A Monitoring Method and System for the Operating State of an Aircraft Main Pump Verification Test Bench

Abstract

The present invention relates to the field of aviation main pump detection. More specifically, the present invention relates to a method and system for monitoring the operating state of an aviation main pump verification test bench. The method includes: obtaining the oscillation frequency, proportional gain, pressure change sequence, and oscillation amplitude change sequence of the aviation main pump; taking the difference between the preset target pressure value and the current pressure value as the adjustment pressure difference, equally dividing the adjustment interval, and arranging it according to the adjustment direction of the pressure, and correcting the length of the pressure adjustment interval based on the oscillation amplitude change sequence; setting the initial proportional gain according to the length of the adjustment interval, taking the ratio between the number of pressure points in the adjustment interval and the response time of the adjustment interval as the pressure change rate, analyzing the positive or negative adjustment evaluation function according to the oscillation frequency and the pressure change rate, and constructing a proportional gain optimization model to complete the dynamic monitoring and adjustment of the proportional gain of the aviation main pump for pressure increase and decrease. The present invention improves the accuracy of state monitoring by optimizing the division of the adjustment interval.

Description

Technical Field

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

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

[0003] The existing Chinese patent application document with the publication number CN112926656A discloses a method, system, and equipment for predicting the state of a circulating water pump in a nuclear power plant. Through a circulating water pump operating state monitoring model and historical normal data in historical sample data, a dynamic reference threshold interval of the circulating water pump under historical normal data is obtained by regression calculation using the bootstrap algorithm. Based on the dynamic reference threshold interval, a confidence interval and a prediction interval of the circulating water pump operating state monitoring model are obtained; the marked fault data of the circulating water pump test bench is used as a fault reference interval, the operating parameters of the circulating water pump are collected in real time, and the rapid prediction of the circulating water pump monitoring fault is realized based on the set thresholds of the confidence interval, prediction interval, and fault reference interval, making up for the lack of actual engineering accumulation in the power plant and being unable to give empirical early warning and the problems of thresholds for slight damage and obvious faults. Using a data-driven statistical model and test bench fault data, combined with the residual result to replace the traditional fixed coarse threshold, the dynamic monitoring of the circulating water pump is intuitively and effectively realized.

[0004] By adopting a data-driven statistical model and test bench fault data, combined with the residual result to replace the traditional fixed coarse threshold, this application document can more accurately monitor the operating state of the circulating water pump, effectively improving the accuracy and reliability of fault diagnosis. Currently, during the pressure increase and decrease process of the aviation main pump, due to the control method of traditional fixed proportional gain being unable to adapt to different working conditions, the response time is too long and the oscillation frequency is too high, affecting the operating efficiency and stability of the main pump. Summary of the Invention

[0005] To solve the problem that the control method of traditional fixed proportional gain 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, the present invention provides solutions in the following aspects.

[0006] In a first aspect, a method for monitoring the operating state of an aviation main pump verification test bench includes: obtaining information data of the aviation main pump, where 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 the current pressure value as the adjustment pressure difference, equally dividing the adjustment pressure difference into multiple pressure adjustment intervals, arranging them in the adjustment direction of the pressure, and correcting the length of the pressure adjustment interval based on the oscillation amplitude change sequence; setting an initial proportional gain according to the length of the adjustment interval, taking the ratio between the number of pressure points included in each adjustment interval and the response time of the adjustment interval as the pressure change rate, and based on the oscillation frequency and the pressure change rate, analyzing a positive or negative adjustment evaluation function, and constructing a proportional gain optimization model to complete the dynamic monitoring and adjustment of the proportional gain of the aviation main pump for pressure increase and decrease; where 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 they are equal, the proportional gain of the fourth adjustment interval is the proportional gain of the third interval, and so on iteratively until the pressure increase and decrease adjustment for this time is completed.

[0007] The effect is that: by obtaining the information data of the aviation main pump, including oscillation frequency, proportional gain, pressure change sequence, and oscillation amplitude change sequence, the operating state of the main pump can be monitored and controlled more precisely. 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, making the control more adaptable to the real-time changes of the system, thereby improving the stability and response speed of the system; setting an initial proportional gain according to the length of the adjustment interval, and using the oscillation frequency and the pressure change rate to analyze a positive or negative adjustment evaluation function, and constructing a proportional gain optimization model. The dynamic monitoring and adjustment of the proportional gain of the aviation main pump for pressure increase and decrease can be completed, the performance of the main pump can be optimized, the response time can be reduced, and the oscillation frequency can be lowered, ultimately improving the operating efficiency and stability of the main pump.

[0008] Preferably, perform wavelet transform on the pressure change sequence, extract the high-frequency part as the oscillation frequency, perform inverse transform on the middle-frequency and low-frequency parts after wavelet transform to obtain a marked pressure change sequence, and calculate the difference between the pressure change sequence and the marked pressure change sequence to obtain the oscillation amplitude change sequence.

[0009] The effects are as follows: Through wavelet transform, 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 precise extraction and analysis of the key features in the pressure change sequence, thus more accurately monitoring and controlling the operating state of the aviation main pump; By calculating the difference between the pressure change sequence and the marked pressure change sequence, the obtained oscillation amplitude change sequence can reflect the stability of the system during the adjustment 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 operating relatively smoothly. This helps to promptly detect and adjust problems that may affect the system stability.

[0010] Preferably, the modifying the length of the pressure adjustment interval based on the oscillation amplitude change sequence includes:

[0011] Clustering the oscillation amplitude change sequence to obtain multiple clustering clusters, arranging all the clustering clusters according to the sequential labels, and taking the number of samples in each clustering cluster as the number of pressure points within the newly adjusted interval.

[0012] The effects are as follows: By clustering the oscillation amplitude change sequence, multiple clustering clusters can be obtained. The number of samples in each clustering cluster reflects the similarity of the pressure changes within that interval. Taking these numbers of samples as the number of pressure points within the new adjustment interval can more reasonably divide the adjustment interval. Arranging all the clustering clusters according to the sequential labels ensures the continuity and logic of the adjustment interval. It helps to identify and handle unstable factors in the system, such as excessive pressure oscillations, thereby improving the stability of the entire system.

[0013] Preferably, the modifying the length of the pressure adjustment interval based on the oscillation amplitude change sequence further includes:

[0014] Presetting the sliding window size according to the oscillation amplitude change sequence, taking any sample point as the starting point of the preset window, and calculating the average oscillation amplitude within each sliding window;

[0015] In response to the average oscillation amplitude being greater than the preset threshold, the position of the starting point corresponding to the preset window is taken as the boundary of the adjustment region, and multiple adjustment intervals are divided according to the boundary.

[0016] The effects are as follows: By using a sliding window to calculate the average oscillation amplitude, the adjustment interval can be dynamically divided according to the actual change of the oscillation amplitude. It can adapt to the local characteristics of the pressure change and more flexibly respond to various changes that may occur in the system; When the average oscillation amplitude within the sliding window exceeds the preset threshold, taking the starting point of the window as the boundary of the adjustment region helps to identify the regions in the system where the oscillations are relatively intense. This enables the control system to more precisely control these regions, thereby improving the overall control accuracy.

[0017] Preferably, the setting of the initial proportional gain includes:

[0018] Set the proportional gain of the first adjustment interval to the minimum value in the value range, and set the proportional gain of the second adjustment interval to the maximum value in the value range, where the value range of the proportional gain depends on the design and specifications of the control system.

[0019] The effect is that 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 carried out 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 response of the system to optimize the control effect.

[0020] Preferably, the setting of the initial proportional gain further includes:

[0021] Select a relatively small initial proportional gain for the adjustment interval, set a step disturbance value, obtain the curve after the step disturbance, and in response to the rapid decay of the curve, the proportional gain needs to be reduced, otherwise it needs to be increased, and iterate until a preset proportion of the decay oscillation process appears, determine the proportional gain and the oscillation period, so as to set the initial proportional gain.

[0022] The effect is that by setting the step disturbance value and observing the response curve of the system, the proportional gain can be accurately adjusted. This method allows starting from a relatively small initial proportional gain and gradually iterating to the optimal value, thus avoiding the influence of too large or too small proportional gain on the 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 resulting in 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.

[0023] Preferably, the positive or negative adjustment evaluation function satisfies the following relational expression:

[0024] ;

[0025] In the formula, represents the positive adjustment evaluation index, represents the negative adjustment evaluation index, represents the oscillation frequency of the th adjustment interval, represents the oscillation frequency of the th adjustment interval, represents the oscillation frequency of the th adjustment interval, The pressure change rate of the adjustment interval indicating the pressure change rate of the adjustment interval.

[0026] In a second aspect, a monitoring system for the operating state of an aviation main pump verification test bench includes: a processor and a memory. The memory stores computer program instructions, and when the computer program instructions are executed by the processor, the above-mentioned monitoring method for the operating state of the aviation main pump verification test bench is implemented.

[0027] The present invention has the following effects:

[0028] 1. By dynamically monitoring and adjusting the proportional gain to adapt to different working conditions, the present invention can significantly improve the adaptability of the aviation main pump control system, solve the problem that the traditional fixed proportional gain control method may not provide the optimal control effect when facing different working conditions, and dynamically adjust the proportional gain by real-time analyzing the oscillation frequency and pressure change rate, so as to ensure that the system can maintain the best performance under various working conditions.

[0029] 2. By constructing an optimization model for proportional gain, the present invention can accurately set the proportional gain of each adjustment interval, effectively reduce the response time of the system, and reduce the oscillation frequency. It is crucial for improving the operating efficiency and stability of the main pump, reducing the additional energy consumption and mechanical stress caused by pressure oscillation, thereby prolonging the service life of the equipment and improving the operating reliability.

[0030] 3. By extracting the oscillation frequency and the oscillation amplitude change sequence through wavelet transform, and dynamically correcting the adjustment interval length based on these data, the present invention is beneficial to realizing the precise control of the pressure rise and fall process of the aviation main pump. In addition, by determining the initial proportional gain through an iterative process, this method can also optimize the overall performance of the control system, ensure the stable operation of the main pump during the pressure rise and fall process, and reduce the risk of system failures caused by improper control. Description of the Drawings

[0031] 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 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:

[0032] Figure 1 is the flowchart of the method from step S1 to step S3 in a monitoring method for the operating state of an aviation main pump verification test bench according to an embodiment of the present invention.

[0033] Figure 2 is a schematic diagram of dividing the adjustment interval in a monitoring method for the operating state of an aviation main pump verification test bench according to an embodiment of the present invention.

[0034] Figure 3 It is a schematic diagram of the pressure change in a method for monitoring the operating state of an aviation main pump verification test bench according to an embodiment of the present invention.

[0035] Figure 4 It is a structural block diagram of a system for monitoring the operating state of an aviation main pump verification test bench according to an embodiment of the present invention. Detailed implementation manners

[0036] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts belong to the scope of protection of the present invention.

[0037] Next, the specific implementation manners of the present invention will be described in detail in conjunction with the accompanying drawings.

[0038] Refer to Figure 1 , a method for monitoring the operating state of an aviation main pump verification test bench includes steps S1 - S3, specifically as follows:

[0039] It should be noted that the proportional gain is an important parameter in the control system of the test bench. It is mainly used to adjust the relationship between the input and output in the control system. In the aviation main pump verification test bench, the proportional gain can be used to adjust the control parameters of the main pump, such as flow rate, pressure, etc. By reasonably setting the proportional gain, the control system of the test bench can respond more stably and quickly to the changes in the operating state of the main pump, ensuring that all parameters during the test can accurately track the set values, thereby improving the accuracy and reliability of the test. For example, when controlling the flow rate of the main pump, the proportional gain can adjust the control signal according to the deviation between the actual flow rate and the set flow rate in a certain proportion to achieve precise regulation of the flow rate.

[0040] The proportional gain can be used as the sensitivity when the aviation main pump adjusts its internal pressure. Currently, in the field of automatic control of aviation main pumps, a fixed proportional gain is usually adopted, and the adjustment effect of this proportional gain is different under different atmospheric pressures.

[0041] S1: Obtain the information data of the aviation main pump, where the information data includes: oscillation frequency, proportional gain, pressure change sequence, and oscillation amplitude change sequence.

[0042] In this embodiment, the pressure change sequence inside the aviation main pump is collected through a pressure sensor , and the proportional gain of the aviation main pump is read 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.

[0043] 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 .

[0044] 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.

[0045] 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.

[0046] 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.

[0047] The length of the pressure adjustment interval is corrected based on the oscillation amplitude change sequence, including:

[0048] 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.

[0049] 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 , and the sample data within each cluster are all sequences of the variation of the oscillation amplitude which is a subset. The implementer can adjust according to specific circumstances. If there are isolated sample points in the DBSCAN clustering process, the isolated sample points will be incorporated into the cluster where the sample point with the smallest distance metric parameter to itself is located.

[0050] In addition, in another embodiment, by presetting the sliding window size according to the sequence of the variation of the oscillation amplitude, taking any sample point as the starting point of the preset window, and calculating the average oscillation amplitude within each sliding window;

[0051] In response to the average oscillation amplitude being greater than the preset threshold, the position of the starting point corresponding to the preset window is used as the boundary of the adjustment region, and multiple adjustment intervals are divided according to the boundary.

[0052] Specifically, the average oscillation amplitude satisfies the following relational expression:

[0053] ;

[0054] In the formula, represents the average oscillation amplitude of the preset window corresponding to the th sample point in the sequence of the variation of the oscillation amplitude, represents the size of the preset window, represents the th sample point in the sequence of the variation of the oscillation amplitude.

[0055] In this embodiment, the size of the preset window is 5 and 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 of the set pressure value. The pressure value of the main pump of the aeroengine needs to meet the following requirements:

[0056] 1. Engine design parameters: The design of the engine will determine the pressure range required by the main pump;

[0057] 2. Flight conditions: Different flight conditions (such as takeoff, climb, cruise) may require different pressure setting values;

[0058] 3. Environmental factors: Environmental factors such as temperature and atmospheric pressure will also affect the set pressure value;

[0059] The turbopumps of some commercial aeroengines may have a relatively high pressure setting value during takeoff, while the pressure setting value during cruise is relatively low. And the specific values need to refer to the data and guidance provided by the engine manufacturer.

[0060] It should also be noted that the proportional gain is the sensitivity when adjusting the internal pressure in the main aero 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 oscillation frequency of the pressure and the more violent the oscillation, but the smaller the response time to adjust to the corresponding pressure value. Conversely, the smaller the proportional gain, the lower the oscillation frequency of the pressure and the smoother the oscillation, but the longer the response time to adjust to the corresponding pressure value. Therefore, it is necessary to find an appropriate proportional gain so that both the response time and the oscillation frequency of the pressure are at a relatively low level. The response time is the time required to complete one pressure increase and decrease cycle.

[0061] S3: Set the initial proportional gain according to the length of the adjustment interval. Take the ratio between the number of pressure points included in each adjustment interval and the response time of the adjustment interval as the pressure change rate. Based on the oscillation frequency and the pressure change rate, use it to analyze the positive or negative adjustment evaluation function, and construct a proportional gain optimization model to complete the dynamic monitoring and adjustment of the proportional gain for the pressure increase and decrease of the main aero pump.

[0062] Example 1: Setting the initial proportional gain includes:

[0063] Refer to Figure 3 , the dotted line above in the figure represents the preset target pressure value, which is the ultimate goal of the pressure increase and decrease adjustment process. The figure shows six adjustment intervals (the 1st adjustment interval to the 6th adjustment interval), and each interval represents a stage in the pressure adjustment process. The pressure change in each adjustment interval is represented by a stepped dotted line, showing the gradual change of the pressure in each stage. The arrow in the figure indicates the direction of pressure adjustment, 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 adjustment interval, showing the key time nodes in the pressure adjustment process.

[0064] Set the proportional gain of the first adjustment interval to the minimum value in the value range, and set the proportional gain of the second adjustment interval to the maximum value in the value range, where the value range of the proportional gain depends on the design and specifications of the control system.

[0065] 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, applicable to the proportional gain adjustment under different working conditions, and can quickly find the appropriate proportional gain range. However, since the initial proportional gain is set at the extreme values, it may cause the initial response of the system to be too fast or too slow, and more adjustment times are required to reach the optimal state. This method lacks fine adjustment of the proportional gain in the initial stage and may require more iterations to optimize the proportional gain.

[0066] Example 2: Setting the initial proportional gain also includes:

[0067] Select a relatively small initial proportional gain for the adjustment range, set a step disturbance value, obtain the curve after the step disturbance. In response to the rapid decay of the curve, it is necessary to reduce the proportional gain; otherwise, increase the proportional gain. Iterate until a preset proportional decay oscillation process appears, and determine the proportional gain and the oscillation period, thereby setting the initial proportional gain.

[0068] It should be noted that according to the design and specifications of the control system, the value range of the proportional gain is determined. Among them, selecting a relatively small initial proportional gain means: selecting the value at the 30% position of the value range as the relatively small initial proportional gain. That is to say, if the value range is from to , then the initial proportional gain satisfies the following relational expression:

[0069] ;

[0070] In the formula, represents the initial proportional gain, represents the minimum proportional gain within the value range, represents the maximum proportional gain within the value range.

[0071] Exemplarily, according to the control system, the value range of the proportional gain is determined. Among them, the minimum proportional gain , the maximum proportional gain , , , and selecting the proportional gain at the 30% position as the starting point of the initial proportional gain is an empirical value and can be adjusted according to specific circumstances.

[0072] In this embodiment, the method of step disturbance is used to set the initial proportional gain. Among them, step disturbance is a commonly used technique in the fields of control theory and signal processing. It is usually used to test and analyze the dynamic response characteristics of the system. This is a well-known technology to those skilled in the art and will not be described in detail.

[0073] That is to say, by gradually adjusting the proportional gain, a more appropriate initial proportional gain can be found more precisely, optimizing the response performance of the system. According to the actual response curve of the system after the step disturbance, dynamically adjusting the proportional gain can better adapt to the dynamic characteristics of the system. Through the preset decay oscillation process, a suitable proportional gain can be found faster, reducing the number of iterations required for adjustment.

[0074] Implementers can select the implementation method according to specific circumstances. In the first embodiment, it is applicable to scenarios where a rapid coverage of the proportional gain value range is required. The operation is simple, but the initial response may not be ideal and requires more adjustment times. In the second embodiment, it is applicable to scenarios where fine adjustment of the proportional gain is required. Through dynamic adjustment, it can better adapt to the dynamic characteristics of the system, reduce the number of iterations, but the operation is relatively complex and the time cost is high.

[0075] It should be noted that the preset ratio is 4:1, and implementers can adjust it according to specific circumstances.

[0076] The positive or negative adjustment evaluation function satisfies the following relational expression:

[0077] ;

[0078] In the formula, represents the positive adjustment evaluation index, represents the negative adjustment evaluation index, represents the oscillation frequency of the th adjustment interval, represents the oscillation frequency of the th adjustment interval, represents the oscillation frequency of the th adjustment interval,

[0079] That is to say, represents the adjustment evaluation index, expressing the effects of two adjacent proportional gains. This effect expresses the advantages and disadvantages of the gain adjustment effect from two perspectives: the oscillation frequency of the pressure and the pressure change rate; in response to the positive adjustment evaluation index being less than the negative adjustment evaluation index , it indicates that the proportional gain needs to be adjusted downward. Conversely, the proportional gain needs to be adjusted upward.

[0080] Among them, the proportional gain optimization model satisfies the following conditions:

[0081] In response to the proportional gain of the second adjustment interval being greater than that 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 they are equal, the proportional gain of the fourth adjustment interval is the proportional gain of the third interval. Iterate in this way until this step-up / step-down adjustment is completed.

[0082] So far, starting from the current pressure point and ending at the pressure target point, several adjustments of the proportional gain have been completed for the adjustment interval, realizing the dynamic adjustment of the proportional gain during the step-up / step-down process of the aviation main pump, which can effectively reduce the response time and the oscillation frequency of the pressure.

[0083] The present invention also provides a monitoring system for the operating state of an aviation main pump verification test bench. As Figure 4 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, it realizes a method for monitoring the operating state of an aviation main pump verification test bench according to the first aspect of the present invention.

[0084] The system also includes other components well-known to those skilled in the art such as a communication bus and a communication interface. Their settings and functions are known in the art, so they will not be elaborated here.

[0085] In the present invention, the aforementioned memory can be any tangible medium that contains or stores a program, and this program can be used by or in combination with an instruction execution system, device, or apparatus. For example, the computer-readable storage medium can be any suitable magnetic storage medium or magneto-optical storage medium, such as resistive random access memory (RRAM), dynamic random access memory (DRAM), static random access memory (SRAM), enhanced dynamic random access memory (EDRAM), high-bandwidth memory (HBM), hybrid memory cube (HMC), etc., or any other medium that can be used to store the required information and can be accessed by an application program, module, or both. Any such computer storage medium can be a part of the device or accessible or connectable to the device. Any application or module described in the present invention can be implemented by computer-readable / executable instructions stored or otherwise held by such a computer-readable medium.

[0086] In the description of this specification, the meanings of "a plurality of" and "several" are at least two, such as two, three or more, etc., unless otherwise specifically defined.

[0087] Although this specification has shown and described multiple embodiments of the present invention, it is obvious to those skilled in the art that such embodiments are provided only by way of example. Those skilled in the art will think of many changes, alterations and alternative ways without departing from the spirit and concept of the present invention. It should be understood that various alternative solutions to the embodiments of the present invention described herein may be adopted in the practice of the present invention.

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; Perform wavelet transformation on the pressure change sequence, extract the high-frequency part as the oscillation frequency, perform reverse transformation on the intermediate frequency and low-frequency parts after the wavelet transformation, obtain the marked pressure change sequence, calculate the difference between the pressure change sequence and the marked pressure change sequence, and obtain the 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; in response to the positive adjustment evaluation function being equal to the negative adjustment evaluation function, the proportional gain of the fourth adjustment interval is the proportional gain of the third interval, and this iteration is repeated until the current step-up and step-down regulation 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: 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.

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 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.

4. 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.

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 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.

6. 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.

7. 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 6 is implemented.

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