Method and device for determining parameters of sensor embedded in charging structure and related equipment

Abstract

The invention relates to the technical field of mechanical state monitoring, and discloses a method and device for determining parameters of a sensor embedded with a charging structure and related equipment, and the method comprises the steps: building a finite element model through a solid propellant test piece based on an embedded sensor; performing tensile simulation on the finite element model to obtain a stress-strain field of the solid propellant test piece embedded with the sensor; carrying out mechanical state analysis on the stress-strain field, and determining strain coordination and a stress concentration coefficient between the sensor and the solid propellant; the target material parameter of the sensor is determined based on the strain coordination and the stress concentration coefficient, and the material parameter of the sensor embedded with the propellant is optimized, so that the measurement accuracy of the mechanical state of the charging structure is improved, and the complexity of integrity evaluation of the charging structure of the engine is further reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of mechanical state monitoring, and in particular to a method, device, computer equipment and storage medium for determining parameters of a sensor embedded in a charge structure. Background Art

[0002] In order to effectively verify the calculation results of the structural integrity of solid motor charge, it is necessary to monitor the mechanical state of the motor charge structure. The monitoring results can, on the one hand, judge the failure of the motor charge structure such as debonding and cracking in real time, and on the other hand, lay a data foundation for the "virtual-real" digital twin technology of the engine. At present, the mechanical state of the solid motor is detected by burying sensors in the propellant and interface or arranging them in the inner cavity, thereby providing richer data support for the simulation verification of the structural integrity of the solid motor charge.

[0003] However, due to the discontinuity of the material in the solid motor charge structure and the change in material performance due to aging, the measurement accuracy of the mechanical state of the motor charge structure is low, making the assessment of the motor charge structure integrity more complicated. Therefore, how to determine the material parameters of the sensor embedded in the propellant is an urgent problem to be solved. Summary of the invention

[0004] The present application proposes a method, device, computer equipment and storage medium for determining sensor parameters embedded in a charge structure, which optimizes the material parameters of a sensor embedded in a propellant to improve the measurement accuracy of the mechanical state of the charge structure, thereby reducing the complexity of the integrity assessment of the engine charge structure.

[0005] In a first aspect, a method for determining parameters of a sensor embedded in a charge structure is provided, comprising:

[0006] Establish a finite element model based on a solid propellant specimen with embedded sensors;

[0007] Performing a tensile simulation on the finite element model to obtain a stress-strain field of a solid propellant specimen embedded with a sensor;

[0008] Performing a mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant;

[0009] A target material parameter of the sensor is determined based on the strain compatibility and the stress concentration factor.

[0010] In a second aspect, a sensor parameter determination device embedded in a charge structure is provided, comprising:

[0011] Building a module for building finite element models based on solid propellant specimens with embedded sensors;

[0012] A simulation module, used for performing a tensile simulation on the finite element model to obtain a stress-strain field of a solid propellant specimen embedded with a sensor;

[0013] An analysis module, used to perform mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant;

[0014] A determination module is used to determine a target material parameter of the sensor based on the strain compatibility and the stress concentration factor.

[0015] Optionally, in some embodiments of the present application, the analysis module includes:

[0016] An extraction submodule, used for extracting tensile equivalent stress data of a solid propellant specimen from the stress-strain field;

[0017] The analysis submodule is used to perform mechanical state analysis on the tensile equivalent stress data to determine the strain coordination and the stress concentration factor.

[0018] Optionally, in some embodiments of the present application, the analysis submodule includes:

[0019] A first acquisition unit, configured to acquire the longitudinal stress on the upper surface of the sensor based on the tensile equivalent stress data;

[0020] A second acquisition unit is used to acquire the average stress of the solid propellant without the embedded sensor;

[0021] The normalization unit is used to normalize the longitudinal stress on the upper surface of the sensor with the average stress of the solid propellant without the embedded sensor to obtain a stress concentration factor.

[0022] Optionally, in some embodiments of the present application, the analysis submodule includes:

[0023] a first determining unit, configured to determine, based on the tensile equivalent stress data, an average strain difference between the sensor and a solid propellant around the sensor, an average strain of the solid propellant around the sensor, an average strain difference between the sensor and a non-buried propellant at the same position, and an average strain difference of the non-buried solid propellant at the same position;

[0024] a second determining unit, configured to determine a first relative strain difference based on an average strain difference between the sensor and the solid propellant around the sensor and an average strain of the solid propellant around the sensor;

[0025] a third determination unit, configured to determine a second relative strain difference based on an average strain difference between the sensor and the unburied solid propellant at the same position and an average strain difference of the unburied solid propellant at the same position;

[0026] The fourth determining unit is used to determine the strain coordination based on the first relative strain difference and the second relative strain difference.

[0027] Optionally, in some embodiments of the present application, the simulation module includes:

[0028] A partitioning unit, used for performing mesh partitioning on the finite element model;

[0029] The simulation unit is used to perform a tensile simulation on the finite element model in response to a model parameter setting operation of the finite element model to obtain the stress-strain field.

[0030] Optionally, in some embodiments of the present application, the finite element model is a two-dimensional plane model.

[0031] Optionally, in some embodiments of the present application, the sensor is a flexible sensor, and the flexible sensor includes two parallel electrode plates and a flexible interlayer arranged between the two electrode plates.

[0032] In a third aspect, a computer device is provided, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the above-mentioned method for determining sensor parameters embedded in a charge structure when executing the computer program.

[0033] In a fourth aspect, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps of the above-mentioned method for determining sensor parameters embedded in a charge structure are implemented.

[0034] The present application provides a method, device, computer equipment and storage medium for determining sensor parameters of an embedded charge structure, by establishing a finite element model based on a solid propellant specimen embedded with a sensor; performing a tensile simulation on the finite element model to obtain the stress-strain field of the solid propellant specimen embedded with the sensor; performing a mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant; and determining the target material parameters of the sensor based on the strain coordination and stress concentration coefficient. In the sensor parameter determination scheme for an embedded charge structure provided in the present application, a finite element model is established based on a solid propellant specimen embedded with a sensor, and then a tensile simulation is performed on the finite element model to perform a mechanical state analysis on the stress-strain field of the solid propellant specimen embedded with the sensor, to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant, thereby determining the target material parameters of the sensor. It can be seen that the mechanical state analysis of the stress-strain field of the solid propellant specimen embedded with the sensor is carried out through the tensile simulation of the finite element model corresponding to the solid propellant specimen embedded with the sensor, so as to optimize the material parameters of the sensor embedded in the propellant, improve the measurement accuracy of the mechanical state of the charge structure, and thus reduce the complexity of the evaluation of the integrity of the engine charge structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0036] Figure 1 A diagram of the application environment of the method for determining sensor parameters embedded in a charge structure provided in an embodiment of the present application;

[0037] Figure 2 A flow chart of a method for determining sensor parameters embedded in a charge structure provided in an embodiment of the present application;

[0038] Figure 3 A schematic diagram of the structure of a solid propellant specimen with an embedded sensor provided in an embodiment of the present application;

[0039] Figure 4 A schematic diagram of the stress-strain field of a rectangular specimen embedded with a flexible sensor provided in an embodiment of the present application when stretched;

[0040] Figure 5 A schematic diagram of the coordinates of the Mises stress on the upper surface of the sensor in the solid propellant specimen provided in the embodiment of the present application;

[0041] Figure 6A schematic diagram of a Mises stress change curve of a rigid sensor and a Mises stress change curve of a flexible sensor provided in an embodiment of the present application;

[0042] Figure 7 A schematic diagram of normalized longitudinal stress on the upper surface of a rigid sensor and a flexible sensor provided in an embodiment of the present application;

[0043] Figure 8 A schematic diagram of tensile stress curves corresponding to different moduli provided in an embodiment of the present application;

[0044] Fig. 9 A schematic diagram of a curve of relative stress difference corresponding to different moduli provided in an embodiment of the present application;

[0045] Fig.10 A schematic diagram of a longitudinal tensile strain trend change curve of a flexible interlayer provided in an embodiment of the present application;

[0046] Fig.11 A schematic diagram of a curve of relative strain difference corresponding to different moduli provided in an embodiment of the present application;

[0047] Fig.12 A schematic diagram of the Mises stress curve of the upper surface of the flexible sensor under different moduli provided in an embodiment of the present application;

[0048] Fig.13 A schematic diagram of the variation of Mises stress with the modulus of the flexible interlayer provided in the embodiment of the present application;

[0049] Fig.14 A schematic diagram of a variation curve between the average strain of the interlayer of the flexible sensor made of different materials and the average strain of the surrounding propellant provided in an embodiment of the present application;

[0050] Fig.15 A schematic diagram of a curve showing the variation of the relative difference of two types of strains of flexible sensors made of different materials provided in an embodiment of the present application;

[0051] Fig.16 A structural block diagram of a sensor parameter determination device embedded in a charge structure provided in an embodiment of the present application;

[0052] Fig.17 A structural block diagram of a computer device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0053] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0054] In addition, described feature, structure or characteristic can be combined in one or more embodiments in any suitable manner. In the following description, many specific details are provided to provide a full understanding of the embodiments of the present application. However, those skilled in the art will appreciate that the technical scheme of the present application can be put into practice without one or more of the specific details, or other methods, components, devices, steps, etc. can be adopted. In other cases, known methods, devices, realizations or operations are not shown or described in detail to avoid blurring the various aspects of the application.

[0055] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically independent entities. That is, these functional entities may be implemented in software form, or in one or more hardware modules or integrated circuits, or in different networks and / or processor devices and / or microcontroller devices.

[0056] The flowcharts shown in the accompanying drawings are only exemplary and do not necessarily include all the contents and operations / steps, nor must they be executed in the order described. For example, some operations / steps can be decomposed, and some operations / steps can be combined or partially combined, so the actual execution order may change according to actual conditions.

[0057] The method for determining the parameters of the sensor embedded in the charge structure provided by the embodiment of the present invention can be applied in the following aspects: Figure 1in an application environment. Among them, the computer device 110 communicates with the server 120 through the network 130. The computer device 110 can establish a finite element model based on a solid propellant specimen embedded with a sensor; perform a tensile simulation on the finite element model to obtain a stress-strain field of the solid propellant specimen embedded with a sensor; perform a mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration factor between the sensor and the solid propellant; determine the target material parameters of the sensor based on the strain coordination and the stress concentration factor, and display the target material parameters through the computer device 110. In the present invention, a finite element model is established based on a solid propellant specimen embedded with a sensor, and then a tensile simulation is performed on the finite element model to perform a mechanical state analysis on the stress-strain field of the solid propellant specimen embedded with a sensor, determine the strain coordination and stress concentration factor between the sensor and the solid propellant specimen, and thereby determine the target material parameters of the sensor. It can be seen that the mechanical state analysis of the stress-strain field of the solid propellant specimen embedded with the sensor is performed through the tensile simulation of the finite element model corresponding to the solid propellant specimen embedded with the sensor, so as to optimize the material parameters of the sensor embedded in the propellant, improve the measurement accuracy of the mechanical state of the charge structure, and thus reduce the complexity of the evaluation of the integrity of the engine charge structure. Among them, the computer device 110 can be but is not limited to various smart phones 110-1, tablet computers 110-2 and laptop computers 110-3. The present invention is described in detail below through specific embodiments.

[0058] See also Figure 2 As shown, Figure 2 A flow chart of a method for determining sensor parameters embedded in a charge structure provided in an embodiment of the present invention is provided. The method can be applied to both a terminal and a server. This embodiment is described by applying the method to the server as an example. The method for determining sensor parameters embedded in a charge structure comprises the following steps:

[0059] 101:Establish a finite element model based on a solid propellant specimen with embedded sensors.

[0060] The sensor is an interface stress sensor. According to the actual application of the interface stress sensor in the solid motor grain results, the sensor is embedded in the insulation layer / propellant interface of the solid propellant specimen with reference to the aerospace industry standards. Its position and actual size are shown in the figure. Figure 3 As shown, the sensor may be a capacitive sensor, the capacitive sensor plate thickness is 0.4 mm, and the thickness of the flexible interlayer is 2 mm.

[0061] The sensor may be a flexible sensor, which includes two parallel plates and a flexible interlayer disposed between the two plates. The solid propellant specimen may be a rectangular specimen. Figure 3 As shown in the figure, when the sensor is embedded in the solid propellant case, the flexible interlayer of the sensor is in close contact with the two electrodes, the sensor and the solid propellant, and the insulation layer, and the bonding interfaces are all fully bound constraints. Among them, the propellant specimen shell can be considered as a linear elastic material with a density of 7.8g / cm3, an elastic modulus of MPa, and a Poisson's ratio of 0.3. The insulation layer is considered as a hyperelastic material of the neo-Hookean model with a density of 1.1g / cm3, C10 of 0.9916, and D1 of 0.0103. The propellant is considered as a linear viscoelastic material with a density of 1.7g / cm3 and a Poisson's ratio of 0.49. Please refer to Table 1 for its relaxation modulus, which shows the relaxation modulus E measured at different time points. i The density of the sensor material plate is 0.8g / cm3, the density of the flexible interlayer is 1g / cm3, and the remaining material mechanical parameters are selected differently in different analysis processes and can be set according to the actual application scenario, and no specific restrictions are made here.

[0062]

[0063]

[0064] Table 1

[0065] 102: Performing a tensile simulation on the finite element model to obtain a stress-strain field of the solid propellant specimen in which the sensor is embedded.

[0066] The stress-strain field can be obtained by adjusting the parameters of the finite element model to deform the finite element model. The stress-strain field can include the stress field and the strain field.

[0067] For example, the sensor embedded in the solid propellant is a flexible sensor, the size of the flexible sensor is 2.9*11mm, the modulus of the flexible sensor electrode plate is 3GPa, the Poisson's ratio is 0.3, the modulus of the flexible interlayer is 8MPa, and the Poisson's ratio is 0.496. Among them, the solid propellant specimen is a rectangular specimen, the lower shell of the rectangular specimen is fixed, the upper shell is stretched at a speed of 20mm / min, and the total displacement is 20mm.

[0068] like Figure 4 The stress-strain field of the rectangular specimen embedded with the flexible sensor is shown. Figure 4 The Mises stress field shown in a and Figure 4b shows the maximum principal strain field. By performing a mechanical state analysis on the stress data in the Mises stress field, the stress variation result between the stress inside the flexible interlayer of the sensor and the stress between the external solid propellant is determined. The stress variation result is that the stress inside the flexible interlayer of the sensor is similar to the stress between the external solid propellant, and the stress is smaller as it approaches the middle. The sensor plate is bent after the solid propellant specimen is stretched, and both sides of the upper and lower plates are bent upward, and the stress concentration at the corner in contact with the propellant is reduced. By performing a mechanical state analysis on the maximum principal strain field, the sensor strain result can be obtained. Specifically, the sensor strain result is that the strain of the sensor plate hardly changes, while the flexible interlayer part of the sensor produces a large strain.

[0069] In one application scenario, the finite element model may be meshed, and the model parameters of the finite element model may be adjusted to perform a tensile simulation on the finite element model to obtain a stress-strain field. That is, in one embodiment, the step of "performing a tensile simulation on the finite element model to obtain a stress-strain field of a solid propellant specimen embedded with a sensor" includes:

[0070] (11) meshing the finite element model;

[0071] (12) In response to a model parameter setting operation of the finite element model, a tensile simulation is performed on the finite element model to obtain the stress-strain field.

[0072] In order to improve the computational efficiency and facilitate the analysis, the finite element model can be a two-dimensional plane model. When the sensor is embedded in the propellant, the sensor flexible interlayer is in close contact with the two poles, the sensor and the solid propellant, and the solid propellant and the insulation layer. The bonding interface is fully bound, and damage factors such as interface debonding are ignored. Among them, the shear stress is transmitted through the friction between the contact interfaces. When the solid propellant is a concrete component, the sensor is in close contact with the surrounding concrete when embedded in the concrete component.

[0073] Among them, the model parameter setting operation can be triggered by the user, such as displaying a model parameter adjustment button on the display screen of the terminal device, triggering a model parameter adjustment instruction in response to the user's adjustment operation on the model parameter adjustment button, and then triggering the model parameter adjustment operation according to the model parameter adjustment instruction.

[0074] The model parameters of the finite element model may include the relaxation elastic modulus of the electrode plate of the sensor, the relaxation elastic modulus of the flexible interlayer, the distance between the two electrode plates of the sensor, and the like.

[0075] Exemplarily, the mesh division of the finite element model may be that the solid propellant part is divided into 9864 units, the flexible sandwich part of the sensor is divided into 1022 units, the upper and lower plates are divided into 219 units respectively, and the mesh near the sensor part is encrypted.

[0076] Among them, the propellant specimen shell in the finite element model adopts linear elastic material; the insulation layer adopts the hyperelastic material of the nonlinear hyperelastic model; and the propellant adopts linear viscoelastic material.

[0077] 103: Performing a mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant.

[0078] The Mises stress data on the sensor surface and the longitudinal stress on the sensor surface can be extracted from the stress-strain field. Figure 5 As shown, the specimen is a solid propellant specimen, the upper electrode plate is the upper electrode plate of the sensor, the lower electrode plate is the lower electrode plate of the sensor, the flexible interlayer is the flexible interlayer of the sensor, the x-axis starting point of the sensor is 1.5 mm to the left of the left end point of the upper surface of the sensor, and the end point is 1.5 mm to the right of the right end point of the upper surface, so that the Mises stress data of the upper surface of the rigid sensor and the Mises stress data of the flexible sensor and the longitudinal stress of the upper surface of the sensor can be obtained.

[0079] The Mises stress change curve is generated based on the Mises stress data, and the mechanical state analysis of the Mises stress change curve is performed to determine the stress concentration factor. Figure 6 As shown, the Mises stress change curves of the rigid sensor and the Mises stress change curves of the flexible sensor are shown. It can be determined that the corners where the upper surfaces of the rigid sensor and the flexible sensor contact the propellant have obvious stress concentration, and the stress of the flexible sensor is significantly less than that of the rigid sensor. Since the electrode plate of the flexible sensor is bent and subjected to bending stress, the stress on the electrode plate of the flexible sensor is greater than that of the rigid sensor near the middle.

[0080] like Figure 7 As shown, the normalized longitudinal stress at the corner where the upper surface of the rigid sensor and the flexible sensor contact the propellant also has stress concentration, but the longitudinal stress of the flexible sensor is significantly smaller than that of the rigid sensor, and the longitudinal stress near the middle of the upper plate is similar to that of the rigid sensor.

[0081] The stress concentration factor was calculated by normalizing the longitudinal stress on the sensor surface with the average stress of the propellant without embedded sensors.

[0082] Based on the stress data in the stress-strain field, the average strain inside the sensor, the average strain of the solid propellant around the sensor, and the average strain of the embedded solid propellant at the same position can be calculated, and then the relative strain difference of the sensor can be determined. As shown in Table 2, the first relative strain difference and the second relative strain difference of the rigid sensor, as well as the first relative strain difference and the second relative strain difference of the flexible sensor are determined based on the average strain inside the sensor, the average strain of the solid propellant around the sensor, and the average strain of the embedded solid propellant at the same position. The strain coordination between the sensor and the solid propellant can be determined according to the first relative strain difference and the second relative strain difference. As can be seen from Table 2, the values ​​of the first relative strain difference and the second relative strain difference of the rigid sensor are -99.99%, while the first relative strain difference of the flexible sensor is -18.74%, and the second relative strain difference is -39.49%, which are both smaller than those of the rigid sensor. Based on this, it can be seen that when the flexible sensor is embedded in the solid propellant, the stress-strain field of the propellant specimen is less affected, and it has a great improvement on the quality of the engine charge interface structure.

[0083]

[0084]

[0085] Table 2

[0086] In one application scenario, the tensile equivalent stress data of the solid propellant specimen can be extracted from the stress-strain field, so as to perform a mechanical state analysis on the tensile equivalent stress data to determine the strain coordination and stress concentration factor. That is, in one embodiment, the step of "performing a mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration factor between the sensor and the solid propellant" includes:

[0087] (21) obtaining tensile equivalent stress data of the solid propellant specimen based on the stress-strain field;

[0088] (22) Performing a mechanical state analysis on the tensile equivalent stress data to determine the strain coordination and the stress concentration factor.

[0089] Among them, the tensile equivalent stress data include the longitudinal stress on the upper surface of the sensor, the average strain difference between the flexible interlayer of the sensor and the surrounding propellant, the average strain of the propellant around the sensor, the propellant tensile stress-strain and the flexible interlayer stress-strain, etc. The strain coordination and stress concentration factor can be determined by performing a mechanical state analysis on the tensile equivalent stress data.

[0090] In one application scenario, the longitudinal stress on the upper surface of the sensor can be obtained from the tensile equivalent stress data, and the longitudinal stress on the upper surface of the sensor is normalized with the average stress of the solid propellant without an embedded sensor to obtain the stress concentration factor. That is, in one embodiment, the step of "performing a mechanical state analysis on the tensile equivalent stress data to determine the stress concentration factor" includes:

[0091] (31) obtaining the longitudinal stress on the upper surface of the sensor based on the tensile equivalent stress data;

[0092] (32) Obtaining the average stress of solid propellant without embedded sensors;

[0093] (33) The longitudinal stress on the upper surface of the sensor is normalized with the average stress of the solid propellant without an embedded sensor to obtain a stress concentration factor.

[0094] The stress concentration factor is calculated by normalizing the longitudinal stress on the sensor surface with the average stress of the solid propellant without embedded sensors. Specifically, the stress concentration factor can be calculated according to the following formula (1):

[0095] k=σ yy / σ0 (1)

[0096] Where k is the stress concentration factor, σ yy The longitudinal stress on the sensor surface, σ0 is the average stress of the solid propellant without embedded sensors.

[0097] In one application scenario, the strain coordination can be determined by determining the relative strain difference between the average strain difference between the sensor and the unburied solid propellant at the same position and the average strain difference of the unburied solid propellant at the same position, and the average strain difference between the sensor and the solid propellant around the sensor and the average strain of the solid propellant around the sensor, that is, in one embodiment, the step of "performing a mechanical state analysis on the tensile equivalent stress data to determine the strain coordination" includes:

[0098] (41) determining, based on the tensile equivalent stress data, an average strain difference between the sensor and the solid propellant around the sensor, an average strain of the solid propellant around the sensor, an average strain difference between the sensor and an unburied propellant at the same position, and an average strain difference of the unburied solid propellant at the same position;

[0099] (42) determining a first relative strain difference based on an average strain difference between the sensor and the solid propellant surrounding the sensor and an average strain of the solid propellant surrounding the sensor;

[0100] (43) determining a second relative strain difference based on an average strain difference between the sensor and the unburied solid propellant at the same position and an average strain difference of the unburied solid propellant at the same position;

[0101] (44) Determine strain compatibility based on the first relative strain difference and the second relative strain difference.

[0102] The first relative strain difference is obtained by dividing the average strain difference between the flexible interlayer of the sensor and the surrounding propellant by the average strain of the propellant surrounding the sensor. Specifically, the first relative strain difference is calculated according to the following formula (2):

[0103]

[0104] In the formula, Δε relative1 is the first relative strain difference, is the average strain difference between the sensor's flexible interlayer and its surrounding propellant, The first relative strain difference is obtained by the average strain of the propellant around the sensor, wherein the average strain of the propellant around the sensor refers to the average strain of the propellant within 1 mm on both sides of the flexible interlayer.

[0105] The second relative strain difference is obtained by dividing the average strain difference between the flexible interlayer of the sensor and the unburied propellant at the same position by the average strain of the unburied propellant at the same position. Specifically, the second relative strain difference is calculated according to the following formula (3):

[0106]

[0107] In the formula, Δε relative2 is the second relative strain difference, is the average strain difference between the sensor flexible interlayer and the unburied propellant at the same position, is the average strain of unburied propellant at the same position.

[0108] The strain compatibility is determined based on the first relative strain difference and the second relative strain difference.

[0109] Specifically, when the first relative strain difference and the second relative strain difference are smaller than the strain difference threshold, the strain coordination is good.

[0110] 104: Determine a target material parameter of the sensor based on the strain compatibility and the stress concentration factor.

[0111] Among them, the target material parameters include the plate modulus and the flexible interlayer modulus.

[0112] The average stress of the flexible interlayer of the sensor must be consistent with the stress value of the engine charge, so that the stress of the flexible interlayer of the sensor accurately reflects the actual stress of the engine charge structure, thereby ensuring the accuracy of the measurement. Based on this, it is necessary to analyze the sensor measurement accuracy of the mechanical parameters of different plates and flexible interlayer materials of the sensor. In this application, the average longitudinal stress strain of the middle layer of the solid propellant specimen set is selected as the propellant tensile stress strain, and the average longitudinal stress strain of the flexible interlayer of the sensor is selected as the flexible interlayer stress strain, that is, the tensile equivalent stress data includes the propellant tensile stress strain and the flexible interlayer stress strain.

[0113] The flexible stress sensor is composed of a sandwich structure of two types of materials, a double-layer electrode plate and an intermediate flexible interlayer. In addition to meeting the functional requirements of capacitance measurement, the mechanical performance parameters of the material of the flexible stress sensor have a great influence on the accuracy of sensor measurement and the stress field of the embedded interface. Based on this, in this application, since the modulus of the electrode plate of the sensor is large, the relaxation elastic modulus of the electrode plate is 500MPa, 1KMPa, 3KPa and 30KMPa. The modulus of the flexible interlayer is small, and the modulus of the flexible interlayer can be 5MPa, 8MPa, 10MPa, 12MPa, 15MPa, 30MPa, 50MPa.

[0114] When the modulus of the flexible interlayer is constant, the tensile stress cloud maps corresponding to the relaxation elastic modulus of the plate of 500Mpa, 1KMPa, 3KPa and 30KMPa are obtained, and the data of the above tensile stress cloud maps are analyzed to obtain the tensile stress curves of the flexible interlayer and the tensile stress curves of the solid propellant rectangular specimen under different elastic relaxation moduli, such as Figure 8 As shown in Figure a, the mechanical state analysis is performed through the tensile stress curve of the flexible interlayer to determine the variation law of the tensile stress inside the sensor with the modulus of the sensor material. Within the selected range of the sensor material modulus, the stress variation amplitude is about 13.71%. The interlayer stress also increases with the increase of the modulus of the electrode plate material, but compared with the modulus of the flexible interlayer, the modulus of the electrode plate has little effect. Figure 8 As shown in Figure b, the tensile stress of the propellant specimen increases with the increase of the modulus of the sensor flexible interlayer. Within the selected sensor material parameter variable range, the stress variation is about 0.78%. Compared with the internal stress of the flexible interlayer, the change of the sensor material modulus has very little effect on the stress of the propellant specimen.

[0115] In order to see the difference between the stress of the flexible interlayer and the stress of the propellant specimen, the relative stress difference is defined as the absolute value of the ratio of the average stress of the sensor flexible interlayer to the stress difference of the solid propellant specimen middle layer and the stress of the specimen middle layer. Specifically, the relative stress difference between the average stress of the sensor flexible interlayer and the stress difference of the solid propellant specimen middle layer and the stress ratio of the solid propellant specimen middle layer can be calculated according to the following formula (4):

[0116]

[0117] In the formula, Δσ relative is the relative stress difference, is the average stress of the sensor flexible interlayer, is the stress in the middle layer of the solid propellant specimen.

[0118] Relative stress difference of different sensor material parameters Fig. 9 As shown in the figure, the relative stress difference decreases first and then increases with the interlayer modulus, and the flexible interlayer modulus reaches the minimum at 8MPa, thus determining that when the flexible interlayer modulus is 8MPa, the sensor flexible interlayer stress is most similar to the solid propellant specimen stress. At the same time, according to the relative stress difference, it can be determined that the influence of the plate modulus on the relative stress difference is generally small.

[0119] When the relaxation elastic modulus of the sensor's electrode is 3KMPa, the longitudinal tensile strain cloud maps of different flexible interlayer moduli (5MPa, 8MPa, 10MPa, 12MPa, 15MPa, 30MPa, 50MPa) of the sensor are obtained, and stress data analysis is performed on each longitudinal tensile strain cloud map to obtain the longitudinal tensile strain trend change curves of the flexible interlayer with different sensor material parameters and the longitudinal tensile strain trend change curves of the solid propellant rectangular specimen; as the modulus of the flexible interlayer increases, the distance between the electrodes decreases, and the tensile strain decreases. When the interlayer modulus is large, the strain in the corner area of ​​the interface between the upper electrode and the propellant increases significantly. Fig.10 As shown in Figure a, by analyzing the longitudinal tensile strain trend curve of the flexible interlayer, the variation law of the tensile strain of the sensor interlayer with the modulus of the flexible interlayer can be determined, that is, when the modulus of the flexible interlayer is small, the rate of change of the strain with the modulus is large, and the rate of change becomes slower as the modulus of the flexible interlayer increases. The overall change amplitude of the flexible interlayer strain is large, about 91.45%. Fig.10 As shown in Figure b, by analyzing the longitudinal tensile strain trend curve of the solid propellant rectangular specimen, it can be determined that the tensile strain of the propellant specimen increases slowly with the increase of the sensor flexible interlayer modulus, and the strain change amplitude is about 0.59%, which can be ignored. Based on this, it can be seen that compared with the internal stress of the flexible interlayer, the change in the interlayer modulus has a very small effect on the strain of the propellant specimen.

[0120] The relative strain difference is defined as the absolute value of the ratio of the average strain of the sensor interlayer to the strain of the specimen middle layer and the strain of the specimen middle layer, which represents the difference between the strain of the interlayer and the strain of the propellant specimen. Specifically, the relative strain difference is calculated according to the following formula (5):

[0121]

[0122] In the formula, Δε relative is the relative strain difference, is the average strain of the sensor flexible interlayer, is the strain of the middle layer of the solid propellant specimen.

[0123] The relative strain difference of different sensor material parameters is as follows Fig.11 As shown, through Fig.11 By analyzing the relative strain difference in the data, it can be found that the relative strain difference decreases with the interlayer modulus.

[0124] Based on this step, it can be seen that the modulus of the flexible interlayer of the sensor has a greater impact on its internal stress and strain, while the modulus of the sensor plate has a relatively smaller impact. Whether it is the sensor plate or the flexible interlayer, its material modulus does not have much effect on the overall stress and strain of the propellant specimen. However, since the modulus of the flexible interlayer is at a special value (such as 8MPa), the difference between the internal stress and the relative stress of the propellant specimen is small, and the stress of the flexible interlayer in this state can accurately reflect the stress of the propellant specimen. The smaller the modulus of the flexible interlayer, the closer the internal strain is to the strain of the propellant specimen. Therefore, considering the measurement accuracy of the sensor, the flexible interlayer material selected should be as close as possible to this special value (such as 8MPa).

[0125] The Mises stress data on the upper surface of the flexible sensor can be extracted from the stress-strain field. Figure 5 As shown, the starting point of the x-axis of the sensor is 1.5 mm to the left of the left end point of the upper surface of the sensor, and the end point is 1.5 mm to the right of the right end point of the upper surface. Therefore, by setting different plate moduli of the sensor, the Mises stress curve of the upper surface of the flexible sensor under different moduli can be obtained. Fig.12 As shown, Fig.12 [a] to Fig.12 The plate modulus of [d] is 500Mpa, 1000Mpa, 3000Mpa and 30000Mpa respectively and according to Fig.12It can be seen that the Mises stress curve is generally divided into three regions. Region 1 is the propellant region, that is, x∈(0,1]∪[13,14). Region 2 is the stress concentration region, that is, x∈(1,2]∪[12,13), and region 3 is the intermediate region, that is, x∈(2,12). In region 1, the Mises stresses of different plates are similar in magnitude and have the same rules. They all decrease slowly with the increase of the interlayer modulus and change smoothly along the x-axis. In region 2, due to the stress concentration at the corner, the stress has a large mutation along the x-axis. The maximum stress increases with the increase of the interlayer modulus and the increase of the plate modulus. In region 3, the main reason for the stress on the plate is bending. When the plate modulus is small, the stress on the plate shows a double peak, which becomes more obvious with the increase of the plate modulus. When the plate modulus increases to 30KMPa, with the increase of interlayer modulus, the plate stress gradually transitions from a single peak to a double peak. This phenomenon is mainly related to the natural frequency of the plate.

[0126] According to each Mises stress curve, we can get the curve of Mises stress changing with the modulus of the flexible interlayer, such as Fig.13 As shown in the figure, by analyzing the correlation diagram of the change of Mises stress with the flexible interlayer modulus, it is determined that the sensor plate modulus is small, such as 500MPa and 1KMPa, the maximum mises stress decreases with the increase of the interlayer modulus, and is all in area 2. When the sensor plate modulus is 3KMPa, most of the maximum mises stress is located in area 3, indicating that the bending stress is gradually dominant. When the sensor plate modulus is 30KMPa, the maximum mises stress has a significant increase, and is all in area 3, indicating that the maximum stress is caused by the bending of the plate, and due to the different number of peaks, its value increases first and then decreases with the interlayer modulus. It can be seen from the interface stress analysis that the modulus of the plate and the flexible interlayer should be reduced as much as possible to reduce stress concentration and plate bending stress.

[0127] The average strain of the interlayer of flexible sensors of different materials and the average strain of the surrounding propellant are shown in Fig.14 As shown in the figure, the black line is the average strain of the flexible interlayer, and the red line is the average strain of the surrounding propellant. Both strains decrease with the increase of the modulus of the flexible interlayer, and the reduction speed is from fast to slow. The change of the average strain of the surrounding propellant is larger than that of the flexible interlayer. The change of the plate modulus has little effect on the strain of the flexible interlayer and the surrounding propellant.

[0128] The relative difference between the two types of strains of flexible sensors made of different materials is as follows Fig.15As shown, the red line is the first relative strain difference and the blue line is the second relative strain difference. After the interlayer modulus exceeds 7MPa, the first relative strain difference and the second relative strain difference both increase with the increase of the flexible interlayer modulus, and the speed is from fast to slow. The second relative strain difference has a larger change amplitude than the first relative strain difference, indicating that the strain of the flexible interlayer is much larger than the strain of the propellant at the same position when the sensor is not embedded. The change of the plate modulus has little effect on the relative strain differences 1 and 2. Therefore, we can conclude that when the flexible interlayer modulus is 6MPa~7MPa, the strain of the flexible interlayer is closer to the strain of the surrounding propellant and the propellant at the same position without the sensor embedded. The selection range of the flexible interlayer modulus obtained by the strain relative difference analysis is almost the same as the selection range of the flexible interlayer modulus obtained by the sensor measurement accuracy analysis.

[0129] Based on the interlayer modulus of 8MPa, it can be seen from Table 3 that the deflection of the upper plate of the sensor decreases with the increase of the plate modulus. In practical applications, in order to ensure that the measured capacitance data meets the linearity requirements, the smaller the deflection of the plate, the better. Therefore, the selected plate modulus is as large as possible. Fig.12 The Mises stress curves of the upper surface of the flexible sensor under different moduli provide that under the same conditions, too large a modulus will result in too large a bending stress, thus affecting the service life of the sensor. Therefore, the plate modulus should not be too large or too small, and the final modulus is about 3KMPa.

[0130] Table 3

[0131] Plate modulus / MPa 500 1K 3K 30K Upper plate deflection / mm 0.212 0.206 0.191 0.103

[0132] In summary, in the embodiment of the present application, based on the finite element numerical calculation of the stress-strain field of the propellant rectangular specimen embedded with a flexible sensor under a tensile load, the strain coordination, stress concentration, and measurement accuracy between the sensor and the surrounding propellant are analyzed to determine the optimal design of the sensor material parameters. First, the stress concentration of the propellant specimen embedded with a flexible sensor and the strain difference between the inside of the sensor and the outside world under the same load conditions are analyzed; then, the optimal material parameters are obtained by measuring the measurement accuracy, strain coordination, and stress concentration coefficient of the flexible sensor with different material parameters, that is, the relaxation elastic modulus of the sensor's electrode plate and the relaxation elastic modulus of the flexible interlayer. Specifically, the present application draws the following conclusions after analyzing the measurement accuracy, strain compatibility, and stress concentration of flexible sensors with different material parameters:

[0133] The tensile stress of the flexible interlayer inside the sensor decreases with the increase of the flexible interlayer modulus of the sensor, and the plate material parameters have little effect on the tensile stress of the flexible interlayer inside. The relative stress difference shows a trend of first decreasing and then increasing with the increase of the interlayer modulus, reaching the minimum when the interlayer modulus is about 8MPa. In this state, the stress of the flexible interlayer is closest to the stress of the specimen;

[0134] The longitudinal tensile strain of the flexible interlayer inside the sensor decreases with the increase of the flexible interlayer modulus of the sensor. When the flexible interlayer modulus is small, the change rate is large, and the change rate becomes slow as the flexible interlayer modulus increases. The relative strain difference increases with the increase of the interlayer modulus, and the interlayer modulus reaches the minimum when the minimum value is 5MPa. In this state, the flexible interlayer strain is closest to the specimen strain;

[0135] The increase in the modulus of the interlayer and the plate will make the stress concentration at the contact interface between the sensor and the propellant more serious. For the middle area without stress concentration, the increase in the plate modulus will significantly increase the bending stress. Therefore, from the perspective of the stress field, the modulus of the plate and the flexible interlayer should be reduced as much as possible;

[0136] The calculation and analysis results of the relative strain difference show that when the modulus of the flexible interlayer is 5MPa-8MPa, the strain of the flexible interlayer is close to the strain of the surrounding propellant and the propellant at the same position without the embedded sensor. In order to control the deflection of the plate after stretching and ensure the linearity of the capacitance measurement, the plate modulus cannot be too small.

[0137] The above is the process for determining the sensor parameters of the embedded charge structure of the present application.

[0138] As mentioned above, the present application provides a method, device, computer equipment and storage medium for determining sensor parameters of an embedded charge structure, by establishing a finite element model based on a solid propellant specimen embedded with a sensor; performing a tensile simulation on the finite element model to obtain the stress-strain field of the solid propellant specimen embedded with the sensor; performing a mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant; and determining the target material parameters of the sensor based on the strain coordination and the stress concentration coefficient. In the sensor parameter determination scheme for an embedded charge structure provided in the present application, a finite element model is established based on a solid propellant specimen embedded with a sensor, and then a tensile simulation is performed on the finite element model to perform a mechanical state analysis on the stress-strain field of the solid propellant specimen embedded with the sensor, to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant specimen, thereby determining the target material parameters of the sensor. It can be seen that the mechanical state analysis of the stress-strain field of the solid propellant specimen embedded with the sensor is carried out through the tensile simulation of the finite element model corresponding to the solid propellant specimen embedded with the sensor, so as to optimize the material parameters of the sensor embedded in the propellant, improve the measurement accuracy of the mechanical state of the charge structure, and thus reduce the complexity of the evaluation of the integrity of the engine charge structure.

[0139] It should be understood that the order of execution of the steps in the above embodiment does not necessarily mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiment of the present invention.

[0140] In one embodiment, a sensor parameter determination device embedded in a charge structure is provided, and the sensor parameter determination device embedded in a charge structure corresponds to the sensor parameter determination method embedded in a charge structure in the above embodiment. Fig.16 As shown, the sensor parameter determination device embedded in the charge structure includes:

[0141] Building a module for building finite element models based on solid propellant specimens with embedded sensors;

[0142] A simulation module, used for performing a tensile simulation on the finite element model to obtain a stress-strain field of a solid propellant specimen embedded with a sensor;

[0143] An analysis module, used to perform mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant;

[0144] A determination module is used to determine a target material parameter of the sensor based on the strain compatibility and the stress concentration factor.

[0145] In this embodiment, a finite element model is established based on a solid propellant specimen embedded with a sensor; a tensile simulation is performed on the finite element model to obtain a stress-strain field of the solid propellant specimen embedded with a sensor; a mechanical state analysis is performed on the stress-strain field to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant; and the target material parameters of the sensor are determined based on the strain coordination and the stress concentration coefficient. In the sensor parameter determination scheme for the embedded charge structure provided in the present application, a finite element model is established based on a solid propellant specimen embedded with a sensor, and then a tensile simulation is performed on the finite element model to perform a mechanical state analysis on the stress-strain field of the solid propellant specimen embedded with a sensor, determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant specimen, and thereby determine the target material parameters of the sensor. It can be seen that the mechanical state analysis of the stress-strain field of the solid propellant specimen embedded with a sensor is performed through the tensile simulation of the finite element model corresponding to the solid propellant specimen embedded with a sensor, so as to optimize the material parameters of the sensor embedded in the propellant, improve the measurement accuracy of the mechanical state of the charge structure, and thereby reduce the complexity of the evaluation of the integrity of the engine charge structure.

[0146] Optionally, in some embodiments of the present application, the analysis module includes:

[0147] An extraction submodule, used for extracting tensile equivalent stress data of a solid propellant specimen from the stress-strain field;

[0148] The analysis submodule is used to perform mechanical state analysis on the tensile equivalent stress data to determine the strain coordination and the stress concentration factor.

[0149] Optionally, in some embodiments of the present application, the analysis submodule includes:

[0150] A first acquisition unit, configured to acquire the longitudinal stress on the upper surface of the sensor based on the tensile equivalent stress data;

[0151] A second acquisition unit is used to acquire the average stress of the solid propellant without the embedded sensor;

[0152] The normalization unit is used to normalize the longitudinal stress on the upper surface of the sensor with the average stress of the solid propellant without the embedded sensor to obtain a stress concentration factor.

[0153] Optionally, in some embodiments of the present application, the analysis submodule includes:

[0154] a first determining unit, configured to determine, based on the tensile equivalent stress data, an average strain difference between the sensor and a solid propellant around the sensor, an average strain of the solid propellant around the sensor, an average strain difference between the sensor and a non-buried propellant at the same position, and an average strain difference of the non-buried solid propellant at the same position;

[0155] a second determining unit, configured to determine a first relative strain difference based on an average strain difference between the sensor and the solid propellant around the sensor and an average strain of the solid propellant around the sensor;

[0156] a third determination unit, configured to determine a second relative strain difference based on an average strain difference between the sensor and the unburied solid propellant at the same position and an average strain difference of the unburied solid propellant at the same position;

[0157] The fourth determining unit is used to determine the strain coordination based on the first relative strain difference and the second relative strain difference.

[0158] Optionally, in some embodiments of the present application, the simulation module includes:

[0159] A partitioning unit, used for performing mesh partitioning on the finite element model;

[0160] The simulation unit is used to perform a tensile simulation on the finite element model in response to a model parameter setting operation of the finite element model to obtain the stress-strain field.

[0161] Optionally, in some embodiments of the present application, the finite element model is a two-dimensional plane model.

[0162] Optionally, in some embodiments of the present application, the sensor is a flexible sensor, and the flexible sensor includes two parallel electrode plates and a flexible interlayer arranged between the two electrode plates.

[0163] In one embodiment, a computer device is provided, the internal structure diagram of which can be as follows: Fig.17 As shown. The computer device includes a processor, a memory, a network interface, a display screen and an input device connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external server through a network connection. When the computer program is executed by the processor, the functions or steps of a method for determining sensor parameters embedded in a charge structure are implemented.

[0164] In one embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the computer program, the following steps are implemented:

[0165] A finite element model is established based on a solid propellant specimen embedded with a sensor; a tensile simulation is performed on the finite element model to obtain a stress-strain field of the solid propellant specimen embedded with a sensor; a mechanical state analysis is performed on the stress-strain field to determine the strain coordination and stress concentration factor between the sensor and the solid propellant; and a target material parameter of the sensor is determined based on the strain coordination and the stress concentration factor.

[0166] In the sensor parameter determination scheme for the embedded charge structure provided in the present application, a finite element model is established based on a solid propellant specimen embedded with a sensor, and then a tensile simulation is performed on the finite element model to perform a mechanical state analysis on the stress-strain field of the solid propellant specimen embedded with the sensor, and the strain coordination and stress concentration coefficient between the sensor and the solid propellant specimen are determined, thereby determining the target material parameters of the sensor. It can be seen that the mechanical state analysis of the stress-strain field of the solid propellant specimen embedded with the sensor is performed through the tensile simulation of the finite element model corresponding to the solid propellant specimen embedded with the sensor, so as to optimize the material parameters of the sensor embedded in the propellant, improve the measurement accuracy of the mechanical state of the charge structure, and thus reduce the complexity of the evaluation of the integrity of the engine charge structure.

[0167] In one embodiment, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the following steps are implemented:

[0168] A finite element model is established based on a solid propellant specimen embedded with a sensor; a tensile simulation is performed on the finite element model to obtain a stress-strain field of the solid propellant specimen embedded with a sensor; a mechanical state analysis is performed on the stress-strain field to determine the strain coordination and stress concentration factor between the sensor and the solid propellant; and a target material parameter of the sensor is determined based on the strain coordination and the stress concentration factor.

[0169] In the sensor parameter determination scheme for the embedded charge structure provided in the present application, a finite element model is established based on a solid propellant specimen embedded with a sensor, and then a tensile simulation is performed on the finite element model to perform a mechanical state analysis on the stress-strain field of the solid propellant specimen embedded with the sensor, and the strain coordination and stress concentration coefficient between the sensor and the solid propellant specimen are determined, thereby determining the target material parameters of the sensor. It can be seen that the mechanical state analysis of the stress-strain field of the solid propellant specimen embedded with the sensor is performed through the tensile simulation of the finite element model corresponding to the solid propellant specimen embedded with the sensor, so as to optimize the material parameters of the sensor embedded in the propellant, improve the measurement accuracy of the mechanical state of the charge structure, and thus reduce the complexity of the evaluation of the integrity of the engine charge structure.

[0170] It should be noted that the above functions or steps that can be implemented by the computer-readable storage medium or computer device can refer to the relevant descriptions on the server side and the client side in the aforementioned method embodiment. To avoid repetition, they will not be described one by one here.

[0171] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiments can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in the present application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0172] Those skilled in the art can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional units and modules is used as an example. In actual applications, the above-mentioned functions can be distributed and completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above.

[0173] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the protection scope of the present invention.

Claims

1. A method for determining parameters of a sensor embedded in a charge structure, characterized in that: include: Establish a finite element model based on a solid propellant specimen with embedded sensors; Performing a tensile simulation on the finite element model to obtain a stress-strain field of a solid propellant specimen embedded with a sensor; Performing a mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant; A target material parameter of the sensor is determined based on the strain compatibility and the stress concentration factor.

2. The method for determining sensor parameters of an embedded charge structure according to claim 1, characterized in that: The performing mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant includes: extracting tensile equivalent stress data of the solid propellant specimen from the stress-strain field; A mechanical state analysis is performed on the tensile equivalent stress data to determine the strain coordination and the stress concentration factor.

3. The method for determining sensor parameters of an embedded charge structure according to claim 2, characterized in that: The performing mechanical state analysis on the tensile equivalent stress data to determine the strain coordination and the stress concentration factor includes: Acquiring the longitudinal stress on the upper surface of the sensor based on the tensile equivalent stress data; Obtain the average stress of solid propellant without embedded sensors; The stress concentration factor is obtained by normalizing the longitudinal stress on the upper surface of the sensor with the average stress of the solid propellant without the embedded sensor.

4. The method for determining sensor parameters of an embedded charge structure according to claim 2, characterized in that: The performing mechanical state analysis on the tensile equivalent stress data to determine the strain coordination and the stress concentration factor includes: Determine, based on the tensile equivalent stress data, an average strain difference between the sensor and the solid propellant around the sensor, an average strain of the solid propellant around the sensor, an average strain difference between the sensor and an unburied propellant at the same position, and an average strain difference of the unburied solid propellant at the same position; determining a first relative strain difference based on an average strain difference between the sensor and the solid propellant surrounding the sensor and an average strain of the solid propellant surrounding the sensor; Determining a second relative strain difference based on an average strain difference between the sensor and the unburied solid propellant at the same position and an average strain difference of the unburied solid propellant at the same position; The strain compatibility is determined based on the first relative strain difference and the second relative strain difference.

5. The method for determining sensor parameters of an embedded charge structure according to claim 1, characterized in that: The stretching simulation of the finite element model to obtain the stress-strain field of the solid propellant specimen embedded with the sensor includes: Meshing the finite element model; In response to the model parameter setting operation of the finite element model, a tensile simulation is performed on the finite element model to obtain the stress-strain field.

6. The method for determining sensor parameters embedded in a charge structure according to any one of claims 1 to 5, characterized in that: The finite element model is a two-dimensional plane model.

7. The method for determining sensor parameters embedded in a charge structure according to any one of claims 1 to 5, characterized in that: The sensor is a flexible sensor, which includes two parallel-arranged polar plates and a flexible interlayer arranged between the two polar plates.

8. A sensor parameter determination device embedded in a charge structure, characterized in that: include: Building a module for building finite element models based on solid propellant specimens with embedded sensors; A simulation module, used for performing a tensile simulation on the finite element model to obtain a stress-strain field of a solid propellant specimen embedded with a sensor; An analysis module, used to perform mechanical state analysis on the stress-strain field to determine the strain coordination and stress concentration coefficient between the sensor and the solid propellant; A determination module is used to determine a target material parameter of the sensor based on the strain compatibility and the stress concentration factor.

9. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the method for determining parameters of a sensor embedded in a charge structure according to any one of claims 1 to 7 are implemented.

10. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the steps of the method for determining parameters of a sensor embedded in a charge structure according to any one of claims 1 to 7 are implemented.

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