Pilot elastic sheet design method based on simulation analysis
By using simulation analysis and optimization design methods, the problems of complexity and high cost in the design of missile fins were solved, and efficient stiffness calculation was achieved, reducing processing costs and time.
Patent Information
- Application Number
- CN202512031823.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-30
- Publication Date
- 2026-02-06
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
The design of missile plates is complex and cumbersome, and existing technologies make it difficult to efficiently calculate their stiffness, resulting in high processing costs and wasted time.
A three-dimensional model was constructed using simulation analysis methods. Static simulation analysis was performed using finite element software. The actual stiffness was calculated using Hooke's law. The design was optimized by adjusting the important dimensions of the three-dimensional model until the difference between the actual stiffness and the design stiffness was less than a set threshold.
By calculating the stiffness of the spring sheet through simulation analysis, the time and financial costs of processing and re-verification are saved.
Smart Images
Figure CN121480194A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of simulation analysis design methods, and in particular to a preliminary missile design method based on simulation analysis. Background Technology
[0002] The spring clip, an internal component of a solenoid valve, functions similarly to a spring and conforms to Hooke's Law. Different applications require different structural shapes, including, but not limited to, the length, number, and width of the spring clip "bridge." Simultaneously, the spring clip must maintain a certain elastic modulus, making its design process complex and cumbersome. This invention aims to provide a method for calculating the stiffness of the spring clip using simulation analysis, thereby saving time and costs associated with manufacturing and verification, and reducing the financial costs incurred in manufacturing. Summary of the Invention
[0003] The purpose of this invention is to overcome the shortcomings of the prior art and provide a simulation analysis-based advanced missile design method.
[0004] The objective of this invention is achieved through the following technical solution: A simulation-based design method for pre-launched missile assemblies, comprising: S10, constructing a three-dimensional model of the pre-launched missile assemblies; S20, performing static simulation analysis on the three-dimensional model using finite element software to obtain simulation analysis results of the three-dimensional model under set boundary conditions; S30, calculating the actual stiffness of the three-dimensional model using Hooke's law based on the simulation analysis results; S40, optimizing the three-dimensional model by adjusting important dimensions when there is a difference between the actual stiffness and the design stiffness of the three-dimensional model; S50, repeating steps S10 to S40 until the difference between the actual stiffness and the design stiffness is less than a set threshold.
[0005] Preferably, the key dimensions include the first dimension A1, the second dimension A2, and the third dimension A3 of the bridge structure of the pilot missile piece, and the first diameter Φ of the pilot missile piece. １ Second diameter Φ ２ And the third diameter Φ3.
[0006] Preferably, the boundary conditions are set as follows: using the "static" and "general" modes in Abaqus software; applying a cylinder to the 3D model, and applying a set displacement to the cylinder to apply a load to the 3D model; creating a contact pair with the 3D model surface as the master surface and the cylinder surface as the slave surface; constraining the cylinder as a rigid body, and selecting the center of the 3D model as the reference point; and using a hexahedral and neutral axis algorithm for the mesh properties of the 3D model.
[0007] Preferably, the calculation of the actual stiffness includes the following steps: S301, setting the boundary conditions as follows: the outer ring of the first missile piece is fixed, and the inner ring of the first missile piece moves a set distance; S302, extracting the force conditions of the coupling nodes of the first missile piece from the simulation analysis results, the force conditions including the reaction force RF2 and the spatial displacement U2 in the force direction of the first missile piece; S303, designating the reaction force RF2 as variable F, designating the spatial displacement U2 as variable Δx, and calculating the parameter k based on the Huke's law formula F=kΔx, the parameter k being the actual stiffness of the first missile piece.
[0008] Preferably, the set distance is 0.1 mm.
[0009] Preferably, the adjustment step for important dimensions of the three-dimensional model is as follows: S401, when the actual stiffness is greater than the design stiffness, the first diameter Φ is maintained. １ Second diameter Φ ２ S402, keeping the first dimension A1 unchanged, increasing the second dimension A2, increasing the third dimension A3, and / or decreasing the third diameter Φ3; S402, if the actual stiffness is less than the design stiffness, keeping the first diameter Φ １ Second diameter Φ ２ The first dimension A1 remains unchanged, the second dimension A2 is decreased, the third dimension A3 is decreased, and / or the third diameter Φ3 is increased.
[0010] The present invention has the following advantages: it uses simulation analysis to calculate the stiffness of the spring sheet, which saves the time cost of processing and verification, and reduces the capital cost of processing. Attached Figure Description
[0011] Figure 1 This is a flowchart illustrating the missile design method of the present invention; Figure 2 This is a schematic diagram showing the effect of applying a cylinder to a 3D model. Figure 3 Set up a schematic diagram for boundary conditions; Figure 4 Provide a schematic diagram for the interactions; Figure 5 Provide a diagram for setting up the grid; Figure 6 This is a schematic diagram of the stiffness results; Figure 7 A schematic diagram of the force conditions at the coupling node is extracted; Figure 8 A schematic diagram of the force extraction results for the coupled nodes. Figure 9 This is a schematic diagram showing important dimensions. Detailed Implementation
[0012] The present invention will be further described below with reference to the accompanying drawings. The scope of protection of the present invention is not limited to the following description: like Figures 1 to 9 As shown, this invention provides a simulation-based design method for pre-launched slabs, comprising: S10, constructing a three-dimensional model of the pre-launched slab; S20, performing static simulation analysis on the three-dimensional model using finite element software to obtain simulation analysis results of the three-dimensional model under set boundary conditions; S30, calculating the actual stiffness of the three-dimensional model using Hooke's law based on the simulation analysis results; S40, optimizing the three-dimensional model by adjusting important dimensions when there is a difference between the actual stiffness and the design stiffness of the three-dimensional model; S50, repeating steps S10 to S40 until the difference between the actual stiffness and the design stiffness is less than a set threshold.
[0013] Preferably, key dimensions include the first dimension A1, the second dimension A2, and the third dimension A3 of the bridge structure of the pilot missile piece, and the first diameter Φ of the pilot missile piece. １ Second diameter Φ ２ And the third diameter Φ3.
[0014] Preferably, the boundary conditions are set as follows: using the "static" and "general" modes in Abaqus software; applying a cylinder to the 3D model and applying a set displacement to the cylinder to apply a load to the 3D model; creating a contact pair with the 3D model surface as the master surface and the cylinder surface as the slave surface; constraining the cylinder as a rigid body and selecting the center of the 3D model as the reference point; and using the hexahedral and neutral axis algorithm for the mesh properties of the 3D model.
[0015] Preferably, the calculation of the actual stiffness includes the following steps: S301, setting the boundary conditions to fix the outer ring of the first missile piece and move the inner ring of the first missile piece a set distance; S302, extracting the force situation of the coupling node of the first missile piece from the simulation analysis results, including the reaction force RF2 and spatial displacement U2 in the force direction of the first missile piece; S303, designating the reaction force RF2 as variable F and the spatial displacement U2 as variable Δx, and calculating the parameter k based on the Huke's law formula F=kΔx, where parameter k is the actual stiffness of the first missile piece. Specifically, when setting the boundary conditions for finite element analysis, the outer ring of the missile piece is fixed according to the actual situation (its actual placement position is that the outer ring rests on the valve seat, and the inner ring is unsupported), and the inner ring is set to move a certain distance (this distance is taken within the range of movement under actual working conditions), and the simulation model takes a value of 0.1mm; the force situation of the coupling node of the missile piece, i.e., F, can be extracted from the simulation analysis results. The above two variables are presented in the simulation results as follows. Figure 7The left figure shows the variable selection interface for the extracted field output results. The reaction force RF2 and spatial displacement U2 in the direction of the force applied to the spring are selected. Figure 7 The right image shows the node selection interface; select the spring coupling node. Figure 8 The left figure is a data chart of the forces at the nodes. The horizontal axis represents the time step, and the vertical axis represents the forces at the nodes, i.e., F. Figure 8 The right figure is a data graph of nodal displacements. The horizontal axis represents the time step, and the vertical axis represents the nodal displacement, i.e., x. Since both variables have the same horizontal axis, the stiffness can be obtained by redrawing a curve from the Y-variable of the two graphs according to Hooke's Law, using the force scalar as the vertical axis and the displacement variable as the horizontal axis. For example... Figure 6 After plotting the curves for the two variables, add a trend line to display the equation of the curve, and its slope represents the actual stiffness of the spring.
[0016] Preferably, the distance is set to 0.1mm.
[0017] Preferably, the adjustment steps for important dimensions of the 3D model are as follows: S401, when the actual stiffness is greater than the design stiffness, maintain the first diameter Φ １ Second diameter Φ ２ S402: Keep the first dimension A1 unchanged, increase the second dimension A2, increase the third dimension A3, and / or decrease the third diameter Φ3; S402: If the actual stiffness is less than the design stiffness, keep the first diameter Φ １ Second diameter Φ ２ Without changing the dimensions, increase the first dimension A1, decrease the second dimension A2, decrease the third dimension A3, and / or increase the third diameter Φ3. Specifically, the shorter the "bridge" design of the inner ring of the spring and the wider the root, the greater the spring stiffness; conversely, the longer the bridge and the narrower the root, the smaller the spring stiffness. If other conditions remain unchanged, controlling a single variable, decreasing the first dimension decreases the spring stiffness; decreasing the second dimension increases the spring stiffness; decreasing the third dimension increases the spring stiffness. In general, with the first dimension of the connection between the inner and outer rings remaining unchanged, a larger mass in the inner ring of the spring will lead to a smaller spring stiffness. The first and second diameters remain basically unchanged, and their sizes are related to the size of the mating valve seat; with other conditions remaining unchanged, decreasing the third diameter decreases the spring stiffness.
[0018] How this application works: Analysis was performed using Abaqus software, employing the "static, general" approach; such as... Figure 2 As shown, to facilitate the application of loads, a rigid body is applied to the spring sheet, and displacement is applied through this cylinder; as... Figure 3 As shown, the side of the spring is set to be completely fixed, and a downward displacement is applied to the cylinder (the amount of displacement depends on the actual working conditions). Figure 4Create a contact pair, with the surface of the spring as the master surface and the surface of the cylinder as the slave surface; constrain the cylinder as a rigid body, and select the center of the spring as the reference point. The spring mesh properties use a hexahedral, neutral axis algorithm (e.g., ...). Figure 5 (As shown).
[0019] like Figure 6 As shown, after obtaining the force value under a certain displacement, the stiffness of the designed spring is calculated according to Hooke's Law. The calculation result is compared with the target stiffness, and the spring design parameters are continuously adjusted and recalculated to approximate the target stiffness result. When the result is consistent with the target stiffness, the spring is processed. The processed spring is then tested to verify its stiffness. Once it meets the stiffness requirements for spring use, it is put into service.
[0020] Finally, it should be noted that the above descriptions are merely preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. A method for designing advanced missile shrapnel based on simulation analysis, characterized in that, include: S10, construct the three-dimensional model of the missile fragment; S20, Perform static simulation analysis on the three-dimensional model based on finite element software to obtain the simulation analysis results of the three-dimensional model under set boundary conditions; S30. Based on the simulation analysis results, calculate the actual stiffness of the three-dimensional model using Hooke's law; S40, when there is a difference between the actual stiffness and the design stiffness of the three-dimensional model, the three-dimensional model is optimized by adjusting the important dimensions of the three-dimensional model; S50, repeat steps S10~S40 until the difference between the actual stiffness and the design stiffness is less than the set threshold.
2. The missile slab design method according to claim 1, characterized in that, The key dimensions include the first dimension A1, the second dimension A2, and the third dimension A3 of the bridge structure of the pre-launched missile sheet, as well as the first diameter Φ1 and the second diameter Φ of the pre-launched missile sheet. ２ And the third diameter Φ3.
3. The missile slab design method according to claim 1, characterized in that, The boundary conditions are set as follows: The "Static" and "General" modes in Abaqus software are used. A cylinder is applied to the three-dimensional model, and a set displacement is applied to the cylinder to apply a load to the three-dimensional model; Contact pairs are created using the surface of the 3D model as the primary surface and the cylindrical surface as the secondary surface. The cylinder is constrained as a rigid body, and the reference point is selected as the center of the 3D model. The mesh properties of the 3D model are achieved using a hexahedral and neutral axis algorithm.
4. The missile slab design method according to claim 1, characterized in that, The calculation of the actual stiffness includes the following steps: S301, the set boundary conditions are set to fix the outer ring of the missile piece first, and move the inner ring of the missile piece a set distance first; S302, Extract the force conditions of the coupling nodes of the first missile piece in the simulation analysis results. The force conditions include the reaction force RF2 and the spatial displacement U2 in the force direction of the first missile piece. S303, the reaction force RF2 is designated as variable F, the spatial displacement U2 is designated as variable Δx, and the parameter k is calculated based on the Huke's law formula F=kΔx. The parameter k is the actual stiffness of the missile sheet.
5. The missile slab design method according to claim 4, characterized in that, The set distance is 0.1 mm.
6. The missile slab design method according to claim 1, characterized in that, The steps for adjusting important dimensions of a 3D model are as follows: S401, if the actual stiffness is greater than the design stiffness, maintain the first diameter Φ1 and the second diameter Φ ２ The dimensions remain unchanged, but the first dimension A1 is decreased, the second dimension A2 is increased, the third dimension A3 is increased, and / or the third diameter Φ3 is decreased. S402, when the actual stiffness is less than the design stiffness, maintain the first diameter Φ1 and the second diameter Φ ２ The first dimension A1 remains unchanged, the second dimension A2 is decreased, the third dimension A3 is decreased, and / or the third diameter Φ3 is increased.