Method and system for monitoring running state of aviation main pump verification test bed

Abstract

The invention relates to the field of aviation main pump detection, in particular to an aviation main pump verification test bed operation state monitoring method and system, and the method comprises the steps: obtaining the oscillation frequency, proportional gain, pressure change sequence and oscillation amplitude change sequence of an aviation main pump; a difference value between a preset target pressure value and a current pressure value is used as an adjusting pressure difference, an adjusting interval is equally divided and arranged according to the pressure adjusting direction, and the length of the pressure adjusting interval is corrected based on an oscillation amplitude change sequence; setting an initial proportional gain according to the length of the adjustment interval, taking the ratio of the number of pressure points in the adjustment interval to the response time of the adjustment interval as a pressure change rate, analyzing a positive or negative adjustment evaluation function according to the oscillation frequency and the pressure change rate, and constructing a proportional gain optimization model; and dynamic monitoring and adjustment of the proportional gain of pressure boosting and reducing of the aviation main pump are completed. According to the method, the accuracy of state monitoring is improved by optimizing adjustment interval division.

Description

Technical Field

[0001] The present invention relates to the field of aviation main pump detection, and more specifically, to a method and system for monitoring the operating status of an aviation main pump verification test bench. Background Art

[0002] The aviation main pump verification test bench is a large-scale ground test equipment used to test and verify the performance of the main pump of an aircraft engine. It is mainly used to verify the performance, reliability and safety of the main pump under various working conditions. The test bench can simulate the working environment of an aircraft engine under different flight conditions, including takeoff, cruise, climb, descent, etc. Through high-precision sensors and measuring equipment, the key performance parameters of the main pump, such as flow, pressure, speed, efficiency, etc., are monitored and accurately measured in real time, providing important guarantees for the safe operation of aircraft engines.

[0003] The existing Chinese patent application document with publication number CN112926656A discloses a method, system and equipment for predicting the state of circulating water pumps in nuclear power plants. Through the circulating water pump operation state monitoring model and the historical normal data in the historical sample data, the dynamic reference threshold interval of the circulating water pump under the historical normal data is obtained by regression calculation using the bootstrap algorithm. The confidence interval and prediction interval of the circulating water pump operation state monitoring model are solved based on the dynamic reference threshold interval. The marked fault data of the circulating water pump test bench are used as the fault reference interval, and the operating parameters of the circulating water pump are collected in real time. The thresholds of the confidence interval, prediction interval and fault reference interval are set to realize the rapid prediction of the monitoring fault of the circulating water pump, which makes up for the problem that the actual engineering accumulation of the power plant is insufficient and the experience warning and slight damage and obvious fault thresholds cannot be given. The data-driven statistical model and the test bench fault data are used, and the residual results are combined to replace the traditional fixed coarse thresholds to intuitively and effectively realize the dynamic monitoring of the circulating water pump.

[0004] This application document adopts data-driven statistical models and test bench fault data, combined with residual results instead of traditional fixed coarse thresholds, to more accurately monitor the operating status of the circulating water pump and effectively improve the accuracy and reliability of fault diagnosis. At present, in the process of increasing and decreasing pressure of the aviation main pump, the traditional fixed proportional gain control method cannot adapt to different working conditions, resulting in too long response time and too high oscillation frequency, affecting the operating efficiency and stability of the main pump. Summary of the invention

[0005] In order to solve the problem that the traditional fixed proportional gain control method cannot adapt to different working conditions, resulting in long response time and high oscillation frequency, which affects the operating efficiency and stability of the main pump, the present invention provides solutions in the following aspects.

[0006] In a first aspect, a method for monitoring the operating status of an aviation main pump verification test bench includes: obtaining information data of the aviation main pump, wherein the information data includes: oscillation frequency, proportional gain, pressure change sequence, and oscillation amplitude change sequence; taking the difference between a preset target pressure value and a current pressure value as a regulating pressure difference, dividing the regulating pressure difference into a plurality of pressure regulating intervals, and arranging them according to the pressure regulation direction, and correcting the length of the pressure regulating interval based on the oscillation amplitude change sequence; setting an initial proportional gain according to the length of the regulating interval, taking the ratio between the number of pressure points contained in each regulating interval and the response time of the regulating interval as the pressure change rate, and using the oscillation frequency and the pressure change rate to divide the pressure difference into a plurality of pressure regulating intervals. Analyze the positive or negative regulation evaluation function, and construct a proportional gain optimization model to complete the dynamic monitoring and adjustment of the proportional gain of the aviation main pump pressure increase and decrease; wherein, the proportional gain optimization model satisfies the following conditions: in response to the proportional gain of the second regulation interval being greater than the proportional gain of the first regulation interval, the proportional gain of the third regulation interval is the average value between the proportional gains of the first and second regulation intervals; in response to the positive regulation evaluation function being greater than or less than the negative regulation evaluation function, the proportional gain of the fourth regulation interval is the average value between the proportional gains of the third and second regulation intervals; if it is equal to, the proportional gain of the fourth regulation interval is the proportional gain of the third interval, and it is iterated in this way until the pressure increase and decrease regulation is completed.

[0007] The effect is that by obtaining the information data of the aviation main pump, including the oscillation frequency, proportional gain, pressure change sequence and oscillation amplitude change sequence, the operating state of the main pump can be more accurately monitored and controlled. By clustering the oscillation amplitude change sequence or using a sliding window to calculate the average oscillation amplitude, the length of the adjustment interval can be effectively corrected. The interval length can be dynamically adjusted according to the actual oscillation situation, so that the control is more adaptable to the real-time changes of the system, thereby improving the stability and response speed of the system; the initial proportional gain is set according to the length of the adjustment interval, and the positive or negative adjustment evaluation function is analyzed using the oscillation frequency and pressure change rate to construct a proportional gain optimization model. It can complete the dynamic monitoring and adjustment of the proportional gain of the aviation main pump pressure increase and decrease, realize the optimization of the main pump performance, reduce the response time and reduce the oscillation frequency, and ultimately improve the operating efficiency and stability of the main pump.

[0008] Preferably, the pressure change sequence is subjected to wavelet transformation, the high-frequency part is extracted as the oscillation frequency, the intermediate frequency and low-frequency parts after the wavelet transformation are reversely transformed to obtain a marked pressure change sequence, and the difference between the pressure change sequence and the marked pressure change sequence is calculated to obtain an oscillation amplitude change sequence.

[0009] The effect is that through wavelet transformation, the high-frequency and low-frequency components in the signal can be effectively separated. The high-frequency part is usually related to the oscillation frequency, while the low-frequency and medium-frequency parts contain the smooth change information of the signal. This separation allows for more accurate extraction and analysis of key features in the pressure change sequence, thereby more accurately monitoring and controlling the operating status of the aviation main pump; by calculating the difference between the pressure change sequence and the marked pressure change sequence, the oscillation amplitude change sequence obtained can reflect the stability of the system during the regulation process. A larger oscillation amplitude may indicate that the system responds too quickly or there are unstable factors, while a smaller oscillation amplitude indicates that the system is running more smoothly. This helps to promptly discover and adjust problems that may affect the stability of the system.

[0010] Preferably, the method of correcting the pressure adjustment interval length based on the oscillation amplitude change sequence includes: The oscillation amplitude change sequence is clustered to obtain multiple clusters, all clusters are arranged according to the sequential labels, and the number of samples in each cluster is used as the number of pressure points in the new adjustment range.

[0011] The effect is that by clustering the oscillation amplitude change sequence, multiple clusters can be obtained, and the number of samples in each cluster reflects the similarity of pressure changes in the interval. Using these sample numbers as the number of pressure points in the new adjustment interval, the adjustment interval can be divided more reasonably, and all clusters are arranged according to the sequential labels to ensure the continuity and logic of the adjustment interval. It helps to identify and deal with unstable factors in the system, such as excessive pressure oscillations, thereby improving the stability of the entire system.

[0012] Preferably, the method of correcting the pressure adjustment interval length based on the oscillation amplitude change sequence further includes: The sliding window size is preset according to the oscillation amplitude change sequence, and any sample point is used as the starting point of the preset window to calculate the average oscillation amplitude in each sliding window; In response to the average oscillation amplitude being greater than a preset threshold, the position of the starting point corresponding to the preset window is used as the boundary of the adjustment area, and a plurality of adjustment intervals are divided according to the boundary.

[0013] The effect is that by using a sliding window to calculate the average oscillation amplitude, the adjustment interval can be dynamically divided according to the actual changes in the oscillation amplitude. It can adapt to the local characteristics of pressure changes and respond more flexibly to various changes that may occur in the system; when the average oscillation amplitude in the sliding window exceeds the preset threshold, the starting point of the window is used as the boundary of the adjustment area, which helps to identify areas in the system where the oscillation is more severe. This allows the control system to control these areas more accurately, thereby improving the overall control accuracy.

[0014] Preferably, the setting of the initial proportional gain includes: The proportional gain of the first adjustment interval is set to the minimum value in the value range, and the proportional gain of the second adjustment interval is set to the maximum value in the value range, wherein the value range of the proportional gain depends on the design and specifications of the control system.

[0015] The effect is: by setting the minimum and maximum proportional gains, it can be ensured that the control system can cover the entire possible operating range, so that effective control can be performed under different working conditions. After determining the extreme values ​​of the proportional gain, the proportional gain of the subsequent adjustment interval can be dynamically adjusted according to the system response to optimize the control effect.

[0016] Preferably, the setting of the initial proportional gain further includes: Select a smaller initial proportional gain for the adjustment interval, set the step disturbance value, obtain the curve after the step disturbance, and in response to the rapid decay of the curve, reduce the proportional gain, otherwise increase the proportional gain, iterate until the attenuation oscillation process of the preset proportion appears, determine the proportional gain and oscillation period, and then set the initial proportional gain.

[0017] The effect is that the proportional gain can be adjusted accurately by setting the step disturbance value and observing the response curve of the system. This method allows starting from a smaller initial proportional gain and gradually iterating to the optimal value, thereby avoiding the impact of too large or too small proportional gain on system stability. By adjusting the proportional gain to control the decay rate of the response curve, the dynamic response of the system can be optimized. If the response is too fast and causes oscillation, reduce the proportional gain to slow down the response speed; if the response is too slow, increase the proportional gain to speed up the response.

[0018] Preferably, the positive or negative adjustment evaluation function satisfies the following relationship: ; In the formula, Represents a positive regulation evaluation index, Indicates a negative adjustment evaluation index, Indicates Adjust the oscillation frequency of the interval, Indicates Adjust the oscillation frequency of the interval, Indicates Adjust the oscillation frequency of the interval, Indicates The pressure change rate in the adjustment range, Indicates The pressure change rate in the adjustment range, Indicates The rate of change of pressure in the regulation range.

[0019] In a second aspect, an aviation main pump verification test bench operation status monitoring system includes: a processor and a memory, wherein the memory stores computer program instructions, and when the computer program instructions are executed by the processor, the above-mentioned aviation main pump verification test bench operation status monitoring method is implemented.

[0020] The present invention has the following effects: 1. The present invention adapts to different working conditions by dynamically monitoring and adjusting the proportional gain. It can significantly improve the adaptability of the aviation main pump control system and solve the problem that the traditional fixed proportional gain control method may not provide the best control effect when facing different working conditions. By analyzing the oscillation frequency and pressure change rate in real time and dynamically adjusting the proportional gain, it ensures that the system can maintain the best performance under various working conditions.

[0021] 2. The present invention can accurately set the proportional gain of each adjustment interval by constructing a proportional gain optimization model, effectively reducing the response time of the system and reducing the oscillation frequency. It is very important to improve the operating efficiency and stability of the main pump, reduce the additional energy consumption and mechanical stress caused by pressure oscillation, thereby extending the service life of the equipment and improving the reliability of operation.

[0022] 3. The present invention extracts the oscillation frequency and oscillation amplitude change sequence through wavelet change, and dynamically corrects the adjustment interval length based on these data, which is conducive to realizing accurate control of the pressure increase and decrease process of the aviation main pump. In addition, by determining the initial proportional gain through an iterative process, the method can also optimize the overall performance of the control system, ensure the smooth operation of the main pump during the pressure increase and decrease process, and reduce the risk of system failure caused by improper control. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] By reading the following detailed description with reference to the accompanying drawings, the above and other objects, features and advantages of the exemplary embodiments of the present invention will become readily understood. In the accompanying drawings, several embodiments of the present invention are shown in an exemplary and non-limiting manner, and the same or corresponding reference numerals represent the same or corresponding parts, wherein: Figure 1 It is a method flow chart of steps S1 to S3 in a method for monitoring the operating status of an aviation main pump verification test bench according to an embodiment of the present invention.

[0024] Figure 2 It is a schematic diagram of dividing adjustment intervals in a method for monitoring the operating status of an aviation main pump verification test bench according to an embodiment of the present invention.

[0025] Figure 3 It is a schematic diagram of pressure changes in a method for monitoring the operating status of an aviation main pump verification test bench according to an embodiment of the present invention.

[0026] Figure 4The present invention is a structural block diagram of an aviation main pump verification test bench operation status monitoring system according to an embodiment of the present invention. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0028] The specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0029] Reference Figure 1 A method for monitoring the operating status of an aviation main pump verification test bench includes steps S1 to S3, which are specifically as follows: It should be noted that proportional gain is an important parameter in the control system of the test bench, which is mainly used to adjust the relationship between input and output in the control system. In the aviation main pump verification test bench, proportional gain can be used to adjust the control parameters of the main pump, such as flow, pressure, etc. By setting the proportional gain reasonably, the control system of the test bench can respond more stably and quickly to the changes in the operating status of the main pump, ensuring that various parameters can accurately track the set values ​​during the test, thereby improving the accuracy and reliability of the test. For example, when controlling the flow of the main pump, the proportional gain can adjust the control signal according to a certain proportion based on the deviation between the actual flow and the set flow, so as to achieve precise regulation of the flow.

[0030] The proportional gain can be used as the sensitivity of the aviation main pump when adjusting the internal pressure. At present, in the field of automatic control of aviation main pumps, a fixed proportional gain is usually used, and the proportional gain exhibits different regulation effects under different atmospheric pressures.

[0031] S1: Acquire information data of an aviation main pump, wherein the information data includes: oscillation frequency, proportional gain, pressure change sequence, and oscillation amplitude change sequence.

[0032] In this embodiment, the pressure sensor is used to collect the pressure change sequence inside the aviation main pump. , read the proportional gain of the aviation main pump through the PLC controller terminal , according to the data collection rate of 100 times per second, the implementers can make adjustments according to the specific situation.

[0033] Perform wavelet transformation on the pressure change sequence and extract the high-frequency part as the oscillation frequency , reversely change the intermediate frequency and low frequency parts after wavelet transformation to obtain the marked pressure change sequence , calculate the difference between the pressure change sequence and the marked pressure change sequence , and get the oscillation amplitude change sequence .

[0034] S2: Taking the difference between the preset target pressure value and the current pressure value as the adjustment pressure difference, dividing the adjustment pressure difference into multiple pressure adjustment intervals, arranging them according to the pressure adjustment direction, and correcting the length of the pressure adjustment interval based on the oscillation amplitude change sequence.

[0035] In this embodiment, the preset target pressure value is exemplarily: 4000psi, which can be adjusted according to the specifications of the aviation main pump design and the pressure value required by the mission to be performed. The number of pressure adjustment intervals is 10, and the implementer can adjust it according to the specific situation. For details, refer to Figure 2 The starting point on the left side of the figure indicates the current pressure value of the aviation main pump. The arrow on the right side of the figure points to the target pressure value of the adjustment, which indicates the final goal of the adjustment process. The difference between the current pressure value and the target pressure value is defined as the adjustment pressure difference. , the first section between the current pressure value and the target pressure value in the figure is marked as the first adjustment range, indicating the first stage of the adjustment process. The arrow in the figure indicates the direction of pressure adjustment, that is, increasing from the current pressure value to the target pressure value.

[0036] It should be noted that when the second step-up / down voltage regulation is performed, the oscillation amplitude change sequence based on the first step-up / down voltage regulation is , correct the adjustment interval. Since the adjustment interval length is composed of pressure points, each pressure point corresponds to an oscillation amplitude point, so changing the number of oscillation amplitude points in the adjustment interval is equivalent to changing the adjustment interval length.

[0037] The length of the pressure adjustment interval is corrected based on the oscillation amplitude change sequence, including: The oscillation amplitude change sequence is clustered to obtain multiple clusters, all clusters are arranged according to the sequential labels, and the number of samples in each cluster is used as the number of pressure points in the new adjustment range.

[0038] In this embodiment, the DBSCAN clustering method is used for clustering, where the neighborhood distance threshold is set to 2, the neighborhood sample number threshold is set to 50, the nearest neighbor distance metric parameter is the Euclidean distance, and the output is clusters, and the difference within each cluster is greater than , the sample data in each cluster is a sequence of oscillation amplitude changes A subset of , which can be adjusted by the implementer according to the specific situation; if there are isolated sample points in the DBSCAN clustering process, each isolated sample point will be merged into the cluster where the sample point with the smallest distance measurement parameter is located.

[0039] In addition, in another embodiment, by presetting the sliding window size according to the oscillation amplitude change sequence, taking any sample point as the starting point of the preset window, the average oscillation amplitude in each sliding window is calculated; In response to the average oscillation amplitude being greater than a preset threshold, the position of the starting point corresponding to the preset window is used as the boundary of the adjustment area, and a plurality of adjustment intervals are divided according to the boundary.

[0040] Specifically, the average oscillation amplitude satisfies the following relationship: ; In the formula, Indicates the first The average oscillation amplitude of the preset window corresponding to the sample points, Indicates the size of the preset window. Indicates the first Sample points.

[0041] In this embodiment, the preset window size is 5, which can be adjusted according to specific circumstances. In this embodiment, the average oscillation amplitude is greater than the preset threshold, where the preset threshold is the set pressure value. , the pressure value of the aircraft engine main pump needs to meet the following requirements: 1. Engine design parameters: The design of the engine will determine the pressure range required by the main pump; 2. Flight conditions: Different flight conditions (such as takeoff, climb, cruise) may require different pressure settings; 3. Environmental factors: Environmental factors such as temperature and atmospheric pressure will also affect the set pressure value; The turbo pumps of some commercial aircraft engines may have a higher pressure setting value during takeoff and a relatively lower pressure setting value during cruise. The specific values ​​need to refer to the data and guidance provided by the engine manufacturer.

[0042] It should also be noted that the proportional gain is the sensitivity of adjusting the internal pressure in the aviation main pump PID system. The oscillation frequency and response time of the pressure are directly affected by the proportional gain. The larger the proportional gain, the higher the vibration frequency of the pressure, the more violent the oscillation, but the shorter the response time to the corresponding pressure value. Conversely, the smaller the proportional gain, the lower the vibration frequency of the pressure, the gentler the oscillation, but the longer the response time to the corresponding pressure value. Therefore, it is necessary to find a suitable proportional gain so that the response time and the vibration frequency of the pressure are at a lower level. The response time is the time required to complete a pressure increase or decrease.

[0043] S3: Set the initial proportional gain according to the length of the adjustment interval, take the ratio of the number of pressure points contained in each adjustment interval to the response time of the adjustment interval as the pressure change rate, and use it to analyze the positive or negative adjustment evaluation function based on the oscillation frequency and pressure change rate, and build a proportional gain optimization model to complete the dynamic monitoring and adjustment of the proportional gain of the aviation main pump pressure increase and decrease.

[0044] Embodiment 1: Setting the initial proportional gain includes: Reference Figure 3 The dotted line above the figure indicates the preset target pressure value, which is the final goal of the pressure regulation process. The figure shows six regulation intervals (1st regulation interval to 6th regulation interval), each of which represents a stage in the pressure regulation process. The pressure change in each regulation interval is represented by a step-shaped dotted line, showing the gradual change of pressure in each stage. The arrow in the figure indicates the direction of pressure regulation, that is, gradually increasing from the current pressure value to the target pressure value. Several time points are marked in the figure ,These time points correspond to the start or end time of each regulation interval, showing the key time nodes in the pressure regulation process.

[0045] The proportional gain of the first adjustment interval is set to the minimum value in the value range, and the proportional gain of the second adjustment interval is set to the maximum value in the value range, wherein the value range of the proportional gain depends on the design and specifications of the control system.

[0046] That is to say, by setting the minimum and maximum values, the entire value range of the proportional gain can be quickly covered, which is convenient for subsequent dynamic adjustment and suitable for proportional gain adjustment under different working conditions. The appropriate proportional gain range can be quickly found. However, since the initial proportional gain is set at an extreme value, the initial response of the system may be too fast or too slow, requiring more adjustments to reach the optimal state. This method lacks fine adjustment of the proportional gain in the initial stage, and more iterations may be required to optimize the proportional gain.

[0047] Embodiment 2: Setting the initial proportional gain also includes: Select a smaller initial proportional gain for the adjustment interval, set the step disturbance value, obtain the curve after the step disturbance, and in response to the rapid decay of the curve, reduce the proportional gain, otherwise increase the proportional gain, iterate until the attenuation oscillation process of the preset proportion appears, determine the proportional gain and oscillation period, and then set the initial proportional gain.

[0048] It should be noted that the value range of the proportional gain is determined according to the design and specifications of the control system. Selecting a smaller initial proportional gain means: selecting the value at the 30% position of the value range as the smaller initial proportional gain. That is to say, if the value range is from arrive , then the initial proportional gain Satisfies the following relationship: ; In the formula, represents the initial proportional gain, Indicates the minimum proportional gain within the value range, Indicates the maximum proportional gain within the value range.

[0049] Exemplarily, the proportional gain value range is determined according to the control system, wherein the minimum proportional gain , maximum proportional gain , , , choosing the 30% position proportional gain as the starting point of the initial proportional gain is an empirical value and can be adjusted according to specific circumstances.

[0050] In this embodiment, the initial proportional gain is set by a step disturbance method, wherein the step disturbance is a common technique in the field of control theory and signal processing, and is usually used to test and analyze the dynamic response characteristics of a system. It is a well-known technique in the art and will not be described in detail.

[0051] That is to say, by gradually adjusting the proportional gain, the appropriate initial proportional gain can be found more precisely and the response performance of the system can be optimized. The proportional gain can be dynamically adjusted according to the actual response curve of the system after a step disturbance, which can better adapt to the dynamic characteristics of the system. Through the preset attenuation oscillation process, the appropriate proportional gain can be found more quickly and the number of iterations required for adjustment can be reduced.

[0052] The implementer may select an implementation method according to the specific situation. Example 1 is suitable for scenarios where the proportional gain value range needs to be quickly covered. The operation is simple, but the initial response may not be ideal and more adjustments are required. Example 2 is suitable for scenarios where fine adjustment of the proportional gain is required. Dynamic adjustment can better adapt to the dynamic characteristics of the system and reduce the number of iterations, but the operation is relatively complex and the time cost is high.

[0053] It should be noted that the preset ratio is 4:1, and implementers can adjust it according to specific circumstances.

[0054] The positive or negative adjustment evaluation function satisfies the following relationship: ; In the formula, Represents a positive regulation evaluation index, Indicates a negative adjustment evaluation index, Indicates Adjust the oscillation frequency of the interval, Indicates Adjust the oscillation frequency of the interval, Indicates Adjust the oscillation frequency of the interval, Indicates The pressure change rate in the adjustment range, Indicates The pressure change rate in the adjustment range, Indicates The rate of change of pressure in the regulation range.

[0055] That is to say, Indicates the adjustment evaluation index, which expresses the effect of two adjacent proportional gains. This effect expresses the quality of the gain adjustment effect from the two perspectives of pressure oscillation frequency and pressure change rate; responds to the positive adjustment evaluation index Less than negative regulation evaluation index , indicating that the proportional gain needs to be reduced, otherwise, the proportional gain needs to be increased.

[0056] Among them, the proportional gain optimization model meets the following conditions: In response to the proportional gain of the second adjustment interval being greater than the proportional gain of the first adjustment interval, the proportional gain of the third adjustment interval is the average value between the proportional gains of the first and second adjustment intervals; in response to the positive adjustment evaluation function being greater than or less than the negative adjustment evaluation function, the proportional gain of the fourth adjustment interval is the average value between the proportional gains of the third and second adjustment intervals; if it is equal to, then the proportional gain of the fourth adjustment interval is the proportional gain of the third interval, and this iteration is repeated until the boost / boost adjustment is completed.

[0057] At this point, starting from the current pressure point and ending at the pressure target point, the proportional gain is adjusted several times for the adjustment range, realizing the dynamic adjustment of the proportional gain during the pressure increase and decrease of the aviation main pump, which can effectively reduce the response time and the pressure oscillation frequency.

[0058] The present invention also provides an aviation main pump verification test bench operation status monitoring system. Figure 4 As shown, the system includes a processor and a memory, the memory stores computer program instructions, and when the computer program instructions are executed by the processor, a method for monitoring the operating status of an aviation main pump verification test bench according to the first aspect of the present invention is implemented.

[0059] The system also includes other components familiar to those skilled in the art, such as a communication bus and a communication interface. The configuration and functions of these components are known in the art and will not be described in detail here.

[0060] In the present invention, the aforementioned memory may be any tangible medium containing or storing a program, which may be used by or in combination with an instruction execution system, apparatus or device. For example, a computer-readable storage medium may be any appropriate magnetic storage medium or magneto-optical storage medium, such as a resistive random access memory RRAM (Resistive Random Access Memory), a dynamic random access memory DRAM (Dynamic Random Access Memory), a static random access memory SRAM (Static Random-Access Memory), an enhanced dynamic random access memory EDRAM (Enhanced Dynamic Random Access Memory), a high-bandwidth memory HBM (High-Bandwidth Memory), a hybrid memory cube HMC (Hybrid Memory Cube), etc., or any other medium that can be used to store the required information and can be accessed by an application, a module, or both. Any such computer storage medium may be part of a device or accessible or connectable to a device. Any application or module described in the present invention may be implemented by computer-readable / executable instructions stored or otherwise maintained by such a computer-readable medium.

[0061] In the description of this specification, "plurality" or "several" means at least two, such as two, three or more, etc., unless otherwise clearly and specifically defined.

[0062] Although this specification has shown and described a number of embodiments of the present invention, it will be apparent to those skilled in the art that such embodiments are provided by way of example only. Those skilled in the art will conceive of many modifications, changes and alternatives without departing from the ideas and spirit of the present invention. It should be understood that in the practice of the present invention, various alternatives to the embodiments of the present invention described herein may be employed.

Claims

1. A method for monitoring the operating status of an aviation main pump verification test bench, characterized in that: include: Acquire information data of the aviation main pump, wherein the information data includes: oscillation frequency, proportional gain, pressure change sequence, and oscillation amplitude change sequence; The difference between the preset target pressure value and the current pressure value is used as the adjustment pressure difference, the adjustment pressure difference is equally divided into a plurality of pressure adjustment intervals, and the pressure adjustment intervals are arranged according to the pressure adjustment direction, and the length of the pressure adjustment interval is corrected based on the oscillation amplitude change sequence; The initial proportional gain is set according to the length of the adjustment interval, and the ratio between the number of pressure points contained in each adjustment interval and the response time of the adjustment interval is used as the pressure change rate. According to the oscillation frequency and the pressure change rate, it is used to analyze the positive or negative adjustment evaluation function, and to build a proportional gain optimization model to complete the dynamic monitoring and adjustment of the proportional gain of the aviation main pump pressure increase and decrease; Among them, the proportional gain optimization model satisfies the following conditions: in response to the proportional gain of the second adjustment interval being greater than the proportional gain of the first adjustment interval, the proportional gain of the third adjustment interval is the average value between the proportional gains of the first and second adjustment intervals; in response to the positive adjustment evaluation function being greater than or less than the negative adjustment evaluation function, the proportional gain of the fourth adjustment interval is the average value between the proportional gains of the third and second adjustment intervals; if , then the proportional gain of the fourth adjustment interval is the proportional gain of the third interval, and this iteration is carried out until the current step-up and step-down adjustment is completed.

2. The method for monitoring the operating status of an aviation main pump verification test bench according to claim 1, characterized in that: in, The pressure change sequence is subjected to wavelet transformation, and the high-frequency part is extracted as the oscillation frequency. The intermediate frequency and low-frequency parts after the wavelet transformation are reversely transformed to obtain the marked pressure change sequence. The difference between the pressure change sequence and the marked pressure change sequence is calculated to obtain the oscillation amplitude change sequence.

3. The method for monitoring the operating status of an aviation main pump verification test bench according to claim 1, characterized in that: The method of correcting the pressure adjustment interval length based on the oscillation amplitude change sequence includes: The oscillation amplitude change sequence is clustered to obtain multiple clusters, all clusters are arranged according to the sequential labels, and the number of samples in each cluster is used as the number of pressure points in the new adjustment range.

4. The method for monitoring the operating status of an aviation main pump verification test bench according to claim 1, characterized in that: The method of correcting the pressure adjustment interval length based on the oscillation amplitude change sequence also includes: The sliding window size is preset according to the oscillation amplitude change sequence, and any sample point is used as the starting point of the preset window to calculate the average oscillation amplitude in each sliding window; In response to the average oscillation amplitude being greater than a preset threshold, the position of the starting point corresponding to the preset window is used as the boundary of the adjustment area, and a plurality of adjustment intervals are divided according to the boundary.

5. The method for monitoring the operating status of an aviation main pump verification test bench according to claim 1, characterized in that: The setting of the initial proportional gain comprises: The proportional gain of the first adjustment interval is set to the minimum value in the value range, and the proportional gain of the second adjustment interval is set to the maximum value in the value range, wherein the value range of the proportional gain depends on the design and specifications of the control system.

6. The method for monitoring the operating status of an aviation main pump verification test bench according to claim 1, characterized in that: The setting of the initial proportional gain further includes: Select a smaller initial proportional gain for the adjustment interval, set the step disturbance value, obtain the curve after the step disturbance, and in response to the rapid decay of the curve, reduce the proportional gain, otherwise increase the proportional gain, iterate until the attenuation oscillation process of the preset proportion appears, determine the proportional gain and oscillation period, and then set the initial proportional gain.

7. The method for monitoring the operating status of an aviation main pump verification test bench according to claim 1, characterized in that: The positive or negative adjustment evaluation function satisfies the following relationship: ； In the formula, Represents a positive regulation evaluation index, Indicates a negative adjustment evaluation index, Indicates Adjust the oscillation frequency of the interval, Indicates Adjust the oscillation frequency of the interval, Indicates Adjust the oscillation frequency of the interval, Indicates The pressure change rate in the adjustment range, Indicates The pressure change rate in the adjustment range, Indicates The rate of change of pressure in the regulation range.

8. An aviation main pump verification test bench operation status monitoring system, characterized in that: include: A processor and a memory, wherein the memory stores computer program instructions, and when the computer program instructions are executed by the processor, the method for monitoring the operating status of an aviation main pump verification test bench according to any one of claims 1 to 7 is implemented.

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