Method and apparatus for analyzing thermal vacuum environment deformation of an induction synchronizer

Abstract

The application relates to the technical field of inductive synchronizer, and discloses a thermal vacuum environment deformation analysis method and equipment of an inductive synchronizer, wherein the method comprises the following steps: constructing a finite element model of the inductive synchronizer, and determining structure constraint conditions and temperature field conditions of the finite element model; simulating the finite element model based on the temperature field conditions and the structure constraint conditions to obtain simulation results; determining stator deformation characteristics and rotor deformation characteristics of the inductive synchronizer under different environmental temperatures according to the simulation results; determining comprehensive deformation characteristics of the inductive synchronizer according to the stator deformation characteristics and the rotor deformation characteristics, so as to determine deformation analysis results of the inductive synchronizer under different environmental temperatures according to the comprehensive deformation characteristics. The application can accurately quantify the deformation influence of temperature change on the inductive synchronizer, thereby greatly improving the accuracy of the deformation analysis results of the inductive synchronizer under the thermal vacuum environment.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of inductive synchronizer, and particularly relates to a thermal vacuum environment deformation analysis method and device of inductive synchronizer. BACKGROUND

[0002] In the field of aerospace, inductive synchronizers are widely used in remote sensing observation systems of spacecraft such as high-orbit satellites to achieve fine detection of the earth's surface by using high-precision scanning control.

[0003] However, in the vacuum environment of the spacecraft, extreme temperature changes will cause thermal expansion of the material, which will change the electromagnetic coupling gap between the stator and the rotor of the inductive synchronizer, causing the measurement results of the inductive synchronizer to deviate, and ultimately leading to geometric distortion of the satellite remote sensing image or distortion of the scientific detection data.

[0004] Therefore, how to accurately determine the thermal expansion effect of the inductive synchronizer in the thermal vacuum environment has become a problem to be solved. SUMMARY

[0005] The present application provides a thermal vacuum environment deformation analysis method and device of inductive synchronizer, which solves the technical problem that related technologies are difficult to accurately analyze the thermal expansion effect of the inductive synchronizer in the thermal vacuum environment. The present application can accurately quantify the deformation influence of temperature change on the inductive synchronizer through finite element modeling and analysis of multiple physical field coupling, thereby greatly improving the accuracy of the deformation analysis result of the inductive synchronizer in the thermal vacuum environment.

[0006] In order to achieve the above purpose, the main technical scheme adopted by the present application includes:

[0007] In a first aspect, the present application provides a thermal vacuum environment deformation analysis method of inductive synchronizer, which comprises:

[0008] constructing a finite element model of the inductive synchronizer and determining the structure constraint conditions and temperature field conditions of the finite element model;

[0009] simulating the finite element model based on the temperature field conditions and the structure constraint conditions to obtain a simulation result;

[0010] determining the stator deformation characteristics and rotor deformation characteristics of the inductive synchronizer under different environmental temperatures according to the simulation result;

[0011] determining the comprehensive deformation characteristics of the inductive synchronizer according to the stator deformation characteristics and the rotor deformation characteristics, and determining the deformation analysis result of the inductive synchronizer under different environmental temperatures according to the comprehensive deformation characteristics.

[0012] The thermal vacuum environment deformation analysis method provided in the embodiments of the present application divides the continuous inductive synchronizer structure into a plurality of interconnected units by using a finite element model, so as to realize discretization analysis on the complex deformation of the inductive synchronizer under the thermal vacuum environment. Compared with the related art, the embodiments of the present application deeply couple the heat conduction and the mechanical response by using the structural constraint condition and the temperature field condition, can accurately match the physical principle of the deformation of the inductive synchronizer, effectively simulate the actual situation of the inductive synchronizer under the thermal vacuum environment, so as to accurately obtain the deformation characteristics of the stator and the rotor under different environmental temperatures, and then accurately quantify the influence of the temperature change on the deformation of the inductive synchronizer by comprehensively considering the deformation characteristics of the stator and the rotor, thereby greatly improving the accuracy of the deformation analysis result of the inductive synchronizer under the thermal vacuum environment.

[0013] Optionally, in some embodiments of the present application, the inductive synchronizer comprises a stator, a rotor and a rigid mounting platform, and the finite element model of the inductive synchronizer is constructed by:

[0014] constructing a three-dimensional geometric model of the inductive synchronizer according to the geometric parameters and the connection relationship of the stator, the rotor and the rigid mounting platform;

[0015] determining the key positions and the non-key positions of the stator, the rotor and the rigid mounting platform, and respectively determining a first grid size corresponding to the key positions and a second grid size corresponding to the non-key positions, wherein the first grid size is smaller than the second grid size;

[0016] performing grid division on the three-dimensional geometric model based on the first grid size and the second grid size, to obtain the finite element model.

[0017] When performing grid division on the finite element model, the embodiments of the present application can adaptively adjust appropriate grid sizes according to the characteristics of different components of the inductive synchronizer, use the first grid size to realize encryption division for the key positions, greatly improve the calculation accuracy of these key positions, and use the second grid size to divide the non-key positions, effectively balance the calculation accuracy and the calculation efficiency while ensuring the analysis accuracy of the overall model.

[0018] Optionally, in some embodiments of the present application, the structural constraint condition is determined by:

[0019] determining the fixed positions of the stator and the rotor on the rigid mounting platform;

[0020] determining a deformation constraint parameter based on the fixed positions, so as to determine the structural constraint condition according to the deformation constraint parameter.

[0021] The embodiment of the present application accurately characterizes the deformation restriction of the stator and the rotor on the rigid installation platform due to the fixed position, so that the simulation process of the finite element model is more in line with the actual situation, and the accuracy of the finite element simulation result is greatly improved.

[0022] Optionally, in some embodiments of the present application, the temperature field condition is determined by:

[0023] The radiation boundary condition of the finite element model is determined based on the Stefan-Boltzmann law;

[0024] The internal heat source power of the induction synchronizer is determined, and the thermal conductivity coefficient between the stator, the rotor and the rigid installation platform is obtained, so as to determine the heat conduction condition of the finite element model according to the internal heat source power and the thermal conductivity coefficient;

[0025] The temperature field condition is determined according to the radiation boundary condition and the heat conduction condition.

[0026] The embodiment of the present application considers that the induction synchronizer exchanges heat with the vacuum environment only through thermal radiation, accurately determines the radiation boundary condition by using the Stefan-Boltzmann law, and considers the Joule heat generated in the actual work of the induction synchronizer, so as to determine the heat conduction condition by using the internal heat source power and the thermal conductivity coefficient, so as to comprehensively and accurately construct the temperature field condition of the induction synchronizer in the thermal vacuum environment, so that the finite element model can accurately simulate the heat transfer process of the induction synchronizer in the thermal vacuum environment, and the accuracy of the finite element simulation result is greatly improved.

[0027] Optionally, in some embodiments of the present application, the simulation of the finite element model based on the temperature field condition and the structure constraint condition to obtain a simulation result comprises:

[0028] Different environment temperatures are set, and actual surface temperatures of each unit under each environment temperature are obtained based on the temperature field condition;

[0029] The unit deformation of each unit is simulated based on the actual surface temperature, the thermal expansion coefficient and the structure constraint condition, so as to obtain the simulation result according to the unit deformation, wherein the simulation result comprises the stator radial deformation distribution, the stator axial deformation distribution, the rotor radial deformation distribution and the rotor axial deformation distribution under the different environment temperatures.

[0030] The embodiment of the present application realizes the discrete simulation analysis of the complex deformation of the induction synchronizer through the deformation simulation of each unit, and performs deformation analysis from multiple dimensions of the stator radial deformation, the stator axial deformation, the rotor radial deformation and the rotor axial deformation based on the unit deformation of each unit on the stator and the rotor, thereby avoiding the limitation of single-dimensional analysis and being able to more accurately quantify the influence of temperature change on the complex deformation of the induction synchronizer.

[0031] Optionally, in some embodiments of the present application, the stator deformation features include stator radial deformation features and stator axial deformation features, and the rotor deformation features include rotor radial deformation features and rotor axial deformation features.

[0032] The stator deformation features and the rotor deformation features of the induction synchronizer under different environmental temperatures are determined according to the simulation results, and the method comprises the following steps.

[0033] The maximum deformation values of the stator radial deformation distribution, the stator axial deformation distribution, the rotor radial deformation distribution and the rotor axial deformation distribution corresponding to the different environmental temperatures are respectively determined.

[0034] The stator radial deformation features, the stator axial deformation features, the rotor radial deformation features and the rotor axial deformation features corresponding to each of the environmental temperatures are determined according to the maximum deformation values.

[0035] The embodiment of the present application extracts the key features of each deformation dimension of the induction synchronizer under different environmental temperatures by using the maximum deformation value, so as to comprehensively analyze the deformation influence of temperature change on multiple dimensions of the stator radial deformation, the stator axial deformation, the rotor radial deformation and the rotor axial deformation.

[0036] Optionally, in some embodiments of the present application, the comprehensive deformation features of the induction synchronizer are determined according to the stator deformation features and the rotor deformation features, and the method comprises the following steps.

[0037] The radial comprehensive deformation features of the induction synchronizer corresponding to the different environmental temperatures are determined according to the first difference absolute value of the stator radial deformation features and the rotor radial deformation features.

[0038] The axial comprehensive deformation features of the induction synchronizer corresponding to the different environmental temperatures are determined according to the second difference absolute value of the stator axial deformation features and the rotor axial deformation features.

[0039] The comprehensive deformation features are determined according to the average value of the radial comprehensive deformation features and the axial comprehensive deformation features.

[0040] The embodiment of the present application quantitatively represents the electromagnetic coupling gap change between the stator and the rotor by using the radial comprehensive deformation characteristic, and quantitatively represents the size error change of the stator and the rotor by using the axial comprehensive deformation characteristic, and then comprehensively and accurately represents the overall deformation of the inductive synchronizer in the thermal vacuum environment by using the average value of the radial comprehensive deformation characteristic and the axial comprehensive deformation characteristic, thereby facilitating to improve the accuracy of the deformation analysis result.

[0041] Optionally, in some embodiments of the present application, the deformation analysis result of the inductive synchronizer under different environmental temperatures is determined according to the comprehensive deformation characteristic, comprising:

[0042] fitting the mapping relationship between the environmental temperature and the comprehensive deformation characteristic to obtain a first fitting curve, so as to determine the deformation analysis result according to the first fitting curve.

[0043] Optionally, in some embodiments of the present application, after the deformation analysis result of the inductive synchronizer under different environmental temperatures is determined, the method further comprises:

[0044] obtaining a first slope of the first fitting curve;

[0045] obtaining output sampling data of the inductive synchronizer under the different environmental temperatures, and fitting the mapping relationship between the environmental temperature and the output sampling data to obtain a second fitting curve, so as to obtain a second slope of the second fitting curve;

[0046] analyzing the orthogonality of the first fitting curve and the second fitting curve according to the first slope and the second slope, and adjusting the finite element model in the case that the orthogonality does not meet a preset condition.

[0047] The embodiment of the present application uses the orthogonality analysis of the first slope and the second slope to effectively verify the modeling accuracy of the finite element model, ensures that the finite element model can adapt to the deformation simulation requirements of the inductive synchronizer under different working conditions, so that the finite element model always maintains high precision, thereby further improving the accuracy of the deformation analysis result.

[0048] In a second aspect, the embodiment of the present application provides a thermal vacuum environment deformation analysis device of an inductive synchronizer, comprising:

[0049] a modeling module, configured to construct a finite element model of the inductive synchronizer, and determine structure constraint conditions and temperature field conditions of the finite element model;

[0050] a simulation module, configured to simulate the finite element model based on the temperature field conditions and the structure constraint conditions to obtain a simulation result;

[0051] The feature processing module is configured to determine stator deformation features and rotor deformation features of the induction synchro under different ambient temperatures according to the simulation result.

[0052] The analysis module is configured to determine comprehensive deformation features of the induction synchro according to the stator deformation features and the rotor deformation features, and determine deformation analysis results of the induction synchro under different ambient temperatures according to the comprehensive deformation features.

[0053] The thermal vacuum environment deformation analysis device provided in the embodiments of the present application divides the continuous induction synchro structure into a plurality of interconnected units by using a finite element model, so as to realize discretization analysis on the complex deformation of the induction synchro under the thermal vacuum environment. Compared with the related art, the embodiments of the present application deeply couple heat conduction and mechanical response by using structure constraint conditions and temperature field conditions, can accurately match the physical principle of deformation of the induction synchro, effectively simulate the actual situation of the induction synchro under the thermal vacuum environment, so as to accurately obtain the deformation features of the stator and the rotor under different ambient temperatures, and then accurately quantify the influence of temperature change on the deformation of the induction synchro by comprehensively determining the stator deformation features and the rotor deformation features, thereby greatly improving the accuracy of the deformation analysis result of the induction synchro under the thermal vacuum environment.

[0054] In a third aspect, the embodiments of the present application provide a computer device, comprising:

[0055] A memory and a processor, which are in communication connection with each other, and the memory stores computer instructions, and the processor executes the computer instructions to perform the thermal vacuum environment deformation analysis method of the induction synchro provided in the above embodiments. BRIEF DESCRIPTION OF DRAWINGS

[0056] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed in the specific embodiments or the prior art description will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.

[0057] Figure 1 It is an electrical principle schematic diagram of an absolute type circular induction synchro in the related art;

[0058] Figure 2 It is a flowchart of an induction synchro thermal vacuum environment deformation analysis method provided in the embodiments of the present application;

[0059] Figure 3 It is a schematic diagram of a finite element model provided in the embodiments of the present application;

[0060] Figure 4 Fig. 1 is a schematic diagram of the radial deformation distribution of the stator in the embodiment of the present application;

[0061] Figure 5 Fig. 2 is a schematic diagram of the axial deformation distribution of the stator in the embodiment of the present application;

[0062] Figure 6 Fig. 3 is a schematic diagram of the radial deformation distribution of the rotor in the embodiment of the present application;

[0063] Figure 7 Fig. 4 is a schematic diagram of the axial deformation distribution of the rotor in the embodiment of the present application;

[0064] Figure 8 Fig. 5 is a schematic diagram of the deformation fitting curve of the inductive synchronizer in the embodiment of the present application;

[0065] Figure 9 Fig. 6 is a schematic diagram of the coarse channel temperature rising and falling curve of the inductive synchronizer in the embodiment of the present application;

[0066] Figure 10 Fig. 7 is a schematic diagram of the fine channel temperature rising and falling curve of the inductive synchronizer in the embodiment of the present application;

[0067] Figure 11 Fig. 8 is a schematic diagram of the orthogonality of the fitting curve in the embodiment of the present application;

[0068] Figure 12 Fig. 9 is a structural schematic diagram of a thermal vacuum environment deformation analysis device of an inductive synchronizer according to the embodiment of the present application;

[0069] Figure 13 Fig. 10 is a structural schematic diagram of a computer device according to the embodiment of the present application. DETAILED DESCRIPTION

[0070] In order to make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme of the embodiments of the present application will be described clearly and completely below with reference to the drawings of the embodiments of the present application. Obviously, the described embodiments are some embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0071] In the field of aerospace, the remote sensing observation system of high-orbit satellites relies on high-precision scanning control to achieve fine detection of the earth's surface, and the angle measurement system as the core part of scanning control directly determines the accuracy of target positioning. Inductive synchronizer, due to its non-contact measurement, anti-electromagnetic interference and other characteristics, has become the preferred angle measuring device in the above application scenarios, especially the 360-pair absolute inductive synchronizer, which can achieve 0.05" level angle resolution through multi-pole winding design, meeting the stringent requirements of aerospace and high-end industries.

[0072] Absolute circular inductive synchronizer (CIS) as a kind of inductive synchronizer, is usually composed of a stator and a rotor, and works by electromagnetic induction principle. Its basic principle is to convert the angle change into electrical signal change through the electromagnetic coupling between the stator and rotor windings.

[0073] Figure 1 The electrical principle of the stator and rotor of the absolute circular inductive synchronizer is shown, as shown in Figure 1 The stator includes sine winding terminals A1, A2, cosine winding terminals B1 and B2, and the rotor includes continuous winding terminals Z1 and Z2. When an alternating excitation signal is passed through the continuous winding of the rotor, a multi-pole alternating magnetic field will be generated near the rotor plane, and the number of poles depends on the number of conductive sheets.

[0074] Let the alternating excitation signal of the sine winding be As shown in the following formula (1):

[0075] Formula (1)

[0076] Let the alternating excitation signal of the cosine winding be As shown in the following formula (2):

[0077]

[0078] In formula (1) and formula (2), denotes the amplitude of the alternating excitation signal, denotes the angular frequency of the alternating excitation signal, denotes time.

[0079] Where, according to the characteristics of the inductive synchronizer, the rotation angle of the rotor relative to the stator is θ, and the number of pole pairs of the rotor and stator windings is n, then the induced electromotive force on the stator is expressed as the following formula (3):

[0080]

[0081] wherein, is a coupling coefficient, which is related to winding structure, magnetic permeability and other parameters.

[0082] It can be seen that the phase of the induced electromotive force on the stator has a linear relationship with the rotation angle θ of the rotor relative to the stator. By detecting the phase of the induced electromotive force, the rotation angle θ of the rotor relative to the stator can be measured. For example, given the number of pole pairs n and the coupling coefficient k, the rotation angle θ can be calculated by measuring the phase of the induced electromotive force .

[0083] In the vacuum environment of a spacecraft, extreme temperature changes can cause the on-board temperature control system to change, causing material thermal expansion effects. This thermal expansion effect can change the electromagnetic coupling gap between the stator and the rotor of the inductive synchro, thereby affecting the change of the coupling coefficient k, causing the measurement results of the inductive synchro to deviate, and ultimately leading to geometric distortion of satellite remote sensing images or distortion of scientific exploration data.

[0084] However, in the related art, on the one hand, the influence of material anisotropy characteristics and the difference in deformation response of different spatial dimensions is not considered, and on the other hand, only a single thermal field or structural field is independently analyzed, which cannot accurately analyze the deformation transmission process under the coupling of the temperature field and the structural field. Therefore, the related art has not established a multi-dimensional deformation analysis model integrating the thermal-structural coupling effect and combining the relative offset law of the stator and the rotor, resulting in insufficient deformation analysis accuracy of the inductive synchro in a thermal vacuum environment, and the related art cannot accurately quantify the correlation between temperature changes and stator-rotor deformation, electromagnetic coupling gap changes and angle measurement deviation, making it difficult to meet the engineering needs of deformation analysis of angle measuring devices in the field of aviation and aerospace.

[0085] To solve the above technical problems, an embodiment of the present application provides a method for analyzing deformation of an inductive synchro in a thermal vacuum environment. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0086] In this embodiment, a method for analyzing deformation of an inductive synchro in a thermal vacuum environment is provided, Figure 2 is a method flowchart according to an embodiment of the present application, as shown in Figure 2 the method comprises the following steps:

[0087] Step S1, constructing a finite element model of the inductive synchro, and determining the structural constraint conditions and temperature field conditions of the finite element model.

[0088] ​Specifically, the actual continuous structure of the induction synchronizer is discretized into a plurality of units by using a finite element model, and finite element analysis (FEA) is performed on the units. In some embodiments of the present application, geometric parameters of the actual structure of the induction synchronizer are first determined, and then the geometric parameters are imported into ANSYS finite element analysis software to construct a corresponding finite element model. Subsequently, the structure constraint conditions and the temperature field conditions are determined, respectively, wherein the structure constraint conditions represent the actual installation constraints of the components of the induction synchronizer, and the temperature field conditions represent the heat exchange of the induction synchronizer in a hot vacuum environment.

[0089] In step S3, the finite element model is simulated based on the temperature field conditions and the structure constraint conditions to obtain simulation results.

[0090] Specifically, the structure constraint conditions and the temperature field conditions are imported into the finite element model, and the environmental temperature is set at a preset step size. In some examples of the embodiments of the present application, the temperature variation range can be set to 0-50℃, and the preset step size can be 5℃. The ANSYS finite element analysis software simulates and calculates the deformation distribution of each unit under the structure constraint conditions and the temperature field conditions at different environmental temperatures, and outputs corresponding simulation results, which represent the deformation of each component of the induction synchronizer with temperature variation.

[0091] In step S5, the stator deformation characteristics and the rotor deformation characteristics of the induction synchronizer at different environmental temperatures are determined according to the simulation results.

[0092] Specifically, the embodiments of the present application use the ANSYS finite element analysis software to perform FEA calculation on the deformation amount of each unit due to temperature variation. To achieve the FEA calculation, the elastic modulus, the linear expansion coefficient, and the Poisson's ratio of each unit in the finite element model and other related material property parameters need to be set in advance.

[0093] Further, in one example of the embodiments of the present application, the induction synchronizer includes a stator, a rotor, and a rigid mounting platform, and for the material types of the components in the induction synchronizer, the material property parameters shown in Table 1 are set. Among them, the martensitic stainless steel is the material of the rigid mounting platform, and the epoxy plate, the copper foil winding, and the hard aluminum are the materials of the stator and the rotor.

[0094] Table 1

[0095]

[0096] For each unit in the finite element model, the radial deformation and the axial deformation of each unit are analyzed based on the hoop stress formula and the radial stress formula. Among them, the hoop stress formula is shown in the following formula (4):

[0097] Formula (4)

[0098] In the formula, represents the hoop stress, represents the temperature change amount, represents the elastic modulus, which represents the rigidity of the material, represents the linear expansion coefficient, which represents the expansion or contraction ability of the material when the temperature changes, wherein the elastic modulus and the linear expansion coefficient are related to the material type corresponding to each unit.

[0099] The above radial stress formula is shown in the following formula (5):

[0100] Formula (5)

[0101] In the formula, represents the radial stress, represents the Poisson's ratio, which is the ratio of the transverse normal strain to the axial normal strain when the material is subjected to unidirectional tension or compression, and is also related to the material type corresponding to each unit.

[0102] The deformation amount of each unit corresponding to the stator and the rotor in the finite element model with temperature change is taken as the simulation result, which represents the radial deformation distribution and the axial deformation distribution of the stator and the rotor of the inductive synchronizer in the temperature change process, and then the corresponding stator deformation feature and rotor deformation feature are extracted based on the radial deformation distribution and the axial deformation distribution.

[0103] Step S7, determining the comprehensive deformation feature of the inductive synchronizer according to the stator deformation feature and the rotor deformation feature, so as to determine the deformation analysis result of the inductive synchronizer under different environmental temperatures according to the comprehensive deformation feature.

[0104] Specifically, the stator deformation feature represents the deformation performance of the stator of the inductive synchronizer along the axial direction and the radial direction under different environmental temperatures, the rotor deformation feature represents the deformation performance of the rotor of the inductive synchronizer along the axial direction and the radial direction under different environmental temperatures, and the stator deformation feature and the rotor deformation feature jointly determine the relative deformation amount between the stator and the rotor of the inductive synchronizer. According to the relative deformation amount, the analysis of the electromagnetic coupling gap change is realized, and then the mapping relationship between the environmental temperature change and the deformation of the stator and the rotor is accurately quantitatively analyzed.

[0105] The thermal vacuum environment deformation analysis method provided by the embodiment utilizes a finite element model to divide the continuous inductive synchronizer structure into a plurality of interconnected units to realize discretization analysis on the complex deformation of the inductive synchronizer in the thermal vacuum environment. Compared with the related art, the embodiment of the application deeply couples the heat conduction and the mechanical response by utilizing the structural constraint conditions and the temperature field conditions, can accurately match the physical principle of the deformation of the inductive synchronizer, effectively simulate the actual situation of the inductive synchronizer in the thermal vacuum environment, and thus accurately obtain the deformation characteristics of the stator and the rotor under different environmental temperatures, and then accurately quantify the influence of the temperature change on the deformation of the inductive synchronizer by comprehensively considering the deformation characteristics of the stator and the rotor, thereby greatly improving the accuracy of the deformation analysis result of the inductive synchronizer in the thermal vacuum environment.

[0106] In some embodiments of the present application, the above step S1 can include the following steps:

[0107] Step S11, constructing a three-dimensional geometric model of the inductive synchronizer according to the geometric parameters and connection relationship of the stator, the rotor and the rigid mounting platform.

[0108] Specifically, the stator and the rotor of the inductive synchronizer are fixedly connected with the rigid mounting platform through mounting members such as screws, wherein the mounting members include but are not limited to screws. The corresponding geometric model is constructed according to the geometric parameters such as the inner and outer diameters and thicknesses of the stator, the rotor and the rigid mounting platform, and the outer diameter edge of the stator is fixed with the rigid mounting platform through a plurality of screws, and the inner diameter edge of the rotor is fixed with the rigid mounting platform through a plurality of screws.

[0109] Step S13, determining the key positions and non-key positions of the stator, the rotor and the rigid mounting platform, and respectively determining the first grid size corresponding to the key positions and the second grid size corresponding to the non-key positions, wherein the first grid size is smaller than the second grid size.

[0110] Specifically, in some embodiments of the present application, the above key positions include the contact areas of the winding and the slide ruler, and the positions prone to large deformation such as the corner and the stress concentration point. For these key positions, a grid with a very small size is used for encryption division, and the corresponding first grid size can reach millimeter or sub-millimeter level to improve the calculation accuracy. For the non-key positions with relatively simple structure and small deformation, such as the large-area flat plate structure part, the grid size can be appropriately increased, and the corresponding second grid size can be controlled within the centimeter level to balance the calculation accuracy and the calculation efficiency.

[0111] Step S15, performing grid division on the three-dimensional geometric model based on the first grid size and the second grid size to obtain a finite element model.

[0112] Specifically, the embodiments of the present application adopt a tetrahedron or hexahedron grid with strong adaptability to divide the three-dimensional geometric model into grids, so as to realize the discretization processing of the inductive synchronizer structure. Figure 3 A finite element model obtained after the grid division in the three-dimensional space of the x-axis, y-axis and z-axis is shown, as shown in Figure 3 The uppermost layer corresponds to the rotor of the inductive synchronizer, the middle layer corresponds to the stator of the inductive synchronizer, and the lowermost layer corresponds to the rigid mounting platform of the inductive synchronizer.

[0113] It should be noted that in the grid division process, the embodiments of the present application also utilize the grid quality checking tool of the ANSYS finite element analysis software to check the shape regularity, aspect ratio, Jacobian determinant and other indicators of the grid. For the grid with irregular shape, too large aspect ratio or Jacobian determinant not meeting the requirements, the node position is manually adjusted, the local area is re-divided, and the like, so as to optimize, ensure the grid quality of the entire model to meet the calculation requirements, and thus ensure the reliability of the calculation results.

[0114] Compared with the embodiments shown in Figure 2 , in the embodiments of the present application, when the finite element model is divided into grids, the appropriate grid size can be adaptively adjusted according to the characteristics of different components of the inductive synchronizer. The first grid size is used to realize the encryption division for the key parts, which greatly improves the calculation accuracy of these key parts. The second grid size is used to divide the non-key parts, which effectively balances the calculation accuracy and calculation efficiency while ensuring the analysis accuracy of the overall model.

[0115] In some embodiments of the present application, the structure constraint condition is determined by the following way:

[0116] The fixed positions of the stator and the rotor on the rigid mounting platform are determined, the deformation constraint parameters are determined based on the fixed positions, and the structure constraint condition is determined according to the deformation constraint parameters.

[0117] Specifically, in some embodiments of the present application, the coarse channel of the inductive synchronizer is located in the inner diameter region, and the fine channel is located in the outer ring region. The outer diameter edge of the stator is fixedly connected with the rigid mounting platform by 6 evenly distributed screws, and the inner diameter edge of the rotor is fixed with the rigid mounting platform by 6 evenly distributed screws. The fixed positions are as shown in Figure 3 .

[0118] Further, the stator is set by a deformation constraint parameter, which defines a deformation constraint of the stator and the rotor in a specified direction at a screw mounting position. In addition, the material expansion coefficients of the induction synchronizer and the mounting member are defined by the deformation constraint parameter. Since the material expansion coefficients of the induction synchronizer and the mounting member are significantly different, when the ambient temperature changes, the induction synchronizer stator and rotor are deformed axially and radially under the combined action of thermal expansion and contraction and the constraint of the screw on the rigid mounting platform.

[0119] The deformation constraint parameter accurately characterizes the deformation limitation of the stator and the rotor on the rigid mounting platform due to the fixed position, so that the simulation process of the finite element model is more in line with the actual situation, and the accuracy of the finite element simulation result is greatly improved.

[0120] In some embodiments of the present application, the temperature field condition is determined by the following method:

[0121] The radiation boundary condition of the finite element model is determined based on the Stefan-Boltzmann law;

[0122] The internal heat source power of the induction synchronizer is determined, and the heat conduction coefficient between the stator, the rotor and the rigid mounting platform is obtained, so as to determine the heat conduction condition of the finite element model according to the internal heat source power and the heat conduction coefficient;

[0123] The temperature field condition is determined according to the radiation boundary condition and the heat conduction condition.

[0124] Specifically, in a hot vacuum environment, the induction synchronizer mainly exchanges heat with the surrounding environment through thermal radiation. In order to simulate the vacuum environment, when setting the radiation boundary condition for each unit of the finite element model, the present application only considers thermal radiation and closes the convective heat transfer. Then, the heat radiation exchange amount of each component of the induction synchronizer with the vacuum environment is calculated based on the Stefan-Boltzmann law, and the specific calculation formula is shown in the following formula (6):

[0125] Formula (6)

[0126] In the formula, represents the above heat radiation exchange amount, represents the surface emissivity, which is taken as 0.8 in some examples of the present application, represents the Stefan-Boltzmann constant, which is , represents the radiation surface area, represents the surface temperature of each component, represents the ambient temperature.

[0127] It should be noted that the above emissivity It can be obtained by experimental measurement or reference to relevant data of similar materials, for example, the emissivity of a metal surface is generally between 0.2 and 0.8, and different surface treatments will cause the emissivity to vary. In the finite element software, the accurate emissivity and the environmental radiation temperature, such as when simulating a space environment, the environmental radiation temperature can be approximately 2.7K, i.e. the cosmic microwave background radiation temperature.

[0128] In some embodiments of the present application, it is also considered that the induction synchronizer has internal heat sources in actual operation, such as Joule heat generated by the current passing through the winding. Therefore, when setting the heat conduction conditions for each element of the finite element model, the internal heat source power needs to be accurately set in the finite element model. Preferably, based on the resistance of the winding and the current passing through, the heat generated per unit time is determined according to the Joule law, and is loaded as an internal heat source to the element of the finite element model corresponding to the winding.

[0129] At the same time, considering the propagation of heat conduction inside the induction synchronizer, the heat conduction coefficients between the components are set to accurately simulate the heat transfer process between different material components. Preferably, the heat conduction coefficients of the epoxy plate, copper foil winding, hard aluminum and martensitic stainless steel and other internal materials of the induction synchronizer follow the Fourier law, and the specific calculation formula is shown in the following formula (7):

[0130] Formula (7)

[0131] In the formula, q represents the heat flux density, k represents the thermal conductivity of the material, and represents the temperature gradient.

[0132] Further, the above radiation boundary condition and heat conduction condition are introduced into the finite element model as the temperature field condition. In the subsequent deformation simulation process under different environmental temperatures using the finite element model, the actual thermal conditions of each element under the current environmental temperature can be determined through the above temperature field condition, so that the deformation and stress distribution caused by thermal expansion under the thermal conditions can be calculated.

[0133] The embodiments of the present application consider that the induction synchronizer exchanges heat with the vacuum environment only through thermal radiation, accurately determine the radiation boundary condition using the Stefan-Boltzmann law, and at the same time consider the Joule heat generated inside the induction synchronizer in actual operation, so as to determine the heat conduction condition using the internal heat source power and the heat conduction coefficient, so as to comprehensively and accurately construct the temperature field condition of the induction synchronizer in the hot vacuum environment, so that the finite element model can accurately simulate the heat transfer process of the induction synchronizer in the hot vacuum environment, and greatly improve the accuracy of the finite element simulation results.

[0134] ​In some embodiments of the present application, the step S3 described above can include the following steps:

[0135] Step S31, set different ambient temperatures, and obtain the actual surface temperature of each element in the finite element model under different ambient temperatures based on the temperature field conditions.

[0136] Specifically, in some embodiments of the present application, the temperature variation range of the ambient temperature is 0℃ to 50℃, and a preset step size is set to 5℃ to simulate the vacuum temperature variation condition.

[0137] For each set ambient temperature, the determined radiation boundary condition and heat conduction condition are loaded into the finite element model synchronously, and then the influence of the heat radiation exchange between the ambient temperature and the inductive synchronizer on the surface temperature of each element in the finite element model is solved to obtain the actual surface temperature of each element under the corresponding ambient temperature.

[0138] Step S33, solve the element deformation of each element based on the actual surface temperature and the structure constraint condition to obtain the simulation result according to the solved element deformation, wherein the simulation result includes the stator radial deformation distribution, the stator axial deformation distribution, the rotor radial deformation distribution and the rotor axial deformation distribution under different ambient temperatures.

[0139] Specifically, in some embodiments of the present application, the ANSYS finite element analysis software is used to load the temperature field conditions and the structure constraint conditions in the finite element model, and the corresponding ambient temperature is set, so that the finite element solver of the ANSYS finite element analysis software is run, and the element deformation of each element output by the software can be obtained. In the process of solving by the finite element solver, the difference between the actual surface temperature of each element and the initial temperature before temperature variation is taken as the temperature load, and the thermal expansion coefficient and the elastic modulus of the material to which the element belongs are combined to calculate the hoop stress generated by the element by using the hoop stress formula shown in the above formula (4), and the radial stress is determined according to the Poisson's ratio of the material to which the element belongs by using the above formula (5), so that the element deformation generated by the hoop stress and the radial stress to the element is solved under the above structure constraint condition, wherein each element will generate corresponding element deformation in the axial and radial directions under the joint action of the hoop stress and the radial stress.

[0140] Compared with the embodiment shown in Figure 2 Compared with the embodiment shown in

[0141] In some embodiments of this application, step S5 may include the following steps:

[0142] Step S51: Determine the maximum deformation of the stator radial deformation distribution, stator axial deformation distribution, rotor radial deformation distribution, and rotor axial deformation distribution at different ambient temperatures.

[0143] Specifically, Figure 4 The simulation results of the stator radial deformation distribution as a function of ambient temperature are shown. Figure 4 It can be seen that the radial deformation of the stator caused by changes in ambient temperature gradually increases from the inner ring to the outer ring, and the maximum radial deformation of the stator is 8.122e. -5 m, which is approximately equal to 0.08 mm. Figure 5 The simulation results of the stator axial deformation distribution as a function of ambient temperature are shown. Figure 5 It can be seen that the axial deformation of the stator caused by changes in ambient temperature gradually decreases from the inner ring to the outer ring, and the maximum axial deformation of the stator is 2.144e. -5 m, which is approximately equal to 0.021 mm. Figure 6 The simulation results of rotor radial deformation distribution as a function of ambient temperature are shown. Figure 6 It can be seen that the radial deformation of the rotor caused by changes in ambient temperature gradually increases from the inner ring to the outer ring, and the maximum radial deformation of the rotor is 4.26e. -5 m, which is approximately equal to 0.042 mm. Figure 7 The simulation results of rotor axial deformation distribution as a function of ambient temperature are shown. Figure 7 It can be seen that the axial deformation of the rotor caused by changes in ambient temperature gradually increases from the inner ring to the outer ring, and the maximum axial deformation of the rotor is 5.91e. - 6 m, which is approximately equal to 0.0057 mm.

[0144] Step S53: Determine the stator radial deformation characteristics, stator axial deformation characteristics, rotor radial deformation characteristics, and rotor axial deformation characteristics corresponding to each ambient temperature based on the maximum deformation. The stator deformation characteristics include stator radial deformation characteristics and stator axial deformation characteristics, and the rotor deformation characteristics include rotor radial deformation characteristics and rotor axial deformation characteristics.

[0145] Specifically, such as Figure 4 As shown, the stator radial deformation distribution consists of the radial deformation of each unit. By iterating through the radial deformation data of all units belonging to the stator at various ambient temperatures, the largest value (0.08 mm) is selected as the stator radial deformation characteristic for that ambient temperature. Figure 5As shown, the stator axial deformation distribution is composed of the unit deformation of each unit in the axial direction, and the radial deformation variable data corresponding to all units belonging to the stator at each environmental temperature are traversed, and the maximum deformation variable 0.021 mm is selected as the stator axial deformation feature corresponding to the environmental temperature.

[0146] Similarly, as Figure 6 and Figure 7 shown, based on the rotor radial deformation distribution and the rotor axial deformation distribution, the rotor radial deformation feature is determined as 0.042 mm, and the rotor axial deformation feature is determined as 0.0057 mm. For details, please refer to the foregoing description, which will not be repeated here.

[0147] Compared with the embodiment shown in Figure 2 , the embodiments of the present application extract the key features of the inductive synchronizer in each deformation dimension at different environmental temperatures by using the maximum deformation variable, so as to comprehensively analyze the deformation influence of temperature change on multiple dimensions of the stator radial deformation, the stator axial deformation, the rotor radial deformation and the rotor axial deformation.

[0148] In some embodiments of the present application, the above step S7 can include the following steps:

[0149] Step S71, determining a radial comprehensive deformation feature of the inductive synchronizer corresponding to different environmental temperatures according to the first difference absolute value of the stator radial deformation feature and the rotor radial deformation feature.

[0150] Specifically, the radial comprehensive deformation feature represents the dimensional error change of the stator and the rotor at different environmental temperatures, and the greater the radial comprehensive deformation feature, the greater the dimensional error between the stator and the rotor. The radial comprehensive deformation feature is calculated based on the following formula (8):

[0151] Formula (8)

[0152] In the formula, represents the radial comprehensive deformation feature at the i th environmental temperature, represents the stator radial deformation feature at the i th environmental temperature, represents the rotor radial deformation feature at the i th environmental temperature.

[0153] Step S73, determining an axial comprehensive deformation feature of the inductive synchronizer corresponding to different environmental temperatures according to the second difference absolute value of the stator axial deformation feature and the rotor axial deformation feature.

[0154] Specifically, the axial comprehensive deformation feature represents the change of the stator-rotor gap at different environmental temperatures, and the greater the axial comprehensive deformation feature, the greater the stator-rotor gap. The axial comprehensive deformation feature is calculated based on the following formula (9):

[0155] Formula (9)

[0156] In the formula, represents the axial comprehensive deformation characteristic at the i th ambient temperature, represents the stator axial deformation characteristic at the i th ambient temperature, represents the rotor axial deformation characteristic at the i th ambient temperature.

[0157] Step S75, determining the comprehensive deformation characteristic according to the average of the radial comprehensive deformation characteristic and the axial comprehensive deformation characteristic.

[0158] Specifically, the radial comprehensive deformation characteristic and the axial comprehensive deformation characteristic are subjected to mean processing to obtain the comprehensive deformation characteristic to represent the total deformation of the stator and the rotor. The comprehensive deformation characteristic is calculated based on the following formula (10):

[0159] Formula (10)

[0160] In the formula, represents the comprehensive deformation characteristic at the i th ambient temperature.

[0161] Step S77, fitting the mapping relationship between the ambient temperature and the comprehensive deformation characteristic to obtain a first fitting curve, so as to determine the deformation analysis result according to the first fitting curve.

[0162] Specifically, the discrete data points corresponding to the ambient temperature and the comprehensive deformation characteristic are subjected to curve fitting to obtain the first fitting curve, and the expression of the first fitting curve is shown in the following formula (11):

[0163] Formula (11)

[0164] In the formula, represents the total deformation of the inductive synchronizer, represents the ambient temperature, so the first fitting curve is the total deformation fitting curve of the inductive synchronizer.

[0165] Therefore, the comprehensive deformation of the stator and the rotor of the inductive synchronizer is positively correlated with the ambient temperature. Further, Figure 8 The fitting curves between the radial comprehensive deformation characteristic , the axial comprehensive deformation characteristic and the comprehensive deformation characteristic and the ambient temperature are shown, and it can be seen from Figure 8 that the comprehensive deformation characteristic is the radial comprehensive deformation characteristic and the axial comprehensive deformation characteristic The average value.

[0166] and Figure 2 Compared to the embodiments shown, the embodiments of this application utilize axial comprehensive deformation features to quantitatively characterize the change in stator-rotor gap, and utilize radial comprehensive deformation features to quantitatively characterize the change in stator-rotor dimensional error. Furthermore, the average values ​​of radial and axial comprehensive deformation features are used to comprehensively and accurately characterize the overall deformation of the induction synchro under a thermal vacuum environment, thereby improving the accuracy of deformation analysis results.

[0167] In some embodiments of this application, after determining the deformation analysis results of the inductive synchro at different ambient temperatures, the method further includes step S9, which may specifically include the following steps:

[0168] Step S91: Obtain the first slope of the first fitted curve.

[0169] Specifically, the first slope is obtained as 0.0139 according to the above formula (11).

[0170] Step S93: Obtain the output sampling data of the inductive synchro at different ambient temperatures, and fit the mapping relationship between the ambient temperature and the output sampling data to obtain a second fitting curve, so as to obtain the second slope of the second fitting curve.

[0171] Specifically, to verify the accuracy of the simulation results of the aforementioned finite element model, this embodiment of the application obtains the output sampling data from the thermal vacuum test measurement of the inductive synchro, that is, measures the actual digital quantities (codewords) output by the fine and coarse channels of the inductive synchro under a thermal vacuum simulation environment. Then, the deformation analysis results from the finite element simulation are compared with the output sampling data, ensuring comparability under the same temperature dimension and characteristic scale, to construct a two-channel data model under variable temperature conditions.

[0172] First, four key phases of the sine and cosine phases within half an electrical cycle of the inductive synchro are selected: 0, π / 4, π / 2, and 3π / 4. The corresponding mechanical angles for these four key phases are determined to be 0 degrees, 7.5 arcminutes, 15 arcminutes, and 22.5 arcminutes. At the measurement positions corresponding to these four mechanical angles, the temperature range is set from 0°C to 50°C. During heating and cooling processes at 10°C intervals, the digital outputs of the coarse and fine channels of the inductive synchro are sampled. Based on the sampling results, the above-mentioned output sampling data is obtained, and the corresponding heating and cooling curves are fitted.

[0173] Figure 9 and Figure 10 The coarse channel temperature rise and fall curves and the fine channel temperature rise and fall curves corresponding to the four measurement positions mentioned above are shown respectively. Figure 9 and Figure 10It can be seen that the coarse channel temperature rising and falling curve and the fine channel temperature rising and falling curve represent that the digital quantity corresponding to the output sampling data of the inductive synchro is negatively correlated with the temperature, and the change slope of the negative correlation is different for the temperature rising and falling stages.

[0174] Subsequently, the average curves of the temperature rising and falling stages are fitted for the coarse channel and the fine channel respectively. Specifically, the temperature rising curves and the temperature falling curves corresponding to each measurement position are averaged respectively for the coarse channel to obtain the coarse channel temperature rising average curve and the coarse channel temperature falling average curve. Similarly, the temperature rising curves and the temperature falling curves corresponding to each measurement position are averaged respectively for the fine channel to obtain the fine channel temperature rising average curve and the fine channel temperature falling average curve. Finally, the coarse channel temperature rising average curve and the coarse channel temperature falling average curve are averaged twice to finally obtain the coarse channel average temperature change fitting curve LC in the full temperature range, and similarly, the fine channel temperature rising average curve and the fine channel temperature falling average curve are averaged twice to finally obtain the fine channel average temperature change fitting curve LF in the full temperature range.

[0175] In the embodiment of the present application, the second fitting curve can be one of the coarse channel average temperature change fitting curve LC and the fine channel average temperature change fitting curve LF, or a curve obtained by averaging the coarse channel average temperature change fitting curve LC and the fine channel average temperature change fitting curve LF.

[0176] In step S95, the orthogonality of the first fitting curve and the second fitting curve is analyzed according to the first slope and the second slope, and the finite element model is adjusted if the orthogonality does not meet the preset condition.

[0177] Specifically, to verify the consistency of the theoretical angle of the finite element simulation and the actual angle of the hot vacuum test, the orthogonality of the first slope of the total deformation fitting curve LX and the second slope of the coarse channel average temperature change fitting curve LC or the fine channel average temperature change fitting curve LF is analyzed under the same temperature dimension and characteristic scale. Since the temperature is positively correlated with the total deformation, and the temperature is negatively correlated with the digital quantity output by the fine channel and the coarse channel, if the total deformation fitting curve LX and the coarse channel average temperature change fitting curve LC and the fine channel average temperature change fitting curve LF achieve a certain degree of orthogonality, it can be verified that the finite element model can accurately analyze the deformation characteristics of the inductive synchro.

[0178] Figure 11The total deformation fitting curve LX, the coarse channel average temperature fitting curve LC, and the fine channel average temperature fitting curve LF are shown. The orthogonality of the total deformation fitting curve LX with both the coarse channel average temperature fitting curve LC and the fine channel average temperature fitting curve LF meets the preset condition. Specifically, the reciprocal of the slope of the total deformation fitting curve LX calculated by the finite element simulation has a small difference in error compared to the slopes of the actually tested coarse channel average temperature fitting curve LC and the fine channel average temperature fitting curve LF, indicating that the accuracy of the finite element model meets the requirements. If the orthogonality does not meet the preset condition, parameter adjustments to the finite element model are required, such as adjusting the mesh generation.

[0179] In addition, Figure 11 In the fitted curves shown, the orthogonality between the total deformation LX obtained from the finite element simulation and the measured fine channel LF is 7.9%, and the orthogonality between the total deformation LX and the measured coarse channel LC is 30.7%. In other words, the consistency between the finite element simulation and the measured data is particularly prominent in the fine channel.

[0180] and Figure 2 Compared to the embodiments shown, the embodiments of this application utilize orthogonality analysis of the first slope and the second slope to effectively verify the modeling accuracy of the finite element model, ensuring that the finite element model can adapt to the deformation simulation requirements of the induction synchronizer under different operating conditions, so that the finite element model always maintains high precision, thereby further improving the accuracy of the deformation analysis results.

[0181] Accordingly, please refer to Figure 12 This application provides a thermal vacuum environment deformation analysis device for an inductive synchro, the device comprising:

[0182] Modeling module 100 is used to construct a finite element model of the inductive synchro and determine the structural constraints and temperature field conditions of the finite element model. For details, please refer to step S1.

[0183] The simulation module 200 is used to simulate the finite element model based on the temperature field conditions and the structural constraints to obtain simulation results. For details, please refer to step S3.

[0184] The feature processing module 300 is used to determine the stator deformation characteristics and rotor deformation characteristics of the inductive synchro under different ambient temperatures based on the simulation results. For details, please refer to step S5.

[0185] Analysis module 400 is used to determine the comprehensive deformation characteristics of the inductive synchro based on the stator deformation characteristics and the rotor deformation characteristics, so as to determine the deformation analysis results of the inductive synchro under different ambient temperatures based on the comprehensive deformation characteristics. For details, please refer to step S7.

[0186] Further function description of each module and unit is the same as the corresponding embodiment described above, and will not be repeated here.

[0187] The thermal vacuum environment deformation analysis device in the embodiment is presented in the form of functional units. The units refer to ASIC (Application Specific Integrated Circuit) circuits, processors and memories that execute one or more software or fixed programs, and / or other devices that can provide the above functions.

[0188] Please refer to Figure 13 , Figure 13 is a structural schematic diagram of a computer device provided by the embodiment of the present application, as Figure 13 shown, the computer device includes one or more processors 10, a memory 20, and an interface for connecting various components, including a high-speed interface and a low-speed interface. Various components are communicatively connected to each other by different buses, and can be installed on a common motherboard or in other ways as needed. The processor can process instructions executed within the computer device, including instructions stored in the memory or on the memory to display GUI graphics information on an external input / output device, such as a display device coupled to the interface. In some alternative embodiments, multiple processors and / or multiple buses can be used with multiple memories and multiple memories, if necessary. Similarly, multiple computer devices can be connected, each providing part of the necessary operations (for example, as a server array, a group of blade servers, or a multi-processor system). Figure 13 In the embodiment, the processor 10 is taken as an example.

[0189] The processor 10 can be a central processor, a network processor, or a combination thereof. The processor 10 can further include a hardware chip. The hardware chip can be an application specific integrated circuit, a programmable logic device, or a combination thereof. The programmable logic device can be a complex programmable logic device, a field programmable logic gate array, a general array logic, or any combination thereof.

[0190] The memory 20 stores instructions executable by the at least one processor 10, so that the at least one processor 10 executes the method shown in the above embodiment.

[0191] The memory 20 can include a program storage area and a data storage area. The program storage area can store an operating system, application programs required for at least one function, etc. The data storage area can store data created by the computer device, etc. In addition, the memory 20 can include a high-speed random access memory, and can also include a non-transitory memory such as at least one disk storage device, a flash memory device, or other non-transitory solid state memory device. In some alternative embodiments, the memory 20 can optionally include memory that is remotely located with respect to the processor 10, and which can be connected to the computer device through a network. Examples of such networks include, but are not limited to, the Internet, an enterprise intranet, a local area network, a mobile communications network, and combinations thereof.

[0192] The memory 20 can include a volatile memory, such as a random access memory, and / or can include a non-volatile memory, such as at least one disk storage device, a flash memory device, or other non-volatile solid state memory device. The memory 20 can also include an embedded dynamic or static random access memory (DRAM or SRAM), and / or can include both a volatile memory and a non-volatile memory. The memory 20 can further include a combination of memory types. For example, the memory 20 can include a combination of SRAM and DRAM as the volatile memory, and can include a combination of flash memory and one or more hard disk storage devices as the non-volatile memory.

[0193] The computer device also includes a communication interface 30 for communicating with other devices or communication networks.

[0194] The systems, apparatuses, modules, or units illustrated in the above embodiments can be implemented by computer chips or entities, or by products with certain functions. A typical implementation device is a computer. Specifically, the computer can be, for example, a personal computer, a laptop computer, a cellular phone, a camera phone, a smart phone, a personal digital assistant, a media player, a navigation device, an email device, a game console, a tablet computer, a wearable device, or a combination of any of these devices.

[0195] For the convenience of description, the above apparatuses are described in various units by function respectively. Of course, the functions of the units can be implemented in the same or multiple software and / or hardware in the implementation of the present application.

[0196] It should also be noted that the terms "comprising", "including", or any other variant thereof are intended to cover a non-exclusive inclusion, such that processes, methods, articles, or devices that comprise a list of elements do not include only those elements in the list, but can also include other elements not expressly listed or inherent to such processes, methods, articles, or devices. Without more limitations, an element defined by the phrase "comprising a" does not exclude the existence of additional identical elements in the process, method, article, or device including the element.

[0197] The various embodiments described in this specification are presented by way of example, and not limitation. Each embodiment is presented in a separate section, and the same or similar elements in different embodiments are cross-referenced. Each embodiment highlights the differences from other embodiments.

[0198] The embodiments of the present application described above are merely exemplary and are not intended to limit the present application. The skilled in the art can make various modifications and variations without departing from the spirit and scope of the present application. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present application shall be included in the scope of the claims of the present application.

[0199] Although the embodiments of the present application are described in conjunction with the accompanying drawings, various modifications and changes can be made by those skilled in the art without departing from the spirit and scope of the present application, and such modifications and changes are intended to fall within the scope of the appended claims.

Claims

1. A method for analyzing the deformation of an inductive synchro in a thermal vacuum environment, characterized in that, The method includes: Construct a finite element model of the inductive synchro and determine the structural constraints and temperature field conditions of the finite element model; The finite element model is simulated based on the temperature field conditions and the structural constraints to obtain simulation results. Based on the simulation results, the stator deformation characteristics and rotor deformation characteristics of the inductive synchro under different ambient temperatures were determined. The comprehensive deformation characteristics of the inductive synchro are determined based on the stator deformation characteristics and the rotor deformation characteristics, so as to determine the deformation analysis results of the inductive synchro under different ambient temperatures based on the comprehensive deformation characteristics; The inductive synchro includes a stator, a rotor, and a rigid mounting platform. The structural constraints are determined in the following manner: Determine the fixed positions of the stator and the rotor on the rigid mounting platform; Deformation constraint parameters are determined based on the fixed position, and the structural constraint conditions are determined according to the deformation constraint parameters.

2. The method according to claim 1, characterized in that, The finite element model for constructing the inductive synchronizer includes: Based on the geometric parameters and connection relationships of the stator, the rotor, and the rigid mounting platform, a three-dimensional geometric model of the inductive synchronizer is constructed. The critical and non-critical parts of the stator, the rotor, and the rigid mounting platform are determined, and the first grid size corresponding to the critical part and the second grid size corresponding to the non-critical part are determined respectively, wherein the first grid size is smaller than the second grid size; The three-dimensional geometric model is meshed based on the first mesh size and the second mesh size to obtain the finite element model.

3. The method according to claim 2, characterized in that, The temperature field conditions are determined in the following manner: The radiation boundary conditions of the finite element model are determined based on the Stefan-Boltzmann law; The internal heat source power of the inductive synchro is determined, and the thermal conductivity coefficient between the stator, the rotor, and the rigid mounting platform is obtained, so as to determine the thermal conduction conditions of the finite element model based on the internal heat source power and the thermal conductivity coefficient. The temperature field conditions are determined based on the radiation boundary conditions and the heat conduction conditions.

4. The method according to claim 1, characterized in that, The simulation of the finite element model based on the temperature field conditions and the structural constraints to obtain simulation results includes: Different ambient temperatures are set, and the actual surface temperature of each element in the finite element model is obtained under different ambient temperatures based on the temperature field conditions; The element deformation of each element is solved based on the actual surface temperature and the structural constraints, so as to obtain the simulation results based on the solved element deformation. The simulation results include the stator radial deformation distribution, stator axial deformation distribution, rotor radial deformation distribution and rotor axial deformation distribution under different ambient temperatures.

5. The method according to claim 4, characterized in that, The stator deformation characteristics include stator radial deformation characteristics and stator axial deformation characteristics, and the rotor deformation characteristics include rotor radial deformation characteristics and rotor axial deformation characteristics; The determination of the stator deformation characteristics and rotor deformation characteristics of the inductive synchro under different ambient temperatures based on the simulation results includes: The maximum deformation values ​​corresponding to the stator radial deformation distribution, the stator axial deformation distribution, the rotor radial deformation distribution, and the rotor axial deformation distribution at different ambient temperatures are determined respectively. The stator radial deformation characteristic, the stator axial deformation characteristic, the rotor radial deformation characteristic, and the rotor axial deformation characteristic are determined based on the maximum deformation for each of the ambient temperatures.

6. The method according to claim 5, characterized in that, Determining the comprehensive deformation characteristics of the inductive synchro based on the stator deformation characteristics and the rotor deformation characteristics includes: The radial composite deformation characteristics of the inductive synchro corresponding to the different ambient temperatures are determined based on the absolute value of the first difference between the stator radial deformation characteristics and the rotor radial deformation characteristics. The axial comprehensive deformation characteristics of the inductive synchro corresponding to the different ambient temperatures are determined based on the absolute value of the second difference between the stator axial deformation characteristics and the rotor axial deformation characteristics. The comprehensive deformation feature is determined based on the average value of the radial comprehensive deformation feature and the axial comprehensive deformation feature.

7. The method according to claim 1, characterized in that, The determination of the deformation analysis results of the inductive synchro under different ambient temperatures based on the comprehensive deformation characteristics includes: A first fitting curve is obtained by fitting the mapping relationship between the ambient temperature and the comprehensive deformation characteristics, and the deformation analysis result is determined based on the first fitting curve.

8. The method according to claim 7, characterized in that, After determining the deformation analysis results of the inductive synchro under different ambient temperatures, the method further includes: Obtain the first slope of the first fitted curve; The output sampling data of the inductive synchro at different ambient temperatures is acquired, and the mapping relationship between the ambient temperature and the output sampling data is fitted to obtain a second fitting curve, so as to obtain the second slope of the second fitting curve; The orthogonality of the first fitted curve and the second fitted curve is analyzed based on the first slope and the second slope, and the finite element model is adjusted if the orthogonality does not meet the preset conditions.

9. A computer device, characterized in that, include: A memory and a processor are communicatively connected, the memory stores computer instructions, and the processor executes the computer instructions to perform the thermal vacuum environment deformation analysis method for the inductive synchro according to any one of claims 1 to 8.

Images