Modeling method for piston pump of civil aircraft

Abstract

The application relates to the technical field of hydraulic pressure and discloses a modeling method for a plunger pump of a civil aircraft, which comprises the following steps: obtaining operation parameters of the plunger pump; determining the available flow of the pump and the adjusting pressure output by the pump through proportional calculation; and in the process of constructing a dynamic model of the plunger pump, the shaft rotating speed is associated with key definition points A, C, D and E for real-time correlation calculation through setting a dynamic key point coupling mechanism, so that the pressure-flow characteristics of the pump are dynamically updated along with the change of working conditions at all times, the nonlinear response characteristics of the hydraulic system in high-speed flight can be reflected in real time, the accuracy and reliability of the model under variable-speed working conditions are ensured, the hydraulic control prediction deviation is reduced, flight safety is further strengthened, the physical consistency of the pressure-flow relationship is automatically maintained in the model simulation process, the accuracy of system pressure fluctuation simulation under extreme working conditions is ensured, and high-confidence decision-making basis is provided for a health management system.

Description

Technical Field

[0001] This invention relates to the field of hydraulic technology, specifically to a method for modeling piston pumps for civil aircraft. Background Technology

[0002] Hydraulic technology is a mechanical transmission technology based on Pascal's law. It amplifies power by transmitting pressure through a closed liquid, solving problems of roundness and surface roughness in industrial and civilian fields. Its core principle is to apply a small force through a small-area piston, so that the liquid pressure is uniformly transmitted to a large-area piston to generate a multiplier force.

[0003] Hydraulic system modeling for civil aircraft is one of the core aspects of safe aircraft operation. As a key power component of the hydraulic system, the modeling accuracy of the piston pump directly affects the reliability of system simulation and the effect of design optimization. This is one of the core requirements in the field of hydraulic system simulation. A high-precision dynamic model can accurately reflect the pressure-flow characteristics of the pump under complex operating conditions, ensuring the real-time performance and stability of aircraft hydraulic control, and providing technical support for ensuring flight safety.

[0004] Currently, due to the drastic changes in the operating conditions of the hydraulic system of civil aircraft, existing piston pump modeling methods have limitations in the dynamic characteristic characterization: when analyzing the pump's flow output characteristics, most models use static parameters to simplify the coupling relationship between shaft speed and pressure, which cannot reflect the nonlinear pressure-flow correlation of the pump under variable speed conditions in real time. This results in a large deviation in the prediction of hydraulic response during high-speed flight, which seriously affects the accuracy of system fault diagnosis.

[0005] Therefore, a modeling method for plunger pumps in civil aircraft is proposed to solve the above problems. Summary of the Invention

[0006] (a) Technical problems to be solved

[0007] To address the shortcomings of existing technologies, this invention provides a method for modeling plunger pumps in civil aircraft, thus solving the problems mentioned in the background section.

[0008] (II) Technical Solution

[0009] To achieve the above objectives, the present invention provides the following technical solution: a method for modeling a plunger pump in a civil aircraft, comprising the following steps:

[0010] S1. Obtain the operating parameters of the plunger pump, including the pump shaft speed, maximum shaft speed, and key points A, C, D, and E in the predefined coordinate system. Point A represents the pressure at zero flow rate, point C represents the maximum pump speed corresponding to the flow rate at zero pressure, point D represents the position of the characteristic curve intersection point B on the pressure coordinate axis, and point E represents the position of the characteristic curve intersection point B on the flow coordinate axis.

[0011] S2. Based on the shaft speed, maximum shaft speed, and point C, the available flow rate of the pump is determined by proportional calculation, wherein the available flow rate represents the output flow rate of the pump under zero pressure conditions;

[0012] S3. Based on point D, the available flow rate of the pump, point C, and point E, calculate the theoretical unadjusted pressure through a linear relationship. The theoretical unadjusted pressure represents the unadjusted pressure value of the pump under zero flow conditions.

[0013] S4. Compare the theoretical unadjusted pressure with the pressure value at point A. If the theoretical unadjusted pressure is greater than the pressure value at point A, then set the pump's adjustment pressure to the pressure value at point A; otherwise, set the pump's adjustment pressure to the theoretical unadjusted pressure.

[0014] S5. Output the regulating pressure of the pump to construct an accurate dynamic model of the plunger pump. The model is applied to the simulation and performance optimization of the hydraulic system of civil aircraft.

[0015] Preferably, in step S1, the key points A, C, D, and E are obtained through experimental data and historical simulation data and stored in a database. The pressure unit of point A is Pa, the flow unit of point C is m³ / s, and points D and E are expressed in pressure units and flow units, respectively. The acquisition step also includes parameter normalization processing, converting all units to the International System of Units (SI), and performing range checks and consistency verification to ensure the validity of the parameters.

[0016] Preferably, in step S2, the ratio calculation is achieved using the following normalization formula:

[0017]

[0018] in, The pump's available flow rate, expressed in m³ / s, represents the pump's flow capacity when there is no pressure output.

[0019] The pump shaft speed is expressed in rad / s, normalized from the original unit rpm. The conversion formula is as follows: ;

[0020] This is the maximum shaft speed of the pump, in rad / s, and is normalized as above.

[0021] To define the flow rate at point C, in m³ / s, normalize it from the original unit gpm using the following formula: .

[0022] The calculation process also includes an error correction mechanism to address deviations caused by shaft speed fluctuations and ensure the accuracy of flow calculation results under dynamic operating conditions.

[0023] Preferably, in step S3, the calculation of the theoretical unregulated pressure is achieved using the following normalization formula:

[0024]

[0025] in, This is the theoretical unadjusted pressure, expressed in Pa (Pascal), representing the theoretical pressure value of the pump when there is no flow output.

[0026] To define the pressure value at point D, in Pa, normalize it from the original unit psi using the following formula: ;

[0027] The pump's available flow rate, in units of This is consistent with the definition in S2;

[0028] Define the flow rate at point C, in units of The normalization process is consistent with that described in S2.

[0029] Define the flow rate at point E, in units of The normalization process is the same as above, representing the flow coordinate position of intersection point B;

[0030] The calculation is based on linear interpolation, reflecting the inverse relationship between pump pressure and flow rate. The denominator of the formula... Ensure consistent dimensions; all units are equal. To avoid dimensionless conflicts.

[0031] Preferably, in step S4, the comparison process includes threshold judgment: the threshold is defined as the pressure value at point A, in Pa. Specifically, when the theoretical unadjusted pressure is greater than the threshold, the pressure adjustment mechanism is triggered, and the adjustment pressure of the pump is set to the threshold. Otherwise, the theoretical unadjusted pressure is maintained as the output. The threshold is determined based on the maximum working pressure range of the pump, with a typical value of 2-30 MPa, and is continuously effective within the dynamic working range of the pump through stability analysis.

[0032] Preferably, in step S5, after adjusting the output pump pressure, a model building step is further included: the adjustment pressure is used as a core parameter and input into the simulation model of the piston pump, and a two-dimensional rectangular coordinate system model is generated by combining the flow characteristic curve. The model simulates the actual working conditions of the pump in the hydraulic system of a civil aircraft, including the influence of the reciprocating motion of the piston in the cylinder on the oil suction and oil pressure efficiency.

[0033] Preferably, the method further includes S6: calibrating the position of the intersection point B, specifically, dynamically updating the position of the intersection point B in the coordinate system based on the normalized coordinate values ​​of points D and E. The calibration step includes an iterative optimization algorithm to adapt to the changes in the characteristic curve under different speeds and improve the accuracy of the model under varying operating conditions.

[0034] Preferably, the method is applied to a specific scenario of a civil aircraft hydraulic system, including step S7: after model construction, performing simulation tests, the tests including simulating the dynamic response of changes in sealing volume to hydraulic oil intake and discharge, and outputting a simulation report for use in aircraft component maintenance decisions.

[0035] Preferably, the method further includes S8: parameter optimization feedback, specifically, based on the model output results, comparing with the actual running data, adjusting the defined values ​​of points A, C, D, and E. The optimization step adopts a machine learning algorithm to automatically iteratively update the parameters to enhance the adaptability and robustness of the model in long-term use.

[0036] Preferably, the overall process of the method includes preprocessing and postprocessing steps. Preprocessing includes data acquisition and unit normalization initialization, and postprocessing includes model verification and result visualization. The method overcomes the shortcomings of existing technologies in simplifying Boolean variables by calculating dynamic parameters and integrating pressure-flow relationships, thereby improving the realism and credibility of simulation.

[0037] (III) Beneficial Effects

[0038] Compared with the prior art, the present invention provides a method for modeling plunger pumps in civil aircraft, which has the following beneficial effects:

[0039] 1. In this invention, by setting a dynamic key point coupling mechanism, when constructing the dynamic model of the plunger pump, the shaft speed is correlated with the key definition points A, C, D, and E in real time for calculation. This ensures that the pump's pressure-flow characteristics are always dynamically updated with changes in operating conditions, which can reflect the nonlinear response characteristics of the hydraulic system in high-speed flight in real time, ensuring the accuracy and reliability of the model under variable speed conditions, reducing hydraulic control prediction deviations, and further enhancing flight safety assurance.

[0040] 2. In this invention, by setting an adaptive compensator for the characteristic curve, the dynamic position calibration mechanism of the intersection point B during the modeling of the pump's characteristic curve corrects the correlation mapping relationship between points D and E in the coordinate system in real time. This enables the system to adapt to the shape changes of the characteristic curve at different speeds, avoids pressure output distortion when the pump operates under non-design conditions, and automatically maintains the physical consistency of the pressure-flow relationship during model simulation, ensuring the accuracy of the simulation of system pressure fluctuations under extreme conditions.

[0041] 3. In this invention, by setting a dynamic threshold regulator, when the model outputs pressure parameters, the logical judgment of comparing the theoretical unadjusted pressure with the pressure stabilization threshold at point A is made to lock the safe pressure range of the pump in real time. This enables the system to automatically suppress the risk of abnormal overpressure during takeoff / landing, dynamically optimize the adjustment strategy according to the pressure requirements under different flight conditions, improve the reliability of the plunger pump model in aircraft hydraulic failure prediction, and provide a high-confidence decision basis for the health management system. Attached Figure Description

[0042] Figure 1 This is a schematic diagram of the overall system architecture of the present invention. Detailed Implementation

[0043] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0044] Please see Figure 1 The modeling method for the plunger pump of this civil aircraft includes the following steps:

[0045] S1. Obtain the operating parameters of the plunger pump, including the pump shaft speed, maximum shaft speed, and key points A, C, D, and E in the predefined coordinate system. Point A represents the pressure at zero flow rate, point C represents the maximum pump speed corresponding to the flow rate at zero pressure, point D represents the position of the characteristic curve intersection point B on the pressure coordinate axis, and point E represents the position of the characteristic curve intersection point B on the flow coordinate axis.

[0046] S2. Based on the shaft speed, maximum shaft speed, and point C, the available flow rate of the pump is determined by proportional calculation. The available flow rate represents the output flow rate of the pump under zero pressure conditions.

[0047] S3. Based on point D, the pump's available flow rate, point C, and point E, calculate the theoretical unadjusted pressure through a linear relationship. The theoretical unadjusted pressure represents the unadjusted pressure value of the pump under zero flow conditions.

[0048] S4. Compare the theoretical unadjusted pressure with the pressure value at point A. If the theoretical unadjusted pressure is greater than the pressure value at point A, then set the pump's adjustment pressure to the pressure value at point A; otherwise, set the pump's adjustment pressure to the theoretical unadjusted pressure.

[0049] S5. Adjust the output pump pressure and construct an accurate dynamic model of the piston pump. The model is applied to the simulation and performance optimization of the hydraulic system of civil aircraft.

[0050] In step S1, key points A, C, D, and E are obtained through experimental data and historical simulation data and stored in the database. The pressure unit of point A is Pa, the flow unit of point C is m³ / s, and points D and E are expressed in pressure units and flow units, respectively. The acquisition step also includes parameter normalization processing, converting all units to the International System of Units (SI), and performing range checks and consistency verification to ensure the validity of the parameters.

[0051] Normalized unit conversion formula:

[0052]

[0053] in, The normalized parameter value, with units determined according to the parameter type;

[0054] : Original parameter value, unit determined by input;

[0055] Unit conversion factor.

[0056] In step S2, the proportion is calculated using the following normalization formula:

[0057]

[0058] in, The pump's available flow rate, expressed in m³ / s, represents the pump's flow capacity when there is no pressure output.

[0059] The pump shaft speed is expressed in rad / s, normalized from the original unit rpm. The conversion formula is as follows: ;

[0060] This is the maximum shaft speed of the pump, in rad / s, and is normalized as above.

[0061] To define the flow rate at point C, in m³ / s, normalize it from the original unit gpm using the following formula: .

[0062] The calculation process also includes an error correction mechanism to address deviations caused by shaft speed fluctuations and ensure the accuracy of flow calculation results under dynamic operating conditions.

[0063] In step S3, the theoretical unregulated pressure is calculated using the following normalization formula:

[0064]

[0065] in, This is the theoretical unadjusted pressure, expressed in Pa (Pascal), representing the theoretical pressure value of the pump when there is no flow output.

[0066] To define the pressure value at point D, in Pa, normalize it from the original unit psi using the following formula: ;

[0067] The pump's available flow rate, in units of This is consistent with the definition in step S2;

[0068] Define the flow rate at point C, in units of The normalization process is consistent with step S2;

[0069] Define the flow rate at point E, in units of The normalization process is the same as above, representing the flow coordinate position of intersection point B;

[0070] The calculation is based on linear interpolation, reflecting the inverse relationship between pump pressure and flow rate. The denominator of the formula... Ensure consistent dimensions; all units are equal. To avoid dimensionless conflicts;

[0071] In step S4, the comparison process includes threshold judgment: the threshold is defined as the pressure value at point A, in Pa. Specifically, when the theoretical unadjusted pressure is greater than the threshold, the pressure regulation mechanism is triggered, and the pump's regulation pressure is set to the threshold. Otherwise, the theoretical unadjusted pressure is maintained as the output.

[0072] Dynamic threshold adjustment formula:

[0073]

[0074] in, The adjusted pressure threshold, in Pa, represents the dynamically optimized safe pressure critical point.

[0075] Define the pressure value at point A, in Pa.

[0076] Sensitivity factor, range [0.1, 0.5], represents the response strength of the threshold to changes in operating conditions; typical values ​​are calibrated experimentally.

[0077] Speed ​​deviation rate, calculated using the following formula: ,in The pump's design speed is expressed in rad / s.

[0078] The threshold is determined based on the pump's maximum operating pressure range, with a typical value of 18 MPa, and is ensured to be continuously effective within the pump's dynamic operating range through stability analysis.

[0079] In step S5, after adjusting the output pump pressure, the model building step is further included: the adjustment pressure is used as the core parameter and input into the simulation model of the piston pump. A two-dimensional rectangular coordinate system model is generated by combining the flow characteristic curve. The model simulates the actual working conditions of the pump in the hydraulic system of civil aircraft, including the effect of the reciprocating motion of the piston in the cylinder on the oil suction and oil pressure efficiency.

[0080] The method also includes S6: calibrating the position of intersection point B, specifically, dynamically updating the position of intersection point B in the coordinate system based on the normalized coordinate values ​​of points D and E. The calibration step includes an iterative optimization algorithm to adapt to the changes in the characteristic curve under different speeds.

[0081] Formula for calculating the position of intersection B:

[0082]

[0083] in, : The coordinates of intersection point B, in dimensionless coordinate system, including pressure and flow dimensions;

[0084] Define the pressure value at point D, in Pa.

[0085] The pump's available flow rate, expressed in m³ / s;

[0086] Correction factor, range [0.8, 1.2], represents the dynamic scaling ratio of the flow dimension to compensate for changes in rotational speed;

[0087] Real-time calibration of characteristic curve intersections improves model accuracy under varying operating conditions;

[0088] The method is applied to specific scenarios of hydraulic systems for civil aircraft, including step S7: after model building, simulation tests are performed, including simulating the dynamic response of changes in seal volume to hydraulic oil intake and discharge, and outputting a simulation report for use in aircraft component maintenance decisions;

[0089] Dynamic response simulation formula:

[0090]

[0091] in, : Plunger displacement, in meters, represents the amplitude of the reciprocating motion of the plunger within the cylinder.

[0092] : Plunger stroke radius, in meters, normalized self-design parameters;

[0093] Phase angle, in rad, represents the angle of piston movement;

[0094] Pump shaft speed, in rad / s;

[0095] Time variable, unit is seconds;

[0096] Physical significance: Simulates the dynamic impact of plunger motion on changes in sealing volume, evaluates oil suction and pressure efficiency, and provides quantitative output for simulation;

[0097] The method also includes S8: parameter optimization feedback, which involves adjusting the defined values ​​of points A, C, D, and E based on the model output results and comparing them with the actual running data. The optimization steps use machine learning algorithms to automatically iterate and update the parameters.

[0098] Parameter optimization and update formula:

[0099]

[0100] in, The optimized definition point value, with units determined based on the point type;

[0101] : The original definition point value, in the same unit as above;

[0102] : Learning rate, range [0.01, 0.1], control parameter update step size;

[0103] Error gradient: Represents the partial derivative of the model output error with respect to the defined point value. The error is defined as the difference between the simulation result and the actual data.

[0104] Physical meaning: By automatically iteratively optimizing key point parameters through the gradient descent algorithm, the adaptability and robustness of the model in long-term use are enhanced;

[0105] The overall process of the method includes preprocessing and postprocessing steps. Preprocessing includes data acquisition and unit normalization initialization, while postprocessing includes model verification and result visualization. The method overcomes the shortcomings of existing technologies in simplifying Boolean variables by calculating dynamic parameters and integrating pressure-flow relationships, thereby improving the realism and credibility of simulation.

[0106] The operational steps of the modeling method for plunger pumps in civil aircraft are as follows:

[0107] Step 1: Dynamic parameter acquisition and normalization preprocessing:

[0108] The principle is to collect the operating parameters of the plunger pump and convert them into standard units to ensure dimensional consistency.

[0109] Operation procedure: Obtain the original values ​​of shaft speed and maximum shaft speed, extract key definition points A, C, D, and E, perform unit normalization, convert the speed to rad / s, shaft speed = original value × π / 30, convert the pressure to Pa, pressure = original value × 6894.76, convert the flow rate to m³ / s, flow rate = original value × 6.309e-5, and verify the validity of the parameters.

[0110] Step 2: Dynamic Flow Characteristic Modeling:

[0111] Principle: Establish the proportional relationship between shaft speed and zero-pressure flow rate;

[0112] Operating procedures: Calculate the speed ratio factor: speed ratio = current shaft speed / maximum shaft speed; derive the zero pressure flow rate: available flow rate = speed ratio × flow rate value at point C; introduce dynamic compensation: automatically correct the flow rate deviation based on the speed fluctuation amplitude.

[0113] Step 3: Establishing the pressure-flow coupling relationship:

[0114] Principle: Dynamic correlation between pressure and flow is achieved through key point mapping;

[0115] Operation procedure: Calculate the theoretical unadjusted pressure, update the characteristic curve intersection point B, fix the pressure coordinate to the value of point D, and set the flow rate at point B as: flow rate = available flow rate × dynamic correction factor.

[0116] Step 4: Safety pressure threshold decision mechanism:

[0117] Principle: Dynamically adjust the pressure safety boundary based on operating conditions;

[0118] Operation process: Calculate dynamic pressure threshold, execute pressure decision, output pressure value at point A when the theoretical pressure is greater than the adjustment threshold, otherwise output theoretical pressure value, extreme condition protection, and automatically strengthen threshold constraints during takeoff and landing.

[0119] Step 5: Implementation of plunger kinematics simulation:

[0120] Principle: Simulates the effect of volume change through equations of motion;

[0121] Operation process: Construct a plunger displacement model, calculate the rate of change of sealing volume, correlate with hydraulic oil dynamics, during the oil suction stage, negative displacement → volume increase → oil intake, during the oil pressure stage, positive displacement → volume decrease → oil discharge;

[0122] Step 6: Adaptive parameter optimization mechanism:

[0123] Principle: Machine learning drives iterative optimization of keypoint parameters;

[0124] Operation process: Define model error, error = simulation result - actual running data; calculate parameter gradient: gradient = ∂error / ∂key point value; perform parameter update, new point value = origin value - learning rate × gradient; convergence judgment: terminate when the error change rate is less than 1% for 3 consecutive iterations.

[0125] Step 7: Full-condition model verification process:

[0126] Principle: Verify the reliability of the model in flight scenarios from multiple dimensions;

[0127] Operating procedures: steady-state verification, cruise condition, pressure-flow curve matching test at constant speed, idling condition, pressure stability analysis in low flow range, transient verification, takeoff phase, step response test from 0 to maximum speed, emergency braking, pressure change recovery time measurement, fault simulation, plunger jamming, pressure anomaly detection when displacement returns to zero, oil circuit leakage, pressure maintenance capability assessment when flow rate increases abnormally.

[0128] Step 8: Health Management Decision Support

[0129] Principle: The model output is transformed into a basis for maintenance decisions;

[0130] Operation process: Generate a three-dimensional spatiotemporal feature map of pressure and flow, extract key indicators, pressure fluctuation index, flow response delay, volumetric efficiency decay rate, fault warning, yellow warning (indicator exceeds design value by 80%), red warning (indicator exceeds design value by 90% and lasts for 5 minutes), maintenance decision output, warning level + fault location + remaining life prediction.

[0131] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0132] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A method for modeling plunger pumps in civil aircraft, characterized in that: Includes the following steps: S1. Obtain the operating parameters of the plunger pump, including the pump shaft speed, maximum shaft speed, and key points A, C, D, and E in a predefined coordinate system. The predefined coordinate system is a two-dimensional rectangular coordinate system of pressure and flow rate. Point A represents the pressure at zero flow rate under the steady-state pressure, point C represents the flow rate value corresponding to the maximum pump speed under zero pressure conditions, point D represents the position of the characteristic curve intersection point B on the pressure coordinate axis, and point E represents the position of the characteristic curve intersection point B on the flow rate coordinate axis. The characteristic curve intersection point B is a key point on the pump pressure-flow rate characteristic curve. S2. Based on the shaft speed, maximum shaft speed, and point C, the available flow rate of the pump is determined by proportional calculation, wherein the available flow rate represents the output flow rate of the pump under zero pressure conditions; S3. Based on point D, the available flow rate of the pump, point C, and point E, calculate the theoretical unadjusted pressure through a linear relationship. The theoretical unadjusted pressure represents the unadjusted pressure value of the pump under zero flow conditions. S4. Compare the theoretical unadjusted pressure with the pressure value at point A. If the theoretical unadjusted pressure is greater than the pressure value at point A, then set the pump's adjustment pressure to the pressure value at point A; otherwise, set the pump's adjustment pressure to the theoretical unadjusted pressure. S5. Output the regulating pressure of the pump and construct an accurate dynamic model of the plunger pump. The model is applied to the simulation and performance optimization of the hydraulic system of civil aircraft. The method further includes S6: calibrating the position of intersection point B, specifically, dynamically updating the position of intersection point B in the coordinate system based on the normalized coordinate values ​​of points D and E. The calibration step includes an iterative optimization algorithm to adapt to the changes in characteristic curves under different speeds and improve the accuracy of the model under varying operating conditions.

2. The method for modeling a plunger pump for a civil aircraft according to claim 1, characterized in that: In step S1, the key points A, C, D, and E are obtained through experimental data and historical simulation data and stored in the database. The pressure unit of point A is Pa, the flow unit of point C is m³ / s, and points D and E are expressed in pressure units and flow units, respectively. The acquisition step also includes parameter normalization processing, converting all units to the International System of Units (SI), and performing range checks and consistency verification to ensure the validity of the parameters.

3. The method for modeling a plunger pump for a civil aircraft according to claim 1, characterized in that: In step S2, the ratio calculation is achieved using the following normalization formula: in, The pump's available flow rate, expressed in m³ / s, represents the pump's flow capacity when there is no pressure output. The pump shaft speed is expressed in rad / s, normalized from the original unit rpm. The conversion formula is as follows: ; This is the maximum shaft speed of the pump, in rad / s, and the normalization method is the same as that for the shaft speed. To define the flow rate at point C, in m³ / s, normalize it from the original unit gpm using the following formula: ; The calculation process also includes an error correction mechanism to address deviations caused by shaft speed fluctuations and ensure the accuracy of flow calculation results under dynamic operating conditions.

4. The method for modeling a plunger pump for a civil aircraft according to claim 3, characterized in that: In step S3, the calculation of the theoretical unregulated pressure is achieved using the following normalization formula: in, This is the theoretical unadjusted pressure, expressed in Pa, representing the theoretical pressure value of the pump when there is no flow output. To define the pressure value at point D, in Pa, normalize it from the original unit psi using the following formula: ; Define the flow rate at point E, in units of Its normalization process is the same as that for point C; The calculation is based on linear interpolation, reflecting the inverse relationship between pump pressure and flow rate. The denominator of the formula... Ensure consistent dimensions; all units are equal. To avoid dimensionless conflicts.

5. The method for modeling a plunger pump for a civil aircraft according to claim 1, characterized in that: In step S4, the comparison process includes threshold judgment: the threshold is defined as the pressure value at point A, in Pa. Specifically, when the theoretical unadjusted pressure is greater than the threshold, the pressure adjustment mechanism is triggered, and the adjustment pressure of the pump is set to the threshold. Otherwise, the theoretical unadjusted pressure is maintained as the output. The threshold is determined based on the maximum working pressure range of the pump and is continuously effective within the dynamic working range of the pump through stability analysis.

6. The method for modeling a plunger pump for a civil aircraft according to claim 1, characterized in that: In step S5, after adjusting the output pump pressure, a model building step is further included: the adjustment pressure is used as a core parameter and input into the simulation model of the piston pump. A two-dimensional rectangular coordinate system model is generated by combining the flow characteristic curve. The model simulates the actual working conditions of the pump in the hydraulic system of a civil aircraft, including the influence of the reciprocating motion of the piston in the cylinder on the oil suction and oil pressure efficiency.

7. The method for modeling a plunger pump for a civil aircraft according to claim 1, characterized in that: The method is applied to specific scenarios of hydraulic systems for civil aircraft, including step S7: after model construction, a simulation test is performed, the test includes simulating the dynamic response of changes in sealing volume to hydraulic oil intake and discharge, and outputting a simulation report for use in aircraft component maintenance decisions.

8. The method for modeling a plunger pump for a civil aircraft according to claim 1, characterized in that: The method also includes S8: parameter optimization feedback, which involves adjusting the defined values ​​of points A, C, D, and E based on the model output results and comparing them with actual operating data. The optimization step uses a machine learning algorithm to automatically iterate and update the parameters to enhance the adaptability and robustness of the model in long-term use.

9. The method for modeling a plunger pump for a civil aircraft according to claim 1, characterized in that: The overall process of the method includes preprocessing and postprocessing steps. Preprocessing includes data acquisition and unit normalization initialization, while postprocessing includes model validation and result visualization.

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