Cylinder structure vortex-induced vibration simulation, suppression scheme determination method and suppression device

Abstract

The embodiment of the application discloses a vortex-induced vibration simulation method and a suppression scheme determination method and a suppression device for a cylindrical structure, and the method comprises the following steps: constructing a fluid-solid coupling model of the cylindrical structure of a vehicle; and performing vortex-induced vibration simulation of the cylindrical structure based on the fluid-solid coupling model by using an immersed smooth point interpolation method, wherein the immersed smooth point interpolation method is used to fill a virtual fluid in a region where a solid domain is located, movable Lagrangian grids are used to divide the solid domain into grids, Euler grids are used to divide a fluid domain into grids, a fluid-solid coupling grid model is obtained, and vortex-induced vibration simulation of the cylindrical structure is performed based on the fluid-solid coupling grid model; and the virtual fluid has the same physical properties as real fluid. The present application combines the immersed smooth point interpolation method, and the partition adaptation of the Euler grids and the movable Lagrangian grids can improve the simulation accuracy.

Description

Technical Field

[0001] This invention relates to the field of simulation computing technology, and in particular to a method and device for simulating and suppressing vortex-induced vibration of a cylindrical structure. Background Technology

[0002] Cylindrical structures are typical load-bearing and flow field-affected components in underwater vehicles, marine engineering risers, and underwater towed bodies. When fluid flows around a cylindrical structure, periodically alternating vortices are formed in the structure's wake region, inducing vortex-induced vibration (VIV). Vortex-induced vibration is a strongly nonlinear fluid-structure interaction dynamic behavior, and long-term exposure can easily lead to structural fatigue damage, excessive vibration amplitude, and even structural failure, directly affecting the navigation stability, structural safety, and service life of the vehicle.

[0003] Currently, there are two main methods for suppressing wake vortex shedding from cylindrical structures: active suppression and passive suppression. Active suppression typically requires external energy input to reduce wake vortex shedding behind the cylinder, while passive suppression usually involves adding external structures around the cylinder to alter the flow field distribution, thereby suppressing wake vortex shedding. Currently, passive suppression can be achieved by installing a baffle plate downstream of the cylindrical structure.

[0004] In current research on vortex-induced vibration suppression, the effect of setting a partition plate downstream of a cylindrical structure can be simulated and determined using vortex-induced vibration simulation technology. However, current vortex-induced vibration simulation technology is prone to problems such as mesh distortion and inaccurate interface capture, which means that the accuracy of existing vortex-induced vibration simulation technology for cylindrical structures of aircraft still needs to be improved. Summary of the Invention

[0005] Based on this, it is necessary to propose a method for simulating and determining the suppression scheme of vortex-induced vibration of cylindrical structures, as well as a suppression device, to address the above-mentioned problems, aiming to solve the problem of low accuracy in vortex-induced vibration simulation technology for cylindrical structures of aircraft.

[0006] In a first aspect, embodiments of this application provide a method for simulating vortex-induced vibration of a cylindrical structure, the method comprising: A fluid-structure interaction (FSI) model of a cylindrical structure of a spacecraft is constructed. This model includes a fluid domain and a solid domain. The volume of the solid domain is the sum of the volume of the cylindrical structure and the volume of a partition plate located downstream of the cylindrical structure. The relative length of the partition plate is a preset length, and the relative distance between the partition plates is a preset distance. The relative length is the ratio of the partition plate length to the cylinder diameter of the cylindrical structure, and the relative distance is the ratio of the distance between the partition plate and the cylindrical structure to the cylinder diameter of the cylindrical structure. An immersion smooth point interpolation method is used to simulate the vortex-induced vibration of the cylindrical structure based on the fluid-structure interaction model. The immersion smooth point interpolation method involves filling the solid domain with a virtual fluid, and using a movable Lagrange mesh to mesh the solid domain and an Eulerian mesh to mesh the fluid domain, resulting in a fluid-structure interaction mesh model. The vortex-induced vibration of the cylindrical structure is then simulated based on this fluid-structure interaction mesh model. The virtual fluid has the same physical properties as the real fluid.

[0007] In some embodiments, the above method includes: during the vortex-induced vibration simulation process, solving for the fluid velocity gradient in the fluid domain or solving for the smooth displacement gradient at each location point in the solid domain; determining the drag and lift of the cylindrical structure in the flow field based on the fluid velocity gradient, or determining the drag and lift of the cylindrical structure in the flow field based on the smooth displacement gradient.

[0008] In some embodiments, the above-described solution for the fluid velocity gradient in the fluid domain includes: solving the first fluid control equation of the fluid domain to obtain the mid-time velocity of the J-th fluid node; J takes values ​​from 1 to Q, where Q represents the number of fluid nodes in the fluid domain, and the mid-time velocity is the velocity of the J-th fluid node at the mid-time between step m and step m+1. The first fluid control equation is as follows: ,in, Represents the fluid mass matrix. Let represent the velocity at the midpoint of the J-th fluid node. Indicates the m-th step. The fluid velocity at each fluid node Indicates the time step. Represents the fluid convection matrix. This represents the viscous force acting on the fluid in step m. This represents the fluid viscosity matrix at step m. This represents the fluid-structure interaction interfacial force acting on the fluid in step m. Let m represent the external force acting on the fluid at step m; based on the velocity at the midpoint of the J-th fluid node, solve the second fluid control equation for the fluid domain to obtain the force at step (m+1). The pressure at each fluid node; the second fluid control equation is as follows: , Indicates the (m+1)th step. Pressure at each fluid node Represents the pressure Poisson matrix. Represents the divergence matrix; according to the (m+1)th step... The pressure at each fluid node is used to solve the third fluid control equation for the fluid domain, yielding the result at step (m+1). The target fluid velocity at each fluid node; the third fluid control equation is as follows: , Indicates the m-th step. Pressure at each fluid node Indicates the target fluid velocity. The gradient matrix is ​​represented by the formula; the fluid velocity gradient is determined by solving the fluid velocity gradient calculation formula based on the target fluid velocity at each fluid node; the fluid velocity gradient calculation formula is as follows: , Represents the fluid velocity gradient. Indicates the first The target fluid velocity at each fluid node Indicates the first The gradient of the shape function of each fluid node; the above-mentioned solution of the smooth displacement gradient at each location point in the solid domain includes: Solving the smooth displacement gradient equation for the solid domain yields the smooth displacement gradient at each location point within the solid domain; wherein the smooth displacement gradient equation is as follows: , Represents any point within a solid domain The displacement of the smooth domain at point P, where P represents the number of nodes in the smooth domain. Indicates the first The area of ​​the smooth domain of a solid node. Indicates the first A smooth region of a solid node. Indicates the first A solid node shape function Represents the node coordinates within the smooth domain. This represents the outward normal vector of the smooth domain boundary. Represents the first in the smooth domain The displacement vectors of K solid nodes, where K represents the number of Gaussian points in the smooth domain. This represents the weight coefficient of the nth Gaussian point.

[0009] In some embodiments, determining the drag and lift of the cylindrical structure in the flow field based on the fluid velocity gradient includes: determining the tangential shear stress by multiplying the fluid dynamic viscosity coefficient by the fluid velocity gradient; and solving the drag calculation formula based on the tangential shear stress and the fluid pressure to obtain the drag; the drag calculation formula is as follows: , = , Indicates resistance. Indicates tangential shear stress. The pressure represents the fluid pressure, and S represents the contact area between the fluid and the solid. Represents the area of ​​a microelement. Let n represent the component of the normal vector n of the mesh element surface in the x-direction. The component of the tangent vector t on the mesh element surface in the x-direction is represented by the tangential shear stress and fluid pressure. The lift force is obtained by solving the lift force calculation formula, which is as follows: , = , Indicates lift. Let n represent the component of the normal vector n of the mesh element surface in the y-direction. The component of the tangent vector t on the mesh element surface in the y-direction is represented. The determination of the drag and lift forces experienced by the cylindrical structure in the flow field based on the smooth displacement gradient includes: obtaining the solid element displacement gradient by solving for the smooth displacement gradient; and obtaining the second type of Piola-Kirchhoff stress by solving the second type of Piola-Kirchhoff stress formula based on the solid element displacement gradient. The second type of Piola-Kirchhoff stress is as follows: ,in, , , This represents the second type of Piola-Kirchhoff stress. Represents a unit tensor. The displacement gradient of the solid element is represented by [insert value here]. Based on the second type of Piola-Kirchhoff stress and the displacement gradient of the solid element, the calculation formula for the first type of Piola-Kirchhoff stress is solved to obtain the first type of Piola-Kirchhoff stress. The calculation formula for the first type of Piola-Kirchhoff stress is as follows: Type I Piola-Kirchhoff stress, This represents the second type of Piola-Kirchhoff stress; based on the first type of Piola-Kirchhoff stress, the resultant force of drag and lift is obtained by solving the drag-lift resultant force formula; the drag-lift resultant force formula is as follows: , This represents the resultant force of drag and lift. Represents the density of a solid. This represents the acceleration of a particle within a solid domain. This represents the divergence operator; based on the resultant force of drag and lift, drag and lift are calculated inversely.

[0010] In some embodiments, the above method includes: during eddy-induced vibration simulation, using a sharp plane correction method to correct the interface between the fluid domain and the solid domain; the sharp plane correction method involves obtaining a solid element surface on the outer surface of the solid structure and at least two fluid nodes passing through the solid element surface, obtaining the vertical distance between each of the at least two fluid nodes and the solid element surface, selecting the fluid node corresponding to the largest distance as the boundary surface correction point, and generating a new interface between the fluid domain and the solid domain based on the boundary surface correction point using a geometric reconstruction method; the solid element surface is composed of at least three solid nodes.

[0011] Secondly, embodiments of this application provide a method for determining a vortex-induced vibration suppression scheme for a cylindrical structure, the method comprising: For each first target parameter in the preset first target parameter set, the first target parameter is used as the first preset parameter. The drag and lift corresponding to the first target parameter are determined by using the method for simulating vortex-induced vibration of a cylindrical structure as described in the first aspect above. The first preset parameter is a preset length or a preset distance. When the first preset parameter is a preset length, the first target parameter is the target length. When the first preset parameter is a preset distance, the first target parameter is the target distance. The first target parameters in the first target parameter set are selected from a preset range. For each first target parameter in the preset first target parameter set, the vortex-induced vibration parameter corresponding to the first target parameter is determined according to the drag and lift corresponding to the first target parameter; the vortex-induced vibration parameter is used to characterize the severity of vortex-induced vibration of the cylindrical structure. Based on the vortex-induced vibration parameters corresponding to each first target parameter, the optimal first target parameter within a preset range corresponding to the first target parameter set is determined; the suppression scheme includes the optimal first target parameter.

[0012] In some embodiments, after determining the optimal first target parameter within a preset range corresponding to the first target parameter set based on the vortex-induced vibration parameters corresponding to each first target parameter, the method includes: for each second target parameter in the preset second target parameter set, using the second target parameter as a second preset parameter and the optimal first target parameter as a first preset parameter, and employing the method for simulating vortex-induced vibration of a cylindrical structure as described in the first aspect to determine the drag and lift corresponding to the second target parameter; when the first preset parameter is a preset length, the second preset parameter is a preset distance; when the first preset parameter is a preset distance, the second preset parameter is a preset length; the second target parameters in the second target parameter set are selected from a preset range; for each second target parameter in the preset second target parameter set, determining the vortex-induced vibration parameter corresponding to the second target parameter based on the drag and lift corresponding to the second target parameter; determining the optimal second target parameter within the preset range corresponding to the second target parameter set based on the vortex-induced vibration parameters corresponding to each second target parameter; the suppression scheme includes the optimal second target parameter.

[0013] In some embodiments, the vortex-induced vibration parameters include at least one of the following: Strouhal number, drag coefficient, lift coefficient, and fluctuation amplitude of lift coefficient. Determining the vortex-induced vibration parameters corresponding to the first target parameter based on the drag and lift corresponding to the first target parameter includes: When the vortex-induced vibration parameters include the Strouhal number, the Strouhal number is calculated using the Strouhal number calculation formula; wherein the Strouhal number calculation formula is as follows: , Representing the Strauhal number, This indicates the resistance ratio, and , H represents the diameter of the cylindrical structure, and H represents the height of the fluid domain. This represents the average flow velocity at the velocity inlet of the fluid domain. The vortex frequency represents the flow around a cylinder. When the vortex-induced vibration parameters include a drag coefficient, the drag coefficient is calculated using the drag coefficient calculation formula based on the drag corresponding to the first target parameter; the drag coefficient calculation formula is as follows: , Indicates the drag coefficient. This represents the resistance corresponding to the first target parameter. Indicates fluid density, This represents the thickness of the fluid domain in the Z direction; When the vortex-induced vibration parameters include the lift coefficient, the lift coefficient is calculated using the lift coefficient calculation formula based on the lift corresponding to the first target parameter; the lift coefficient calculation formula is as follows: , Indicates the lift coefficient. This represents the lift force corresponding to the first target parameter; When the vortex-induced vibration parameters include the fluctuation amplitude of the lift coefficient, the difference between the maximum value and the minimum value of the lift coefficient within a preset time period is determined as the fluctuation amplitude of the lift coefficient.

[0014] In some embodiments, determining the optimal first target parameter within a preset range corresponding to the first target parameter set based on the vortex-induced vibration parameters corresponding to each first target parameter includes: when the vortex-induced vibration parameters include multiple vortex-induced vibration parameters, for each vortex-induced vibration parameter, constructing a continuous response curve function between the first target parameter and the vortex-induced vibration parameter using a smooth interpolation analysis method based on the vortex-induced vibration parameters corresponding to each first target parameter; using a preset multi-objective optimization decision strategy to comprehensively analyze the continuous response curve functions of the multiple vortex-induced vibration parameters, determining the optimal first target parameter within a preset range corresponding to the first target parameter set that minimizes the overall continuous response curve function of the multiple vortex-induced vibration parameters; when the vortex-induced vibration parameters include a single vortex-induced vibration parameter, constructing a continuous response curve function between the first target parameter and the vortex-induced vibration parameter using a smooth interpolation analysis method based on the vortex-induced vibration parameters corresponding to each first target parameter; and determining the value within a preset range corresponding to the first target parameter set that minimizes the continuous response curve function as the optimal first target parameter.

[0015] Thirdly, embodiments of this application provide a cylindrical structure vortex-induced vibration suppression device. The device includes a cylindrical structure of a vehicle, and a partition plate is provided on the downstream side of the cylindrical structure. The relative length and relative distance of the partition plate are determined by the cylindrical structure vortex-induced vibration suppression scheme determination method described in the second aspect. The relative length is the ratio of the length of the partition plate to the cylindrical diameter of the cylindrical structure, and the relative distance is the ratio of the interval distance between the partition plate and the cylindrical structure to the cylindrical diameter of the cylindrical structure.

[0016] Fourthly, embodiments of this application provide a device for simulating vortex-induced vibration of a cylindrical structure, the device comprising: A model building module is used to construct a fluid-structure interaction (FSI) model of the cylindrical structure of the aircraft. The FSI model includes a fluid domain and a solid domain. The volume of the solid domain is the sum of the volume of the cylindrical structure and the volume of the partition plate located downstream of the cylindrical structure. The relative length of the partition plate is a preset length, and the relative distance between the partition plates is a preset distance. The relative length is the ratio of the partition plate length to the cylinder diameter of the cylindrical structure, and the relative distance is the ratio of the interval between the partition plate and the cylindrical structure to the cylinder diameter of the cylindrical structure. The simulation module is used to simulate the vortex-induced vibration of the cylindrical structure based on the fluid-structure interaction model using the immersion smooth point interpolation method. The immersion smooth point interpolation method involves filling the solid domain with a virtual fluid, and then using a movable Lagrange mesh to mesh the solid domain and an Eulerian mesh to mesh the fluid domain, resulting in a fluid-structure interaction mesh model. The vortex-induced vibration simulation of the cylindrical structure is then performed based on this fluid-structure interaction mesh model. The virtual fluid has the same physical properties as the real fluid.

[0017] Fifthly, embodiments of this application provide a device for determining a vortex-induced vibration suppression scheme for a cylindrical structure, the device comprising: The first determining module is used to determine the drag and lift corresponding to each first target parameter in the preset first target parameter set, taking the first target parameter as a first preset parameter, and using the method of simulating vortex-induced vibration of a cylindrical structure as described above; the first preset parameter is a preset length or a preset distance; when the first preset parameter is a preset length, the first target parameter is a target length; when the first preset parameter is a preset distance, the first target parameter is a target distance; the first target parameters in the first target parameter set are selected from a preset range; The second determining module is used to determine the vortex-induced vibration parameter corresponding to each first target parameter in the preset first target parameter set, based on the drag and lift corresponding to the first target parameter; the vortex-induced vibration parameter is used to characterize the severity of vortex-induced vibration of the cylindrical structure. The third determining module is used to determine the optimal first target parameter within a preset range corresponding to the first target parameter set based on the vortex-induced vibration parameters corresponding to each first target parameter; the suppression scheme includes the optimal first target parameter.

[0018] In a sixth aspect, embodiments of this application provide a computer device including a memory and a processor. The memory stores a computer program. When the computer device includes a cylindrical structure vortex-induced vibration simulation device, the computer program, when executed by the processor, causes the processor to execute various steps of the cylindrical structure vortex-induced vibration simulation method. Alternatively, when the computer device includes a device for determining a vortex-induced vibration suppression scheme for a cylindrical structure, when the computer program is executed by the processor, the processor performs each step of the method for determining a vortex-induced vibration suppression scheme for a cylindrical structure.

[0019] In a seventh aspect, embodiments of this application provide a computer-readable storage medium storing a computer program. When the computer-readable storage medium is located in a cylindrical structure vortex-induced vibration simulation device, the computer program is executed by the processor, causing the processor to execute various steps of the cylindrical structure vortex-induced vibration simulation method. Alternatively, when the computer-readable storage medium is located in the device for determining a vortex-induced vibration suppression scheme for a cylindrical structure, the computer program is executed by the processor, causing the processor to perform each step of the method for determining a vortex-induced vibration suppression scheme for a cylindrical structure.

[0020] The method and device for simulating and suppressing vortex-induced vibration of a cylindrical structure in this application combine immersion smooth point interpolation with virtual fluid settings and differentiated mesh generation strategies for the fluid-structure interaction model of the cylindrical structure of the aircraft. The fluid uses a fixed Eulerian mesh, which does not move with the structure and is neither stretched nor twisted, while the solid uses a movable Lagrange mesh, which is distortion-free. No fluid mesh reconstruction is performed throughout the process, which can eliminate distortion from a mechanism perspective. This effectively solves the defects of single mesh generation, avoids the mesh entanglement problem that easily occurs when using Lagrange meshes in the fluid domain, and avoids the drawback of Eulerian meshes being difficult to capture the dynamic motion of solids when used in the solid domain. In addition, the solid domain is filled with virtual fluids of the same properties, and the fluid and solid are mathematically unified fields, resulting in a natural and continuous interface. Furthermore, the use of smooth point interpolation for fluid-structure information exchange ensures a smooth interface without jumps, which can improve the accuracy of interface capture and thus improve the simulation accuracy of vortex-induced vibration of the cylindrical structure of the aircraft. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] in: Figure 1A flowchart illustrating the vortex-induced vibration simulation method for a cylindrical structure provided in this application embodiment; Figure 2 A schematic diagram of the flow field model provided in the embodiments of this application; Figure 3 This is a schematic diagram of a fluid-structure interaction mesh model after mesh generation, provided in an embodiment of this application. Figure 4 A schematic diagram illustrating the determination of boundary surface correction points using the sharp plane correction method provided in this application embodiment; Figure 5 A flowchart illustrating the method for determining a vortex-induced vibration suppression scheme for a cylindrical structure, as provided in an embodiment of this application. Figure 6 A structural block diagram of a cylindrical structure vortex-induced vibration simulation and suppression device provided in this application embodiment; Figure 7 A structural block diagram of a cylindrical structure vortex-induced vibration simulation device provided in this application embodiment; Figure 8 A structural block diagram of a device for determining a vortex-induced vibration suppression scheme for a cylindrical structure, provided in an embodiment of this application; Figure 9 This is a structural block diagram of a computer device in one embodiment. Detailed Implementation

[0023] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] refer to Figure 1 , Figure 1 This is a flowchart illustrating the vortex-induced vibration simulation method for a cylindrical structure provided in this application embodiment. Specifically, it includes the following steps S101-S102: Step S101: Construct a fluid-structure interaction model of the cylindrical structure of the aircraft.

[0025] The aforementioned vehicles can be surface vehicles or underwater vehicles.

[0026] The fluid-structure interaction model described above includes a fluid domain and a solid domain. The volume of the solid domain is the sum of the volume of the cylindrical structure and the volume of the partition plate located downstream of the cylindrical structure.

[0027] The size of the fluid domain can be set as needed. See also Figure 2 , Figure 2A schematic diagram of the flow field model provided in the embodiments of this application, such as Figure 2 As shown, the diameter of the cylinder is The cylindrical structure is surrounded by a fluid domain, and the length of the fluid domain is... High fluid domain Thickness of the fluid domain .

[0028] The key geometric parameters of the cylindrical structure can be determined based on the actual cylindrical structure dimensions of the aircraft. These key geometric parameters may include the cylinder diameter D and the cylinder length L. The key geometric parameters of the cylinder can be obtained based on the design drawings of the actual cylindrical structure of the aircraft.

[0029] The relative length of the aforementioned partition plate is a preset length, which is the ratio of the partition plate length to the cylinder diameter of the cylindrical structure. The preset length can be, but is not limited to, 3.0. The cylinder diameter D is 0.1m, meaning the partition plate length is 3.0 × 0.1 = 0.3m. Therefore, once the relative length of the partition plate is determined, the partition plate length can be determined.

[0030] The relative distance between the aforementioned partition plates is a preset distance, which is the ratio of the interval between the partition plate and the cylindrical structure to the diameter of the cylindrical structure. The preset distance can be, but is not limited to, a value of 5.0. The cylinder diameter D is 0.1m, meaning the interval between the partition plate and the cylindrical structure is 5.0 × 0.1 = 0.5m.

[0031] In one embodiment, the partition plate can be a rigid plate made of the same material as the cylindrical structure. The thickness of the partition plate can be preset, and can be, but is not limited to, 0.01m. The width of the partition plate can be the same as the length L of the cylinder, so as to ensure the compatibility between the partition plate and the cylindrical structure.

[0032] Step S102: Using the immersion smooth point interpolation method, the vortex-induced vibration of the cylindrical structure is simulated based on the fluid-structure interaction model.

[0033] Among them, the immersion smooth point interpolation method fills the region where the solid domain is located with virtual fluid, and uses a movable Lagrange grid to divide the solid domain and an Eulerian grid to divide the fluid domain, thus obtaining a fluid-structure interaction grid model. Based on the fluid-structure interaction grid model, the vortex-induced vibration simulation of the cylindrical structure is carried out.

[0034] Virtual fluids share the same physical properties as real fluids. Real fluids can be the fluids that a cylindrical structure of a spacecraft experiences during actual use.

[0035] In this embodiment, based on the fluid-structure interaction model constructed in step S101, the Immersed Smoothed Point Interpolation Method (IS-PIM) is used to mesh the fluid and solid domains separately. Specifically, for the solid domain, a movable Lagrange mesh is used for meshing. The mesh is bound to the solid model and moves synchronously with the solid's motion, eliminating the need for frequent re-meshing. This accurately captures the solid's displacement, deformation, and other motion states while avoiding mesh distortion. For the fluid domain, an Eulerian mesh is used. The mesh remains fixed, and the fluid flows within the mesh, ensuring the flow characteristics of the real fluid. This allows for accurate simulation of continuous fluid movements such as diffusion, flow, and phase transitions without needing to adjust the mesh to follow the fluid's movement, ensuring that the fluid flow pattern is completely replicated from the real fluid and improving simulation accuracy. Triangular meshes can be used; automatically generated triangular meshes are effective for simulating irregular fluid-structure interaction objects such as cylinders. (See also...) Figure 3 , Figure 3 This is a schematic diagram of the fluid-structure interaction mesh model after meshing provided in the embodiments of this application. Number 1 refers to the partition plate, number 2 refers to the fluid domain, and number 3 refers to the cylindrical structure.

[0036] The immersion smooth point interpolation method can complete the mesh coupling and information transfer of the fluid-structure interaction. By setting interpolation points near the fluid-structure interaction, a smooth transition and accurate transfer of load and displacement information between the Eulerian mesh (fluid domain) and the movable Lagrange mesh (solid domain) can be achieved, eliminating numerical dispersion and stress oscillation caused by mismatched meshes. Ultimately, this can improve the effectiveness of fluid-structure interaction mesh model construction and the accuracy of simulation.

[0037] In this embodiment, the fluid-structure interaction model obtained above can be imported into simulation software to simulate the vortex-induced vibration of a cylindrical structure using the immersion smooth point interpolation method based on the fluid-structure interaction model. Specifically, boundary conditions and solution parameters for the vortex-induced vibration simulation can be set, such as fluid inflow velocity and Reynolds number (which conform to the actual underwater navigation conditions of the aircraft). The fluid inlet adopts velocity inlet boundary conditions, and the outlet adopts pressure outlet boundary conditions (the pressure can be set to standard atmospheric pressure 101325 Pa). The sidewalls and bottom of the fluid domain can adopt no-slip boundary conditions, the two ends of the cylindrical structure in the solid domain adopt simply supported boundary conditions, and the partition plate adopts fixed constraint boundary conditions to simulate the installation state of the actual cylindrical structure of the aircraft.

[0038] It is possible, but not limited to, that the diameter of the cylinder is The length of the fluid domain ,high Thickness of the fluid domain The material properties of the fluid are as follows: density Poisson's ratio of solid structural materials In this example, the solid cylindrical structure remains stationary; the fluid domain is subject to non-slip velocity boundary conditions above and below, and impenetrable velocity boundary conditions before and after; the right side of the fluid domain is a pressure outlet, and the left end is a velocity inlet, with the velocity at the inlet satisfying the following conditions: ; in , , These represent the velocities of the fluid along the x, y, and z axes, respectively. y is the average flow velocity at the inlet, y is the Y coordinate of the current position, and H is the height of the fluid domain.

[0039] In this embodiment, a virtual fluid setting and differentiated meshing strategy are adopted for the fluid-structure interaction model of the cylindrical structure of the aircraft by combining the immersion smooth point interpolation method. The fluid uses a fixed Eulerian mesh, which does not move with the structure and is not stretched or twisted. The solid uses a movable Lagrange mesh, which is distortion-free. No fluid mesh reconstruction is performed throughout the process, which can eliminate distortion from the mechanism. This can effectively solve the defects of single meshing, avoid the mesh entanglement problem that is easy to occur when Lagrange mesh is used in the fluid domain, and avoid the disadvantage of Eulerian mesh being difficult to capture the dynamic motion of solid when used in the solid domain. In addition, the solid domain is filled with virtual fluid of the same property, the fluid and solid are mathematically unified fields, the interface is natural and continuous, and the smooth point interpolation is used for fluid-structure information exchange, the interface is smooth and without jumps, which can improve the accuracy of interface capture, thereby improving the simulation accuracy of vortex-induced vibration of the cylindrical structure of the aircraft.

[0040] In some embodiments, the above method may include the following steps: In the simulation of eddy-induced vibration, the fluid velocity gradient is obtained by solving the fluid domain or the smooth displacement gradient at each point in the solid domain is obtained by solving the solid domain.

[0041] The drag and lift forces experienced by a cylindrical structure in a flow field can be determined based on the fluid velocity gradient, or based on the smooth displacement gradient.

[0042] In this embodiment, during the simulation of vortex-induced vibration of a cylindrical structure based on a fluid-structure interaction mesh model, the coupled solutions of the fluid domain and the solid domain are performed in real time. The fluid domain is numerically solved to obtain the flow field information within the fluid domain, and the fluid velocity gradient is further calculated. At the same time, the solid domain is dynamically solved, and the smooth displacement gradient at each location point within the solid domain is calculated based on the smooth interpolation characteristics of the immersion smooth point interpolation method.

[0043] If fluid information is used as the basis, the drag and lift of the cylindrical structure in the flow field are determined based on the fluid velocity gradient; if solid structure information is used as the basis, the drag and lift of the cylindrical structure in the flow field are determined based on the smooth displacement gradient.

[0044] In some embodiments, the above-described solution for the fluid velocity gradient in the fluid domain may include the following steps: Solving the first fluid control equation for the fluid domain yields the mid-time velocity of the J-th fluid node. J ranges from 1 to Q, where Q represents the number of fluid nodes in the fluid domain. The mid-time velocity is the velocity of the J-th fluid node at the mid-time between steps m and m+1. m is a positive integer.

[0045] Based on the velocity at the intermediate time of the J-th fluid node, the second fluid control equation of the fluid domain is solved to obtain the equation at the (m+1)-th step. Pressure at each fluid node.

[0046] According to the (m+1)th step, the... The pressure at each fluid node is used to solve the third fluid control equation for the fluid domain, yielding the result at step (m+1). The target fluid velocity at each fluid node.

[0047] Based on the target fluid velocity at each fluid node, the fluid velocity gradient calculation formula is solved to determine the fluid velocity gradient.

[0048] The first fluid control equation is shown below: ; in, Represents the fluid mass matrix. Let represent the velocity at the midpoint of the J-th fluid node. Indicates the m-th step. The fluid velocity at each fluid node Indicates the time step. Represents the fluid convection matrix. This represents the viscous force acting on the fluid in step m. This represents the fluid viscosity matrix at step m. This represents the fluid-structure interaction interfacial force acting on the fluid in step m. This represents the external force acting on the fluid at step m.

[0049] In one implementation, , Represents the entire fluid domain Volume integral on, Indicates fluid density, For the fluid unit A fluid node shape function, Let J be the shape function of the J-th fluid node of the fluid element. , This represents the spatial coordinate components along the y-axis in the fluid domain. This represents the Cauchy stress tensor in the fluid domain. , This represents the velocity component along the z-axis in the fluid domain at step m. This represents the spatial coordinate component along the z-axis in the fluid domain. , Indicates the boundary of the fluid domain The area integral on, The unit vector representing the direction of the outward normal of the fluid boundary is in directional components, This represents the skew stress tensor component of the fluid element at step m. , Indicates volume force The acceleration component in the axial direction. , This represents the fluid velocity field at the current moment. This represents the gradient of the shape function of the J-th fluid node in the fluid element.

[0050] The second fluid control equation is shown below: ; in, Indicates the (m+1)th step. Pressure at each fluid node Represents the pressure Poisson matrix. This represents the divergence matrix.

[0051] Pressure Poisson matrix It can be obtained using existing methods; in one implementation, Where h is the grid node step size, and This is an index for fluid mesh nodes, used to uniquely identify mesh nodes within the fluid domain.

[0052] In one implementation, .

[0053] The third fluid control equation is shown below: , in, Indicates the m-th step. Pressure at each fluid node Indicates the target fluid velocity. This represents the gradient matrix.

[0054] In one implementation, .

[0055] The formula for calculating the fluid velocity gradient is as follows: ; in, Represents the fluid velocity gradient. Indicates the first The target fluid velocity at each fluid node Indicates the first The gradient of the shape function of each fluid node.

[0056] In some embodiments, the above-described method of solving the smooth displacement gradient at each location point within the solid domain may include the following steps: Solving the smooth displacement gradient equation for the solid domain yields the smooth displacement gradient at each location point within the solid domain.

[0057] The above smooth displacement gradient equation is shown below: ; in, Represents any point within a solid domain The displacement of the smooth domain at point P, where P represents the number of nodes in the smooth domain. Indicates the first The area of ​​the smooth domain of a solid node. Indicates the first A smooth region of a solid node. Indicates the first A solid node shape function Represents the node coordinates within the smooth domain. This represents the outward normal vector of the smooth domain boundary. Represents the first in the smooth domain The displacement vectors of K solid nodes, where K represents the number of Gaussian points in the smooth domain. This represents the weight coefficient of the nth Gaussian point.

[0058] In some embodiments, determining the drag and lift forces experienced by the cylindrical structure in the flow field based on the fluid velocity gradient may include the following steps: The product of the fluid dynamic viscosity coefficient and the fluid velocity gradient is determined as the tangential shear stress.

[0059] The resistance is obtained by solving the resistance calculation formula based on the tangential shear stress and fluid pressure.

[0060] The formula for calculating the resistance mentioned above is as follows: , = ; in, Indicates resistance. Indicates tangential shear stress. The pressure represents the fluid pressure, and S represents the contact area between the fluid and the solid. Represents the area of ​​a microelement. Let n represent the component of the normal vector n of the mesh element surface in the x-direction. This represents the component of the tangent vector t of the mesh element surface in the x-direction.

[0061] The resistance calculated using the above formula based on tangential shear stress and fluid pressure can be obtained by substituting the tangential shear stress, fluid pressure, the component of the normal vector n of the mesh element surface in the x-direction, and the component of the tangential vector t of the mesh element surface in the x-direction into the resistance calculation formula.

[0062] The lift force is obtained by solving the lift force calculation formula based on the tangential shear stress and fluid pressure.

[0063] The lift calculation formula is shown below: , = ; in, Indicates lift. Let n represent the component of the normal vector n of the mesh element surface in the y-direction. This represents the component of the tangent vector t of the mesh element surface in the y direction.

[0064] The above-mentioned lift calculation formula, which is obtained by solving the lift formula based on tangential shear stress and fluid pressure, can be obtained by substituting the tangential shear stress, fluid pressure, the component of the normal vector n of the mesh micro-element surface in the y-direction, and the component of the tangential vector t of the mesh micro-element surface in the y-direction into the lift calculation formula.

[0065] In some embodiments, determining the drag and lift forces experienced by the cylindrical structure in the flow field based on the smooth displacement gradient may include the following steps: The displacement gradient of the solid element is obtained by solving for the smooth displacement gradient. For specific calculations, refer to existing techniques.

[0066] The second type of Piola-Kirchhoff stress is obtained by solving the formula for calculating the second type of Piola-Kirchhoff stress based on the displacement gradient of the solid element.

[0067] Based on the second type of Piola-Kirchhoff stress and the displacement gradient of the solid element, the calculation formula for the first type of Piola-Kirchhoff stress is solved to obtain the first type of Piola-Kirchhoff stress.

[0068] Based on the first type of Piola-Kirchhoff stress, the resultant force of drag and lift can be obtained by solving the formula for the resultant force of drag and lift.

[0069] Based on the resultant force of drag and lift, the drag and lift can be calculated by reverse deduction.

[0070] The above-mentioned method of obtaining the solid element displacement gradient based on the smooth displacement gradient can be achieved by using intra-element interpolation mapping to obtain the solid element displacement gradient at the solid element integration points (such as Gaussian integration points). Specifically, existing techniques can be referenced, for example, using shape function interpolation methods to map the nodal-level smooth displacement gradient to the element integration points, thus obtaining the displacement gradient at each integration point within the element. u e .

[0071] The second type of Piola-Kirchhoff stress mentioned above is as follows: ; in, , , This represents the second type of Piola-Kirchhoff stress. Represents a unit tensor. This represents the displacement gradient of a solid element.

[0072] The formula for calculating the first type of Piola-Kirchhoff stress is shown below: ; This represents the first type of Piola-Kirchhoff stress. This represents the second type of Piola-Kirchhoff stress. The formula for solving the drag-lift resultant force is shown below: ; in, This represents the resultant force of drag and lift. Represents the density of a solid. This represents the acceleration of a particle within a solid domain. This represents the divergence operator.

[0073] The above-mentioned solution to the drag-lift resultant force based on the first-kind Piola-Kirchhoff stress can be obtained by substituting the first-kind Piola-Kirchhoff stress, solid density, acceleration of particles in the solid domain, and divergence operator into the drag-lift resultant force solution formula.

[0074] The above method, which calculates drag and lift by inversely based on the resultant force of drag and lift, can be implemented with reference to existing technologies. It can be, but is not limited to, using the direction of fluid flow as the drag direction (x-direction) and the direction perpendicular to the flow direction as the lift direction (y-direction) to construct a Cartesian coordinate system, thus representing the resultant force of drag and lift. Projecting onto this rectangular coordinate system, we get: = e x , = e y , where e x e y These are the unit vectors in the directions of drag and lift, respectively.

[0075] In some embodiments, the above method may include the following steps: In the simulation of eddy vibration, the sharp plane correction method is used to correct the interface between the fluid domain and the solid domain.

[0076] The aforementioned sharp plane correction method involves obtaining the solid element surface of the outer surface of the solid structure and at least two fluid nodes passing through the solid element surface. The vertical distance between each of the at least two fluid nodes and the solid element surface is obtained. The fluid node with the largest vertical distance is selected as the boundary surface correction point. Based on the boundary surface correction point, a new interface between the fluid domain and the solid domain is generated using a geometric reconstruction method. The aforementioned solid element surface consists of at least three solid nodes. At least two fluid nodes are located on both sides of the solid element surface; that is, the line connecting any two fluid nodes located on either side of the solid element surface passes through the solid element surface.

[0077] In this embodiment, in order to improve the geometric accuracy and numerical stability of the fluid-structure interaction interface during the vortex-induced vibration simulation, the sharp plane correction method is used to correct the interface between the fluid domain and the solid domain.

[0078] Specifically, the process involves traversing all surface elements of the solid domain and selecting a solid element surface Γs composed of at least three solid nodes. This solid element surface Γs is a discrete element surface on the outer surface of a cylindrical structure. Based on the fluid domain mesh, at least two fluid nodes passing through this solid element surface Γs are identified. These fluid nodes are located on either side of the solid element surface and are key candidate points for interface correction. For each fluid node fi passing through the solid element surface Γs, its vertical distance di to the solid element surface is calculated. The distances di from all fluid nodes fi to the solid element surface Γs are compared, and the fluid node fmax corresponding to the maximum distance dmax is selected as the boundary surface correction point. The boundary surface correction point represents the location with the largest deviation between the fluid domain and the solid element surface and is a key control point for correcting the geometry of the interface.

[0079] See Figure 4 , Figure 4 This is a schematic diagram of determining the boundary surface correction point using the sharp plane correction method provided in this embodiment. S2, S3, S4, S5, S7, and S8 are solid nodes, and f1, f2, f3, f4, and f5 are fluid nodes. Taking the outermost unit surface of the solid structure composed of solid nodes S2, S3, and S4 and the fluid nodes f1 and f2 passing through this surface as an example, l1 is the intersection point of the line connecting the outermost unit surface of the solid structure composed of solid nodes S2, S3, and S4 and the fluid nodes f1 and f2. Perpendicular feet are drawn from nodes f1 and f2 to the solid structure unit surface, respectively, and they intersect at points a and b. Then, compare the perpendicular distance Df1,a from node f1 to the solid element surface formed by S2, S3, S4, and the perpendicular distance Df2,b from node f2 to that element surface: if Df2,b > Df1,a, then select fluid node f1 as the boundary correction point for fluid velocity; if Df1,a > Df2,b, then select fluid node f2 as the boundary correction point for fluid velocity. Similarly, solid nodes S3, S4, S7 constitute the outermost element surface of the solid structure, and l2 is the intersection point of the line connecting the outermost element surface of the solid structure formed by solid nodes S3, S4, S7 and fluid nodes f3, f5, and l3 is the intersection point of the line connecting the outermost element surface of the solid structure formed by solid nodes S3, S4, S7 and fluid nodes f3, f4. A similar method can be used to determine the boundary correction point from fluid nodes f3, f4, f5.

[0080] The above-mentioned method of generating a new interface between the fluid and solid domains based on boundary surface correction points and using geometric reconstruction can be based on the boundary surface correction point fmax. Specifically, for each boundary surface correction point fmax, the solid element surface Γs corresponding to the boundary surface correction point fmax is used as the basis. The boundary surface correction point fmax is projected onto the solid element surface Γs to obtain the projection point Pmax. With Pmax as the vertex, combined with the boundary of the solid element surface Γs, a new interface element is generated through triangulation or quadrilateral reconstruction. The interface Γfs obtained in this way is closer to the true geometry of the outer surface of the solid structure.

[0081] In this embodiment, the sharp plane correction method is used to correct the fluid-solid interface, which can accurately identify and correct geometric deviations at the interface between the fluid and solid domains. By selecting the fluid node farthest from the solid element surface as the boundary correction point, the geometric accuracy and sharpness of the fluid-solid interface are effectively improved, avoiding problems such as interface blurring and boundary diffusion. The geometric reconstruction method is used to generate a new interface, which makes the fluid mesh and solid surface fit better, effectively improving the accuracy and stability of fluid-solid coupling information transmission and reducing stress oscillations, numerical dispersion, and interface calculation errors. Interface correction can be completed simply by judging the distance between the solid element surface and the fluid node and geometric reconstruction, without the need for complex mesh reconstruction and large-scale iterative calculations, thus improving simulation accuracy while ensuring computational efficiency.

[0082] This application also provides a method for determining a vortex-induced vibration suppression scheme for a cylindrical structure. This method is used to determine the optimal length of a partition plate located downstream of the cylindrical structure and the optimal distance between the partition plate and the cylindrical structure. The core principle is to iterate through preset lengths and distances, and combine this with the aforementioned vortex-induced vibration simulation method, to select the optimal parameters to form a suppression scheme.

[0083] Reference Figure 5 , Figure 5 This is a flowchart illustrating the method for determining a vortex-induced vibration suppression scheme for a cylindrical structure provided in an embodiment of this application. Figure 5 As shown, the method for determining the vortex-induced vibration suppression scheme for this cylindrical structure includes steps S201-S203: Step S201: For each first target parameter in the preset first target parameter set, the first target parameter is used as the first preset parameter, and the drag and lift corresponding to the first target parameter are determined by using the vortex-induced vibration simulation method of cylindrical structure as described above.

[0084] The first preset parameter is either a preset length or a preset distance. If the first preset parameter is a preset length, the first target parameter is a target length. If the first preset parameter is a preset distance, the first target parameter is a target distance.

[0085] In this embodiment, a first target parameter set is preset, which is set in two scenarios, corresponding to the cases where the first preset parameter is a preset length and a preset distance, respectively: Scenario 1: The first preset parameter is the preset length (relative length), and the first target parameter is the target length. For example, the first target parameter set can be set to {2.0, 2.5, 3.0, 3.5, 4.0}, that is, the target lengths (relative lengths) are 2.0, 2.5, 3.0, 3.5, and 4.0 respectively, D=0.1m, and the corresponding partition lengths are 2.0×D=0.2m, 2.5×D=0.25m, 3.0×D=0.3m, 3.5×D=0.35m, and 4.0×D=0.4m respectively; at this time, the preset distance (relative distance) is fixed, which can be, but is not limited to, a fixed preset distance of 5.0 (corresponding to an interval distance of 5.0×D=0.5m).

[0086] Scenario 2: The first preset parameter is the preset distance (the relative distance between the partition and the cylinder), and the first target parameter is the target distance. The first target parameter set is set to {3.0, 4.0, 5.0, 6.0, 7.0}, that is, the target distances (relative distances) are 3.0, 4.0, 5.0, 6.0, and 7.0 respectively, D=0.1m, and the corresponding interval distances are 3.0×D=0.3m, 4.0×D=0.4m, 5.0×D=0.5m, 6.0×D=0.6m, and 7.0×D=0.7m respectively. At this time, the preset length (relative length) is fixed. For example, it can be, but is not limited to, a fixed preset length of 3.0 (corresponding to the partition length 3.0×D=0.3m).

[0087] Simultaneously, actual basic conditions for vortex-induced vibration simulation can be set, such as, but not limited to, fluid domain physical properties (seawater density 1025 kg / m³, dynamic viscosity 1.07 × 10⁻⁶). -6 m² / s), solid domain physical properties (titanium alloy, density 4510 kg / m³, elastic modulus 110 GPa, Poisson's ratio 0.3), fluid inflow velocity 1.5 m / s, simulation time 10 s, time step 1 × 10⁻⁶. -4 The fluid-solid interface is corrected using the sharp plane correction method to ensure that the simulation conditions corresponding to all first target parameters are consistent, thus guaranteeing the objectivity of the screening results.

[0088] The values ​​in the first target parameter set mentioned above can take values ​​within a preset range, for example, but not limited to the preset range of 0-3.5.

[0089] For each first target parameter in the preset first target parameter set, it is sequentially used as a first preset parameter. The vortex-induced vibration simulation method for cylindrical structures described above is used to conduct vortex-induced vibration simulation, and finally, the drag (F) corresponding to each first target parameter is determined. d ) and lift (F l ).

[0090] Step S202: For each first target parameter in the preset first target parameter set, determine the vortex-induced vibration parameter corresponding to the first target parameter based on the drag and lift corresponding to the first target parameter.

[0091] Vortex-induced vibration parameters are used to characterize the severity of vortex-induced vibration in cylindrical structures.

[0092] For each first target parameter in the first target parameter set, the resistance (F) obtained in step S201 d ) and lift (F l Based on this, the vortex-induced vibration parameters corresponding to each first target parameter are calculated and determined. The vortex-induced vibration parameters may include the Strouhal number. drag coefficient Lift coefficient and the fluctuation range of the lift coefficient At least one of them.

[0093] Step S203: Based on the vortex-induced vibration parameters corresponding to each first target parameter, determine the optimal first target parameter within a preset range corresponding to the first target parameter set.

[0094] The suppression scheme includes the optimal first target parameter.

[0095] Based on the vortex-induced vibration parameters corresponding to each first target parameter obtained in step S203, the optimal first target parameter within the preset range corresponding to the first target parameter set is determined by the comprehensive evaluation method. The core evaluation principle is that the smaller the overall vortex-induced vibration parameter, the better the vortex-induced vibration suppression effect corresponding to that parameter, that is, the parameter is the optimal first target parameter.

[0096] In this embodiment, by traversing a preset set of first target parameters (target length or target distance) and combining it with the high-precision vortex-induced vibration simulation method, the drag, lift, and vortex-induced vibration parameters corresponding to each parameter are quantified. The severity of vortex-induced vibration is used as the evaluation criterion to select the optimal first target parameter, avoiding the subjectivity and blindness of traditional suppression parameter selection. This ensures that the selected parameters can minimize the intensity of vortex-induced vibration (e.g., reduce lift amplitude and vibration amplitude), thereby improving the targeting and effectiveness of tail vortex suppression for cylindrical structures and reducing the risk of structural fatigue damage. Furthermore, by characterizing the severity of vortex-induced vibration with vortex-induced vibration parameters (lift amplitude, vibration amplitude, lift frequency, etc.), the abstract suppression effect is transformed into a quantifiable and comparable numerical indicator. This not only accurately judges the suppression effect of a single target parameter but also clarifies the optimal solution through parameter comparison. This provides scientific and reliable numerical support for the design of the size or installation distance of the downstream partition plate of the cylindrical structure of the aircraft, avoiding the problem of unstable suppression effect caused by relying on experience-based design.

[0097] In some embodiments, after determining the optimal first target parameter within a preset range corresponding to the first target parameter set based on the vortex-induced vibration parameters corresponding to each first target parameter, the method further includes the following steps: For each second target parameter in the preset set of second target parameters, the second target parameter is used as the second preset parameter, and the optimal first target parameter is used as the first preset parameter. The vortex-induced vibration simulation method of the cylindrical structure described above is used to determine the drag and lift corresponding to the second target parameter.

[0098] For each second target parameter in the preset set of second target parameters, the vortex-induced vibration parameters corresponding to the second target parameters are determined based on the drag and lift corresponding to the second target parameters.

[0099] Based on the vortex-induced vibration parameters corresponding to each second objective parameter, determine the optimal second objective parameter in the set of second objective parameters.

[0100] The suppression strategy includes optimal second target parameters.

[0101] The second target parameter in the second target parameter set is selected from a preset range.

[0102] In this embodiment, after determining the optimal first target parameter in the first target parameter set, the optimal second target parameter is further selected by traversing the preset second target parameter set and combining vortex-induced vibration simulation, thereby improving the vortex-induced vibration suppression scheme.

[0103] When the first preset parameter is a preset length, the second preset parameter is a preset distance; when the first preset parameter is a preset distance, the second preset parameter is a preset length. When the second preset parameter is a preset length, the second target parameter is a target length; when the second preset parameter is a preset distance, the second target parameter is a target distance.

[0104] In this embodiment, the optimal first target parameter obtained through screening is used as the premise, and it is fixed as the first preset parameter. All subsequent simulations of the second target parameters are carried out based on this optimal first target parameter.

[0105] The second set of target parameters is preset for two scenarios. The range of values ​​in the set closely matches the actual engineering situation, ensuring that it covers the parameter requirements under different working conditions. The specific settings can be as follows: Scenario 1: The first preset parameter is the preset length, the second preset parameter is the preset distance, and the second target parameter is the target distance (relative distance). The preset set of second target parameters is {3.0, 4.0, 5.0, 6.0, 7.0}, D=0.1m, and the corresponding interval distances are 3.0×D=0.3m, 4.0×D=0.4m, 5.0×D=0.5m, 6.0×D=0.6m, and 7.0×D=0.7m, respectively. Scenario 2: The first preset parameter is the preset distance, the second preset parameter is the preset length, and the second target parameter is the target length (relative length). The preset set of the second target parameters is {2.0, 2.5, 3.0, 3.5, 4.0}, D=0.1m, and the corresponding partition lengths are 2.0×D=0.2m, 2.5×D=0.25m, 3.0×D=0.3m, 3.5×D=0.35m, and 4.0×D=0.4m, respectively.

[0106] For each second objective parameter in the preset set of second objective parameters, they are sequentially used as second preset parameters, while the optimal first objective parameter is used as the first preset parameter. The vortex-induced vibration simulation method for cylindrical structures is then employed to conduct vortex-induced vibration simulation, ultimately determining the drag (F) corresponding to each second objective parameter. d ) and lift (F l ).

[0107] Using the same calculation method and evaluation criteria as the one used to determine the vortex-induced vibration parameters corresponding to the first target parameters, the vortex-induced vibration parameters corresponding to each second target parameter in the preset set of second target parameters are determined based on the drag and lift corresponding to the obtained second target parameters.

[0108] Using the same comprehensive evaluation method as that used to determine the optimal first target parameter, the optimal second target parameter within a preset range is determined based on the vortex-induced vibration parameters corresponding to each of the obtained second target parameters.

[0109] In some embodiments, the vortex-induced vibration parameters include at least one of the following: Strouhal number, drag coefficient, lift coefficient, and fluctuation amplitude of lift coefficient. Determining the vortex-induced vibration parameters corresponding to the first target parameter based on the drag and lift corresponding to the first target parameter may include the following: When the vortex-induced vibration parameters include the Strouhal number, the Strouhal number is calculated using the Strouhal number calculation formula.

[0110] The formula for calculating the Strouhal number is as follows: ; in, Representing the Strauhal number, This indicates the resistance ratio, and , H represents the diameter of the cylindrical structure, and H represents the height of the fluid domain. This represents the average flow velocity at the velocity inlet of the fluid domain. This represents the vortex frequency of the flow around the cylinder.

[0111] The above uses the Strouhal number calculation formula. To calculate the Strouhal number, the obtained flow resistance ratio, the cylinder diameter of the cylindrical structure, the height of the fluid domain, the average flow velocity at the velocity inlet of the fluid domain, and the vortex frequency of the flow around the cylinder are substituted into the Strouhal number calculation formula to obtain the Strouhal number.

[0112] When the vortex-induced vibration parameters include the drag coefficient, the drag coefficient is calculated using the drag coefficient calculation formula based on the drag corresponding to the first target parameter.

[0113] The formula for calculating the drag coefficient is as follows: ; in, Indicates the drag coefficient. This represents the resistance corresponding to the first target parameter. Indicates fluid density, This represents the thickness of the fluid domain in the Z direction.

[0114] The above-mentioned resistance is calculated using the resistance coefficient calculation formula based on the resistance corresponding to the first target parameter. This can be achieved by substituting the obtained resistance corresponding to the first target parameter, the cylinder diameter of the cylindrical structure, the fluid density, the average flow velocity at the inlet of the fluid domain, and the thickness of the fluid domain in the Z direction into the resistance coefficient calculation formula to obtain the resistance coefficient.

[0115] When the vortex-induced vibration parameters include the lift coefficient, the lift coefficient is calculated using the lift coefficient calculation formula based on the lift corresponding to the first target parameter.

[0116] The formula for calculating the lift coefficient is as follows: ; in, Indicates the lift coefficient. This represents the lift force corresponding to the first target parameter.

[0117] The above-mentioned lift coefficient is calculated using the lift coefficient calculation formula based on the lift corresponding to the first target parameter. This can be achieved by substituting the obtained lift, fluid density, cylinder diameter of the cylindrical structure, average flow velocity at the velocity inlet of the fluid domain, and thickness of the fluid domain in the Z direction into the lift coefficient calculation formula.

[0118] When the vortex-induced vibration parameters include the fluctuation amplitude of the lift coefficient, the difference between the maximum and minimum values ​​of the lift coefficient within a preset time period is determined as the fluctuation amplitude of the lift coefficient.

[0119] In some embodiments, determining the optimal first target parameter within a preset range corresponding to the set of first target parameters based on the vortex-induced vibration parameters corresponding to each first target parameter may include the following steps: When the vortex-induced vibration parameters include multiple vortex-induced vibration parameters, for each vortex-induced vibration parameter, a smooth interpolation analysis method is used to construct a continuous response curve function between the first target parameter and the vortex-induced vibration parameter based on the vortex-induced vibration parameter corresponding to each first target parameter. A preset multi-objective optimization decision strategy is adopted to comprehensively analyze the continuous response curve functions of multiple vortex-induced vibration parameters, and to determine the optimal first target parameter within a preset range corresponding to the first target parameter set, which minimizes the overall continuous response curve function of multiple vortex-induced vibration parameters.

[0120] The aforementioned multi-objective optimization decision-making strategies can be weighted summation methods or Pareto optimal solution algorithms, etc.

[0121] The aforementioned multi-objective optimization decision-making strategy can be a weighted summation method. The weighted summation method can be used to sum the continuous response curve functions of multiple vortex-induced vibration parameters in a weighted manner to construct a multi-objective comprehensive objective function. The optimal first objective parameter is determined as the value that minimizes the multi-objective comprehensive objective function within a preset range corresponding to the first objective parameter set.

[0122] When the vortex-induced vibration parameters include a single vortex-induced vibration parameter, a smooth interpolation analysis method is used to construct a continuous response curve function between the first target parameter and the vortex-induced vibration parameter based on the vortex-induced vibration parameters corresponding to each first target parameter. The value that minimizes the continuous response curve function within the preset range corresponding to the set of first target parameters is determined as the optimal first target parameter.

[0123] This application also provides a cylindrical structure vortex-induced vibration suppression device, referring to... Figure 6 , Figure 6 This is a structural block diagram of a cylindrical structure vortex-induced vibration suppression device provided in an embodiment of this application. The cylindrical structure vortex-induced vibration suppression device 600 includes a cylindrical structure 601 of the aircraft, and a partition plate 602 is provided on the downstream side of the cylindrical structure. The relative length and relative distance of the partition plate are determined by the vortex-induced vibration suppression scheme determination method of the cylindrical structure described above. The relative length is the ratio of the length of the partition plate to the diameter of the cylinder of the cylindrical structure, and the relative distance is the ratio of the interval distance between the partition plate and the cylindrical structure to the diameter of the cylinder of the cylindrical structure.

[0124] In this embodiment, the method for determining the vortex-induced vibration suppression scheme of the cylindrical structure described above can improve the effectiveness of the suppression scheme determination. Furthermore, by setting a partition plate corresponding to the suppression scheme, the effectiveness of vortex-induced vibration suppression of the cylindrical structure can be improved.

[0125] To better implement the aforementioned method for simulating vortex-induced vibration of cylindrical structures, this application provides a device for simulating vortex-induced vibration of cylindrical structures, as described above. Figure 7 , Figure 7 A structural block diagram of a cylindrical structure vortex-induced vibration simulation device provided in this application embodiment is shown below. Figure 7 As shown, the cylindrical structure vortex-induced vibration simulation device 700 may specifically include the following: Model building module 701 is used to build a fluid-structure interaction model of the cylindrical structure of the aircraft; wherein, the fluid-structure interaction model includes a fluid domain and a solid domain, the volume of the solid domain is the sum of the volume of the cylindrical structure and the volume of the partition plate located downstream of the cylindrical structure, the relative length of the partition plate is a preset length, the relative distance between the partition plate and the cylindrical structure is a preset distance, the relative length is the ratio of the length of the partition plate to the diameter of the cylindrical structure, and the relative distance is the ratio of the interval distance between the partition plate and the cylindrical structure to the diameter of the cylindrical structure; The simulation module 702 is used to simulate the vortex-induced vibration of the cylindrical structure based on the fluid-structure interaction model using the immersion smooth point interpolation method. The immersion smooth point interpolation method involves filling the solid domain with a virtual fluid, and using a movable Lagrange mesh to mesh the solid domain and an Eulerian mesh to mesh the fluid domain, resulting in a fluid-structure interaction mesh model. The vortex-induced vibration of the cylindrical structure is then simulated based on this fluid-structure interaction mesh model. The virtual fluid has the same physical properties as the real fluid.

[0126] The cylindrical structure vortex-induced vibration simulation device 700 provided in this application embodiment can execute the technical solution shown in the above method embodiment. Its implementation principle and beneficial effects are similar, and will not be repeated here.

[0127] To better implement the above-mentioned method for determining a vortex-induced vibration suppression scheme for cylindrical structures, this application provides a device for determining a vortex-induced vibration suppression scheme for cylindrical structures, as described above. Figure 8 , Figure 8 A structural block diagram of a device for determining a vortex-induced vibration suppression scheme for a cylindrical structure, as provided in an embodiment of this application, is shown below. Figure 8 As shown, the device 800 for determining the vortex-induced vibration suppression scheme of the cylindrical structure may specifically include the following: The first determining module 801 is used to determine the drag and lift corresponding to each first target parameter in the preset first target parameter set, taking the first target parameter as a first preset parameter, and using the vortex-induced vibration simulation method of the cylindrical structure as described above; the first preset parameter is a preset length or a preset distance, where the first preset parameter is a preset length and the first target parameter is a target distance; the first target parameters in the first target parameter set are selected from a preset range; The second determining module 802 is used to determine the vortex-induced vibration parameter corresponding to each first target parameter in the preset first target parameter set, based on the drag and lift corresponding to the first target parameter; the vortex-induced vibration parameter is used to characterize the severity of vortex-induced vibration of the cylindrical structure. The third determining module 803 is used to determine the optimal first target parameter within a preset range corresponding to the first target parameter set based on the vortex-induced vibration parameters corresponding to each first target parameter; the suppression scheme includes the optimal first target parameter.

[0128] The cylindrical structure vortex-induced vibration suppression scheme determination device 800 provided in this application embodiment can execute the technical solution shown in the above method embodiment. Its implementation principle and beneficial effects are similar, and will not be repeated here.

[0129] Figure 9 An internal structural diagram of a computer device in one embodiment is shown. This computer device can specifically be a terminal or a server. Figure 9 As shown, the computer device includes a processor, memory, and network interface connected via a system bus. The memory includes a non-volatile storage medium and internal memory. The non-volatile storage medium stores an operating system and may also store a computer program. When executed by the processor, this computer program enables the processor to implement a method for simulating vortex-induced vibration of a cylindrical structure or a method for determining a vortex-induced vibration suppression scheme for a cylindrical structure. The internal memory may also store a computer program, which, when executed by the processor, enables the processor to implement the method for simulating vortex-induced vibration of a cylindrical structure or a method for determining a vortex-induced vibration suppression scheme for a cylindrical structure. Those skilled in the art will understand that… Figure 9 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0130] In one embodiment, a computer device is provided, including a memory and a processor, the memory storing a computer program that, when executed by the processor, causes the processor to perform various steps of the cylindrical structure vortex-induced vibration simulation method when the computer device includes a cylindrical structure vortex-induced vibration simulation device. Alternatively, when the computer device includes a device for determining a vortex-induced vibration suppression scheme for a cylindrical structure, when the computer program is executed by the processor, the processor performs each step of the method for determining a vortex-induced vibration suppression scheme for a cylindrical structure.

[0131] In one embodiment, a computer-readable storage medium storing a computer program is provided, which, when the computer-readable storage medium is located in a cylindrical structure vortex-induced vibration simulation device, is executed by the processor, causing the processor to perform various steps of the cylindrical structure vortex-induced vibration simulation method. Alternatively, when the computer-readable storage medium is located in the device for determining a vortex-induced vibration suppression scheme for a cylindrical structure, the computer program is executed by the processor, causing the processor to perform each step of the method for determining a vortex-induced vibration suppression scheme for a cylindrical structure.

[0132] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. Any references to memory, storage, databases, or other media used in the embodiments provided in this 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. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0133] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0134] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of this patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims. Please enter the specific implementation details.

Claims

1. A method for simulating vortex-induced vibration of a cylindrical structure, characterized in that, include: A fluid-structure interaction (FSI) model of a cylindrical structure of a spacecraft is constructed. This model includes a fluid domain and a solid domain. The volume of the solid domain is the sum of the volume of the cylindrical structure and the volume of a partition plate located downstream of the cylindrical structure. The relative length of the partition plate is a preset length, and the relative distance between the partition plates is a preset distance. The relative length is the ratio of the partition plate length to the cylinder diameter of the cylindrical structure, and the relative distance is the ratio of the distance between the partition plate and the cylindrical structure to the cylinder diameter of the cylindrical structure. An immersion smooth point interpolation method is used to simulate the vortex-induced vibration of the cylindrical structure based on the fluid-structure interaction model. The immersion smooth point interpolation method involves filling the solid domain with a virtual fluid, and then using a movable Lagrangian mesh to mesh the solid domain and an Eulerian mesh to mesh the fluid domain, resulting in a fluid-structure interaction mesh model. The vortex-induced vibration simulation of the cylindrical structure is then performed based on this fluid-structure interaction mesh model. The virtual fluid has the same physical properties as the real fluid. In the simulation of eddy vibration, a sharp plane correction method is used to correct the interface between the fluid domain and the solid domain. The sharp plane correction method involves obtaining the solid element surface of the outer surface of the solid structure and at least two fluid nodes passing through the solid element surface. The vertical distance between each of the at least two fluid nodes and the solid element surface is obtained. The fluid node corresponding to the largest distance is selected as the boundary surface correction point. Based on the boundary surface correction point, a new interface between the fluid domain and the solid domain is generated by geometric reconstruction. The solid element surface is composed of at least three solid nodes.

2. The method for simulating vortex-induced vibration of a cylindrical structure according to claim 1, characterized in that, include: In the vortex-induced vibration simulation process, the fluid velocity gradient is obtained by solving the fluid domain or the smooth displacement gradient at each position point in the solid domain is obtained by solving the solid domain. The drag and lift forces experienced by the cylindrical structure in the flow field are determined based on the fluid velocity gradient, or based on the smooth displacement gradient.

3. The method for simulating vortex-induced vibration of a cylindrical structure according to claim 2, characterized in that, The process of solving for the fluid velocity gradient in the fluid domain includes: Solving the first fluid control equation for the fluid domain yields the mid-time velocity of the J-th fluid node; J ranges from 1 to Q, where Q represents the number of fluid nodes in the fluid domain. The mid-time velocity is the velocity of the J-th fluid node at the mid-time between step m and step (m+1). The first fluid control equation is as follows: ,in, Represents the fluid mass matrix. Let represent the velocity at the midpoint of the J-th fluid node. Indicates the m-th step. The fluid velocity at each fluid node Indicates the time step. Represents the fluid convection matrix. This represents the viscous force acting on the fluid in step m. This represents the fluid viscosity matrix at step m. This represents the fluid-structure interaction interfacial force acting on the fluid in step m. This represents the external force acting on the fluid in the m-th step; Based on the velocity at the intermediate time of the Jth fluid node, the second fluid control equation of the fluid domain is solved to obtain the equation at the (m+1)th step. The pressure at each fluid node; the second fluid control equation is as follows: , Indicates the (m+1)th step. Pressure at each fluid node Represents the pressure Poisson matrix. Represents the divergence matrix; According to the (m+1)th step, the... The pressure at each fluid node is used to solve the third fluid control equation for the fluid domain, yielding the result at step (m+1). The target fluid velocity at each fluid node; the third fluid control equation is as follows: , Indicates the m-th step. Pressure at each fluid node Indicates the target fluid velocity. Represents the gradient matrix; Based on the target fluid velocity at each fluid node, the fluid velocity gradient calculation formula is solved to determine the fluid velocity gradient; the fluid velocity gradient calculation formula is as follows: , Represents the fluid velocity gradient. Indicates the first The target fluid velocity at each fluid node Indicates the first The gradient of the shape function of each fluid node; The process of solving the solid domain to obtain the smooth displacement gradient at each location point within the solid domain includes: Solving the smooth displacement gradient equation of the solid domain yields the smooth displacement gradient at each location point within the solid domain; wherein the smooth displacement gradient equation is as follows: , Represents any point within a solid domain The displacement of the smooth domain at point P, where P represents the number of nodes in the smooth domain. Indicates the first The area of ​​the smooth domain of a solid node. Indicates the first A smooth region of a solid node. Indicates the first A solid node shape function Represents the node coordinates within the smooth domain. This represents the outward normal vector of the smooth domain boundary. Represents the first smooth region The displacement vectors of K solid nodes, where K represents the number of Gaussian points in the smooth domain. This represents the weight coefficient of the nth Gaussian point.

4. The method for simulating vortex-induced vibration of a cylindrical structure according to claim 2, characterized in that, The step of determining the drag and lift forces experienced by the cylindrical structure in the flow field based on the fluid velocity gradient includes: The product of the hydrodynamic viscosity coefficient and the fluid velocity gradient is determined as the tangential shear stress. The resistance is obtained by solving the formula for calculating the resistance based on the tangential shear stress and fluid pressure; the formula for calculating the resistance is as follows: , = , Indicates resistance. Indicates tangential shear stress. The pressure represents the fluid pressure, and S represents the contact area between the fluid and the solid. Represents the area of ​​a microelement. Let n represent the component of the normal vector n of the mesh element surface in the x-direction. This represents the component of the tangent vector t of the mesh element surface in the x-direction; The lift force is obtained by solving the lift force calculation formula based on the tangential shear stress and fluid pressure; the lift force calculation formula is as follows: , = , Indicates lift. Let n represent the component of the normal vector n of the mesh element surface in the y-direction. This represents the component of the tangent vector t of the mesh element surface in the y-direction; The step of determining the drag and lift forces experienced by the cylindrical structure in the flow field based on the smooth displacement gradient includes: The displacement gradient of the solid element is obtained by solving the smooth displacement gradient. The second type of Piola-Kirchhoff stress is obtained by solving the formula for calculating the second type of Piola-Kirchhoff stress based on the displacement gradient of the solid element; the second type of Piola-Kirchhoff stress is as follows: ,in, , , This represents the second type of Piola-Kirchhoff stress. Represents a unit tensor. Represents the displacement gradient of a solid element; Based on the second type of Piola-Kirchhoff stress and the displacement gradient of the solid element, the calculation formula for the first type of Piola-Kirchhoff stress is solved to obtain the first type of Piola-Kirchhoff stress; the calculation formula for the first type of Piola-Kirchhoff stress is as follows: , This represents the first type of Piola-Kirchhoff stress. This represents the second type of Piola-Kirchhoff stress; Based on the first type of Piola-Kirchhoff stress, the resultant force of drag and lift is obtained by solving the drag-lift resultant force formula; the drag-lift resultant force formula is as follows: , This represents the resultant force of drag and lift. Represents the density of a solid. This represents the acceleration of a particle within a solid domain. Represents the divergence operator; Based on the resultant force of drag and lift, the drag and lift can be calculated by reverse deduction.

5. A method for determining a vortex-induced vibration suppression scheme for a cylindrical structure, characterized in that, include: For each first target parameter in the preset first target parameter set, the first target parameter is used as the first preset parameter, and the drag and lift corresponding to the first target parameter are determined by using the vortex-induced vibration simulation method for cylindrical structures as described in any one of claims 2-4; the first preset parameter is a preset length or a preset distance; when the first preset parameter is a preset length, the first target parameter is a target length; when the first preset parameter is a preset distance, the first target parameter is a target distance; the first target parameter in the first target parameter set is selected from a preset range. For each first target parameter in the preset first target parameter set, the vortex-induced vibration parameter corresponding to the first target parameter is determined according to the drag and lift corresponding to the first target parameter; the vortex-induced vibration parameter is used to characterize the severity of vortex-induced vibration of the cylindrical structure. Based on the vortex-induced vibration parameters corresponding to each first target parameter, the optimal first target parameter within a preset range corresponding to the first target parameter set is determined; the suppression scheme includes the optimal first target parameter.

6. The method for determining the vortex-induced vibration suppression scheme for a cylindrical structure according to claim 5, characterized in that, After determining the optimal first target parameters within a preset range corresponding to the set of first target parameters based on the vortex-induced vibration parameters corresponding to each first target parameter, the process includes: For each second target parameter in the preset second target parameter set, the second target parameter is used as the second preset parameter, and the optimal first target parameter is used as the first preset parameter. The vortex-induced vibration simulation method for cylindrical structures described in any one of claims 2-5 is used to determine the drag and lift corresponding to the second target parameter. When the first preset parameter is a preset length, the second preset parameter is a preset distance. When the first preset parameter is a preset distance, the second preset parameter is a preset length. The second target parameters in the second target parameter set are selected from a preset range. For each second target parameter in the preset set of second target parameters, the vortex-induced vibration parameters corresponding to the second target parameters are determined according to the drag and lift corresponding to the second target parameters. Based on the vortex-induced vibration parameters corresponding to each second target parameter, the optimal second target parameter within a preset range corresponding to the set of second target parameters is determined; the suppression scheme includes the optimal second target parameter.

7. The method for determining the vortex-induced vibration suppression scheme for a cylindrical structure according to claim 5, characterized in that, The vortex-induced vibration parameters include at least one of the following: Strouhal number, drag coefficient, lift coefficient, and fluctuation amplitude of lift coefficient. Determining the vortex-induced vibration parameters corresponding to the first target parameter based on the drag and lift corresponding to the first target parameter includes the following: When the vortex-induced vibration parameters include the Strouhal number, the Strouhal number is calculated using the Strouhal number calculation formula; wherein the Strouhal number calculation formula is as follows: , Representing the Strauhal number, Indicates the resistance ratio, and , H represents the diameter of the cylindrical structure, and H represents the height of the fluid domain. This represents the average flow velocity at the velocity inlet of the fluid domain. The vortex frequency represents the flow around a cylinder. When the vortex-induced vibration parameters include a drag coefficient, the drag coefficient is calculated using the drag coefficient calculation formula based on the drag corresponding to the first target parameter; the drag coefficient calculation formula is as follows: , Indicates the drag coefficient. This represents the resistance corresponding to the first target parameter. Indicates fluid density, This represents the thickness of the fluid domain in the Z direction; When the vortex-induced vibration parameters include the lift coefficient, the lift coefficient is calculated using the lift coefficient calculation formula based on the lift corresponding to the first target parameter; the lift coefficient calculation formula is as follows: , Indicates the lift coefficient. This represents the lift force corresponding to the first target parameter; When the vortex-induced vibration parameters include the fluctuation amplitude of the lift coefficient, the difference between the maximum value and the minimum value of the lift coefficient within a preset time period is determined as the fluctuation amplitude of the lift coefficient.

8. The method for determining the vortex-induced vibration suppression scheme for a cylindrical structure according to claim 5, characterized in that, The step of determining the optimal first target parameter within a preset range corresponding to the first target parameter set based on the vortex-induced vibration parameters corresponding to each first target parameter includes: When the vortex-induced vibration parameters include multiple vortex-induced vibration parameters, for each vortex-induced vibration parameter, a smooth interpolation analysis method is used to construct a continuous response curve function between the first target parameter and the vortex-induced vibration parameter based on the vortex-induced vibration parameter corresponding to each first target parameter; a preset multi-objective optimization decision strategy is used to comprehensively analyze the continuous response curve functions of multiple vortex-induced vibration parameters to determine the optimal first target parameter within a preset range corresponding to the first target parameter set, which minimizes the overall continuous response curve function of the multiple vortex-induced vibration parameters; When the vortex-induced vibration parameters include a single vortex-induced vibration parameter, a continuous response curve function between the first target parameter and the vortex-induced vibration parameter is constructed using a smooth interpolation analysis method based on the vortex-induced vibration parameters corresponding to each first target parameter; the value that minimizes the continuous response curve function within a preset range corresponding to the set of first target parameters is determined as the optimal first target parameter.

9. A cylindrical structure vortex-induced vibration suppression device, comprising a cylindrical structure of a spacecraft, characterized in that, A partition plate is provided on the downstream side of the cylindrical structure; the relative length and relative distance of the partition plate are determined by the method for determining the vortex-induced vibration suppression scheme of the cylindrical structure according to any one of claims 5-8, wherein the relative length is the ratio of the length of the partition plate to the diameter of the cylinder of the cylindrical structure, and the relative distance is the ratio of the interval distance between the partition plate and the cylindrical structure to the diameter of the cylinder of the cylindrical structure.

Images