An aero axial plunger pump vibration radiation noise prediction method, device and electronic equipment

Abstract

The embodiment of the application discloses an aviation axial plunger pump vibration radiation noise prediction method and device and electronic equipment, and relates to the technical field of aerospace dynamics simulation. The method comprises the following steps: obtaining the structure and preset working condition parameters of the aviation axial plunger pump, wherein the structure parameters comprise component geometric dimensions and physical property parameters, and the working condition parameters are working parameters of the pump in a preset operation mode. The dynamics mechanism of the pump is analyzed based on the above parameters, and the plunger dynamics law is obtained, including the time variation law of the plunger friction force, axial displacement, axial movement speed and acceleration. A multi-body dynamics model and a hydraulic model are constructed and coupled. The pump external shell is flexibilized, a rigid-flex coupling simulation model is obtained, and the shell excitation load is obtained by running the rigid-flex coupling simulation model. The load is applied to the corresponding excitation points of the acoustic vibration coupling model, and the pump vibration radiation noise sound field sound pressure distribution result is obtained by solving, and the model is used for simulating the interaction between the shell vibration and the sound field.

Description

Technical Field

[0001] This application relates to the field of aerospace dynamics simulation technology, and in particular to a method, device and electronic equipment for predicting vibration radiation noise of an aerospace axial piston pump. Background Technology

[0002] Axial piston pumps are indispensable key power components in aviation hydraulic systems, widely used in hydraulic power transmission scenarios for various aviation equipment. However, aviation axial piston pumps typically operate continuously under extremely complex conditions of high speed, high pressure, and wide temperature range. The vibration and radiated noise generated during their operation are significant problems, which not only accelerate the wear and aging of the pump body components and shorten their service life, but may also interfere with the normal operation of surrounding aviation equipment and even pose a potential threat to flight safety. Therefore, this has become a key technical problem that urgently needs to be solved in the research and development of aviation equipment.

[0003] In the early stages of research and development of aerospace axial piston pumps, digital simulation analysis technology has been widely used to study their vibration and noise characteristics. However, most current studies only indirectly infer the noise level by obtaining vibration characteristic indicators such as the acceleration and velocity of the shell structure, or use conventional simulation methods to input set excitation loads based on engineering experience values ​​to predict the sound pressure distribution of the vibration radiation noise field outside the shell. Summary of the Invention

[0004] In view of this, embodiments of this application provide a method, apparatus and electronic device for predicting vibration radiation noise of an aircraft axial piston pump, which facilitates the prediction of the sound pressure distribution of the external vibration radiation noise sound field of the aircraft axial piston pump.

[0005] To achieve the above-mentioned objectives, the following technical solution is adopted: In a first aspect, embodiments of this application provide a method for predicting vibration radiation noise of an aircraft axial piston pump, comprising: acquiring structural parameters and preset operating condition parameters of the aircraft axial piston pump, wherein the structural parameters include structural dimensional parameters characterizing the geometric shape of the components and material property parameters characterizing the physical properties of the components, and the preset operating condition parameters are operating parameters characterizing the aircraft axial piston pump under preset operating conditions; based on the structural parameters and preset operating condition parameters, analyzing the dynamic mechanism of the aircraft axial piston pump to obtain the piston dynamics law of the aircraft axial piston pump, wherein the piston dynamics law includes: the variation law of the frictional force on the piston, the variation law of the piston axial displacement with time, the variation law of the piston axial velocity and the variation law of the piston axial acceleration with time; and based on the structural parameters and the piston dynamics law... The following steps are taken: A multibody dynamics model of the aerospace axial piston pump is constructed, and a hydraulic model is constructed based on the structural parameters, preset operating parameters, and piston dynamics laws. The multibody dynamics model and the hydraulic model are coupled through a variable exchange mechanism to form a joint simulation model. The external casing of the aerospace axial piston pump in the joint simulation model is made flexible to obtain a rigid-flexible coupling simulation model. The rigid-flexible coupling simulation model is run to obtain the excitation load borne by the external casing of the aerospace axial piston pump. The excitation load is applied to the corresponding excitation point of the acoustic-vibration coupling model, and the sound pressure distribution of the vibration radiation noise sound field of the aerospace axial piston pump is calculated based on the acoustic-vibration coupling model. The acoustic-vibration coupling model is a simulation model used to simulate the interaction between casing vibration and the sound field.

[0006] According to one embodiment of this application, before obtaining the sound pressure distribution result of the vibration radiation noise sound field of the aerospace axial piston pump based on the acoustic-vibration coupling model, the method further includes: preprocessing the shell model of the aerospace axial piston pump, closing the opening area on the shell model to form a continuous and complete outer surface of the shell; generating an outer envelope mesh on the outer surface of the shell, and generating a convex mesh by extending the outer envelope mesh outward by a preset distance based on the outer envelope mesh; the type of the outer envelope mesh is a three-node triangular element; filling the space between the outer envelope mesh and the convex mesh to form an air domain mesh prototype; specifying acoustic fluid elements for the air domain mesh prototype, and performing the sound pressure distribution based on the acoustic fluid elements. The air domain mesh prototype is discretized to obtain an acoustic mesh. Using the geometric center of the housing model of the aerospace axial piston pump as a reference point, a hemispherical field point mesh is constructed outside the housing and within the acoustic field defined by the acoustic mesh. Measurement points are arranged on the hemispherical field point mesh. A data mapping relationship is established between the corresponding spatial positions of the hemispherical field point mesh and the acoustic mesh. The preprocessed housing model, acoustic mesh, and hemispherical field point mesh are imported into an acoustic simulation analysis environment. A structural acoustic coupling interface is configured between the surface of the housing model and the inner surface of the acoustic mesh to form the acoustic-vibration coupling model. The structural acoustic coupling interface is used to transfer the vibration displacement of the housing model to the acoustic mesh.

[0007] According to one embodiment of this application, the step of obtaining the sound pressure distribution result of the vibration radiation noise of the aircraft axial piston pump based on the acoustic-vibration coupling model includes: configuring the solution parameters of the acoustic-vibration coupling model; the solution parameters include: a simulation frequency range adapted to the preset working conditions of the aircraft axial piston pump for calculating the vibration radiation noise of the aircraft axial piston pump, a residual convergence threshold for the numerical solution of the sound field, and a calculation step size matching the simulation frequency range during the solution process of the acoustic-vibration coupling model; based on the solution parameters, numerically solving the sound field range defined by the acoustic mesh using the finite element method or the boundary element method to obtain the sound field value of the acoustic mesh, wherein the sound field value is the sound pressure related physical quantity value of all discrete nodes of the acoustic mesh; according to the data mapping relationship between the hemispherical field point mesh and the acoustic mesh, extracting the sound pressure value corresponding to the measurement point on the hemispherical field point mesh point by point from the sound field value to obtain the sound pressure distribution result of the vibration radiation noise of the aircraft axial piston pump.

[0008] According to one embodiment of this application, the components include: a main shaft, a cylinder block, a plunger, a slipper, a swashplate, and a distribution plate; the construction of a multibody dynamics model of the aerospace axial plunger pump based on the structural parameters and the plunger dynamics law includes: importing the three-dimensional models corresponding to the main shaft, cylinder block, plunger, slipper, swashplate, and distribution plate into a dynamics simulation tool, configuring the material properties corresponding to the material characteristic parameters for each of the three-dimensional models; configuring kinematic pairs for each three-dimensional model to form a constraint system that conforms to the actual motion relationship; the kinematic pairs include at least one of fixed pairs, rotary pairs, cylindrical pairs, bushings, ball joints, and planar pairs, which is also provided in this application; and loading the variation law of the frictional force on the plunger in the plunger dynamics law into the plunger component in the form of a scalar force to form the multibody dynamics model.

[0009] According to one embodiment of this application, the component further includes: a prime mover module, a spring damping module, and a moment of inertia module; the construction of the hydraulic model based on the structural parameters, preset operating parameters, and plunger dynamics includes: constructing a motor drive model based on the prime mover module, spring damping module, and moment of inertia module; wherein, the prime mover module is used to provide a constant speed matching the operating speed in the preset operating parameters, the spring damping module is used to adjust the stiffness and damping characteristics, and the moment of inertia module is used to configure energy loss-related parameters; the flow distribution plate model is constructed by calling predefined flow distribution plate functional elements of the fluid simulation tool, and a flow distribution plate model is constructed by calling predefined fluid friction pair elements to match the flow distribution plate model. A flow distribution pair model is included. The flow distribution plate model comprises a first input port, a second input port, and an output port. The first input port receives the piston rotational angular displacement signal obtained based on the time-varying laws of the piston axial displacement, piston axial velocity, and piston axial acceleration. The second input port receives the piston cavity working pressure signal and outputs the piston cavity flow rate change signal. The output port of the flow distribution plate model is connected to the input port of the flow distribution pair model. The flow distribution pair model simulates friction and leakage losses during oil suction and discharge processes. The flow distribution pair model also includes a main flow output port and a leakage output port. The main flow output port is connected to the hydraulic system oil circuit, and the leakage output port... The port is connected to the pump casing oil passage; and, the swashplate function model in the fluid simulation tool is called to construct a swashplate model, and inertial elements for simulating the inertial characteristics of the swashplate are configured; the swashplate model contains multiple ports, wherein the first port is used to connect to other swashplate models or inertial elements simulating swashplate inertia, the second port is used to connect to the motor drive model to receive the rotational angular velocity and angular displacement signals of the motor, the third port is used to connect to the first port of other swashplate models to receive the output torque of other swashplate models, the fourth port is used to connect to the plunger pair model, and the fifth port is used to connect to the distributor plate model to output the rotation angle information of the plunger; and, the plunger body, the plunger cavity dead zone volume model, and the plunger pair leakage module are connected. The plunger assembly model is formed by connecting the components. The plunger cavity dead zone volume model is equipped with a volume inlet, a volume-side leakage port, and a pressure signal output port. The working medium output port of the plunger body is connected to the volume inlet of the plunger cavity dead zone volume model to construct a medium transfer channel between the plunger body and the plunger cavity dead zone volume model. The medium input end of the plunger assembly leakage module is connected to the volume-side leakage port of the plunger cavity dead zone volume model to simulate leakage loss between the plunger assembly and the cylinder block. The pressure signal output port of the plunger cavity dead zone volume model is used to interface with the pressure signal input port of the slipper assembly leakage module. The medium output ends of the plunger assembly leakage module and the slipper assembly leakage module are respectively connected to the pump housing oil circuit.

[0010] According to one embodiment of this application, the process of flexibly processing the outer casing of the aerospace axial piston pump in the co-simulation model to obtain a rigid-flexible coupling simulation model includes: calling the flexibility processing function in the motion module of a dynamic simulation tool to perform flexibility processing on the outer casing component, generating a flexible body; replacing the corresponding rigid casing component in the co-simulation model with the flexible body, completing assembly and constraint adjustment, and forming the rigid-flexible coupling simulation model; or, establishing a finite element model of the outer casing of the aerospace axial piston pump using a finite element analysis tool; performing modal analysis on the finite element model to generate a modal neutral file; the modal neutral file includes modal characteristic parameters for indicating the outer casing of the aerospace axial piston pump; importing the modal neutral file into the dynamic simulation tool; transforming the outer casing of the aerospace axial piston pump into a flexible body based on the modal characteristic parameters; replacing the corresponding rigid casing component in the co-simulation model with the flexible body, completing assembly and constraint adjustment, and forming the rigid-flexible coupling simulation model.

[0011] According to one embodiment of this application, the step of obtaining the excitation load borne by the outer housing of the aerospace axial piston pump by running the rigid-flexible coupling simulation model includes: running the rigid-flexible coupling simulation model to simulate the actions performed by various internal components of the aerospace axial piston pump, hydraulic transmission, and the flexible deformation characteristics of the outer housing under preset operating parameters; identifying the internal excitation force that affects the vibration radiation noise of the housing based on the complete force response data of the housing, oil distributor cap, and mounting base output by the rigid-flexible coupling simulation model, wherein the internal excitation force includes: the force of the angular contact ball bearing on the mounting base, the force of the needle roller bearing transmitted to the housing via the distribution plate, the force of the swashplate cylindrical roller bearing on the mounting base, and the force of the follower piston on the oil distributor cap; collecting the dynamic change data of the internal excitation force under the preset operating parameters; wherein the dynamic change data includes: force amplitude, frequency distribution, and time change curve; and integrating the dynamic change data to obtain the excitation load borne by the outer housing of the aerospace axial piston pump.

[0012] According to one embodiment of this application, after constructing the multibody dynamics model of the aerospace axial piston pump, the method further includes: obtaining simulation data of the axial motion velocity and axial acceleration of the piston's center of mass corresponding to a first time node based on the multibody dynamics model, and comparing and verifying the values ​​of each simulation data with the corresponding physical quantities in the piston dynamics law; and, after constructing the hydraulic model, the method further includes: running the hydraulic model simulation to obtain the simulated values ​​of the outlet pressure and outlet flow under preset working conditions, and comparing and verifying the simulated values ​​of the outlet pressure with the measured values ​​of the outlet pressure, and the simulated values ​​of the outlet flow with the measured values ​​of the outlet flow.

[0013] Secondly, embodiments of this application provide a vibration radiation noise prediction device for an aircraft axial piston pump, comprising: an acquisition program unit for acquiring structural parameters and preset operating condition parameters of the aircraft axial piston pump, wherein the structural parameters include structural dimension parameters characterizing the geometric shape of the component and material property parameters characterizing the physical properties of the component, and the preset operating condition parameters are operating parameters characterizing the aircraft axial piston pump under preset operating conditions; an analysis program unit for analyzing the dynamic mechanism of the aircraft axial piston pump based on the structural parameters and preset operating condition parameters, and obtaining the piston dynamic law of the aircraft axial piston pump, wherein the piston dynamic law includes: the variation law of the frictional force on the piston, the variation law of the piston axial displacement with time, the variation law of the piston axial velocity and the variation law of the piston axial acceleration with time; and a construction program unit for constructing a system based on the structural parameters and the piston dynamic mechanism. The system employs mechanical principles to construct a multibody dynamics model of the aerospace axial piston pump, and a hydraulic model based on the structural parameters, preset operating parameters, and piston dynamics principles. A dynamic coupling program unit is used to couple the multibody dynamics model and the hydraulic model through a variable exchange mechanism to form a joint simulation model. The external casing of the aerospace axial piston pump in the joint simulation model is made more flexible to obtain a rigid-flexible coupling simulation model. The rigid-flexible coupling simulation model is then run to obtain the excitation load borne by the external casing of the aerospace axial piston pump. A solution program unit is used to apply the excitation load to the corresponding excitation point of the acoustic-vibration coupling model, and calculate the sound pressure distribution of the vibration radiation noise sound field of the aerospace axial piston pump based on the acoustic-vibration coupling model. The acoustic-vibration coupling model is a simulation model used to simulate the interaction between casing vibration and the sound field.

[0014] Thirdly, embodiments of this application provide an electronic device, the electronic device comprising: one or more processors; a memory; the memory storing one or more executable programs, the one or more processors reading the executable program code stored in the memory to run a program corresponding to the executable program code, for executing the vibration radiation noise prediction method for an aerospace axial piston pump as described in any of the first aspects.

[0015] The vibration radiation noise prediction method, device, and electronic equipment for aircraft axial piston pumps provided in this application obtain the structural parameters and preset operating condition parameters of the aircraft axial piston pump, and then analyze its dynamic mechanism based on these parameters to determine the variation law of friction force, axial displacement, velocity, and acceleration of the piston. Combining the above parameters and dynamic laws, a multibody dynamics model and a hydraulic model are constructed respectively, so that the two models respectively map the mechanical and hydraulic characteristics of the piston pump. Then, the two models are coupled through a variable exchange mechanism, and the outer shell of the aircraft axial piston pump is made flexible to obtain a rigid-flexible coupling simulation model, which can comprehensively simulate the complex operating state of the piston pump. Based on the rigid-flexible coupling simulation model, the excitation load borne by the shell under high-speed and high-pressure conditions is extracted, and the excitation load is applied to the acoustic-vibration coupling model used to simulate the interaction between shell vibration and sound field. Since the excitation load is more realistically derived from the rigid-flexible coupling simulation model simulating the actual operating state of the piston pump, compared with the method of setting the recorded load based on engineering experience, it is easier to accurately calculate the sound pressure distribution result of the external radiated sound field. Therefore, this application facilitates accurate prediction of the sound pressure distribution of the external vibration radiation noise of an aerospace axial piston pump, thereby enabling researchers to accurately grasp the level of external radiated noise. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic flowchart of an embodiment of the method for predicting vibration radiation noise of an aerospace axial piston pump according to this application; Figure 2 This is a schematic diagram of a multibody dynamics model of a plunger pump established in one embodiment of this application; Figure 3 This is a schematic diagram of a hydraulic simulation model established in one embodiment of this application; Figure 4 This is a schematic diagram of the connection of the AMESim co-simulation interface of the rigid-flexible coupling simulation model in one embodiment of this application; Figure 5 This is a schematic diagram of the force exerted by the follower piston on the outer housing in one embodiment of the application; Figure 6 This is a schematic diagram of an acoustic-vibration coupling model established in one embodiment of this application; Figure 7This is a sound pressure distribution cloud map of the external radiated sound field of the piston pump at a frequency of 770Hz, predicted by the vibration radiation noise prediction method of the aviation axial piston pump according to an embodiment of this application. Figure 8 This is a schematic diagram of the structural composition of an embodiment of the vibration radiation noise prediction device for an aerospace axial piston pump according to this application; Figure 9 This is a schematic diagram of an electronic device structure provided in an embodiment of this application. Detailed Implementation

[0018] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0019] It should be understood that the described embodiments are merely some, not all, of the embodiments in this application. All other embodiments obtained by those skilled in the art based on the embodiments in this application without inventive effort are within the scope of protection of this application.

[0020] Currently, for predicting the vibration radiation noise of aerospace axial piston pumps, existing technologies mostly infer noise levels indirectly by evaluating pump body vibration characteristics, or by using the boundary element method or finite element method to calculate isolated structural or acoustic models, without considering the dynamic and hydraulic characteristics of the piston pump. Furthermore, the excitation loads input to simulations often use simplified or assumed load conditions. Because these conditions differ significantly from the actual operating conditions of aerospace piston pumps, and are limited by boundary condition settings, they can only obtain the acoustic response within the computational domain, making it difficult to accurately predict and characterize the sound pressure distribution of the external radiated sound field. This results in an inability to accurately grasp the external radiated noise situation in the early stages of research and development.

[0021] Therefore, see Figure 1 As shown in the figure, this application provides a method for predicting vibration radiation noise of an aerospace axial piston pump, including: S110. Obtain the structural parameters and preset operating condition parameters of the aviation axial piston pump. The structural parameters include structural dimension parameters characterizing the geometric shape of the component and material property parameters characterizing the physical properties of the component. The preset operating condition parameters are the working parameters characterizing the aviation axial piston pump under preset operating conditions.

[0022] Specifically, the structural dimensions in the structural parameters may include geometric data related to components such as spindle diameter, cylinder thickness, plunger distribution circle radius, swashplate tilt angle, plunger diameter, plunger guide length, and contact section length. The material property parameters may include physical property data such as density, elastic modulus, and Poisson's ratio of each component. For example, the preset operating condition parameters may include parameters reflecting the actual operating state of the plunger pump, such as operating speed, operating pressure, and medium temperature. The preset operating condition parameters can be obtained by consulting design drawings, material specifications, mechanical design manuals, or preset according to the actual usage requirements of aviation equipment.

[0023] S120. Based on the structural parameters and preset operating parameters, analyze the dynamic mechanism of the aviation axial piston pump to obtain the piston dynamic law of the aviation axial piston pump. The piston dynamic law includes: the variation law of the friction force on the piston, the variation law of the piston axial displacement with time, the variation law of the piston axial motion speed and the variation law of the piston axial acceleration with time.

[0024] Specifically, by combining structural parameters such as the radius of the plunger distribution circle and the swashplate tilt angle with preset working parameters such as the spindle speed and working pressure, the force situation of the plunger slipper assembly during the movement is analyzed through dynamic theory to determine the fluctuation law of the magnitude of the friction force between the plunger and the cylinder over time; and, based on the basic principles of kinematics, mathematical expressions for the axial displacement, velocity and acceleration of the plunger are derived, thereby obtaining the variation law of the three over time.

[0025] Specifically, the plunger slipper assembly is the main component for energy conversion and motion transmission in the axial plunger pump. The load situation during the oil discharge stage is analyzed as follows: The forces on the plunger slipper assembly mainly include: (1) The axial hydraulic pressure Fb acting on the bottom of the plunger is: In the formula, d is the plunger diameter; (2) The reciprocating linear motion of the plunger relative to the cylinder is a variable acceleration motion, and its axial inertial force Fg is: In the formula, R is the total mass of the plunger and slipper; R is the radius of the plunger distribution circle. The swashplate inclination angle; ω is the cylinder block rotation angle; ω is the angular velocity of the main shaft rotation; (3) The centrifugal reaction force Fa generated by the plunger moving in a circular motion with the cylinder block is: (4) The support reaction force FN of the swashplate on the skate shoe acts perpendicularly to the bottom surface of the skate shoe and is decomposed into radial force and axial force. The radial force will generate load torque and contact stress, and the axial force will balance the hydraulic pressure and other axial forces. Its calculation formula is: In the formula, The coefficient of friction is affected by the properties of the mating materials; generally, it is 0.15 between bronze and steel, and 0.11 between cast iron and steel. The structural parameter represents the contact relationship between the plunger and the cylinder block, and its expression is: ;in, The upper section of the effective guide length of the plunger, that is, the mating length from the center of the plunger ball head to the upper end face of the cylinder bore; The effective guide length of the plunger is the lower section, that is, the fitting length from the center of the plunger ball head to the lower end face of the cylinder bore; (5) The contact stresses F1 and F2 between the plunger and the cylinder, for the plunger initially located at the top dead center, that is, the highest position of the plunger's stroke, the force balance analysis is as follows: ;in This is the resultant force of the plunger in the y-direction, which is perpendicular to the axis of the main shaft. The resultant force of the plunger in the z-direction, which is parallel to the axis of the main shaft; This represents the total torque of the plunger about the origin O; This represents the distance from the center of gravity of the plunger and slipper to the origin O, where the origin O is the center of rotation of the cylinder block; This is the total guide length of the plunger, which is the complete fit length of the plunger within the cylinder bore. This is the distance from the center of the plunger ball head to the upper end face of the plunger guide section; This is the support reaction force of the swashplate on the shoe; This represents the contact stress between the plunger and the upper section of the cylinder block, with its direction along the positive y-axis. The contact stress between the plunger and the lower section of the cylinder block; where, in the equation system , , and Since all variables are unknown, an additional equation is needed to solve the problem, combining the principle of similarity of force distribution triangles. Due to centrifugal reaction force F a Relatively small, neglecting the centrifugal reaction force F a Solving for: (6) Friction between the plunger and the cylinder and for: ; ;in, The coefficient of friction between the piston and the cylinder contact surface is determined by the properties of the contact pairing materials. For example, it is 0.15 when bronze is paired with steel, and 0.11 when cast iron is paired with steel.

[0026] The kinematic characteristics of the plunger are studied as follows: According to the plunger's motion law, its axial displacement S is: S = Rtanγ(1−cosφ), where R is the radius of the plunger distribution circle; γ is the swashplate tilt angle; and φ is the cylinder block rotation angle. Taking the first derivative of this displacement formula with respect to time, the axial velocity v of the plunger can be obtained as: In the formula, ω is the angular velocity of the main shaft rotation, and v is in the same direction as the axial motion of the piston. When sinφ>0, it is outward along the axial direction, and when sinφ<0, it is inward along the axial direction. Taking the first derivative of this velocity formula with respect to time, the axial acceleration of the piston can be obtained. for, acceleration The direction of the axial acceleration is the same as that of the plunger. When cosφ>0, it is outward along the axial direction, and when cosφ<0, it is inward along the axial direction.

[0027] S130. Based on the structural parameters and the piston dynamics law, construct a multibody dynamics model of the aerospace axial piston pump, and based on the structural parameters, preset working condition parameters and piston dynamics law, construct a hydraulic model.

[0028] In some optional embodiments, when constructing the multibody dynamics model, core components such as the main shaft, cylinder block, piston, slipper, swashplate, and distributor plate may be included, while auxiliary components with minor impact on dynamic characteristics are not considered. After importing the 3D models of each core component into the simulation tool, interference checks are performed first, and then material properties are configured. The model is then built by combining the frictional force variation law in piston dynamics. When constructing the hydraulic model, the working pressure and speed requirements in the preset working condition parameters are referenced, and the motion parameters in piston dynamics are combined to build a model covering functional modules such as motor drive, distributor, and piston pair, thereby reflecting the mechanical and hydraulic characteristics of the piston pump respectively.

[0029] S140. The multibody dynamics model and the hydraulic model are coupled through a variable exchange mechanism to form a joint simulation model. The outer casing of the aerospace axial piston pump in the joint simulation model is made flexible to obtain a rigid-flexible coupling simulation model. The rigid-flexible coupling simulation model is run to obtain the excitation load borne by the outer casing of the aerospace axial piston pump.

[0030] It should be noted that in existing technologies, simulation models of aerospace axial piston pumps are typically constructed as separate multibody dynamics or hydraulic models. Because real-time feedback and variable exchange are not possible, the mechanical and hydraulic characteristics of the model are separated, failing to accurately represent the dynamic interaction between fluid pressure and structural motion. Furthermore, the shell is often idealized, typically treating the outer shell of the aerospace axial piston pump as a rigid body, ignoring the flexible deformation that occurs under high-speed, high-pressure conditions. This can lead to significant discrepancies between the extracted excitation load and the actual operating conditions of the aerospace axial piston pump. When used as input data for acoustic analysis, this distortion affects the accuracy of predicting the sound pressure distribution of the vibration-radiated noise field of the aerospace axial piston pump.

[0031] Therefore, in this embodiment, by coupling the multibody dynamics model and the hydraulic model through a variable exchange mechanism, the actual working state of the aerospace axial piston pump can be simulated more realistically. Furthermore, compared to conventional rigidification, this embodiment transforms the outer shell into a flexible body variable, which can more realistically reproduce the actual state of the shell undergoing flexible deformation after the internal excitation force acts on it. This, to a certain extent, helps improve the accuracy of predicting the sound pressure distribution of the vibration radiation noise field of the aerospace axial piston pump.

[0032] S150. Apply the excitation load to the corresponding excitation point of the acoustic-vibration coupling model, and calculate the sound pressure distribution of the vibration radiation noise sound field of the aviation axial piston pump based on the acoustic-vibration coupling model; wherein, the acoustic-vibration coupling model is a simulation model used to simulate the interaction between shell vibration and sound field.

[0033] For example, the extracted excitation load is applied to the corresponding excitation point of the acoustic-vibration coupling model according to the actual force position. The model is then numerically solved using simulation tools to obtain the sound pressure values ​​at different locations outside the plunger pump, forming a complete sound field sound pressure distribution result and intuitively presenting the distribution state of the plunger pump vibration radiation noise.

[0034] The vibration radiation noise prediction method, device, and electronic equipment for aircraft axial piston pumps provided in this application acquire the structural parameters and preset operating condition parameters of the aircraft axial piston pump. Based on these parameters, the dynamic mechanism is analyzed to determine the variation laws of frictional force, axial displacement, velocity, and acceleration of the piston. A multibody dynamics model and a hydraulic model are constructed by combining the above parameters and dynamic laws, respectively mapping the mechanical and hydraulic characteristics of the piston pump. Then, the two models are coupled through a variable exchange mechanism, and the external casing of the aircraft axial piston pump is made flexible to obtain a rigid-flexible coupled simulation model, which can comprehensively... By simulating the complex operating conditions of a plunger pump, the excitation load borne by the shell under high-speed and high-pressure conditions is extracted based on the rigid-flexible coupling simulation model. The excitation load is then applied to the acoustic-vibration coupling model used to simulate the interaction between shell vibration and sound field. Since the excitation load is more realistically derived from the rigid-flexible coupling simulation model that simulates the actual operating conditions of a plunger pump, compared to the method of setting the recorded load based on engineering experience, it is easier to accurately calculate the sound pressure distribution of the external radiated sound field. This facilitates the prediction of the sound pressure distribution of the external vibration radiated noise of the aerospace axial plunger pump, allowing researchers to more accurately grasp the level of external radiated noise.

[0035] In some embodiments, before obtaining the sound pressure distribution of the vibration radiation noise sound field of the aerospace axial plunger pump based on the acoustic-vibration coupling model, the method further includes the following steps: S210. Preprocess the housing model of the aviation axial piston pump to close the opening area on the housing model and form a continuous and complete outer surface of the housing.

[0036] Specifically, this can be performed in the Acoustics module of Simcenter3D software. The opening areas that need to be closed for preprocessing include bolt holes, valve mounting holes, and oil inlet / outlet ports on the housing. By closing these discontinuous areas, the outer surface of the housing is ensured to be complete and continuous, thus providing a regular geometry for subsequent mesh generation.

[0037] S220. An outer envelope mesh is generated on the outer surface of the shell, and a convex mesh is generated by extending the outer envelope mesh outward by a preset distance; the type of the outer envelope mesh is a three-node triangular element.

[0038] The outer envelope mesh is a surface mesh generated by conforming to the outer surface of the shell. Its specific element type is a three-node triangular element, identified as CTRIA3, which is used for discretization of complex shell surfaces. The preset distance of outward expansion can be set according to the shell size and the sound field simulation range to ensure that the convex mesh can completely cover the main propagation area of ​​shell vibration radiation noise. The generation of the convex mesh maintains geometric consistency with the outer envelope mesh to avoid mesh breakage or overlap.

[0039] S230. Fill the space between the outer envelope grid and the convex grid to form an air domain grid prototype.

[0040] The space between the outer envelope mesh and the convex mesh is the core medium environment for noise propagation, namely the air domain. The cavity between the two meshes can be filled by generating solids from shell elements using the Acoustics module of Simcenter 3D software. Once filled, the prototype of the air domain mesh is formed, which is used to simulate the medium environment for sound field propagation.

[0041] S240. Assign acoustic fluid elements to the air domain mesh prototype, and perform mesh discretization processing on the air domain mesh prototype based on the acoustic fluid elements to obtain an acoustic mesh.

[0042] Specifically, the acoustic fluid unit can be a four-node tetrahedral acoustic fluid unit.

[0043] S250. Using the geometric center of the housing model of the aviation axial piston pump as a reference point, a hemispherical field point grid is constructed outside the housing and within the acoustic field range defined by the acoustic grid, and measuring points are arranged on the hemispherical field point grid; wherein, a data mapping relationship is established between the corresponding spatial positions of the hemispherical field point grid and the acoustic grid.

[0044] For example, referring to the ISO 3744 testing standard and following the general specifications for acoustic testing, the radius of the hemispherical field point grid can be set to 1m, and the number of measuring points can be 19. In this way, sound field data from different directions can be captured comprehensively.

[0045] S260. Import the preprocessed shell model, acoustic mesh, and hemispherical field point mesh into the acoustic simulation analysis environment, and configure a structural acoustic coupling interface between the surface of the shell model and the inner surface of the acoustic mesh to form the acoustic-vibration coupling model, such as... Figure 6 As shown; the structural acoustic coupling interface is used to transmit the vibration displacement of the shell model to the acoustic mesh.

[0046] In some embodiments, obtaining the sound pressure distribution of the vibration radiation noise sound field of the aerospace axial plunger pump based on the acoustic-vibration coupling model includes: S310. Configure the solution parameters of the acoustic-vibration coupling model; the solution parameters include: the simulation frequency range for solving the vibration radiation noise of the aviation axial piston pump under the preset working conditions of the aviation axial piston pump, the residual convergence threshold for the numerical solution of the sound field, and the calculation step size that matches the simulation frequency range during the solution process of the acoustic-vibration coupling model.

[0047] Specifically, the simulation frequency range can be set according to the vibration and noise main frequency characteristics of the high-speed and high-pressure working condition of the aviation axial piston pump. The residual convergence threshold is generally set to 1e-6, and the calculation step size is generally selected as 1 / 50 to 1 / 20 of the upper limit of the simulation frequency range.

[0048] S320. Based on the solution parameters, the sound field range defined by the acoustic mesh is numerically solved using the finite element method or the boundary element method to obtain the sound field values ​​of the acoustic mesh. The sound field values ​​are the sound pressure-related physical quantities of all discrete nodes of the acoustic mesh. The numerical solution process is completed in the Acoustics module of the Simcenter D software based on the solution parameters.

[0049] S330. Based on the data mapping relationship between the hemispherical field point grid and the acoustic grid, extract the sound pressure value corresponding to the measuring point on the hemispherical field point grid point by point from the sound field values ​​to obtain the sound pressure distribution result of the vibration radiation noise sound field of the aviation axial piston pump.

[0050] Specifically, the sound pressure distribution results can be presented intuitively in the form of sound pressure distribution cloud maps or data tables to show the noise intensity at different locations.

[0051] To help understand the technical solutions and effects of the embodiments of this application, the following detailed explanation is provided in conjunction with the specific solution process after completing the acoustic-vibration coupling model in the Acoustics module of Simcenter 3D software: The Acoustics module receives the dynamic excitation load borne by the housing of an aerospace axial piston pump, transmitted based on a rigid-flexible coupling simulation model. The excitation load is the full dynamic time-varying load extracted after the rigid-flexible coupling simulation model runs, including the force of the angular contact ball bearing on the mounting seat, the force of the needle roller bearing transmitted to the housing through the distribution plate, the force of the swashplate large / small cylindrical roller bearing on the mounting seat, and the force of the follower piston on the oil distributor cap. It includes the time-varying characteristics of the load amplitude and frequency, as well as the spatial coordinate information of the corresponding excitation point.

[0052] Based on the spatial coordinate information of the excitation load, various excitation loads are accurately mapped and applied to the corresponding shell excitation point mesh nodes in the acoustic-vibration coupling model. Furthermore, the time-varying amplitude and frequency characteristics of the dynamic excitation load are decoupled and transformed into a load excitation signal adapted to the frequency domain solution of the acoustic field, so that the full dynamic excitation characteristics of the excitation load are completely transmitted to the shell flexible body model.

[0053] After the excitation load is applied, the system receives the calculation parameters configured by the operator to adapt to the preset working conditions of the aviation axial piston pump, including the simulation frequency range, residual convergence threshold, and calculation step size of the matching frequency range. After receiving the solution parameters, the Helmholtz equation is discretized using each tetrahedral element of the acoustic mesh as an independent local spatial unit. This process transforms the Helmholtz equation, which characterizes the continuous sound field propagation domain, into a local algebraic equation for each tetrahedral element. Based on the node association relationship of the acoustic mesh, all local algebraic equations are solved simultaneously to obtain a global set of nodal equations with the sound pressure of all discrete nodes of the acoustic mesh as unknowns. Dynamic boundary conditions are applied to the acoustic-vibration coupling interface. The vibration displacement generated by the flexible deformation of the shell under excitation load is transformed into the normal vibration velocity boundary conditions of the inner surface of the acoustic mesh, and applied to the mesh nodes corresponding to each nodal equation set. In addition, non-reflection boundary conditions are configured on the outer surface of the acoustic mesh. According to the simulation frequency range and calculation step size, the simulation frequency start point, frequency interval and frequency end point are determined. Starting from the simulation frequency start point, frequency points are selected sequentially according to the preset calculation step size, and numerical iteration is performed on the overall nodal equation set one by one until the residual value reaches the preset residual convergence threshold. The sound pressure related physical quantity values ​​of the discrete nodes corresponding to all frequency points of the acoustic mesh are obtained, forming a numerical set of acoustic mesh sound field covering the entire frequency domain.

[0054] Based on the numerical mapping relationship, from the acoustic grid sound field numerical set, the spatial coordinates of each measuring point on the hemispherical field point grid are matched and linearly interpolated point by point to extract the sound pressure value corresponding to each measuring point. The sound pressure values ​​of all measuring points are integrated and processed to generate a visualized sound pressure distribution cloud map containing the sound pressure distribution patterns at different spatial locations outside the aircraft axial plunger pump, and the sound pressure distribution results of the vibration radiation noise sound field of the aircraft axial plunger pump are output. For example, see... Figure 7 The image shows the sound pressure distribution cloud map of the vibration radiation noise field of an aircraft axial piston pump at a frequency of 770 Hz.

[0055] In this embodiment, the dynamic excitation load, the normal velocity boundary generated by the shell vibration, and the non-reflection propagation characteristics of the infinite domain sound field extracted from the simulated operation of the plunger pump are transformed into mathematical solution conditions for the global node equation system through grid nodes. This allows the sound pressure value of the grid nodes obtained from the external noise calculation of the plunger pump to correspond to the physical location of the actual sound field space outside the plunger pump shell. As a result, the obtained vibration radiation noise sound field distribution results can truly reflect the radiation noise distribution law in the actual operation of the plunger pump. Therefore, it is convenient to accurately predict the sound pressure distribution of the external vibration radiation noise sound field of the aerospace axial plunger pump.

[0056] See Figure 2 In some embodiments, obtaining the structural parameters of the aerospace axial piston pump mainly involves the following components: main shaft, cylinder block, piston, slipper, swashplate, and distributor plate; the construction of the multibody dynamics model of the aerospace axial piston pump based on the structural parameters and the piston dynamics law includes: S410. Import the three-dimensional models corresponding to the main shaft, cylinder block, plunger, slipper, swashplate and distributor plate into the dynamics simulation tool, and configure the material properties corresponding to the material property parameters for each of the three-dimensional models.

[0057] Specifically, before importing, the 3D model needs to be checked for interference to ensure that there is no geometric interference between the components. When configuring material properties, parameters such as density, elastic modulus, and Poisson's ratio need to be accurately entered, and the influence of auxiliary components is not considered at this time.

[0058] S420. Configure kinematic pairs for each three-dimensional model to form a constraint system that conforms to the actual motion relationship; the kinematic pairs include at least one of fixed pairs, revolute pairs, cylindrical pairs, bushings, ball joints and planar pairs.

[0059] For example, a rotary joint is configured between the spindle and the cylinder block, a cylindrical joint is configured between the plunger and the cylinder block, and a planar joint is configured between the slipper and the swashplate. By setting reasonable constraints, the actual motion relationship of each component of the plunger pump can be restored.

[0060] S430. The variation law of friction force on the plunger in the plunger dynamics law is applied to the plunger component in the form of scalar force to form the multibody dynamics model.

[0061] In some alternative embodiments, among the three friction pairs of the plunger pump, the slipper pair and the distribution pair have a relatively small impact on the dynamic simulation due to oil film lubrication. Therefore, only the friction of the plunger pair is considered, and the applied scalar force value can be calculated based on the friction force variation law obtained from the dynamic mechanism analysis, which is used to accurately simulate the friction effect between the plunger and the cylinder.

[0062] Continue reading Figure 2 The multibody dynamics model constructed in this embodiment shows the assembly relationship of core components such as the main shaft, cylinder block, plunger, slipper, swashplate, and distributor plate. It also marks the positions of key supporting components such as angular contact ball bearings, needle roller bearings, and swashplate large / small cylindrical roller bearings, intuitively presenting the overall structure of the model and the connection method of each component. This can provide a clear geometric reference for setting kinematic pair constraints and applying external forces.

[0063] Figure 3 This is a schematic diagram of a hydraulic simulation model used to simulate the internal oil flow characteristics of a piston pump. The piston pump super-component in this model integrates the previously established distribution plate model, swashplate model, piston pair model, and slipper pair model, representing the media transmission path and signal exchange of the hydraulic system. The throttle orifice is used to simulate the load on the piston pump. See also... Figure 3 In some embodiments, the component further includes a prime mover module, a spring damping module, and a moment of inertia module. The construction of the hydraulic model based on the structural parameters, preset operating parameters, and piston dynamics includes: S510. Construct a motor drive model based on the prime mover module, spring damping module, and moment of inertia module; wherein, the prime mover module is used to provide a constant speed matching the working speed in the preset operating condition parameters, the spring damping module is used to adjust the stiffness and damping characteristics, and the moment of inertia module is used to configure energy loss related parameters.

[0064] Specifically, the motor drive model can be constructed based on AMESim software. The prime mover module simulates external drive to provide stable speed, the spring damping module adapts to the overall stiffness and damping adjustment requirements of the system, and the moment of inertia module is specifically set with energy loss parameters such as Coulomb friction torque and viscous damping to form a complete power input unit.

[0065] S520. A distribution disk model is constructed by calling predefined distribution disk functional elements from a fluid simulation tool, and a distribution pair model matching the distribution disk model is constructed by calling predefined fluid friction pair elements. The distribution disk model includes a first input port, a second input port, and an output port. The first input port is used to receive the plunger rotational angular displacement signal obtained based on the time-varying law of the plunger axial displacement, the plunger axial motion speed, and the plunger axial acceleration. The second input port is used to receive the plunger cavity working pressure signal and output the plunger cavity flow rate change signal. The output port of the distribution disk model is connected to the input port of the distribution pair model. The distribution pair model is used to simulate friction and leakage losses during oil suction and discharge processes. The distribution pair model is also configured with a main flow output port and a leakage output port. The main flow output port is connected to the hydraulic system oil circuit, and the leakage output port is connected to the pump casing oil circuit.

[0066] For example, the distribution plate model adopts the predefined distribution plate super element in AMESim software. Its first input port is connected to the swashplate model to receive angular displacement signals, and its second input port is connected to the plunger pair model to transmit pressure and flow signals. The distribution pair model corresponding to the output port realizes the transmission of working medium and leakage return through the main flow and leakage output ports, respectively.

[0067] S530. Construct a swashplate model by calling the swashplate function model in the fluid simulation tool, and configure inertial elements for simulating the inertial characteristics of the swashplate. The swashplate model contains multiple ports, wherein the first port is used to connect to other swashplate models or inertial elements simulating swashplate inertia, the second port is used to connect to the motor drive model to receive the rotational angular velocity and angular displacement signals of the motor, the third port is used to connect to the first port of other swashplate models to receive the output torque of other swashplate models, the fourth port is used to connect to the plunger pair model, and the fifth port is used to connect to the distributor plate model to output the rotation angle information of the plunger.

[0068] S540. Connect the plunger body, the plunger cavity dead zone volume model, and the plunger pair leakage module to form the plunger pair model; wherein, the plunger cavity dead zone volume model is configured with a volume inlet, a volume-side leakage port, and a pressure signal output port; the working medium output port of the plunger body is connected to the volume inlet of the plunger cavity dead zone volume model to construct a medium transmission channel between the plunger body and the plunger cavity dead zone volume model; the medium input end of the plunger pair leakage module is connected to the volume-side leakage port of the plunger cavity dead zone volume model to simulate leakage loss between the plunger pair and the cylinder block; the pressure signal output port of the plunger cavity dead zone volume model is used to interface with the pressure signal input port of the slipper pair leakage module; the medium output ends of the plunger pair leakage module and the slipper pair leakage module are respectively connected to the pump housing oil circuit to simulate the leakage characteristics of the hydraulic system.

[0069] After the multibody dynamics model and the hydraulic model are constructed, the two models are coupled through a variable exchange mechanism. Specifically, this includes making the external casing of the aerospace axial piston pump more flexible and setting up a co-simulation interface between software programs, such as... Figure 4 As shown, a rigid-flexible coupling simulation model of an aerospace axial piston pump is established. Force sensors receive the hydraulic pressure at the bottom of the 11 pistons in the hydraulic model and transmit this pressure to the rigid-flexible coupling simulation model of the piston pump via a co-simulation interface module. The co-simulation interface module also receives the spindle speed signal from the rigid-flexible coupling dynamics model and transmits this signal to the hydraulic simulation model via a motor drive module, enabling data interaction between the two models. The specific implementation method for making the outer casing of the aerospace axial piston pump flexible to obtain the rigid-flexible coupling simulation model includes: S610A, calling the flexibility processing function in the motion module of the dynamics simulation tool to perform flexibility processing on the outer casing component, generating a flexible body; S620A, replacing the corresponding rigid casing component in the co-simulation model with the flexible body, completing assembly and constraint adjustment, and forming the rigid-flexible coupling simulation model.

[0070] In another alternative embodiment, the specific implementation of making the outer casing of the aerospace axial piston pump flexible to obtain a rigid-flexible coupling simulation model may include: S610B, establishing a finite element model of the outer casing of the aerospace axial piston pump using a finite element analysis tool; S620B, generating a modal neutral file (MNF) after performing modal analysis on the finite element model; the modal neutral file includes modal characteristic parameters for indicating the outer casing of the aerospace axial piston pump; S630, importing the modal neutral file into a dynamic simulation tool, and transforming the outer casing of the aerospace axial piston pump into a flexible body based on the modal characteristic parameters; S640, replacing the corresponding rigid shell component in the co-simulation model with the flexible body, completing the assembly and constraint adjustment, and forming the rigid-flexible coupling simulation model.

[0071] Specifically, the dynamic simulation tool Simcenter 3D can be used to implement the flexible scheme of the first embodiment described above using the AutoFlex automatic flexibility function of the Motion module. Considering the complex structure of the aerospace axial piston pump, the flexible implementation scheme of importing external modal neutral files is preferred.

[0072] In some relevant testing scenarios, the vibration load borne by the external casing of a piston pump is typically determined by testing personnel based on engineering experience and reference to load data from similar piston pumps, or by manually inputting load-related parameters through simulation software. However, this method of obtaining the vibration load does not take into account the actual movement of internal components, hydraulic transmission, and casing flexibility deformation during the actual operation of the piston pump. It fails to reflect the actual stress state transmitted from the key internal components to the casing, leading to a deviation between the set vibration load and the actual load borne by the pump, thus affecting the accuracy and reliability of vibration radiation noise prediction.

[0073] Therefore, in some embodiments, the step of running the rigid-flexible coupling simulation model to obtain the excitation load borne by the outer housing of the aerospace axial piston pump includes: S710. Run the rigid-flexible coupling simulation model to simulate the actions performed by the internal components of the aviation axial piston pump, the hydraulic transmission, and the flexible deformation characteristics of the external shell under preset working conditions.

[0074] For example, during operation, the high-speed rotation of the spindle and cylinder, the reciprocating motion of the piston, the pressure transmission of hydraulic oil, and the flexible deformation of the outer casing under internal forces can be simulated to restore the real operating state of the aviation axial piston pump under high-speed and high-pressure conditions.

[0075] S720. Based on the complete force response data of the housing, oil distributor cap, and mounting base output by the rigid-flexible coupling simulation model, identify the internal excitation forces that affect the vibration radiation noise of the housing. The internal excitation forces include: the force of the angular contact ball bearing on the mounting base, the force of the needle roller bearing transmitted to the housing through the distribution plate, the force of the swash plate cylindrical roller bearing on the mounting base, and the force of the follower piston on the oil distributor cap.

[0076] S730. Collect dynamic change data of the internal excitation force under the preset working conditions; the dynamic change data includes: force amplitude, frequency distribution, and time change curve.

[0077] See Figure 4 and Figure 5 In some optional embodiments, dynamic data of four types of excitation forces can be collected in real time through force sensing in simulation software. For example, the fluctuation curve of the force exerted by the follower piston on the oil distributor cap over time. Since the oil distributor cap and the outer shell are rigidly connected, the force exerted by the follower piston on the oil distributor cap is ultimately applied to the outer shell. Its amplitude and frequency distribution directly reflect the dynamic characteristics of the excitation load, providing accurate time domain and frequency domain data for acoustic-vibration coupling analysis.

[0078] S740. The dynamically changing data is integrated to obtain the excitation load borne by the outer casing of the aerospace axial piston pump. During the data integration process, interference signals need to be removed, and the effective load data directly related to the casing vibration radiation noise is retained.

[0079] In this embodiment, a rigid-flexible coupling simulation model, which couples a multibody dynamics model with a hydraulic model and features a flexible outer casing, is used to simulate the actions of various moving parts inside the aerospace axial piston pump under preset operating parameters, the hydraulic oil transmission process, and the flexible deformation characteristics of the outer casing caused by the movement of internal parts. This model simulates the aerospace axial piston pump's near-realistic operating state, replacing the manual experience-based setting method and fundamentally solving the problem of existing technology being out of touch with actual operating conditions. Simultaneously, the model obtains the actual stress data of the casing, oil distributor cap, and mounting base, identifies key internal excitation forces, and integrates them into the actual excitation load borne by the casing. This ensures that the load data closely matches the actual working conditions of the pump. The near-realistic and accurate excitation load serves as the data input for subsequent acoustic-vibration coupling model calculations, effectively guaranteeing the accuracy of vibration radiation noise prediction.

[0080] Understandably, in the simulation modeling of aerospace axial piston pumps, the accuracy of the multibody dynamics model and the hydraulic model will affect the effectiveness of subsequent coupled simulations, excitation load acquisition, and vibration radiation noise prediction. After constructing the multibody dynamics model and the hydraulic model based on structural parameters, piston dynamics laws, and preset operating parameters, the output results may deviate from the actual working characteristics of the aerospace axial piston pump due to issues such as deviations in structural parameter settings, unreasonable constraints, and deviations in hydraulic characteristic simulation. Directly using an unverified model in subsequent applications will affect the reliability of the final noise prediction results.

[0081] Therefore, in some embodiments, after constructing the multibody dynamics model of the aerospace axial piston pump, the method further includes: S810, obtaining the axial motion velocity simulation data and axial acceleration simulation data of the piston's center of mass corresponding to the first time node based on the multibody dynamics model, and comparing and verifying the values ​​of the simulation data with the corresponding physical quantities in the piston dynamics law.

[0082] Specifically, the comparative verification requires selecting multiple key time points, extracting the simulation results of the axial velocity and acceleration of the plunger's center of mass, and comparing them one by one with the theoretical analytical values ​​derived from the dynamic mechanism in S120. If the deviation between the simulation data and the theoretical values ​​is within the allowable range, the multibody dynamics model verification is successful.

[0083] S820. After constructing the hydraulic model, the hydraulic model is run to simulate and obtain the simulated values ​​of the outlet pressure and outlet flow under the preset working conditions. The simulated values ​​of the outlet pressure are compared with the measured values ​​of the outlet pressure, and the simulated values ​​of the outlet flow are compared with the measured values ​​of the outlet flow.

[0084] For example, the preset working conditions can be selected from the typical working pressure and speed of an aviation axial piston pump. The time series data of outlet pressure and flow rate are obtained through hydraulic model simulation, and then compared and verified with the measured data collected by pressure sensor and flow sensor in the experimental test.

[0085] In this embodiment, by verifying the multibody dynamics model and the hydraulic model respectively, it is ensured that the two types of models can realistically reproduce the actual motion characteristics and hydraulic transmission characteristics of the aircraft axial piston pump, which facilitates the reliability of the rigid-flexible coupling simulation model constructed by the coupling of the multibody dynamics model and the hydraulic model.

[0086] Example 2 See Figure 8 As shown in the figure, this application provides a vibration radiation noise prediction device for an aircraft axial piston pump, comprising: The acquisition program unit 210 is used to acquire the structural parameters and preset operating condition parameters of the aviation axial piston pump. The structural parameters include structural dimension parameters that characterize the geometric shape of the component and material property parameters that characterize the physical properties of the component. The preset operating condition parameters are the working parameters that characterize the aviation axial piston pump in a preset operating state. Analysis program unit 220 is used to analyze the dynamic mechanism of the aviation axial piston pump based on the structural parameters and preset working condition parameters, and obtain the piston dynamic law of the aviation axial piston pump. The piston dynamic law includes: the variation law of the friction force on the piston, the variation law of the piston axial displacement with time, the variation law of the piston axial motion velocity and the variation law of the piston axial acceleration with time. The program unit 230 is used to construct a multibody dynamics model of the aerospace axial piston pump based on the structural parameters and the piston dynamics law, and to construct a hydraulic model based on the structural parameters, preset working condition parameters and piston dynamics law. The dynamic coupling program unit 240 is used to couple the multibody dynamics model and the hydraulic model through a variable exchange mechanism to form a joint simulation model, and to perform flexible processing on the outer casing of the aerospace axial piston pump in the joint simulation model to obtain a rigid-flexible coupling simulation model, and to run the rigid-flexible coupling simulation model to obtain the excitation load borne by the outer casing of the aerospace axial piston pump. The calculation program unit 260 is used to apply the excitation load to the corresponding excitation point of the acoustic-vibration coupling model, and calculate the sound pressure distribution of the vibration radiation noise sound field of the aviation axial piston pump based on the acoustic-vibration coupling model; wherein, the acoustic-vibration coupling model is a simulation model used to simulate the interaction between shell vibration and sound field.

[0087] The vibration radiation noise prediction device for an aircraft axial piston pump provided in this application obtains the structural parameters and preset operating condition parameters of the aircraft axial piston pump, and then analyzes its dynamic mechanism based on these parameters to determine the variation law of friction force, axial displacement, velocity, and acceleration of the piston. Combining the above parameters and dynamic laws, a multibody dynamics model and a hydraulic model are constructed respectively, so that the two models respectively map the mechanical and hydraulic characteristics of the piston pump. Then, the two models are coupled through a variable exchange mechanism, and the outer shell of the aircraft axial piston pump is made flexible to obtain a rigid-flexible coupled simulation model, which can comprehensively simulate the piston. In complex pump operation conditions, the excitation load borne by the shell under high-speed and high-pressure conditions is extracted based on the rigid-flexible coupling simulation model. The excitation load is applied to the acoustic-vibration coupling model used to simulate the interaction between shell vibration and sound field. Since the excitation load is more realistically derived from the rigid-flexible coupling simulation model simulating the actual operation of the plunger pump, compared with the recorded load method of setting input based on engineering experience, it is easier to accurately calculate the sound pressure distribution of the external radiated sound field. Therefore, it is easier to predict the sound pressure distribution of the external vibration radiated noise sound field of the aviation axial plunger pump, so that the R&D personnel can more accurately grasp the level of external radiated noise.

[0088] The apparatus provided in this embodiment can be used to perform... Figure 1 The technical solution of the method embodiment shown is similar in principle and technical effect to that of Embodiment 1, so it is described simply and will not be elaborated further. They can be referred to each other.

[0089] Furthermore, since Embodiments 1 and 2 of this application have the same technical concept, the steps and processes of the other embodiments of Embodiment 1 can also be executed by the apparatus provided in Embodiment 2. For the sake of clarity and brevity, they will not be repeated. If necessary, Embodiment 2 can be modified based on the other solutions described in Embodiment 1.

[0090] This application also provides an electronic device, including one or more processors; and a memory; The memory stores one or more executable programs. The one or more processors read the executable program code stored in the memory to run the program corresponding to the executable program code, so as to execute the vibration radiation noise prediction method of the aviation axial piston pump described in any of the embodiments.

[0091] Figure 9This is a schematic diagram of the structure of an electronic device according to an embodiment of this application, which can implement any of the methods described in Embodiment 1 of this application, such as... Figure 9 As shown, as an optional embodiment, the above-mentioned electronic device may include: a housing 41, a processor 42, a memory 43, a circuit board 44, and a power supply circuit 45, wherein the circuit board 44 is disposed inside the space enclosed by the housing 41, and the processor 42 and the memory 43 are disposed on the circuit board 44; the power supply circuit 45 is used to supply power to the various circuits or devices of the above-mentioned electronic device; the memory 43 is used to store executable program code; the processor 42 runs the program corresponding to the executable program code by reading the executable program code stored in the memory 43, for executing the aforementioned method for predicting the vibration radiation noise of the aerospace axial piston pump as described in any of the embodiments.

[0092] For details on the specific execution process of the above steps by the processor 42 and the steps further executed by the processor 42 by running executable program code, please refer to the description of Embodiment 1 of the method for predicting vibration radiation noise of aviation axial piston pump in this application, which will not be repeated here.

[0093] This application also provides a computer-readable storage medium storing one or more programs that can be executed by one or more processors to implement the vibration radiation noise prediction method for an aerospace axial piston pump as described in any of the preceding embodiments.

[0094] In summary, the vibration radiation noise prediction method, device, and electronic equipment for aircraft axial piston pumps provided in this application embodiment facilitate the prediction of the sound pressure distribution of the external vibration radiation noise sound field of aircraft axial piston pumps, thereby enabling researchers to more accurately grasp the level of external radiation noise.

[0095] 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.

[0096] The various embodiments in this specification are described in a related manner. The same or similar parts between the various embodiments can be referred to each other. Each embodiment focuses on describing the differences from other embodiments.

[0097] For ease of description, the above system is described by dividing it into various functional units / modules. Of course, in implementing this application, the functions of each unit / module can be implemented in one or more software and / or hardware.

[0098] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. The storage medium can also be a magnetic disk, optical disk, read-only memory (ROM), or random access memory (RAM), etc.

[0099] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for predicting vibration radiation noise of an aircraft axial piston pump, characterized in that, include: The structural parameters and preset operating condition parameters of the aerospace axial piston pump are obtained. The structural parameters include structural dimension parameters that characterize the geometric shape of the component and material property parameters that characterize the physical properties of the component. The preset operating condition parameters are the working parameters that characterize the aerospace axial piston pump under preset operating conditions. Based on the structural parameters and preset operating parameters, the dynamic mechanism of the aviation axial piston pump is analyzed, and the piston dynamic law of the aviation axial piston pump is obtained. The piston dynamic law includes: the variation law of the friction force on the piston, the variation law of the piston axial displacement with time, the variation law of the piston axial velocity and the variation law of the piston axial acceleration with time. Based on the structural parameters and the piston dynamics law, a multibody dynamics model of the aerospace axial piston pump is constructed, and a hydraulic model is constructed based on the structural parameters, preset working condition parameters and piston dynamics law. The multibody dynamics model and the hydraulic model are coupled through a variable exchange mechanism to form a joint simulation model. The outer casing of the aerospace axial piston pump in the joint simulation model is made flexible to obtain a rigid-flexible coupling simulation model. The rigid-flexible coupling simulation model is run to obtain the excitation load borne by the outer casing of the aerospace axial piston pump. The excitation load is applied to the corresponding excitation point of the acoustic-vibration coupling model, and the sound pressure distribution of the vibration radiation noise sound field of the aerospace axial plunger pump is calculated based on the acoustic-vibration coupling model; wherein, the acoustic-vibration coupling model is a simulation model used to simulate the interaction between the vibration of the external shell and the sound field; The process of making the outer casing of the aerospace axial piston pump in the joint simulation model more flexible to obtain a rigid-flexible coupled simulation model includes: The flexibility processing function is invoked in the motion module of the dynamic simulation tool to perform flexibility processing on the outer shell, generating a flexible body; Replace the corresponding rigid outer shell in the co-simulation model with the flexible body, complete the assembly and constraint adjustment, and form the rigid-flexible coupling simulation model; or... A finite element model of the outer casing of the aerospace axial piston pump was established using finite element analysis tools. Modal analysis is performed on the finite element model to generate a modal neutral file; the modal neutral file includes modal characteristic parameters for indicating the external housing of the aerospace axial piston pump; The modal neutral file is imported into a dynamic simulation tool, and the outer housing of the aerospace axial piston pump is transformed into a flexible body based on the modal characteristic parameters. Replace the corresponding rigid outer shell in the joint simulation model with the flexible body, complete the assembly and constraint adjustment, and form the rigid-flexible coupling simulation model. The process of obtaining the excitation load borne by the outer casing of the aerospace axial piston pump by running the rigid-flexible coupling simulation model includes: The rigid-flexible coupling simulation model is run to simulate the actions of the internal components of the aerospace axial piston pump, hydraulic transmission, and the flexible deformation characteristics of the external shell under preset working conditions. Based on the complete force response data of the outer shell, oil distributor cap, and mounting base output by the rigid-flexible coupling simulation model, the internal excitation forces affecting the vibration radiation noise of the outer shell are identified. The internal excitation forces include: the force of the angular contact ball bearing on the mounting base, the force of the needle roller bearing transmitted to the outer shell through the distribution plate, the force of the swash plate cylindrical roller bearing on the mounting base, and the force of the follower piston on the oil distributor cap. The dynamic change data of the internal excitation force under the preset working conditions are collected; the dynamic change data includes: force amplitude, frequency distribution, and time change curve. By integrating the dynamic change data, the vibration load borne by the outer housing of the aviation axial piston pump is obtained.

2. The method for predicting vibration radiation noise of an aerospace axial piston pump according to claim 1, characterized in that, Before obtaining the sound pressure distribution of the vibration radiation noise sound field of the aerospace axial plunger pump based on the acoustic-vibration coupling model, the method further includes: The outer housing model of the aerospace axial piston pump is preprocessed to close the opening area on the outer housing model, forming a continuous and complete outer surface of the outer housing; An outer envelope mesh is generated on the outer surface of the outer shell, and a convex mesh is generated by extending the outer envelope mesh outward by a predetermined distance; the type of the outer envelope mesh is a three-node triangular element; The space between the outer envelope mesh and the convex mesh is filled by the shell element generating entity command to form the prototype of the air domain mesh; Acoustic fluid elements are assigned to the air domain mesh prototype, and the air domain mesh prototype is discretized based on the acoustic fluid elements to obtain the acoustic mesh; Using the geometric center of the outer casing model of the aerospace axial piston pump as a reference point, a hemispherical field point grid is constructed outside the outer casing and within the acoustic field range defined by the acoustic grid, and measurement points are arranged on the hemispherical field point grid; wherein, a data mapping relationship is established between the corresponding spatial positions of the hemispherical field point grid and the acoustic grid; The preprocessed external shell model, acoustic mesh, and hemispherical field point mesh are imported into the acoustic simulation analysis environment. A structural acoustic coupling interface is configured between the surface of the external shell model and the inner surface of the acoustic mesh to form the acoustic-vibration coupling model. The structural acoustic coupling interface is used to transfer the vibration displacement of the external shell model to the acoustic mesh.

3. The method for predicting vibration radiation noise of an aerospace axial piston pump according to claim 2, characterized in that, The step of obtaining the sound pressure distribution of the vibration radiation noise of the aircraft axial piston pump based on the acoustic-vibration coupling model includes: configuring the solution parameters of the acoustic-vibration coupling model; the solution parameters include: the simulation frequency range for solving the vibration radiation noise of the aircraft axial piston pump under the preset working conditions of the aircraft axial piston pump, the residual convergence threshold for the numerical solution of the sound field, and the calculation step size that matches the simulation frequency range during the solution process of the acoustic-vibration coupling model; Based on the aforementioned solution parameters, the sound field range defined by the acoustic mesh is numerically solved using the finite element method or the boundary element method to obtain the sound field values ​​of the acoustic mesh. The sound field values ​​are the sound pressure-related physical quantity values ​​of all discrete nodes of the acoustic mesh. Based on the data mapping relationship between the hemispherical field point grid and the acoustic grid, the sound pressure value corresponding to the measuring point on the hemispherical field point grid is extracted point by point from the sound field values ​​to obtain the sound pressure distribution result of the vibration radiation noise sound field of the aviation axial piston pump.

4. The method for predicting vibration radiation noise of an aerospace axial piston pump according to claim 1, characterized in that, The components include: a main shaft, a cylinder block, a plunger, a slipper, a swashplate, and a distributor plate; The construction of the multibody dynamics model of the aerospace axial piston pump based on the structural parameters and the piston dynamics law includes: Import the three-dimensional models corresponding to the main shaft, cylinder block, plunger, slipper, swashplate and distributor plate into the dynamics simulation tool, and configure the material properties corresponding to the material property parameters for each three-dimensional model; Kinematic pairs are configured for each 3D model to form a constraint system that conforms to the actual motion relationship; the kinematic pairs include at least one of fixed pairs, revolute pairs, cylindrical pairs, bushings, ball joints and planar pairs; The variation law of friction force on the plunger in the plunger dynamics law is applied to the plunger in the form of scalar force to form the multibody dynamics model.

5. The method for predicting vibration radiation noise of an aerospace axial piston pump according to claim 1, characterized in that, The components also include: a prime mover module, a spring damping module, and a moment of inertia module; The construction of the hydraulic model based on the structural parameters, preset working condition parameters, and piston dynamics includes: A motor drive model is constructed based on the prime mover module, spring damping module, and moment of inertia module; wherein, the prime mover module is used to provide a constant speed that matches the working speed in the preset operating condition parameters, the spring damping module is used to adjust the stiffness and damping characteristics, and the moment of inertia module is used to configure energy loss related parameters; The flow distribution disk model is constructed by calling predefined flow distribution disk functional elements of the fluid simulation tool, and a flow distribution pair model matching the flow distribution disk model is constructed by calling predefined fluid friction pair elements. The flow distribution disk model includes a first input port, a second input port, and an output port. The first input port is used to receive the plunger rotational angular displacement signal obtained based on the time variation law of the plunger axial displacement, the plunger axial motion speed, and the plunger axial acceleration. The second input port is used to receive the plunger cavity working pressure signal and flow signal. The output port of the flow distribution disk model is connected to the input port of the flow distribution pair model. The flow distribution pair model is used to simulate the friction and leakage loss during the oil suction and discharge process. The flow distribution pair model is also configured with a main flow output port and a leakage output port. The main flow output port is connected to the hydraulic system oil circuit, and the leakage output port is connected to the pump casing oil circuit. Furthermore, the swashplate model is constructed by calling the swashplate function model in the fluid simulation tool, and inertial elements are configured to simulate the inertial characteristics of the swashplate. The swashplate model contains multiple ports, wherein the first port is used to connect to other swashplate models or inertial elements that simulate the inertia of the swashplate, the second port is used to connect to the motor drive model to receive the rotational angular velocity and angular displacement signals of the motor, the third port is used to connect to the first port of other swashplate models to receive the output torque of other swashplate models, the fourth port is used to connect to the plunger pair model, and the fifth port is used to connect to the distributor plate model to output the rotation angle information of the plunger. Furthermore, the plunger body, the plunger cavity dead zone volume model, and the plunger pair leakage module are connected to form the plunger pair model; wherein, the plunger cavity dead zone volume model is configured with a volume inlet, a volume-side leakage port, and a pressure signal output port; the working medium output port of the plunger body is connected to the volume inlet of the plunger cavity dead zone volume model to construct a medium transmission channel between the plunger body and the plunger cavity dead zone volume model; the medium input end of the plunger pair leakage module is connected to the volume-side leakage port of the plunger cavity dead zone volume model to simulate leakage loss between the plunger pair and the cylinder block; the pressure signal output port of the plunger cavity dead zone volume model is used to interface with the pressure signal input port of the slipper pair leakage module; and the medium output ends of the plunger pair leakage module and the slipper pair leakage module are respectively connected to the pump housing oil circuit.

6. The method for predicting vibration radiation noise of an aerospace axial piston pump according to claim 1, characterized in that, After constructing the multibody dynamics model of the aerospace axial piston pump, the method further includes: obtaining simulation data of the axial motion velocity and axial acceleration of the piston's center of mass at the first time node based on the multibody dynamics model, and comparing and verifying the simulation data with the values ​​of the corresponding physical quantities in the piston dynamics law; and... After constructing the hydraulic model, the method further includes: running the hydraulic model to simulate and obtain the simulated values ​​of the outlet pressure and outlet flow under preset working conditions, and comparing and verifying the simulated values ​​of the outlet pressure with the measured values ​​of the outlet pressure, and the simulated values ​​of the outlet flow with the measured values ​​of the outlet flow.

7. A device for predicting vibration radiation noise of an aircraft axial piston pump, characterized in that, include: The acquisition program unit is used to acquire the structural parameters and preset operating condition parameters of the aviation axial piston pump. The structural parameters include structural dimension parameters that characterize the geometric shape of the component and material property parameters that characterize the physical properties of the component. The preset operating condition parameters are the working parameters that characterize the aviation axial piston pump in a preset operating state. The analysis program unit is used to analyze the dynamic mechanism of the aviation axial piston pump based on the structural parameters and preset operating parameters, and to obtain the piston dynamic law of the aviation axial piston pump. The piston dynamic law includes: the variation law of the friction force on the piston, the variation law of the piston axial displacement with time, the variation law of the piston axial velocity and the variation law of the piston axial acceleration with time. A program unit is constructed to build a multibody dynamics model of the aerospace axial piston pump based on the structural parameters and the piston dynamics law, and to build a hydraulic model based on the structural parameters, preset working condition parameters and piston dynamics law; The dynamic coupling program unit is used to couple the multibody dynamics model and the hydraulic model through a variable exchange mechanism to form a joint simulation model, and to make the outer casing of the aerospace axial piston pump in the joint simulation model flexible to obtain a rigid-flexible coupling simulation model, and to run the rigid-flexible coupling simulation model to obtain the excitation load borne by the outer casing of the aerospace axial piston pump. The calculation program unit is used to apply the excitation load to the corresponding excitation point of the acoustic-vibration coupling model, and calculate the sound pressure distribution of the vibration radiation noise sound field of the aviation axial plunger pump based on the acoustic-vibration coupling model; wherein, the acoustic-vibration coupling model is a simulation model used to simulate the interaction between the vibration of the external shell and the sound field; The process of making the outer casing of the aerospace axial piston pump in the joint simulation model more flexible to obtain a rigid-flexible coupled simulation model includes: The flexibility processing function is invoked in the motion module of the dynamic simulation tool to perform flexibility processing on the outer shell, generating a flexible body; Replace the corresponding rigid outer shell in the co-simulation model with the flexible body, complete the assembly and constraint adjustment, and form the rigid-flexible coupling simulation model; or... A finite element model of the outer casing of the aerospace axial piston pump was established using finite element analysis tools. Modal analysis is performed on the finite element model to generate a modal neutral file; the modal neutral file includes modal characteristic parameters for indicating the external housing of the aerospace axial piston pump; The modal neutral file is imported into a dynamic simulation tool, and the outer housing of the aerospace axial piston pump is transformed into a flexible body based on the modal characteristic parameters. Replace the corresponding rigid outer shell in the joint simulation model with the flexible body, complete the assembly and constraint adjustment, and form the rigid-flexible coupling simulation model. The process of obtaining the excitation load borne by the outer casing of the aerospace axial piston pump by running the rigid-flexible coupling simulation model includes: The rigid-flexible coupling simulation model is run to simulate the actions of the internal components of the aerospace axial piston pump, hydraulic transmission, and the flexible deformation characteristics of the external shell under preset working conditions. Based on the complete force response data of the outer shell, oil distributor cap, and mounting base output by the rigid-flexible coupling simulation model, the internal excitation forces affecting the vibration radiation noise of the outer shell are identified. The internal excitation forces include: the force of the angular contact ball bearing on the mounting base, the force of the needle roller bearing transmitted to the outer shell through the distribution plate, the force of the swash plate cylindrical roller bearing on the mounting base, and the force of the follower piston on the oil distributor cap. The dynamic change data of the internal excitation force under the preset working conditions are collected; the dynamic change data includes: force amplitude, frequency distribution, and time change curve. By integrating the dynamic change data, the vibration load borne by the outer housing of the aviation axial piston pump is obtained.

8. An electronic device, characterized in that, Includes: a housing, within which one or more processors are provided; And memory; The memory stores one or more executable programs, and the one or more processors read the executable program code stored in the memory to run the program corresponding to the executable program code, so as to execute the vibration radiation noise prediction method of the aerospace axial piston pump according to any one of claims 1 to 6.

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