the third scanning waveform is a damage detection waveform of the reinforcement structure, and the preset parameters include a detection range, ultrasonic sound velocity, gate parameters, and a display mode; the linear scanning of the phased array probe is a linear arrangement of the first probe, the second probe, and the third probe;

[0131] The damage size of the delamination around the hole at the detected damage location is determined according to the second scanning wave and / or the third scanning wave.

[0132] Optionally, the imaging gate parameters are set in the following manner:

[0133] Pre-scanning the inspection object to determine the bottom wave corresponding to the bottom surface of the damaged part;

[0134] The front edge of the last reflected echo is collected within the bottom wave gate range as the bottom wave front edge, and the imaging gate is set to automatically track the bottom wave; wherein the imaging gate width is 0.1 mm.

[0135] Optionally, the ultrasonic sound velocity range is 2800 to 3000 m / s.

[0136] Optionally, the excitation circuit includes:

[0137] A loop consisting of a power supply, a first resistor, a first capacitor and a first switch connected in series in sequence;

[0138] The first switch is connected in parallel with a first branch circuit and a second branch circuit, wherein the first branch circuit is composed of a second capacitor and a second resistor connected in series, and the second branch circuit is composed of a first diode and a third resistor connected in series; the first end of the second capacitor is connected in series with the cathode of the first diode, and the anode of the first diode is connected in series with the third resistor to output a pulse signal;

[0139] The first end of the second resistor is connected in series with the first capacitor, and the second end of the second resistor is connected to the first end of the second capacitor, the cathode of the first diode, and a third branch circuit; wherein the third branch circuit is composed of a second switch and a second diode connected in series, the cathode of the second diode is connected to the second end of the second resistor, and the anode of the second diode is connected to the second switch;

[0140] The switch control end of the first switch is connected to a driver, and the driver is used to receive a pulse signal sent by a system control unit.

[0141] The embodiments of the present application provide Figure 6 The aircraft battle damage rapid detection equipment shown can achieve Figure 1 To avoid repetition, the various processes implemented by the method embodiment are not described here.

[0142] The aircraft combat damage rapid detection equipment provided in the embodiment of the present application adopts a conventional phased array detection module for penetrating damage, and detects by monitoring the bottom wave method to determine the size of the damage area; for non-penetrating damage, a conventional phased array is first used for preliminary inspection to determine the damage range, and then high-frequency ultrasound is used to accurately detect the damage depth. The damage type is refined and distinguished through a processor, and different detection modules are used for detection of different damage types, which can not only achieve accurate measurement of the damage location, size and depth, but also realize multiple uses of one machine, meeting the requirements of portability, miniaturization and combination of field support.

[0143] An embodiment of the present invention also provides an electronic device, including a processor, a communication interface, a memory and a communication bus, a phased array detection module and a high-frequency ultrasonic detection module, wherein the processor, the communication interface, the memory, the phased array detection module and the high-frequency ultrasonic detection module communicate with each other through the communication bus.

[0144] Memory, used to store computer programs;

[0145] The processor is used to execute the program stored in the memory to implement the damage type judgment and detection module scheduling related methods in the rapid detection of aircraft combat damage performed by the processor shown in the above method embodiment.

[0146] The communication bus mentioned in the above terminal can be a Peripheral Component Interconnect (PCI) bus or an Extended Industry Standard Architecture (EISA) bus, etc. The communication bus can be divided into an address bus, a data bus, a control bus, etc. For ease of representation, only one thick line is used in the figure, but it does not mean that there is only one bus or one type of bus.

[0147] The communication interface is used for communication between the above terminal and other devices.

[0148] The memory may include a random access memory (RAM) or a non-volatile memory, such as at least one disk memory. Optionally, the memory may also be at least one storage device located away from the aforementioned processor.

[0149] The above-mentioned processor can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field programmable gate array (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components.

[0150] It should be noted that, in this article, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the existence of other identical elements in the process, method, article or device including the element.

[0151] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A method for rapid detection of aircraft combat damage, characterized in that: The method comprises: Determine the damage type of the composite material-based stealth coating on the fuselage, where the damage type includes: penetrating damage and non-penetrating damage; In the case of penetrating damage, the phased array detection method is used to detect the damaged area according to the preset parameters to determine the damage size of the layer around the hole in the damaged area; wherein the preset parameters include: detection frequency, scanning mode and imaging gate parameters; In the case of non-penetrating damage, a high-frequency ultrasonic detection module with a preset excitation circuit is used to determine the damage depth of the detected damage, wherein the excitation circuit is used to control the sending and receiving of signals of the high-frequency ultrasonic detection module.

2. The method according to claim 1, characterized in that: In the case of penetrating damage, the steps of using phased array detection means to detect the damage site according to preset parameters and determining the damage size of the layer around the hole at the damage site include: In the case of penetrating damage, the change type of the bottom surface thickness of the detected damage is determined by the first scanning waveform obtained by pre-scanning; wherein the change types include: step change of the bottom surface thickness and gradual change of the bottom surface thickness, and the first scanning waveform is a detection signal perpendicular to the reinforcement direction or the thickness change direction; Searching the system for a target detection method that matches the change type; The detected damaged part is detected according to the target detection method and preset parameters to determine the damage size of the layer around the hole in the detected damaged part.

3. The method according to claim 2, characterized in that The step of detecting the damaged part to be detected according to the target detection method and preset parameters to determine the damage size of the layer around the hole in the damaged part to be detected includes: When the change type is a step change in bottom thickness, setting the detection range of the phased array probe to the maximum workpiece thickness; The phased array probe is moved to perform linear scanning along the reinforcement direction to obtain a second scanning waveform and / or a third scanning waveform; wherein the second scanning waveform is a detection waveform of an intact reinforcement structure, and the third scanning waveform is a damage detection waveform of the reinforcement structure, and the preset parameters include a detection range, ultrasonic sound velocity, gate parameters, and a display mode; the linear scanning of the phased array probe is a linear arrangement of the first probe, the second probe, and the third probe; The damage size of the delamination around the hole at the detected damage location is determined according to the second scanning waveform and / or the third scanning waveform.

4. The method according to claim 2, characterized in that: The step of detecting the damaged part to be detected according to the target detection method and preset parameters to determine the damage size of the layer around the hole in the damaged part to be detected includes: When the change type is a gradual change in bottom thickness, setting the detection range of the phased array probe to the maximum workpiece thickness; The phased array probe is moved to perform linear scanning perpendicular to the thickness gradient direction of the bottom surface to obtain a second scanning waveform and / or a third scanning waveform; wherein the second scanning waveform is a detection waveform of an intact structure; the third scanning waveform is a detection waveform of a damaged structure; the preset parameters include detection range, ultrasonic sound velocity, gate parameters, and display mode; The damage size of the delamination around the hole at the detected damage location is determined according to the second scanning waveform and / or the third scanning waveform.

5. The method according to claim 2, characterized in that: The imaging gate parameters are set in the following manner: Pre-scanning the inspection object to determine the bottom wave corresponding to the bottom surface of the damaged part; The front edge of the last reflected echo is collected within the bottom wave gate range as the bottom wave front edge, and the imaging gate is set to automatically track the bottom wave; wherein the imaging gate width is 0.1 mm.

6. The method according to claim 2, characterized in that The ultrasonic sound velocity range is 2800-3000 m / s.

7. The method according to claim 1, characterized in that The excitation circuit comprises: A loop consisting of a power supply, a first resistor, a first capacitor and a first switch connected in series in sequence; The first switch is connected in parallel with a first branch circuit and a second branch circuit, wherein the first branch circuit is composed of a second capacitor and a second resistor connected in series, and the second branch circuit is composed of a first diode and a third resistor connected in series; the first end of the second capacitor is connected in series with the cathode of the first diode, and the anode of the first diode is connected in series with the third resistor to output a pulse signal; The first end of the second resistor is connected in series with the first capacitor, and the second end of the second resistor is connected to the first end of the second capacitor, the cathode of the first diode, and a third branch circuit; wherein the third branch circuit is composed of a second switch and a second diode connected in series, the cathode of the second diode is connected to the second end of the second resistor, and the anode of the second diode is connected to the second switch; The switch control end of the first switch is connected to a driver, and the driver is used to receive a pulse signal sent by a system control unit.

8. A rapid aircraft combat damage detection device, characterized in that: The device comprises: a processor, a phased array detection module and a high-frequency ultrasonic detection module; The processor is used to determine the damage type of the composite material-based stealth coating on the fuselage, and call a matching detection module according to the damage type, wherein the damage type includes: penetrating damage and non-penetrating damage; The phased array detection module is used to be called by the processor to detect the detected damage by using the phased array detection method according to preset parameters in the case of penetrating damage, and determine the damage size of the layer around the hole in the detected damage; wherein the preset parameters include: detection frequency, scanning mode and imaging gate parameters; The high-frequency ultrasonic detection module is used to be called by the processor to detect the detected damaged area in the case of non-penetrating damage, and determine the damage depth of the detected damaged area based on the received signal, wherein, the high-frequency ultrasonic detection module is preset with an excitation circuit, and the excitation circuit is used to control the sending and receiving of the high-frequency ultrasonic detection module signal.

9. The device according to claim 8, characterized in that The phased array detection module comprises: A damage type judgment submodule is used to judge the change type of the bottom surface thickness of the detected damage by the first scanning waveform obtained by the pre-scan when the damage type is penetrating damage; wherein the change types include: step change of the bottom surface thickness and gradual change of the bottom surface thickness, and the first scanning waveform is a detection signal perpendicular to the reinforcement direction or the thickness change direction; A detection mode search submodule is used to search the system for a target detection mode that matches the change type; The detection execution submodule is used to detect the detected damaged part according to the target detection method and preset parameters, and determine the damage size of the layer around the hole in the detected damaged part.

10. The device according to claim 9, characterized in that The detection execution module is specifically used for: When the change type is a step change in bottom thickness, setting the detection range of the phased array probe to the maximum workpiece thickness; The phased array probe is moved to perform linear scanning along the reinforcement direction to obtain a second scanning waveform and / or a third scanning waveform; wherein the second scanning waveform is a detection waveform of an intact reinforcement structure, and the third scanning waveform is a damage detection waveform of the reinforcement structure, and the preset parameters include a detection range, ultrasonic sound velocity, gate parameters, and a display mode; the linear scanning of the phased array probe is a linear arrangement of the first probe, the second probe, and the third probe; The damage size of the delamination around the hole at the detected damage location is determined according to the second scanning wave and / or the third scanning wave.

11. The device according to claim 9, characterized in that The detection execution module is specifically used for: When the change type is a gradual change in bottom thickness, setting the detection range of the phased array probe to the maximum workpiece thickness; The phased array probe is moved to perform linear scanning perpendicular to the thickness gradient direction of the bottom surface to obtain a second scanning waveform and / or a third scanning waveform; wherein the second scanning waveform is a detection waveform of an intact structure, and the third scanning waveform is a detection waveform of a damaged structure; the preset parameters include detection range, ultrasonic sound velocity, gate parameters, and display mode; The damage size of the delamination around the hole at the detected damage location is determined according to the second scanning waveform and / or the third scanning waveform.

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