Special-shaped waveguide rod for monitoring damage of hot end structure of aerospace vehicle

Abstract

The invention relates to the technical field of acoustic emission detection, in particular to a special-shaped waveguide rod for monitoring damage of a hot end structure of an aerospace vehicle. The plurality of sub-waveguides are coupled with the hot end structure of the aerospace vehicle and are integrally arranged on the anchor disc, and each sub-waveguide detects a monitoring area corresponding to the hot end structure; and a plurality of acoustic emission sensors arranged on the anchor disc and used for collecting the acoustic emission signals transmitted to the special-shaped waveguide rod so as to determine a target sub-waveguide for transmitting the signals according to the acoustic emission signals and determine that the monitoring area corresponding to the target sub-waveguide is the damage area of the hot end structure. Therefore, the problems that sensors cannot be directly arranged on a spacecraft hot end structure due to high temperature, and redundancy of an acquisition system is easily caused by a traditional waveguide rod in the prior art are solved.

Description

Technical Field

[0001] The present application relates to the field of launch detection technology, and in particular to a special-shaped waveguide rod for monitoring damage to the hot end structure of an aerospace vehicle. Background Art

[0002] In the related art, when performing acoustic emission detection in a high temperature environment, a high temperature sensor is generally used or a waveguide rod is used to derive the acoustic emission signal from the hot end structure to achieve effective collection of the acoustic emission signal.

[0003] However, in the related technologies, high-temperature sensors have many limitations. At the same time, traditional waveguide rods often adopt a "one rod, one channel" approach when configuring sensors, which makes the acquisition system complex and redundant, affecting the space utilization, efficiency and safety of the aircraft, and urgently needs to be improved. Summary of the invention

[0004] The present application provides a special-shaped waveguide rod for damage monitoring of the hot end structure of an aerospace vehicle, so as to solve the problems in the related art that the hot end structure of the spacecraft cannot be directly equipped with sensors due to the high temperature, and the redundancy of the acquisition system easily caused by the traditional waveguide rod.

[0005] A first aspect of the present application provides a special-shaped waveguide rod for damage monitoring of the hot end structure of an aerospace vehicle, comprising: an anchor plate; a plurality of sub-waveguides, wherein the plurality of sub-waveguides are coupled to the hot end structure of the aerospace vehicle, and the sub-waveguides are integrated on the anchor plate, and each sub-waveguide detects a monitoring area corresponding to the hot end structure; a plurality of acoustic emission sensors arranged on the anchor plate, for collecting acoustic emission signals transmitted to the special-shaped waveguide rod, so as to determine a target sub-waveguide for transmitting a signal according to the acoustic emission signal, and determine that the monitoring area corresponding to the target sub-waveguide is a damaged area of ​​the hot end structure.

[0006] Through the above technical solution, the embodiment of the present application can realize damage monitoring of multiple areas of the hot end structure with only a small number of sensors through the unique design of special-shaped waveguide rods, multiple sub-waveguides coupled with the hot end structure and integrated into the anchor plate, and multiple acoustic emission sensors on the anchor plate. It effectively solves the problem that sensors cannot be directly arranged on the surface of the hot end structure of the spacecraft, and overcomes the redundancy problem of the acquisition system caused by the "one rod and one channel" of the traditional waveguide rod, greatly improving the space utilization rate and system efficiency, enhancing the safety of the aircraft, and can still work reliably in extreme environments, effectively ensuring the healthy monitoring of the hot end structure of the aerospace vehicle.

[0007] Optionally, in one embodiment of the present application, the plurality of acoustic emission sensors are further used to pick up arrival times using Akaike information criterion, and based on the arrival times, determine the target sub-waveguide by the time difference of the acoustic emission waves reaching each acoustic emission sensor.

[0008] Through the above technical scheme, the embodiment of the present application can more accurately determine the time when the acoustic emission wave arrives at each sensor by picking up the arrival time by using the Akaike information criterion, and then determine the target sub-waveguide based on the time difference, thereby effectively improving the accuracy and reliability of the acoustic emission signal processing, so that in the complex monitoring system of multiple sub-waveguides and multiple sensors, the damaged area of ​​the hot end structure can be located more efficiently and accurately, and the accuracy and effectiveness of the entire special-shaped waveguide rod monitoring system for hot end structure damage monitoring are enhanced, providing more powerful technical support for ensuring the safety and reliability of the hot end structure of aerospace vehicles.

[0009] Optionally, in one embodiment of the present application, the calculation formula of the arrival time is:

[0010] AIC(k)=klg{Var(x[1,k])}+(Nk-1)lg{Var(x[k+1,N])},

[0011] Among them, x is the time series of the acoustic emission signal, k is the dividing point of the two time windows in the time series, and N is the total number of time samples.

[0012] Through the above technical solution, the embodiment of the present application can accurately calculate the wave arrival time by cleverly considering the demarcation point of the two time windows before and after the acoustic emission signal time series and the total number of samples and other factors, making full use of the time characteristics of the signal. In a multi-sensor monitoring environment, it can accurately determine the time when the acoustic emission wave arrives at each sensor, thereby providing a reliable data basis for the subsequent determination of the target sub-waveguide based on the time difference. It helps to improve the accuracy and effectiveness of the entire special-shaped waveguide rod system in the damage monitoring of the hot end structure of aerospace vehicles, enhance the detection capability of minor damage or early damage, and provide a strong guarantee for the safe operation of the hot end structure of the aircraft.

[0013] Optionally, in one embodiment of the present application, the sub-waveguide is a bendable waveguide.

[0014] Through the above technical scheme, the embodiment of the present application can better adapt to various irregular installation positions and layout requirements due to its flexible characteristics in a space environment with a complex hot end structure of an aerospace vehicle, facilitate effective coupling with the hot end structure, and ensure monitoring coverage of different areas.

[0015] Optionally, in one embodiment of the present application, the base to which the plurality of sub-waveguides are coupled has a power-law characteristic.

[0016] Through the above technical solution, the power-law characteristics in the embodiment of the present application make the diameter from the bottom of the base to the main part of the waveguide change according to specific rules, which can effectively enhance the signal strength of the waveguide transmission. In the damage monitoring of the hot end structure of aerospace vehicles, stronger signal transmission capability means that weak acoustic emission signals can be captured more keenly, which improves the sensitivity of damage signal detection and helps to detect potential structural damage earlier. At the same time, the optimized signal transmission can also reduce signal attenuation and interference, improve the accuracy and reliability of monitoring data, thereby providing more accurate data support for the health status assessment of the hot end structure of aerospace vehicles and ensuring the safe and stable operation of the aircraft in extreme environments.

[0017] The second aspect of the present application provides a method for monitoring damage to the hot end structure of an aerospace vehicle, including: collecting acoustic emission signals transmitted to the special-shaped waveguide rod; determining the target sub-waveguide of the transmission signal based on the acoustic emission signal; and determining that the monitoring area corresponding to the target sub-waveguide is the damaged area of ​​the hot end structure.

[0018] Through the above technical solution, the embodiment of the present application can realize damage monitoring of multiple areas of the hot end structure with only a small number of sensors through the unique design of special-shaped waveguide rods, multiple sub-waveguides coupled with the hot end structure and integrated into the anchor plate, and multiple acoustic emission sensors on the anchor plate. It effectively solves the problem that sensors cannot be directly arranged on the surface of the hot end structure of the spacecraft, and overcomes the redundancy problem of the acquisition system caused by the "one rod and one channel" of the traditional waveguide rod, greatly improving the space utilization rate and system efficiency, enhancing the safety of the aircraft, and can still work reliably in extreme environments, effectively ensuring the healthy monitoring of the hot end structure of the aerospace vehicle.

[0019] Optionally, in one embodiment of the present application, determining the target sub-waveguide of the transmission signal according to the acoustic emission signal includes: the multiple acoustic emission sensors are further used to pick up the arrival time using the Akaike information criterion, and based on the arrival time, determine the target sub-waveguide by the time difference of the acoustic emission wave reaching each acoustic emission sensor.

[0020] Through the above technical scheme, the embodiment of the present application can more accurately determine the time when the acoustic emission wave arrives at each sensor by picking up the arrival time by using the Akaike information criterion, and then determine the target sub-waveguide based on the time difference, thereby effectively improving the accuracy and reliability of the acoustic emission signal processing, so that in the complex monitoring system of multiple sub-waveguides and multiple sensors, the damaged area of ​​the hot end structure can be located more efficiently and accurately, and the accuracy and effectiveness of the entire special-shaped waveguide rod monitoring system for hot end structure damage monitoring are enhanced, providing more powerful technical support for ensuring the safety and reliability of the hot end structure of aerospace vehicles.

[0021] Optionally, in one embodiment of the present application, the calculation formula of the arrival time is:

[0022] AIC(k)=klg{Var(x[1,k])}+(Nk-1)lg{Var(x[k+1,N])},

[0023] Among them, x is the time series of the acoustic emission signal, k is the dividing point of the two time windows in the time series, and N is the total number of time samples.

[0024] Through the above technical solution, the embodiment of the present application can accurately calculate the wave arrival time by cleverly considering the demarcation point of the two time windows before and after the acoustic emission signal time series and the total number of samples and other factors, making full use of the time characteristics of the signal. In a multi-sensor monitoring environment, it can accurately determine the time when the acoustic emission wave arrives at each sensor, thereby providing a reliable data basis for the subsequent determination of the target sub-waveguide based on the time difference. It helps to improve the accuracy and effectiveness of the entire special-shaped waveguide rod system in the damage monitoring of the hot end structure of aerospace vehicles, enhance the detection capability of minor damage or early damage, and provide a strong guarantee for the safe operation of the hot end structure of the aircraft.

[0025] The third aspect of the present application provides an electronic device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the method for monitoring damage to the hot end structure of an aerospace vehicle as described in the above embodiment.

[0026] The fourth aspect of the present application provides a computer-readable storage medium, which stores a computer program. When the program is executed by a processor, it implements the above method for monitoring damage to the hot end structure of an aerospace vehicle.

[0027] The fifth aspect of the present application provides a computer program, including a computer program, which, when executed, is used to implement the above method for monitoring damage to the hot end structure of an aerospace vehicle.

[0028] The embodiment of the present application uses a unique special-shaped waveguide rod structure, multiple sub-waveguides are coupled with the hot end structure and integrated into the anchor plate and equipped with a small number of acoustic emission sensors, to overcome the difficulty of arranging sensors on the high-temperature surface of the spacecraft, solve the redundancy problem of the traditional waveguide rod acquisition system, significantly improve the space utilization, system efficiency and safety, and ensure reliable monitoring of the health status of the hot end structure in extreme environments. The wave arrival time is picked up by the Akaike information criterion, and the time series characteristics of the acoustic emission signal are accurately calculated. The target sub-waveguide is accurately positioned based on the time difference, which greatly improves the accuracy and reliability of acoustic emission signal processing, enhances the accuracy and effectiveness of complex monitoring systems in locating damaged areas, and effectively ensures the safety of the hot end structure of the aircraft. The bendable sub-waveguide adapts to the complex space environment and realizes effective coupling and comprehensive monitoring coverage. The power-law characteristic base optimizes signal transmission, enhances signal strength, improves the sensitivity of damage signal detection, reduces attenuation interference, provides accurate data for health status assessment, and comprehensively escorts the safe and stable operation of aerospace vehicles in extreme environments.

[0029] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0031] Figure 1 A schematic diagram of the structure of a special-shaped waveguide rod for monitoring damage to the hot end structure of an aerospace vehicle provided according to an embodiment of the present application;

[0032] Figure 2 A schematic diagram of a power-law characteristic of a sub-waveguide coupling base according to an embodiment of the present application;

[0033] Figure 3 A schematic diagram of the distribution of anchor plates and sub-waveguides according to an embodiment of the present application;

[0034] Figure 4 A schematic diagram of a six-area monitoring special-shaped waveguide rod according to a specific embodiment of the present application;

[0035] Figure 5 A schematic diagram of measuring the distance between a sub-waveguide and a sensor according to an embodiment of the present application;

[0036] Figure 6 A flowchart for implementing six-area monitoring of a special-shaped waveguide rod according to a specific embodiment of the present application;

[0037] FIG. 7( a ) is an acoustic emission signal and an AIC curve of a sensor S1 according to a specific embodiment of the present application;

[0038] FIG7( b ) is an acoustic emission signal and an AIC curve of a sensor S2 according to a specific embodiment of the present application;

[0039] FIG7( c ) is an acoustic emission signal and an AIC curve of a sensor S3 according to a specific embodiment of the present application;

[0040] Figure 8 A flowchart of a method for monitoring damage to the hot end structure of an aerospace vehicle provided according to an embodiment of the present application;

[0041] Fig. 9 The figure is a structural example diagram of an electronic device provided according to an embodiment of the present application. DETAILED DESCRIPTION

[0042] Embodiments of the present application are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present application, and should not be construed as limiting the present application.

[0043] The following describes the special-shaped waveguide rod for damage monitoring of the hot end structure of an aerospace vehicle in the embodiment of the present application with reference to the accompanying drawings. In view of the problems mentioned in the above background technology, such as the inability to directly arrange sensors on the hot end structure of the spacecraft due to high temperature and the redundancy of the acquisition system caused by the traditional waveguide rod, the present application provides a special-shaped waveguide rod for damage monitoring of the hot end structure of an aerospace vehicle. In the device, a unique special-shaped waveguide rod design can be used, and multiple sub-waveguides are coupled with the hot end structure and integrated into the anchor plate. With the multiple acoustic emission sensors on the anchor plate, only a small number of sensors can be used to realize damage monitoring of multiple areas of the hot end structure. It effectively solves the problem that the high temperature on the surface of the spacecraft makes it impossible to directly arrange sensors, and at the same time overcomes the redundancy of the acquisition system caused by the "one rod and one channel" of the traditional waveguide rod, greatly improves the space utilization rate and system efficiency, enhances the safety of the aircraft, and can still work reliably in extreme environments, effectively ensuring the health monitoring of the hot end structure of the aerospace vehicle. Therefore, the problems in the related technology that the hot end structure of the spacecraft cannot be directly arranged due to high temperature and the redundancy of the acquisition system caused by the traditional waveguide rod are solved.

[0044] Specifically, Figure 1 A schematic diagram of a special-shaped waveguide rod for monitoring damage to the hot end structure of an aerospace vehicle provided in an embodiment of the present application.

[0045] like Figure 1 As shown, the special-shaped waveguide rod for monitoring the damage of the hot end structure of an aerospace vehicle includes: an acoustic emission sensor 1, an anchor plate 2 and a sub-waveguide 3, and also includes Figure 2 and Figure 3The sub-waveguide base 4, sub-waveguide thread 5, sub-waveguide mounting hole 6 and sensor placement position 7 are shown.

[0046] Specifically, the acoustic emission sensor 1 is an ordinary room temperature sensor; the sub-waveguide 3 is a flexible waveguide (preferably a flexible material with low stiffness, with a minimum diameter d≤5mm); the anchor plate 2 is a circular platform that integrates the sub-waveguide through threaded connection. It should be noted that the connection between the sub-waveguide and the anchor plate includes but is not limited to threads, interference fit, etc., which can effectively ensure the effective propagation of waves. The embodiment of the present application collects the acoustic emission signal transmitted by the sub-waveguide by placing 3 (or more) sensors on the prototype platform, and determines the waveguide rod that transmits the signal through a positioning method, thereby confirming the damaged area.

[0047] The sub-waveguide 3 is coupled with the hot end structure of the aerospace vehicle, and the sub-waveguide is integrated on the anchor plate, and each sub-waveguide detects the monitoring area corresponding to the hot end structure.

[0048] Specifically, the base coupled with the hot end structure has a power law characteristic to enhance the signal strength of the waveguide transmission, wherein the power law characteristic is that the diameter from the bottom end of the base to the waveguide body changes according to the power law rule, and the specific diameter d dz The expression is as follows:

[0049]

[0050] Wherein, x is the distance from the end face of the minimum diameter of the base, D is the maximum diameter of the base, d is the minimum diameter of the base, d is the length of the base, and m is the power exponent (the preferred power exponent is 2.2).

[0051] In actual implementation, the sub-waveguide distribution positions correspond to the monitoring areas of the hot end structure. For example, when it is necessary to monitor multiple specific parts or areas of the hot end structure, the sub-waveguides will be reasonably arranged on the anchor plate according to the layout of these areas to achieve comprehensive and effective monitoring coverage. Assuming that a hot end component with a complex shape is to be monitored, the sub-waveguides may be distributed at certain angles around the center of the anchor plate to ensure that each sub-waveguide can effectively receive the acoustic emission signals generated by its corresponding monitoring area.

[0052] The acoustic emission sensor 1 is arranged on the anchor plate and is used to collect the acoustic emission signal transmitted to the special-shaped waveguide rod, so as to determine the target sub-waveguide of the transmission signal according to the acoustic emission signal, and determine that the monitoring area corresponding to the target sub-waveguide is the damaged area of ​​the hot end structure.

[0053] In the actual implementation process, the sensor and the sub-waveguide work together to locate the damaged area by collecting the time information of the acoustic emission signal from the sensor, combined with the geometric parameters and wave velocity of the sub-waveguide. For example, the Akaike information criterion is used to pick up the wave arrival time, and based on the wave arrival time, the target sub-waveguide is determined by the time difference of the acoustic emission wave reaching each acoustic emission sensor.

[0054] Optionally, in one embodiment of the present application, the calculation formula of the arrival time is:

[0055] AIC(k)=klg{Var(x[1,k])}+(Nk-1)lg{Var(x[k+1,N])},

[0056] Among them, x is the time series of the acoustic emission signal, k is the dividing point of the two time windows in the time series, and N is the total number of time samples.

[0057] Furthermore, the time difference t between the i-th receiving sensor and the j-th receiving sensor is calculated. ij (i, j = 1, 2, 3 and i ≠ j). This time difference reflects the time difference of the acoustic emission wave reaching different sensors through different paths (corresponding to different sub-waveguides). In the actual calculation process, the collected time data can be accurately processed to remove possible noise interference and measurement errors. Data filtering, averaging and other methods can be used to improve the accuracy of time measurement. For example, the arrival time obtained by multiple measurements is averaged to reduce the impact of single measurement errors on the time difference calculation results.

[0058] Furthermore, the sub-waveguides that transmit the acoustic emission signals in the anchor plate are determined using a geometric method. The geometric method is as follows:

[0059] 1) According to the layout requirements of sub-waveguides and sensors, measure Figure 4 The distance L between the sub-waveguide and the sensor is shown mk , where m represents the mth sensor (m=1,2,3) and k represents the kth sub-waveguide (k=1,2,3…,N).

[0060] 2) By measuring the wave velocity v in the anchor plate, the theoretical time difference between the sensors corresponding to the sub-waveguide as the wave source is calculated (i, j = 1, 2, 3 and i ≠ j; k = 1, 2, 3 ..., N), and construct a theoretical time difference database.

[0061] 3) Calculate the deviation Error(k) between the theoretical time difference of each sensor and the test time difference in step 3. The specific expression is:

[0062]

[0063] 4) The deviation between the theoretical time difference and the test time difference of each sub-waveguide is calculated, and the sub-waveguide corresponding to the minimum deviation is taken as the waveguide for transmitting the acoustic emission signal. The specific expression is as follows:

[0064] Min{Error(1),...,Error(k),...,Error(N)},

[0065] Then, the detection area corresponding to the sub-waveguide is the damaged area.

[0066] The following is a specific example to further explain the embodiment of the present application.

[0067] In order to simplify the calculation procedure, this embodiment provides a special-shaped waveguide rod (such as Figure 5 As shown), the six regions are relatively independent. In addition, the anchor plate in this embodiment can be 5 mm thick and 200 mm in diameter; the number of sub-waveguides is 6 and evenly distributed at 70 mm from the center of the anchor plate. The specific implementation process of the case is as follows: Figure 6 As shown:

[0068] Step S601: Calculate the theoretical time difference between each sensor by measuring the distance between the six sub-waveguides and the sensor.

[0069] To calculate the theoretical time difference between the sensors, it is necessary to know the propagation velocity v of the acoustic emission wave in the sub-waveguide. This wave velocity can be obtained through experimental measurement or calculated based on material properties and wave propagation theory.

[0070] Step S602: using the finite element method to perform acoustic emission tests in areas ①, ② and ④ respectively, and using the AIC method to obtain the arrival time of the received signal of each sensor, as shown in FIG7 .

[0071] During the model construction process, the material properties of the hot end structure must be fully considered, including parameters such as elastic modulus, Poisson's ratio, density, etc. These parameters accurately reflect the behavior of the structure under stress and temperature changes.

[0072] Step S603: Calculate the deviation between the acoustic emission signals generated by the tests in different areas and the corresponding theoretical time differences;

[0073] The formula is in, is the theoretical time difference, Δt ij is the time difference between the sensors obtained by the test.

[0074] Step S604: Calculate and search for the deviation between the theoretical time difference and the test time difference of all sub-waveguides, wherein the monitoring area corresponding to the sub-waveguide with the smallest deviation is the area where the damage acoustic emission source is located.

[0075] Minimum deviation means that in all possible monitoring areas, the result obtained based on the sub-waveguide assumption is closest to the actual situation, that is, the error is the smallest. According to the principle of error minimization, the monitoring area corresponding to the sub-waveguide with the smallest deviation is selected as the area where the damage acoustic emission source is located, which can minimize the impact of the error on the positioning result and improve the accuracy of positioning.

[0076] As shown in Table 1, Table 1 gives the positioning results of three test events with regions ①, ② and ④ as the damage regions.

[0077] Table 1

[0078]

[0079]

[0080] It can be seen from the table (the bold data in the table are the minimum deviations between the theoretical time difference and the test time difference of each sub-waveguide during a test process). When damage occurs in areas ①, ② and ④, the minimum deviation between the test and the theory of the sub-waveguide corresponding to area ① is 3.478×10 -12 , the minimum deviation between the test and theory of the sub-waveguide in region ② is 9.107×10 -13 , the minimum deviation between the test and theory of the sub-waveguide in region ④ is 2.986×10 -13 Therefore, in this implementation case, the positioning method based on the special-shaped waveguide rod can effectively determine the damaged area. This shows that the special-shaped waveguide rod provided in the embodiment of the present application can accurately monitor the damage of multiple areas with only a small number of sensors, and has good application prospects in multi-area monitoring of hot end structures.

[0081] According to the special-shaped waveguide rod for damage monitoring of the hot end structure of aerospace vehicles proposed in the embodiment of the present application, multiple sub-waveguides can be coupled with the hot end structure and integrated into the anchor plate through a unique special-shaped waveguide rod design, and multiple acoustic emission sensors on the anchor plate can be used to achieve damage monitoring of multiple areas of the hot end structure with only a small number of sensors. It effectively solves the problem that sensors cannot be directly arranged due to the high temperature on the surface of the spacecraft, and overcomes the redundancy problem of the acquisition system caused by the "one rod and one channel" of the traditional waveguide rod, greatly improving the space utilization rate and system efficiency, enhancing the safety of the aircraft, and can still work reliably in extreme environments, effectively ensuring the healthy monitoring of the hot end structure of the aerospace vehicle.

[0082] Next, a method for monitoring damage to the hot end structure of an aerospace vehicle proposed in accordance with an embodiment of the present application will be described with reference to the accompanying drawings.

[0083] Figure 8 It is a flow chart of a method for monitoring damage to the hot end structure of an aerospace vehicle according to an embodiment of the present application.

[0084] like Figure 8 As shown, the method for monitoring damage to the hot end structure of an aerospace vehicle comprises the following steps:

[0085] In step S801, the acoustic emission signal transmitted to the special-shaped waveguide rod is collected.

[0086] In step S802, a target sub-waveguide for transmitting a signal is determined according to the acoustic emission signal.

[0087] Optionally, in one embodiment of the present application, a target sub-waveguide for transmitting a signal is determined based on an acoustic emission signal, including: a plurality of acoustic emission sensors are further used to pick up a wave arrival time using an Akaike information criterion, and based on the wave arrival time, the target sub-waveguide is determined by the time difference of the acoustic emission wave reaching each acoustic emission sensor.

[0088] Optionally, in one embodiment of the present application, the calculation formula of the arrival time is:

[0089] AIC(k)=klg{Var(x[1,k])}+(Nk-1)lg{Var(x[k+1,N])},

[0090] Among them, x is the time series of the acoustic emission signal, k is the dividing point of the two time windows in the time series, and N is the total number of time samples.

[0091] In step S803, it is determined that the monitoring area corresponding to the target sub-waveguide is a damaged area of ​​the hot end structure.

[0092] It should be noted that the aforementioned explanation of the embodiment of the special-shaped waveguide rod for monitoring the damage of the hot end structure of an aerospace vehicle is also applicable to the method for monitoring the damage of the hot end structure of an aerospace vehicle of this embodiment, and will not be repeated here.

[0093] According to the method for monitoring damage to the hot end structure of an aerospace vehicle proposed in the embodiment of the present application, a unique special-shaped waveguide rod design can be used, and multiple sub-waveguides are coupled to the hot end structure and integrated into the anchor plate. In combination with multiple acoustic emission sensors on the anchor plate, damage monitoring of multiple areas of the hot end structure can be achieved with only a small number of sensors. This effectively solves the problem that sensors cannot be directly arranged due to the high temperature on the surface of the spacecraft, and overcomes the redundancy problem of the acquisition system caused by the "one rod and one channel" of the traditional waveguide rod, greatly improving space utilization and system efficiency, enhancing the safety of the aircraft, and can still work reliably in extreme environments, effectively ensuring the healthy monitoring of the hot end structure of the aerospace vehicle.

[0094] Fig. 9 A schematic diagram of the structure of an electronic device provided in an embodiment of the present application. The electronic device may include:

[0095] A memory 901 , a processor 902 , and a computer program stored in the memory 901 and executable on the processor 902 .

[0096] When the processor 902 executes the program, the method for monitoring damage of the hot end structure of an aerospace vehicle provided in the above embodiment is implemented.

[0097] Furthermore, the electronic device further comprises:

[0098] The communication interface 903 is used for communication between the memory 901 and the processor 902 .

[0099] The memory 901 is used to store computer programs that can be executed on the processor 902 .

[0100] The memory 901 may include a high-speed RAM memory, and may also include a non-volatile memory (non-volatile memory), such as at least one disk memory.

[0101] If the memory 901, the processor 902 and the communication interface 903 are implemented independently, the communication interface 903, the memory 901 and the processor 902 can be connected to each other through a bus and communicate with each other. The bus can be an Industry Standard Architecture (ISA) bus, a Peripheral Component Interconnect (PCI) bus or an Extended Industry Standard Architecture (EISA) bus. The bus can be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Fig. 9 Only one thick line is used in the diagram, but this does not mean that there is only one bus or only one type of bus.

[0102] Optionally, in a specific implementation, if the memory 901, the processor 902 and the communication interface 903 are integrated on a chip, the memory 901, the processor 902 and the communication interface 903 can communicate with each other through an internal interface.

[0103] The processor 902 may be a central processing unit (CPU), or an application specific integrated circuit (ASIC), or one or more integrated circuits configured to implement the embodiments of the present application.

[0104] An embodiment of the present application also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the above method for monitoring damage to the hot end structure of an aerospace vehicle.

[0105] An embodiment of the present application also provides a computer program, including a computer program, which, when executed by a processor, implements the above method for monitoring damage to the hot end structure of an aerospace vehicle.

[0106] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some 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 representations of the above terms do 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 N embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0107] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of this application, "N" means at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0108] Any process or method description in a flowchart or otherwise described herein may be understood to represent a module, fragment or portion of code comprising one or N executable instructions for implementing the steps of a custom logical function or process, and the scope of the preferred embodiments of the present application includes alternative implementations in which functions may not be performed in the order shown or discussed, including performing functions in a substantially simultaneous manner or in reverse order depending on the functions involved, which should be understood by technicians in the technical field to which the embodiments of the present application belong.

[0109] 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, device or apparatus (such as a computer-based system, a system including a processor, or other system that can fetch instructions from an instruction execution system, device or apparatus and execute instructions), or in combination with these instruction execution systems, devices or apparatuses. For the purpose of this specification, "computer-readable medium" can be any device that can contain, store, communicate, propagate or transmit a program for use by an instruction execution system, device or apparatus, or in combination with these instruction execution systems, devices or apparatuses. More specific examples of computer-readable media (a non-exhaustive list) include the following: an electrical connection with one or N wirings (electronic devices), a portable computer disk box (magnetic device), a random access memory (RAM), a read-only memory (ROM), an erasable and programmable read-only memory (EPROM or flash memory), a fiber optic device, and a portable compact disk read-only memory (CDROM). In addition, the computer-readable medium may even be paper or other suitable medium on which the program is printed, since the program may be obtained electronically by optically scanning the paper or other medium and then editing, interpreting or processing in other suitable ways as necessary and then storing it in a computer memory.

[0110] 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 embodiment, the N steps or methods can be implemented by software or firmware stored in a memory and executed by a suitable instruction execution system. If implemented by hardware, as in another embodiment, it can be implemented by any one or a combination of multiple of the following technologies known in the art: 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.

[0111] A person skilled in the art may understand that all or part of the steps in the method for implementing the above-mentioned embodiment may be completed by instructing related hardware through a program, and the program may be stored in a computer-readable storage medium, which, when executed, includes one or a combination of the steps of the method embodiment.

[0112] In addition, each functional unit in each embodiment of the present application may be integrated into a processing module, or each unit may exist physically separately, or two or more units may be integrated into one module. The above-mentioned integrated module may be implemented in the form of hardware or in the form of a software functional module. If the integrated module is implemented in the form of a software functional module and sold or used as an independent product, it may also be stored in a computer-readable storage medium.

[0113] The storage medium mentioned above may be a read-only memory, a magnetic disk or an optical disk, etc. Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limiting the present application. A person of ordinary skill in the art may change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A special-shaped waveguide rod for monitoring damage to the hot end structure of an aerospace vehicle, characterized in that: include: Anchor plate; A plurality of sub-waveguides, wherein the plurality of sub-waveguides are coupled with the hot end structure of the aerospace vehicle, and the sub-waveguides are integrated on the anchor plate, and each sub-waveguide detects a monitoring area corresponding to the hot end structure; A plurality of acoustic emission sensors arranged on the anchor plate are used to collect acoustic emission signals transmitted to the special-shaped waveguide rod, so as to determine the target sub-waveguide for transmitting the signal according to the acoustic emission signals, and determine that the monitoring area corresponding to the target sub-waveguide is the damaged area of ​​the hot end structure.

2. The special-shaped waveguide rod according to claim 1, characterized in that: The multiple acoustic emission sensors are further used to pick up the arrival time using the Akaike information criterion, and based on the arrival time, determine the target sub-waveguide through the time difference of the acoustic emission wave reaching each acoustic emission sensor.

3. The special-shaped waveguide rod according to claim 2, characterized in that: The calculation formula of the wave arrival time is: AIC(k)=klg{Var(x[1,k])}+(Nk-1)lg{Var(x[k+1,N])}, Among them, x is the time series of the acoustic emission signal, k is the dividing point of the two time windows in the time series, and N is the total number of time samples.

4. The special-shaped waveguide rod according to claim 1, characterized in that: The sub-waveguide is a bendable waveguide.

5. The special-shaped waveguide rod according to claim 1, characterized in that: The base to which the plurality of sub-waveguides are coupled has a power-law characteristic.

6. A method for monitoring damage to the hot end structure of an aerospace vehicle, characterized in that: Using the special-shaped waveguide rod for monitoring the damage of the hot end structure of an aerospace vehicle as described in any one of claims 1 to 5, wherein the method comprises the following steps: Collecting the acoustic emission signal transmitted to the special-shaped waveguide rod; Determining a target sub-waveguide for the transmission signal according to the acoustic emission signal; It is determined that the monitoring area corresponding to the target sub-waveguide is a damaged area of ​​the hot end structure.

7. The method according to claim 6, characterized in that The method of determining the target sub-waveguide of the transmission signal according to the acoustic emission signal comprises: the multiple acoustic emission sensors are further used to pick up the arrival time by using the Akaike information criterion, and based on the arrival time, the target sub-waveguide is determined by the time difference of the acoustic emission wave reaching each acoustic emission sensor.

8. An electronic device, characterized in that: include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the method for monitoring damage to the hot end structure of an aerospace vehicle as described in any one of claims 1 to 5.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: The program is executed by a processor to implement the method for monitoring damage to the hot end structure of an aerospace vehicle as described in any one of claims 1 to 5.

10. A computer program product, characterized in that It comprises a computer program, characterized in that the computer program is executed to implement the method for monitoring damage of the hot end structure of an aerospace vehicle as described in any one of claims 1-5.

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