Nondestructive testing simulation method for spacecraft T-shaped structure based on angle beam ultrasonic wave

Abstract

This disclosure provides a simulation method for non-destructive testing of spacecraft T-shaped structural components based on angle-beam ultrasonic waves. The method includes: creating a physical model of the spacecraft T-shaped structural component using COMSOL finite element simulation software and a model developer; setting the excitation source as a voltage source with modulated Gaussian pulses; setting the material physical properties and boundary conditions for different regions in the elastic wave time-domain display module; setting the association between the electrostatic module and the circuit module to complete the driving configuration of the non-destructive testing simulation physical model; generating a non-uniform mesh; completing the solver settings and performing calculations to obtain the detection process of the longitudinal and shear waves of the angle-beam ultrasonic waves and the change process of the voltage signal when the reflected wave reaches the transducer. This disclosure accurately analyzes the changes in pressure waves and shear waves during the non-destructive testing process, providing a theoretical basis for further research on the non-destructive testing process of spacecraft T-shaped structural components.

Description

Technical Field

[0001] This disclosure relates to the field of nondestructive testing and simulation technology, and in particular to a simulation method for nondestructive testing of spacecraft T-shaped structural components based on angle beam ultrasonic waves. Background Technology

[0002] As complex and sophisticated equipment, the integrity and reliability of the structural components of spacecraft directly determine flight safety. Among them, T-shaped structural components, due to their combination of connection strength and lightweight characteristics, are widely used in critical load-bearing parts such as cabin frames and load supports. During the manufacturing (e.g., welding, forming) and service (e.g., vibration, temperature cycling) processes of these structural components, latent defects such as microcracks and inclusions are prone to occur. If these defects are not identified in time, they may lead to structural failure under extreme conditions. Therefore, non-destructive testing technology is needed to achieve early and accurate location of defects.

[0003] Angular beam ultrasonic testing has become one of the mainstream technologies for non-destructive testing of metal structural components due to its advantages of strong penetration and high sensitivity to linear defects. However, the special geometry of T-shaped structural components in spacecraft (with right-angle welds and abrupt thickness changes) makes ultrasonic waves prone to reflection, refraction, and mode conversion (conversion from longitudinal wave to shear wave) during propagation. Traditional testing methods have two major limitations: First, they rely on empirical parameter settings (such as excitation signal frequency and probe angle), requiring extensive physical experiments to verify the rationality of the parameters. This not only consumes high costs in specimen preparation and time but also makes it difficult to cover all potential defect conditions. Second, it is impossible to predict the ultrasonic wave propagation path and defect reflection signal characteristics before actual testing, which can easily lead to missed or false detections due to insufficient parameter adaptability. In particular, the identification accuracy for micro-cracks (width less than 0.1 mm) is difficult to meet the stringent quality requirements of spacecraft.

[0004] The increasing demands for testing efficiency in spacecraft manufacturing and maintenance have rendered traditional trial-and-error physical testing methods inadequate for the rapidly iterative structural design requirements. Against this backdrop, there is an urgent need for a simulation method capable of accurately simulating the propagation and defect interaction of angle-beam ultrasonic waves in spacecraft T-shaped structural components. This method would utilize digital means to optimize testing parameters and predict signal characteristics in advance, reducing physical testing costs while simultaneously improving testing accuracy and reliability. This would provide efficient and controllable technical support for the non-destructive testing of spacecraft T-shaped structural components. Summary of the Invention

[0005] The purpose of this disclosure is to provide a simulation method for non-destructive testing of spacecraft T-shaped structural components based on angle beam ultrasonic waves, in order to solve the problems existing in the prior art.

[0006] The embodiments of this disclosure adopt the following technical solution: a simulation method for non-destructive testing of spacecraft T-shaped structural components based on angle beam ultrasonic waves, comprising: creating a non-destructive testing simulation physical model of the spacecraft T-shaped structural component using COMSOL finite element simulation software and a model developer, wherein the non-destructive testing simulation physical model is a two-dimensional physical geometric model, including a transducer region, a matching layer region, a damping block region, a wedge region, a spacecraft T-shaped structural component region, and a crack region, wherein the crack region is located within the spacecraft T-shaped structural component region; setting the material parameters and simulation parameters of the non-destructive testing simulation physical model in the model developer. The process involves: setting the excitation source as a modulated Gaussian pulse voltage source in the model developer; setting the material physical properties and boundary conditions for different regions in the elastic wave time-domain display module of the model developer; setting the association between the electrostatic module and the circuit module in the model developer to complete the driving configuration of the non-destructive testing simulation physical model; dividing a non-uniform mesh in the model developer and setting different maximum element sizes for different regions in the non-destructive testing simulation physical model; completing the solver settings in the model developer, performing the solution calculation, and obtaining the detection process of the angle beam ultrasonic longitudinal wave and shear wave and the change process of the voltage signal when the reflected wave reaches the transducer.

[0007] The beneficial effects of this disclosure are as follows: By using finite element simulation to assist in the design of non-destructive testing, an integrated geometric model of multiple regions, including the transducer, matching layer, damping block, and spacecraft T-shaped structural component, is constructed during the actual testing process. Key parameters such as the piezoelectric material characteristics, damping effect, and reflection coefficient of the crack interface in each region are fully considered and designed. This enables a visualized simulation of the entire process of non-destructive testing of spacecraft T-shaped structural components using angle beam ultrasonic waves. The changes in the voltage source, terminal voltage, pressure wave, and shear wave of the angle beam ultrasonic waves during the non-destructive testing process are accurately analyzed, providing a theoretical basis for further research on the non-destructive testing process of spacecraft T-shaped structural components. Attached Figure Description

[0008] To more clearly illustrate the technical solutions in one or more embodiments of this specification or in 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 recorded in this specification. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0009] Figure 1 This is a flowchart of a simulation method for non-destructive testing of spacecraft T-shaped structural components based on angle beam ultrasonic waves, as described in this disclosure.

[0010] Figure 2 This is the physical model for non-destructive testing simulation constructed in the embodiments of this disclosure;

[0011] Figure 3 This is a schematic diagram of mesh division in an embodiment of this disclosure;

[0012] Figure 4 This is a waveform diagram of the voltage source in an embodiment of this disclosure;

[0013] Figure 5 This is a schematic diagram illustrating the change in terminal voltage in an embodiment of this disclosure;

[0014] Figure 6 This is a schematic diagram illustrating the changes in pressure waves and shear waves in an embodiment of this disclosure. Detailed Implementation

[0015] To enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the technical solutions in one or more embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this specification, and not all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of this document.

[0016] To address the problems existing in the prior art, this disclosure provides a simulation method for non-destructive testing of spacecraft T-shaped structural components based on angle beam ultrasonic waves, the flowchart of which is shown below. Figure 1 As shown, the main steps include the following:

[0017] S10 uses COMSOL finite element simulation software and a model developer to create a non-destructive testing simulation physical model of a spacecraft T-shaped structural component.

[0018] In this embodiment, when constructing the non-destructive testing simulation physical model for the spacecraft T-shaped structural component, it is necessary to fully consider the physical structure of the angle beam probe and the morphology of the spacecraft T-shaped structural component. This results in a non-destructive testing simulation physical model including a transducer region, a matching layer region, a damping block region, a wedge region, the spacecraft T-shaped structural component region, and a crack region. The transducer region, matching layer region, damping block region, and wedge region correspond to the angle beam probe and are used to simulate the generation and propagation process of real angle beam ultrasonic waves during the simulation. The spacecraft T-shaped structural component region and crack region simulate the actual structural component to be inspected and the damaged area; therefore, the crack region should be located within the spacecraft T-shaped structural component region. It is important to note that when creating the non-destructive testing simulation physical model, only a two-dimensional physical geometric model needs to be constructed. The waveform simulation results in the plane can satisfy the theoretical basis for the waveform characteristics during the actual inspection process.

[0019] Specifically, the non-destructive testing simulation physical model is constructed based on the following steps: A pentagonal region ABCDE containing three right angles is constructed, with the five angles being the upper left (A), upper middle (B), upper right (C), lower right (D), and lower left (E). Points L and M are set between A and B. A rectangular region LMKJ is constructed based on edge LM, and a rectangular region JKIH is constructed based on edge JK. A concave region ALHIMBGF is constructed based on edge AB. Points N and U are set on the extension lines on both sides of edge ED. A T-shaped polygonal region is constructed based on edge NU. A T-shaped polygonal region NUTSRQPO is constructed using the NU framework. Within the NUTSRQPO region, an irregular triangular region VXW is constructed. Specifically, the transducer region is a rectangular region JKIH, the matching layer region is a rectangular region LMKJ, the damping block region is a concave region ALHIMBGF, the wedge region is a pentagonal region ABCDE, the spacecraft T-shaped structural component region is the T-shaped polygonal region NUTSRQPO, and the crack region is the irregular triangular region VXW. The final non-destructive testing simulation physical model is as follows: Figure 2 As shown.

[0020] S20, set the material parameters and simulation parameters of the non-destructive testing simulation physical model in the model developer.

[0021] In this embodiment, the material parameters of the simulation physical model for non-destructive testing of the spacecraft T-shaped structural component include the transducer region, matching layer region, damping block region, wedge region, spacecraft T-shaped structural component region, and crack region. For the spacecraft T-shaped structural component region, crack region, wedge region, and transducer region, their materials can be directly configured from the material library. For example, right-click the "Materials" button in the model developer and select "Add Material from Library." The material for the spacecraft T-shaped structural component region and crack region is set to Aluminum, the material for the wedge region is set to Acrylic plastic, and the material for the transducer region is set to Lead Zirconate Titanate (PZT-5H). For the matching layer region and the damping block region, their corresponding material parameters are configured by adding empty materials. Based on the actual materials and finite element analysis requirements, at least the pressure wave velocity, shear wave velocity, and density are configured. For example, the pressure wave velocity, shear wave velocity, and density of the matching layer region are set to 3400 m / s, 1920 m / s, and 2280 kg / m³ in the material details column. 3 The damping block area has pressure wave velocity, shear wave velocity, and density set to 1500 m / s, 775 m / s, and 6580 kg / m³ in the material details column. 3 The simulation parameters for nondestructive testing include the signal center frequency. and signal period Based on the different workpiece material properties and testing requirements, the signal center frequency in this embodiment... It can be set between 0.5MHz and 10MHz, with a signal period. The value can be between 200 ns and 100 μs. In a preferred embodiment, the signal center frequency is... The signal frequency is 1.5MHz, and the signal period is... The value is 666.67ns.

[0022] S30, in the model developer, set the excitation source to a voltage source that modulates a Gaussian pulse.

[0023] The excitation source is the voltage source that drives the probe to generate ultrasonic waves. In this embodiment, it is set as a voltage source that modulates a Gaussian pulse, and its expression is:

[0024]

[0025] Where A represents the maximum amplitude of the signal, f0 represents the center frequency of the signal, and T0 represents the period of the signal. This represents the Gaussian function window used as a modulator. This represents the sinusoidal carrier wave that constitutes the main body of the signal.

[0026] S40, in the elastic wave time domain display module of the model developer, set the material physical properties and boundary conditions for different regions.

[0027] To realistically simulate the waveform characteristic changes during non-destructive testing of components, this embodiment requires setting the material physical properties and boundary conditions for different regions in the model, including at least linear elastic material parameters, piezoelectric material parameters, low-reflection boundary parameters, crack parameters, and damping parameters. Specifically,

[0028] In the settings window of the elastic wave time-domain explicit module in the model developer, specify the pressure wave velocity and shear wave velocity in the linear elastic material field to visualize the changes in pressure and shear waves. The pressure and shear wave velocities are calculated based on the momentum balance equation, the kinematic relationship between strain rate and velocity gradient, and the constitutive equation. Their functional expressions are as follows:

[0029]

[0030]

[0031]

[0032] in, This indicates the density of the medium, specifically referring to the density of the T-shaped structural components of a spacecraft. The velocity vector describes the motion of a particle. For local acceleration, denoted by the rate of change of velocity over time; For stress tensor, The divergence of the stress tensor represents the spatial cumulative effect of stress within the medium (the effect of internal forces). Volume force per unit volume; The strain tensor describes the deformation of the medium; For strain rate tensor, i.e., the rate of change of strain over time; Let the velocity gradient tensor describe the spatial variation of velocity. It is its transpose; The deformation rate tensor (the symmetric part of the velocity gradient) is the kinematic source of the strain rate; It is a fourth-order constitutive tensor (such as the elastic tensor, viscoelastic tensor, etc.) used to reflect the mechanical response characteristics of materials; This represents the double dot product operation between a fourth-order tensor and a second-order tensor, used for linear mapping between tensors.

[0033] The settings for piezoelectric material parameters, low-reflection boundary parameters, crack parameters, and damping parameters are all designed to simulate the characteristics of various regions involved in the detection process under real-world conditions. Specifically, this includes: clicking Properties in the Physics toolbar, selecting Piezoelectric Material, and specifying the transducer region as the domain; clicking Boundary in the Physics toolbar, selecting Low-Reflection Boundary, and setting edges FG, NO, and UT as low-reflection boundaries; clicking Boundary in the Physics toolbar, selecting Crack, and setting the crack region as Crack; clicking Properties in the Physics toolbar, selecting Damping, specifying the matching layer region as the domain, and selecting Damping Ratio in the input parameter list. Specific parameters can be set as follows: Select Damping, specify the matching layer region as the domain, select Damping Ratio in the input parameter list, and set the parameters as follows: Frequency 1: HZ, damping ratio 1:0.05, frequency 2: HZ, damping ratio 2:0.05; In the physics toolbar, click Properties, select Damping, specify the domain as the wedge region, select Damping Ratio in the input parameter list, and set the parameters as follows: Frequency 1: HZ, damping ratio 1:0.01, frequency 2: HZ, damping ratio 2:0.01; In the physics toolbar, click Properties, select Damping, specify the domain as the damping block region, select Damping Ratio in the input parameter list, and set the parameters as follows: Frequency 1: HZ, damping ratio 1:0.05, frequency 2: HZ, damping ratio 2:0.05; In the physics toolbar, click Properties, select Damping, specify the domain as the spacecraft T-structure area, select Damping Ratio in the input parameter list, and set the parameters as follows: Frequency 1: HZ, damping ratio 1:0.005, frequency 2: HZ, damping ratio 2:0.005.

[0034] S50 allows you to set up the association between the electrostatic module and the circuit module in the model developer to complete the driving configuration of the non-destructive testing simulation physical model.

[0035] The electrostatic module and circuit module are used to configure the electrical characteristics of the model. In this embodiment, the configuration of the electrostatic module and circuit module completes the driving configuration of the transducer region in the non-destructive testing simulation physical model. Specifically, in the settings window of the electrostatic module in the model developer, the domain is specified as the transducer region; right-click on electrostatics and select charge conservation piezoelectric, specifying the domain as the transducer region; click on the boundary in the physics toolbar, select ground, and set the boundary as edge GK; click on the boundary in the physics toolbar, select terminal, set the boundary as edge HI, and set the terminal type to circuit. Based on Gauss's law equation, the equation relating electric displacement vectors, and the equation relating electric field strength and electric potential in Maxwell's equations, its functional expression is:

[0036]

[0037]

[0038]

[0039] Among them, in formula (5) For divergence operations, describe the "source / sink" distribution of a vector field; It is the electric displacement vector (electric flux density), which combines the electric field response of vacuum and medium; The volume density of free charge; It is the vacuum permittivity, which describes the relationship between the electric field and electric displacement in a vacuum; The electric field intensity vector; For the vacuum contribution, i.e., in the absence of a dielectric, the relationship between electric displacement and electric field is: ; The polarization intensity induced by the electric field; Polarization induced by elastic strain exhibits electromechanical coupling, such as the piezoelectric effect, i.e., mechanical strain. This polarizes the dielectric, thereby altering the electric displacement; The potential is in formula (7). For gradient calculation, the negative sign This indicates that the direction of the electric field intensity is the direction in which the electric potential decreases the fastest.

[0040] Subsequently, the terminals of the circuit types set in the electrostatic module are configured through the circuit module, specifically including voltage source parameters, resistance parameters, and external terminal parameters, to form a complete power supply loop to drive the transducer to generate ultrasonic waves. The specific configuration can be as follows: In the circuit module of the model developer, right-click the circuit and select Voltage Source, set the node name of label p to 1, and set the node name of label n to 0; right-click the circuit and select Resistor, set the node name of label p to 1, and set the node name of label n to 2; right-click the circuit and select External I Terminal, set the node name to 2, and set the node name of label n to 2; select Terminal Voltage in the Potential field of the External Terminal section.

[0041] S60 allows for the creation of non-uniform meshes in the model developer, enabling the setting of different maximum element sizes for different regions in the non-destructive testing simulation physical model.

[0042] In finite element analysis (FEM), the continuous model can be discretized into numerous small elements by meshing. The displacement increments of these element nodes constitute the basic unknowns in the finite element iteration process. Therefore, the meshing result affects the accuracy and computational efficiency of the FEM. When performing autonomous meshing using software, a maximum element size can be defined as the condition for non-uniform meshing. In this embodiment, the maximum element size is calculated based on the shear wave velocity of the corresponding material in different regions and the signal center frequency of the excitation source to ensure that the ultrasonic waves can accurately act on each mesh during the FEM process. Subsequently, the maximum element size of different regions is used as the upper limit of the mesh division to perform non-uniform meshing on different regions of the non-destructive testing simulation physical model.

[0043] Specifically, the maximum cell size of the grid in different regions is achieved based on the following formula.

[0044]

[0045] in, The maximum unit size, The shear wave velocity of the material. The center frequency of the excitation source signal. This is the stability coefficient. Different regions use different materials; the shear wave of the corresponding material in each region is substituted into the formula to calculate the corresponding region. That is, stability coefficient The value of stability coefficient is usually between 1 and 10, and can be determined based on the center frequency of the excitation source signal. Typically, the stability coefficient... The value of the signal center frequency The magnitudes are positively correlated. At 1.5MHz, The value can be 1.5.

[0046] In this embodiment, the transducer region and the matching layer region are not excessively meshed. In the mesh module of the model developer, right-click the mesh and select Map, specify the domain as the transducer region and the matching layer region, right-click the map and select Distribution, specify the boundary as edge KI, right-click the map and select Size, specify the boundary as edge KI, specify the geometric entity as the transducer region and the matching layer region, and set the maximum element size to 0.00077 and 0.00085 respectively.

[0047] For the damping block region, wedge region, and spacecraft T-structure region, free triangular meshing is required. Furthermore, the maximum cell size of the corresponding triangular mesh must be limited based on the frequency characteristics of the ultrasonic waves to ensure that the ultrasonic waves can effectively act on each mesh during transmission. Specifically, in the mesh module of the model developer, right-click the mesh and select free triangular mesh. Specify the geometric entities as the damping block region, wedge region, and spacecraft T-structure region. Based on the signal center frequency and signal period set in S20, the maximum cell sizes for the damping block region, wedge region, and spacecraft T-structure region can be set to 0.00034, 0.00044, and 0.00139, respectively. Figure 3 A grid division result is shown.

[0048] S70, complete the solver settings in the model developer, perform the solution calculation, and obtain the detection process of the angle beam ultrasonic longitudinal wave and shear wave and the change process of the voltage signal when the reflected wave reaches the transducer.

[0049] After the above configuration is completed, the solver can be set up and the calculation can be completed to obtain the detection process of the longitudinal and shear waves of the angle beam ultrasonic wave and the change process of the voltage signal when the reflected wave reaches the transducer, which serves as the theoretical basis for non-destructive testing of structural components. Specifically, this embodiment uses a non-uniform step size for simulation calculation. The calculation method is as follows: under the "Research 1" node in the model developer, click "Step 1: Transient", set the time unit in the research settings to: s, and set the output time step to: range(0,0.0000134, 0.002). Then, click "Calculate" in the research toolbar to start the simulation of non-destructive testing based on angle beam ultrasonic waves.

[0050] After solving the calculations, expanding the "Results" list will show the changes of the "voltage source" during the simulation process, as follows: Figure 4 As shown, and in conjunction with formulas (2) to (4), the changes in "terminal voltage" and "pressure wave and shear wave" are calculated as follows: Figure 5 and Figure 6As shown, in actual non-destructive testing, if the waveform of the terminal voltage appears as follows... Figure 5 The changes shown indicate that the structural component under test has a defect.

[0051] This embodiment utilizes finite element simulation to assist in the design of non-destructive testing (NDT). It constructs an integrated geometric model of multiple regions, including the transducer, matching layer, damping block, and spacecraft T-shaped structural components, during the actual testing process. Key parameters such as piezoelectric material properties, damping effect, and reflection coefficient at the crack interface are fully considered and designed for each region. This enables a visualized simulation of the entire NDT process for spacecraft T-shaped structural components using angle-beam ultrasonic waves. The model accurately analyzes the changes in the voltage source, terminal voltage, pressure wave, and shear wave of the angle-beam ultrasonic waves during NDT, providing a theoretical basis for further research on the NDT process of spacecraft T-shaped structural components.

[0052] It should be noted that the solution provided in this embodiment should also be applicable to structural components of other shapes besides T-shaped structural components, including but not limited to rectangular components, spherical components, etc., and the shape of the crack shown in this embodiment is only schematic and should not be used to limit the scope of protection of this disclosure.

[0053] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this disclosure, and are not intended to limit them. Although this disclosure has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this disclosure.

Claims

1. A simulation method for non-destructive testing of spacecraft T-shaped structural components based on angle beam ultrasonic waves, characterized in that, include: Using COMSOL finite element simulation software and the model developer, a non-destructive testing simulation physical model of a spacecraft T-shaped structural component was created. This model is a two-dimensional physical geometric model, including a transducer region, a matching layer region, a damping block region, a wedge region, a spacecraft T-shaped structural component region, and a crack region. The crack region is located within the T-shaped structural component region. The non-destructive testing simulation physical model is constructed based on the following steps: A pentagonal region ABCDE containing three right angles is constructed, with its five angles being the upper left corner A, upper middle corner B, upper right corner C, lower right corner D, and lower left corner E. Points L and M are set between A and B. A rectangular region LMKJ is constructed based on edge LM. A rectangular region JKIH is constructed based on edge JK, a concave region ALHIMBGF is constructed based on edge AB, points N and U are established on the extension lines on both sides of edge ED, a T-shaped polygonal region NUTSRQPO is constructed based on edge NU, and an irregular triangular region VXW is constructed inside the T-shaped polygonal region NUTSRQPO; wherein, the transducer region is a rectangular region JKIH, the matching layer region is a rectangular region LMKJ, the damping block region is a concave region ALHIMBGF, the wedge region is a pentagonal region ABCDE, the spacecraft T-shaped structural component region is a T-shaped polygonal region NUTSRQPO, and the crack region is an irregular triangular region VXW; Set the material parameters and simulation parameters of the non-destructive testing simulation physical model in the model developer; In the model developer, set the excitation source to a voltage source that modulates a Gaussian pulse; In the elastic wave time-domain display module of the model developer, set the material physical properties and boundary conditions for different regions, including: setting the linear elastic material column to pressure wave velocity and shear wave velocity, the pressure wave velocity and the shear wave velocity are calculated based on the momentum balance equation, the kinematic relationship equation between strain rate and velocity gradient and the constitutive equation; setting the transducer region's property to piezoelectric material in the physics toolbar; setting edges FG, NO, UT to low reflection boundaries in the physics toolbar; setting the crack region to a crack in the physics toolbar; and setting the damping parameters for different regions in the physics toolbar. In the model developer, the association between the electrostatic module and the circuit module is set to complete the driving configuration of the non-destructive testing simulation physical model; The maximum cell size of the mesh in different regions is calculated based on the shear wave velocity of the corresponding material in different regions and the signal center frequency of the excitation source. The maximum cell size of different regions is used as the upper limit of the mesh division. Non-uniform mesh division is performed on different regions of the non-destructive testing simulation physical model, and different maximum cell sizes are set for different regions in the non-destructive testing simulation physical model. Complete the solver settings in the model developer, perform the solution calculation, and obtain the detection process of the longitudinal wave and shear wave of the angle beam ultrasonic wave and the change process of the voltage signal when the reflected wave reaches the transducer.

2. The simulation method for non-destructive testing of spacecraft T-shaped structural components according to claim 1, characterized in that, Setting the material parameters and simulation parameters of the nondestructive testing simulation physical model in the model developer includes: Materials are provided in the material library for the spacecraft T-shaped structural component area, the crack area, the wedge block area, and the transducer area; Empty material is added to the matching layer region and the damping block region, and pressure wave velocity, shear wave velocity and density are configured for the empty material according to the material properties of the matching layer region and the damping block region; The simulation parameters for nondestructive testing include the signal center frequency and the signal period.

3. The simulation method for non-destructive testing of spacecraft T-shaped structural components according to claim 2, characterized in that, The expression for the voltage source of the modulated Gaussian pulse is: Where A represents the maximum amplitude of the signal. Indicates the center frequency of the signal. Indicates the signal period. This represents the Gaussian function window used as a modulator. This represents the sinusoidal carrier wave that constitutes the main body of the signal.

4. The simulation method for non-destructive testing of spacecraft T-shaped structural components according to claim 1, characterized in that, The step of setting the association between the electrostatic module and the circuit module in the model developer to complete the driving configuration of the non-destructive testing simulation physical model includes: In the electrostatic module, charge conservation piezoelectric parameters, grounding parameters, and terminal parameters of the transducer region are set; wherein, edge JK of the transducer region is set as ground, edge HI is set as terminal, and the terminal type is set as circuit. In the circuit module of the model developer, voltage source parameters, resistance parameters, and external terminal parameters are set for the circuit to realize the drive configuration of the transducer region.

5. The simulation method for non-destructive testing of spacecraft T-shaped structural components according to claim 1, characterized in that, The calculation of the maximum cell size of the mesh in different regions based on the shear wave velocity of the corresponding material in different regions and the signal center frequency of the excitation source includes: The maximum cell size is calculated based on the following formula: in, The maximum unit size, The shear wave velocity of the material. The center frequency of the excitation source signal. This is the stability coefficient.

6. The simulation method for non-destructive testing of spacecraft T-shaped structural components according to claim 1, characterized in that, The process of setting up the solver and performing the solution calculation in the model developer includes: In the Model Developer, under the Study 1 node, click "Step 1: Transient". Configure the time unit and output time step in the Study Settings, and click "Calculate" in the Study toolbar.

7. The simulation method for non-destructive testing of spacecraft T-shaped structural components according to any one of claims 1 to 6, characterized in that, Also includes: Expanding the results list yields the voltage source variation results, the detection process of the angle beam ultrasonic longitudinal wave and shear wave, and the voltage signal variation process when the reflected wave reaches the transducer.

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