Intelligent spaceflight heat pipe leakage detection system and method

Abstract

The invention relates to the technical field of spaceflight heat pipe detection, and relates to an intelligent leak detection system and method for a spaceflight heat pipe. According to the method, the aerospace heat pipe is placed in a simulated actual environment, the aerospace heat pipe is segmented according to the type and the placement state of the aerospace heat pipe, each aerospace heat pipe segment generates a temperature distribution diagram through infrared thermal imaging, and whether each aerospace heat pipe segment has a leakage area or not is comprehensively judged according to the absolute concentration difference of the tracer gas concentration at the two ends of each aerospace heat pipe segment. The method comprises the following steps: carrying out ultrasonic detection and two-end thermal fluid pressure data analysis on the spaceflight heat pipe with no leakage area in each spaceflight heat pipe section to generate an ultrasonic flaw detection coefficient and a thermal fluid pressure difference coefficient, and comprehensively analyzing the ultrasonic flaw detection coefficient and the thermal fluid pressure difference coefficient to obtain a dangerous hidden danger index and judge a dangerous hidden danger level. According to the method, accurate identification of the leakage area is realized, the state of the heat pipe is comprehensively evaluated, the situation of misjudgment or missed judgment is reduced, and the early warning capability of dangerous hidden dangers is improved.

Description

Technical Field

[0001] The present invention relates to the field of intelligent leak detection of aerospace heat pipes, and in particular to an intelligent leak detection system and method for aerospace heat pipes. Background Art

[0002] Space heat pipes play a crucial role in transporting working fluids within spacecraft. They are one of the primary means of transporting working fluids within a spacecraft, and their sealing performance directly impacts the spacecraft's thermal management efficiency and operational safety. However, the complex operating conditions of space heat pipes make it difficult to apply the same inspection methods used for other pipes. Furthermore, a single inspection method may not be able to effectively detect leaks in space heat pipes. Therefore, detecting defects that cause leaks in space heat pipes has become a pressing issue.

[0003] However, the existing technology has the following problems: 1. The existing technology does not truly simulate the actual aerospace environment, resulting in the inability to accurately assess the leakage risk of aerospace heat pipes in a complex space environment. It cannot truly reflect the impact of the complex space environment on heat pipes, resulting in a large deviation in the assessment of heat pipe leakage risks, which may underestimate or misjudge potential leakage hazards, and ultimately affect the safe operation of aerospace equipment in space.

[0004] 2. Existing technologies mostly use a single detection method to determine whether aerospace heat pipes are leaking. When the leakage of the heat pipe is small or the temperature change is not obvious, it is difficult to accurately identify the leakage area, resulting in low detection accuracy and an inability to comprehensively evaluate the status of the heat pipe, which is prone to misjudgment or missed judgment.

[0005] 3. For high-precision components like aerospace heat pipes, even the smallest leaks or potential hazards can have serious consequences. Existing technologies do not combine acoustic detection results with thermal fluid pressure changes to accurately locate and quantify the associated risk index, failing to meet the stringent aerospace requirements for heat pipe inspection accuracy. Summary of the Invention

[0006] The present invention aims to provide an intelligent leak detection system and method for aerospace heat pipes, which solves the problems existing in existing pipeline detection systems by realizing leakage determination and flaw detection of pipelines and improves the accuracy of pipeline detection systems.

[0007] The present invention solves the technical problem by employing a technical solution: an aerospace heat pipe intelligent leak detection system, comprising an aerospace heat pipe placement module, a heat pipe partitioning and detection module, a heat pipe leakage determination module, a heat pipe flaw detection and analysis module, and a heat pipe early warning and reminder module. The modules are connected as follows: the aerospace heat pipe placement module is connected to the heat pipe partitioning and detection module; the heat pipe leakage determination module is connected to the heat pipe partitioning and detection module and the heat pipe flaw detection and analysis module, respectively; and the heat pipe flaw detection and analysis module is connected to the heat pipe early warning and reminder module.

[0008] The aerospace heat pipe placement module is used to place the aerospace heat pipe to be tested in an aerospace heat pipe test chamber built based on the actual aerospace environment, and to introduce thermal fluid containing tracer gas into the aerospace heat pipe to be tested.

[0009] The heat pipe division detection module is used to divide the aerospace heat pipe to be detected into several aerospace heat pipe segments according to the placement status, and collect infrared thermal imaging and tracer gas concentration data of each aerospace heat pipe segment.

[0010] The heat pipe leakage determination module is used to obtain the heat pipe temperature distribution map from the infrared thermal imaging of each aerospace heat pipe segment, and comprehensively determine whether there is a leakage area in each aerospace heat pipe segment by combining the heat pipe temperature distribution map with the tracer gas concentration data.

[0011] The heat pipe flaw detection and analysis module is used to perform acoustic wave detection on aerospace heat pipe sections through ultrasonic sensors when there are no leakage areas in each aerospace heat pipe section. The acoustic wave detection results are analyzed with the thermal fluid pressure change data of the aerospace heat pipe section to obtain the hazard index of the aerospace heat pipe section.

[0012] The heat pipe early warning reminder module is used to warn of aerospace heat pipe sections with leakage areas and provide corresponding level early warning reminders based on the danger index of the aerospace heat pipe sections.

[0013] An intelligent leak detection method for aerospace heat pipes comprises: S1, placing the aerospace heat pipe to be tested in an aerospace heat pipe test chamber built based on an actual aerospace environment, and introducing a thermal fluid containing a tracer gas into the aerospace heat pipe to be tested.

[0014] S2. Divide the aerospace heat pipe to be inspected into several aerospace heat pipe sections according to the placement status of the aerospace heat pipe, and collect infrared thermal imaging and tracer gas concentration data of each aerospace heat pipe section.

[0015] S3. Obtain a heat pipe temperature distribution map from the infrared thermal imaging of each aerospace heat pipe segment, and comprehensively determine whether there is a leakage area in each aerospace heat pipe segment by combining the heat pipe temperature distribution map with the tracer gas concentration data.

[0016] S4. When there is no leakage area in each aerospace heat pipe segment, the aerospace heat pipe segment is subjected to acoustic wave detection by an ultrasonic sensor, and the acoustic wave detection result is analyzed with the thermal fluid pressure change data of the aerospace heat pipe segment to obtain the hazard index of the aerospace heat pipe segment.

[0017] S5. Alarm the aerospace heat pipe section with leakage area, and issue corresponding level warning reminder according to the danger index of the aerospace heat pipe section.

[0018] Compared with the existing technology, the present invention has the following beneficial effects: (1) The present invention places the aerospace heat pipe to be tested in an aerospace heat pipe test room built based on the actual aerospace environment by introducing an aerospace heat pipe placement module, which truly reflects the impact of the complex space environment on the aerospace heat pipe, accurately assesses the risk of heat pipe leakage, reduces the probability of misjudgment of potential hidden dangers, and ensures the normal operation of aerospace facilities in space.

[0019] (2) The present invention introduces a heat pipe leakage determination module to obtain the heat pipe temperature distribution map and the density of the thermal fluid containing tracer gas to comprehensively determine whether there is a leakage area in each aerospace heat pipe section, accurately identify the leakage area, and comprehensively evaluate the status of the heat pipe to reduce the occurrence of misjudgment or missed judgment.

[0020] (3) The present invention introduces a heat pipe flaw detection and analysis module, which uses an ultrasonic sensor to perform acoustic wave detection on the aerospace heat pipe section, and analyzes the acoustic wave detection results with the thermal fluid pressure change data of the aerospace heat pipe section to obtain the dangerous hidden danger index of the aerospace heat pipe section, thereby improving the early warning capability of dangerous hidden dangers. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0022] Figure 1 This is a schematic diagram of system module connections of the present invention.

[0023] Figure 2 Schematic diagram of the method steps of the present invention.

[0024] Figure 3 Schematic diagram of content analysis of the heat pipe flaw detection and analysis module of the present invention. DETAILED DESCRIPTION

[0025] Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement of components and steps, numerical expressions, and numerical values ​​described in these embodiments do not limit the scope of the present invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the accompanying drawings are not drawn to scale.

[0026] The following description of at least one exemplary embodiment is merely illustrative in nature and is not intended to limit the invention, its application, or uses. Technologies, methods, and apparatus known to those skilled in the art may not be discussed in detail, but where appropriate, such technologies, methods, and apparatus should be considered part of the specification.

[0027] In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not limiting. Therefore, other examples of the exemplary embodiments may have different values.

[0028] See also Figure 1 As shown, the present invention provides an intelligent aerospace heat pipe leak detection system, comprising an aerospace heat pipe placement module, a heat pipe partitioning and detection module, a heat pipe leakage determination module, a heat pipe flaw detection and analysis module, and a heat pipe early warning and reminder module. The modules are connected as follows: the aerospace heat pipe placement module is connected to the heat pipe partitioning and detection module; the heat pipe leakage determination module is connected to the heat pipe partitioning and detection module and the heat pipe flaw detection and analysis module, respectively; and the heat pipe flaw detection and analysis module is connected to the heat pipe early warning and reminder module.

[0029] The aerospace heat pipe placement module is used to place the aerospace heat pipe to be tested in an aerospace heat pipe test chamber built based on the actual aerospace environment, and to introduce thermal fluid containing tracer gas into the aerospace heat pipe to be tested.

[0030] The present invention introduces an aerospace heat pipe placement module to place the aerospace heat pipe to be tested in an aerospace heat pipe test room built based on the actual aerospace environment. It truly reflects the impact of the complex space environment on aerospace heat pipes, accurately assesses the risk of heat pipe leakage, reduces the probability of misjudgment of potential hidden dangers, and ensures the normal operation of aerospace facilities in space.

[0031] The heat pipe segmentation detection module is used to divide the aerospace heat pipe to be inspected into several aerospace heat pipe segments based on their placement. It then collects infrared thermal imaging and tracer gas concentration data for each aerospace heat pipe segment. The tracer gas concentration is the volume ratio of the tracer gas to the thermal fluid.

[0032] It should be noted that the aerospace heat pipe to be tested is divided into several aerospace heat pipe sections according to the placement status. The specific content is as follows: a pipeline diagram of the aerospace heat pipe placement in the aerospace heat pipe test room is obtained, and the pipeline is divided based on the type and placement status of the aerospace heat pipe in the aerospace heat pipe placement pipeline diagram to form several aerospace heat pipe sections.

[0033] The types of aerospace heat pipes include straight aerospace heat pipe sections and curved aerospace heat pipe sections. The placement of aerospace heat pipes is used to distinguish between horizontal and non-horizontal aerospace heat pipe sections. Specifically, aerospace heat pipes are divided into four types: horizontal straight aerospace heat pipe sections, horizontal curved aerospace heat pipe sections, non-horizontal straight aerospace heat pipe sections, and non-horizontal curved aerospace heat pipe sections.

[0034] The heat pipe leakage determination module is used to obtain the heat pipe temperature distribution map from the infrared thermal imaging of each aerospace heat pipe segment, and comprehensively determine whether there is a leakage area in each aerospace heat pipe segment by combining the heat pipe temperature distribution map with the tracer gas concentration data.

[0035] It should be noted that the specific contents of the heat pipe leakage determination module are as follows: extracting the outer surface temperature of each aerospace heat pipe segment from infrared thermal imaging images at different angles, generating a heat pipe temperature distribution map at the position of the corresponding aerospace heat pipe segment based on the outer surface temperature, and combining the heat pipe temperature distribution map with the outer surface temperature of a standard aerospace heat pipe to perform deviation analysis to generate a temperature confidence factor.

[0036] The heat pipe temperature distribution map is generated by extracting the infrared temperature sensors at different positions in the aerospace heat pipe test room to detect the outer surface temperature of the aerospace heat pipe section from different angles.

[0037] The tracer gas concentration data of each aerospace heat pipe section at the same time are extracted, and the absolute difference analysis of the tracer gas concentration data is performed to generate the absolute concentration difference.

[0038] The temperature confidence factor and absolute concentration difference of each aerospace heat pipe section are recorded, and the temperature confidence factor and absolute concentration difference of each aerospace heat pipe section are compared with the preset temperature confidence factor and absolute concentration difference thresholds to determine whether there is a leakage area in each aerospace heat pipe section.

[0039] It should be noted that the temperature confidence factor and absolute concentration difference are generated by selecting the maximum temperature value in the heat pipe temperature distribution diagram of each aerospace heat pipe segment that exceeds the standard aerospace heat pipe outer surface temperature, recording the difference between the temperature value and the standard aerospace heat pipe outer surface temperature, and then calculating the ratio of the difference to the standard aerospace heat pipe outer surface temperature to obtain the temperature confidence factor. The greater the difference between the heat pipe outer surface temperature and the standard surface temperature, the greater the temperature confidence factor.

[0040] Obtain the tracer gas concentration data of the inflow and outflow ends of each aerospace heat pipe segment, and record the absolute concentration difference between the tracer gas concentration at the outflow end and the tracer gas concentration at the inflow end of each aerospace heat pipe segment.

[0041] The specific method for determining whether each aerospace heat pipe segment has a leakage area is as follows: based on the temperature and absolute concentration difference of a standard aerospace heat pipe and a preset error standard, a temperature confidence factor interval and an absolute concentration difference interval are set. When either the temperature confidence factor or the absolute concentration difference of a certain aerospace heat pipe segment exceeds the corresponding set interval, a leakage area exists in the corresponding aerospace heat pipe segment; otherwise, no leakage area exists in the corresponding aerospace heat pipe segment.

[0042] The present invention introduces a heat pipe leakage determination module, which obtains the heat pipe temperature distribution diagram and the density of the thermal fluid containing tracer gas to comprehensively determine whether there is a leakage area in each aerospace heat pipe section, accurately identify the leakage area, and comprehensively evaluate the status of the heat pipe, reducing the possibility of misjudgment or missed judgment.

[0043] like Figure 3As shown, the heat pipe flaw detection and analysis module is used to perform acoustic wave detection on the aerospace heat pipe segments through ultrasonic sensors when there is no leakage area in each aerospace heat pipe segment, and analyze the acoustic wave detection results with the thermal fluid pressure change data of the aerospace heat pipe segment to obtain the danger hidden danger index of the aerospace heat pipe segment.

[0044] It should be noted that the specific contents of the heat pipe flaw detection and analysis module are as follows: the acoustic wave detection results of each aerospace heat pipe segment are retrieved, the maximum length and depth of each crack and the deformation volume of each aerospace heat pipe segment are extracted from the acoustic wave detection results, a linear weight analysis is performed based on the maximum length and depth of each crack to generate the crack influence degree, the maximum length and depth corresponding to the maximum crack influence degree are selected as the crack representative data, and the crack representative data of each aerospace heat pipe segment and the corresponding aerospace heat pipe segment deformation volume are fused and analyzed to generate the ultrasonic flaw detection coefficient of each aerospace heat pipe segment.

[0045] The preset critical values ​​are the maximum acceptable crack length and depth and the maximum deformation volume obtained from the historical data of the measured aerospace heat pipe or industry standards. The method for linear weight analysis of the crack impact degree is as follows: , is the degree of crack influence, is the length of the crack, is the maximum crack depth, is the critical length of the crack, is the critical depth of the crack, is the weight of the crack length, is the weight of the crack depth. They are the crack length weight and crack depth weight, respectively. The crack length weight and crack depth weight can be set according to industry experience, or they can be obtained through a limited number of detection data. For example, first collect the acoustic wave detection data corresponding to the aerospace heat pipe in the ultrasonic detection data, and then calculate the correlation coefficient between the crack length, crack depth and crack influence degree in the acoustic wave detection data corresponding to the aerospace heat pipe. Use the least squares method to perform linear regression equation analysis to determine the contribution of the crack length weight and crack depth weight. Finally, normalize the data and convert the contribution into the weights of the crack length and crack depth, and the sum of them is 1.

[0046] The thermal fluid flow rate of each aerospace heat pipe segment is extracted, and the local head loss is generated by combining the thermal fluid flow rate of each aerospace heat pipe segment and the type of the corresponding aerospace heat pipe segment. The theoretical value of the pressure difference at both ends of each aerospace heat pipe segment is generated by combining the local head loss, placement status and thermal fluid density of each aerospace heat pipe segment. The pressure at both ends of each aerospace heat pipe segment at the same time is obtained for difference analysis to obtain the actual value of the pressure difference at both ends of each aerospace heat pipe. The actual value of the pressure difference at both ends is compared with the theoretical value of the pressure difference at both ends. The comparison value is normalized to obtain the thermal fluid pressure difference coefficient of each aerospace heat pipe segment.

[0047] The actual value of the pressure difference between the two ends can be obtained by arranging pressure sensors at both ends of each aerospace heat pipe segment to collect the difference. When the thermal fluid pressure coefficient is greater than 1, it indicates that the pipeline is leaking. In order to increase the reliability of the thermal fluid pressure difference coefficient combined with the ultrasonic flaw detection coefficient, Normalization is performed to generate the thermal fluid pressure coefficient, where is the ratio of the actual value of the pressure difference between the two ends to the theoretical value of the pressure difference between the two ends, is the thermal fluid pressure coefficient.

[0048] The ultrasonic flaw detection coefficient and thermal fluid pressure difference coefficient of each aerospace heat pipe section are extracted, and the hazard index is obtained by multiplying the ultrasonic flaw detection coefficient and the thermal fluid pressure difference coefficient of each aerospace heat pipe section.

[0049] The hazard index is the product of the ultrasonic flaw detection coefficient and the thermal fluid pressure difference coefficient of each section of the heat pipe, emphasizing the synergistic effect of the length, depth and deformation volume of the cracks in the aerospace heat pipe and the thermal fluid pressure in the aerospace heat pipe. When any one of the ultrasonic flaw detection coefficient and the thermal fluid pressure difference coefficient increases and the other decreases, the hazard index of the aerospace heat pipe is low; when both the ultrasonic flaw detection coefficient and the thermal fluid pressure difference coefficient increase, the hazard index of the aerospace heat pipe increases rapidly.

[0050] The ultrasonic flaw detection coefficient is obtained by performing a ratio analysis on the length, maximum depth and deformation volume of the representative crack data of each aerospace heat pipe segment and the preset corresponding critical values, assigning different weights to the ratios for weighted accumulation, and generating the ultrasonic flaw detection coefficient through normalization processing.

[0051] The ultrasonic flaw detection coefficient is: , where is the weight of the crack length, is the weight of the maximum crack depth, is the weight of the deformation volume, is the length of the crack, is the maximum crack depth, is the deformation volume, The weights for crack length, crack depth, and deformation volume can be set based on industry experience, which stems from long-term engineering practice. Aerospace engineers, relying on their understanding of the physical properties of aerospace heat pipe materials, calculate the correlation coefficients between crack length, crack depth, and deformation volume and pipeline leakage under specific low-Earth orbit operating conditions, based on past crack failure cases of similar heat pipes. Least squares fitting is then used, using crack length as the independent variable and leakage risk as the dependent variable, to accurately analyze their impact on leakage, thereby determining the weights for crack length, crack depth, and deformation volume, with the sum total being 1.

[0052] It should be noted that different materials of aerospace heat pipes have different physical properties and corresponding standards. For example, if the material of the aerospace heat pipe is aluminum alloy, then Set to 0.6, Set to 0.25, Set to 0.15, Assuming it is twice the wall thickness of aerospace heat pipe, Assume that the wall thickness is 0.5 times of the aerospace heat pipe. , where is the cross-sectional area of ​​the aerospace heat pipe, is the wall thickness of aerospace heat pipe, is the yield strain of the material, which can be obtained by looking up the material table.

[0053] The theoretical value of the pressure difference at both ends of each aerospace heat pipe segment is obtained by obtaining the height difference between the inflow end and the outflow end of the corresponding aerospace heat pipe segment based on the placement state of each aerospace heat pipe segment, and combining the height difference at both ends with the thermal fluid density and gravitational acceleration to generate the height pressure difference.

[0054] The altitude pressure difference is: , where is the density of the thermal fluid in the aerospace heat pipe, is the acceleration due to gravity, is the height of the outflow end of each aerospace heat pipe segment, is the height of the inflow end of each aerospace heat pipe section.

[0055] The bending angle and curvature radius ratio of each aerospace heat pipe segment are obtained to evaluate the local resistance coefficient of the corresponding aerospace heat pipe segment. The local resistance coefficient is combined with the thermal fluid flow rate and gravity acceleration to generate the local head loss. The local head loss is combined with the thermal fluid density and gravity acceleration to generate the resistance pressure difference.

[0056] The local head loss is: , where is the local head loss of each aerospace heat pipe section, where is the local resistance coefficient. Based on the type of aerospace heat pipe segment, the local resistance coefficient of the corresponding type of aerospace heat pipe standard is retrieved from the aerospace heat pipe database. is the flow rate of the thermal fluid in the aerospace heat pipe, is the acceleration due to gravity.

[0057] The resistance pressure difference is: The local head loss will increase as the degree of flow resistance of the local structure of the aerospace heat pipe increases, resulting in an increase in the resistance pressure.

[0058] The height pressure difference and resistance pressure difference of each aerospace heat pipe section are accumulated to obtain the theoretical value of the pressure difference at both ends of the corresponding aerospace heat pipe section.

[0059] The present invention introduces a heat pipe flaw detection and analysis module, which uses an ultrasonic sensor to perform acoustic wave detection on aerospace heat pipe sections. The acoustic wave detection results are analyzed with the thermal fluid pressure change data of the aerospace heat pipe sections to obtain the dangerous hidden danger index of the aerospace heat pipe sections, thereby improving the early warning capability of dangerous hidden dangers.

[0060] The heat pipe early warning reminder module is used to warn of aerospace heat pipe sections with leakage areas and provide corresponding level early warning reminders based on the danger index of the aerospace heat pipe sections.

[0061] The specific contents of the heat pipe early warning reminder module include: matching the hazard index of each aerospace heat pipe section with the preset hazard index range of each hazard level, obtaining the hazard level of each aerospace heat pipe section, and providing corresponding level early warning reminders based on the hazard level.

[0062] Furthermore, the various danger levels can be set as level 1, level 2, and level 3. If the danger index of a certain aerospace heat pipe segment is within the range of danger indices corresponding to the first level, the danger level of the aerospace heat pipe segment is level 1, and a low-risk warning is issued, indicating that the aerospace heat pipe can be used normally; if the danger index of a certain aerospace heat pipe segment is within the range of danger indices corresponding to the second level, the danger level of the aerospace heat pipe segment is level 2, and a medium-risk warning is issued, indicating that the aerospace heat pipe needs to be used with caution; if the danger index of a certain aerospace heat pipe segment is within the range of danger indices corresponding to the third level, the danger level of the aerospace heat pipe segment is level 3, and a high-risk warning is issued, indicating that the aerospace heat pipe cannot be used.

[0063] like Figure 2 As shown, an intelligent leak detection method for aerospace heat pipes is specifically as follows: S1. The aerospace heat pipe to be tested is placed in an aerospace heat pipe test chamber built based on the actual aerospace environment, and a hot fluid containing tracer gas is introduced into the aerospace heat pipe to be tested.

[0064] S2. Divide the aerospace heat pipe to be inspected into several aerospace heat pipe sections according to the placement status of the aerospace heat pipe, and collect infrared thermal imaging and tracer gas concentration data of each aerospace heat pipe section.

[0065] S3. Obtain a heat pipe temperature distribution map from the infrared thermal imaging of each aerospace heat pipe segment, and comprehensively determine whether there is a leakage area in each aerospace heat pipe segment by combining the heat pipe temperature distribution map with the tracer gas concentration data.

[0066] S4. When there is no leakage area in each aerospace heat pipe segment, the aerospace heat pipe segment is subjected to acoustic wave detection by an ultrasonic sensor, and the acoustic wave detection result is analyzed with the thermal fluid pressure change data of the aerospace heat pipe segment to obtain the hazard index of the aerospace heat pipe segment.

[0067] S5. Alarm the aerospace heat pipe section with leakage area, and issue corresponding level warning reminder according to the danger index of the aerospace heat pipe section.

[0068] The present invention divides aerospace heat pipes into segments according to their type and placement status in combination with their actual usage environment. By comprehensively analyzing the temperature and tracer gas concentration of each aerospace heat pipe segment, it is determined whether there is a leakage area in each aerospace heat pipe segment. At the same time, a hazard index is generated by combining the ultrasonic flaw detection coefficient and the thermal fluid pressure difference coefficient to assess the hazard level of each aerospace heat pipe segment and generate usage recommendations, thereby achieving precise and refined leak detection of aerospace heat pipes.

[0069] The above formulas are all dimensionless and numerical calculations. The formulas are obtained by collecting a large amount of data and performing software simulation to obtain the most recent real situation. The preset parameters in the formulas are set by technicians in this field according to actual conditions.

[0070] The above embodiments may be implemented in whole or in part through software, hardware, firmware, or any other combination thereof. When implemented using software, the above embodiments may be implemented in whole or in part in the form of a computer program product.

[0071] Those skilled in the art will appreciate that the modules and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0072] In addition, each functional module in each embodiment of the present application may be integrated into one processing module, or each module may exist physically separately, or two or more modules may be integrated into one module.

[0073] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of this application. Therefore, the scope of protection of this application should be based on the scope of protection of the claims.

[0074] Finally, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An aerospace heat pipe intelligent leak detection system, characterized in that: include: The aerospace heat pipe placement module is used to place the aerospace heat pipe to be tested in an aerospace heat pipe test chamber built based on the actual aerospace environment, and introduce thermal fluid containing tracer gas into the aerospace heat pipe to be tested; The heat pipe segmentation detection module is used to divide the aerospace heat pipe to be detected into several aerospace heat pipe segments according to the placement status, and collect infrared thermal imaging and tracer gas concentration data of each aerospace heat pipe segment; The heat pipe leakage determination module is used to obtain the heat pipe temperature distribution map from the infrared thermal imaging of each aerospace heat pipe segment, and comprehensively determine whether there is a leakage area in each aerospace heat pipe segment by combining the heat pipe temperature distribution map with the tracer gas concentration data; The heat pipe flaw detection and analysis module is used to perform acoustic detection on aerospace heat pipe sections using ultrasonic sensors when no leakage areas exist in the sections. The acoustic detection results are combined with the thermal fluid pressure change data of the aerospace heat pipe sections to analyze the danger index of the aerospace heat pipe sections. The heat pipe early warning reminder module is used to warn of aerospace heat pipe sections with leakage areas and provide corresponding level early warning reminders based on the danger index of the aerospace heat pipe sections.

2. The aerospace heat pipe intelligent leak detection system according to claim 1, characterized in that: The specific method of dividing the aerospace heat pipe to be inspected into several aerospace heat pipe sections according to the placement status of the aerospace heat pipe to be inspected is: Obtain a pipeline diagram for placement of aerospace heat pipes in an aerospace heat pipe test chamber, divide the pipelines based on the types and placement states of the aerospace heat pipes in the pipeline diagram, and form several aerospace heat pipe sections.

3. The aerospace heat pipe intelligent leak detection system according to claim 1, characterized in that: The specific contents of the heat pipe leakage determination module include: The outer surface temperature of each aerospace heat pipe segment is extracted from infrared thermal imaging images at different angles. A heat pipe temperature distribution map is generated based on the outer surface temperature at the corresponding aerospace heat pipe segment. The heat pipe temperature distribution map is then combined with the outer surface temperature of a standard aerospace heat pipe for deviation analysis to generate a temperature confidence factor. Extract the tracer gas concentration data of each aerospace heat pipe section at the same time, and perform absolute difference analysis on the tracer gas concentration data to generate absolute concentration difference; The temperature confidence factor and absolute concentration difference of each aerospace heat pipe section are recorded, and the temperature confidence factor and absolute concentration difference of each aerospace heat pipe section are compared with the preset temperature confidence factor and absolute concentration difference thresholds to determine whether there is a leakage area in each aerospace heat pipe section.

4. The aerospace heat pipe intelligent leak detection system according to claim 3, characterized in that: The temperature confidence factor and the absolute concentration difference are generated in the following manner: Screening out the maximum temperature value in the heat pipe temperature distribution diagram of each aerospace heat pipe segment that exceeds the standard aerospace heat pipe outer surface temperature, recording the difference between the temperature value and the standard aerospace heat pipe outer surface temperature and the ratio of the temperature to the standard aerospace heat pipe outer surface temperature to obtain a temperature confidence factor; Obtain the tracer gas concentration data of the inflow and outflow ends of each aerospace heat pipe segment, and record the absolute concentration difference between the tracer gas concentration at the outflow end and the tracer gas concentration at the inflow end of each aerospace heat pipe segment.

5. The aerospace heat pipe intelligent leak detection system according to claim 3, characterized in that: The specific method for determining whether there is a leakage area in each aerospace heat pipe segment is: Based on the temperature and absolute concentration difference of the standard aerospace heat pipe and the preset error standard, the temperature confidence factor interval and the absolute concentration difference interval are set. When either the temperature confidence factor or the absolute concentration difference of a certain aerospace heat pipe section exceeds the corresponding set interval, there is a leakage area in the corresponding aerospace heat pipe section. Otherwise, there is no leakage area in the corresponding aerospace heat pipe section.

6. The aerospace heat pipe intelligent leak detection system according to claim 1, characterized in that: The specific contents of the heat pipe flaw detection and analysis module include: The ultrasonic detection results of each aerospace heat pipe segment are retrieved, and the maximum length and depth of each crack and the deformation volume of each aerospace heat pipe segment are extracted from the ultrasonic detection results. A linear weight analysis is performed based on the maximum length and depth of each crack to generate the crack impact degree. The maximum length and depth corresponding to the maximum crack impact degree are selected as the crack representative data. The crack representative data of each aerospace heat pipe segment and the deformation volume of the corresponding aerospace heat pipe segment are fused and analyzed to generate the ultrasonic flaw detection coefficient of each aerospace heat pipe segment; Extract the thermal fluid flow rate of each aerospace heat pipe segment, combine the thermal fluid flow rate of each aerospace heat pipe segment and the type of the corresponding aerospace heat pipe segment to generate the local head loss, combine the local head loss, placement status and thermal fluid density of each aerospace heat pipe segment to generate the theoretical value of the pressure difference between the two ends of each aerospace heat pipe segment, obtain the pressure at both ends of each aerospace heat pipe segment at the same time, perform difference analysis to obtain the actual value of the pressure difference between the two ends of each aerospace heat pipe, perform ratio analysis on the actual value of the pressure difference between the two ends with the theoretical value of the pressure difference between the two ends, and perform normalization on the comparison value to obtain the thermal fluid pressure difference coefficient of each aerospace heat pipe segment; The ultrasonic flaw detection coefficient and thermal fluid pressure difference coefficient of each aerospace heat pipe section are extracted, and the hazard index is obtained by multiplying the ultrasonic flaw detection coefficient and the thermal fluid pressure difference coefficient of each aerospace heat pipe section.

7. The aerospace heat pipe intelligent leak detection system according to claim 6, characterized in that: The ultrasonic flaw detection coefficient is obtained as follows: The length, maximum depth and deformation volume of the representative crack data of each aerospace heat pipe section are analyzed by ratio with the preset critical value. The ratios are assigned different weights for weighted accumulation and normalized to generate ultrasonic flaw detection coefficients.

8. The aerospace heat pipe intelligent leak detection system according to claim 6, characterized in that: The theoretical value of the pressure difference between the two ends of each aerospace heat pipe segment is obtained as follows: Based on the placement status of each aerospace heat pipe segment, the height difference between the inflow end and the outflow end of the corresponding aerospace heat pipe segment is obtained, and the height difference between the two ends is combined with the thermal fluid density and gravity acceleration to generate the height pressure difference; Obtain the bending angle and curvature radius ratio of each aerospace heat pipe segment to evaluate the local resistance coefficient of the corresponding aerospace heat pipe segment. Combine the local resistance coefficient with the thermal fluid flow rate and gravity acceleration to generate the local head loss. Combine the local head loss with the thermal fluid density and gravity acceleration to generate the resistance pressure difference. The height pressure difference and resistance pressure difference of each aerospace heat pipe section are accumulated to obtain the theoretical value of the pressure difference at both ends of the corresponding aerospace heat pipe section.

9. The aerospace heat pipe intelligent leak detection system according to claim 1, characterized in that: The specific contents of the heat pipe early warning reminder module include: The hazard index of each aerospace heat pipe section is matched with the preset hazard index range of each hazard level to obtain the hazard level of each aerospace heat pipe section, and corresponding level warning reminders are given based on the hazard level.

10. An intelligent leak detection method for aerospace heat pipes, characterized in that: include: S1. Place the aerospace heat pipe to be tested in an aerospace heat pipe test chamber built based on the actual aerospace environment, and introduce a thermal fluid containing tracer gas into the aerospace heat pipe to be tested; S2. Divide the aerospace heat pipe to be inspected into several aerospace heat pipe segments according to their placement status, and collect infrared thermal imaging and tracer gas concentration data of each aerospace heat pipe segment; S3. Obtain a heat pipe temperature distribution map from infrared thermal imaging of each aerospace heat pipe segment, and combine the heat pipe temperature distribution map with tracer gas concentration data to determine whether there is a leakage area in each aerospace heat pipe segment; S4. When no leakage area exists in each aerospace heat pipe segment, ultrasonic wave detection is performed on the aerospace heat pipe segment using an ultrasonic sensor, and the acoustic wave detection results are combined with the thermal fluid pressure change data of the aerospace heat pipe segment to analyze the hazard index of the aerospace heat pipe segment; S5. Alarm the aerospace heat pipe section with leakage area, and issue corresponding level warning reminder according to the danger index of the aerospace heat pipe section.

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