43 results about "Performance design" patented technology

The invention relates to the technical field of sliding bearing design in mechanical engineering, in particular to a sliding bearing multi-mode end-to-end intelligent design system based on a large model. Comprising a multi-modal input and feature recognition module, a high-fidelity performance prediction module, a structural parameter intelligent optimization decision module and a parametric modeling and multi-modal output module which are connected in sequence and form an intelligent design closed loop, and all the modules are seamlessly connected through data interfaces. According to the method, multi-modal input and a high-fidelity simulation closed loop are driven through a large language model, the sliding bearing design efficiency is remarkably improved, the technical threshold is greatly reduced, interaction between a natural language and a drawing is supported, and non-experts can complete high-performance design; full-process automation from requirements to drawings is achieved, and manual intervention errors are avoided; optimizing in a wide-area parameter space by using the large model reasoning capability to realize multi-target global optimization; and multi-modal input and output of texts, drawings and models are supported, and the engineering applicability is enhanced.

The invention relates to the technical field of building structure engineering, in particular to a partition wall structure integrated refined modeling and simulation method based on physical reality. A complete and closed technical chain from refined physical modeling to connection and failure linkage algorithm definition and then to whole-process nonlinear simulation to finally realize automatic multi-target parameter optimization is constructed, and'work-damage-failure-influence 'full-life-cycle behaviors of a partition wall subsystem are subjected to full-process nonlinear simulation, so that the whole-life-cycle behavior of the partition wall subsystem is optimized. A rigorous mathematical model and a numerical algorithm are integrated into the performance design of the whole structure, a special design system which is highly innovative, computable and verifiable is formed, and therefore quantitative and performance design of the damping connection structure is completed. By introducing a series of mathematical models, criteria and linkage algorithms with clear physical significance, the black box experience of traditional'cycle reduction coefficient 'is improved.

The invention relates to the field of digital twinning modeling methods for key parts of wind power generation equipment, in particular to construction of a digital twinning model of a sliding bearing of a gearbox of a wind power generator based on multi-physics field coupling, comprising the following steps: S1, establishing a laser cladding manufacturing sub-model; s2, establishing a mixed bomb flow pressure lubrication sub-model; s3, establishing a wear sub-model; s4, constructing a sliding bearing design-manufacturing-operation digital twinborn model based on a multi-physics field theory, and performing model calibration by utilizing actual measurement data of an experiment table; according to the method, the digital twinborn model for the sliding bearing of the wind power gear box is finally established by constructing the digital twinborn model of'design-manufacturing-operation 'and accurately calibrating the digital twinborn model, and theoretical support and optimization guidance are provided for high-performance design and manufacturing of the sliding bearing of a wind turbine generator.

The present application belongs to the technical field of flexible robots, and relates to a structure optimization method of a fin ray effect gripper, comprising the following steps: step 1: a co-rotation modeling method is used to construct a force-deformation relationship model of the fin ray effect gripper as a fast evaluation model of the performance of the gripper; step 2: structure optimization design parameters and multi-objective performance evaluation indexes of the fin ray effect gripper are determined; step 3: based on a Bayesian optimization algorithm, the fast evaluation model is combined to construct a multi-objective structure optimization framework, global optimal sample search is performed on the design parameters, and a Pareto front is solved; and step 4: experimental verification is performed on typical optimal parameter combinations in the Pareto front, and optimal structure parameters of the gripper suitable for different gripping scenes are output. The present application can be applied to the design and optimization of flexible, rigid and rigid-flexible hybrid robot compliant mechanisms, and can be widely applied to the high-performance design and parameter tuning of gripper structures in industrial gripping, service robots, precision operation and the like.

This invention discloses a robust design method for gas turbine performance based on multi-source stochastic response coordination, relating to the field of gas turbine performance design. The method sequentially performs three types of stochastic influence analysis: design model, manufacturing, and usage process, constructing probability density functions for core performance parameters respectively. Based on the task phase, it determines the risk levels and weights of various stochastic factors, fusing them to generate a comprehensive probability density function. With the goal of minimizing the dispersion and optimizing the expected value of the comprehensive probability density function, it combines the constraints of component thermodynamic state parameters to solve the optimization model, obtaining the optimal combination of performance parameters. This invention achieves multi-source stochastic coordinated quantification and characterization, improving the robustness of gas turbine performance, solving the problems of conservative design and poor adaptability to operating conditions in traditional methods, and enhancing its operational safety and reliability.

The application belongs to the field of aircraft structure dynamic strength design, and particularly relates to a dynamic load static equivalent coefficient determination method and a structure parameter design method, which comprises the following steps: S1: according to a water ditching dynamic load measurement test, a relationship curve between a water pressure load of a bottom of an aircraft fuselage and a time history is obtained, and a peak value Ps of the water pressure load is determined according to the relationship curve; S2: a water ditching test of an elastic model of the bottom of the fuselage is performed to determine a critical failure parameter of the elastic structure; S3: a static mechanical property test is performed with the critical failure parameter of the elastic structure to obtain a maximum static pressure Pd that can be borne by the elastic structure; and S4: a water ditching dynamic load static equivalent coefficient is calculated. The static equivalent coefficient of the water ditching water pressure dynamic load is obtained through a scale model test. The application aims to solve the problem of lacking of design load in aircraft water ditching performance design.

The invention belongs to the technical field of aircraft performance design, and particularly relates to a method and system for designing a maximum voyage cruise mode of a subsonic aircraft, and the method comprises the steps: firstly obtaining a lift coefficient of maximum voyage cruise based on the characteristics of cruise performance and a lift-drag ratio rule at a given speed; then, the Mach number of maximum-voyage cruise is obtained based on the law of aerodynamic characteristics and oil consumption characteristics; and finally, the cruise weight and the atmosphere model are introduced to obtain the optimal cruise height of the maximum voyage cruise, so that the change strategy of the cruise height of the aircraft under different weight conditions is obtained. According to the scheme, the cruise factor is used as an analysis tool, and the maximum voyage cruise modes, including the cruise height, the cruise speed and the lift coefficient, of the subsonic jet aircraft under different weight conditions are constructed. In the model construction process, the method fully considers the balance between the precision requirement of data and the calculation complexity, so that the accuracy of the result is ensured, and the excessive complex calculation process is avoided.

This invention discloses a method and system for optimizing the slag discharge design of a vertical shaft cutting head slag bin, belonging to the technical field of underground coal mine transportation equipment. The method is based on a Python script framework and includes an automatic modeling module, an automatic simulation module, and a data analysis and parameter optimization module. The automatic modeling module performs model verification and efficient automatic modeling of the slag bin structure; the automatic simulation module automatically performs mesh generation and boundary configuration on the modeling results and calls simulation software to run multiphysics simulations; the data analysis and parameter optimization module captures the slag discharge indicators of interest from the simulation results and calculates the slag discharge performance of the model, introducing a Bayesian optimization model for iterative optimization, achieving convergence of the structural parameters of the slag bin structure to the optimal structural parameters with the fewest simulations. This invention features high integration and strong automation, constructs a closed-loop optimization mechanism, breaks through the bottlenecks of existing design processes, and improves the efficiency and quality of structural performance design.

The invention provides a simplified design system for a damping structure. Non-damping structure data calculated through a vibration mode decomposition reaction spectrum method can be obtained through a data importing and preprocessing module; performing calculation and CQC correction on a displacement spectrum according to the obtained acceleration response spectrum through an anti-seismic standard response spectrum calculation module to obtain a displacement spectrum corresponding to the equivalent single-degree-of-freedom system; the performance curve generation module is used for generating a performance curve graph of the system ductility coefficient relative to the rigidity ratio, identifying an optimal performance design point, and generating a damper design scheme according to the number of dampers in each layer; the parameters of the damper are calculated layer by layer according to a preset additional rigidity distribution strategy through a multi-degree-of-freedom system design module, and the matching degree of the deformation capacity of the damper and the interlayer displacement angle requirement is verified; and parameter output and visual display of each layer of damper are realized through a result output and visual module, so that rapid estimation of damper parameters is realized, and preliminary design of a damping structure is completed.

The present application belongs to the technical field of badminton racket, and particularly relates to a badminton racket rod structure and a production process thereof. The present application adopts a combination scheme of a radial three-layer differentiated composite structure and an axial gradient performance design. From inside to outside in the radial direction, a reinforcing framework layer, a middle functional layer and an outer reinforcing layer are arranged, and each layer respectively undertakes the core functions of torsion resistance and shock absorption, rigid and tough balance and rigid enhancement. Different weaves and ply angle designs are matched to realize performance partition customization of different regions of the racket rod, so that the contradiction that rigidity and shock resistance cannot be considered together is solved.

This invention relates to the field of mechanical structure design technology, and in particular to a design method for a ring-shaped braking mechanism. The method includes: using the physical structure of the ring-shaped braking mechanism as a design reference, setting an initial radial clearance matching the design operating conditions, and collecting measured data of the design benchmark throughout the entire process of assembly locking, clearance elimination, and braking operation; establishing an auxiliary design verification method adapted to brake performance design verification and adapting and debugging the auxiliary design verification method; loading in stages according to the actual working sequence, collecting relevant data of the auxiliary design verification, and performing closed-loop iterative verification with the measured data of the design benchmark to finally obtain the finalized design scheme of the ring-shaped braking mechanism. This invention effectively solves the technical problems of long cycle and high cost in traditional design modes, and insufficient accuracy and large deviation in design results of conventional auxiliary design methods, achieving high-precision and efficient design, and providing reliable support for the research, development, design, and engineering verification of ring-shaped braking mechanisms.

The invention relates to a high-pressure heater for an electric vehicle and a performance design method and a performance test method, the high-pressure heater comprises long wave turbulence ribs and short wave turbulence ribs, and a slope-shaped area with a gradually-reduced sectional area is arranged in a water channel of the high-pressure heater so as to increase the water flow speed. According to the high-pressure heater performance design method, target parameters are determined according to performance design indexes, an optimization thought is provided for structural design of the high-pressure heater, and the method comprises performance definition of the high-pressure heater, acquisition of input parameters and calculation of heat efficiency. The high-pressure heater performance test method comprises the following steps: building a test bench; setting parameters; connecting low-voltage communication control equipment; recording data by using an upper computer and Tsmaster software; and outputting a heater product performance report. The invention has the following positive effects: the cooling liquid is promoted to turn continuously, uniform heating is realized, and the heat conduction effect of a heat source is enhanced; the design of the heater product is guided and optimized, and the performance test method can accurately output specific performance parameters of the heater product.

The invention relates to an optical cable flame-retardant performance design method and a flame-retardant gas-blowing micro cable, the optical cable flame-retardant performance design method adopts a layer-stranded full-dry structure, the core is that the overall flame-retardant performance of an optical cable is ensured through a quantitative model, and the model comprehensively considers each element of the optical cable. The number and the size of the outer sheath, the loose tube, the central reinforcing piece and the like and the key performance index of the used flame-retardant material are improved. Meanwhile, the mechanical rigidity of the optical cable is optimized by setting the lower limit of the load ratio of the central reinforcer. According to the method, a whole set of quantitative design criteria from performance prediction, structural design to rigid control is provided for the flame-retardant gas-blowing micro-cable for the first time, the design process is converted from experience-dependent trial and error into predictable and optimizable accurate calculation, the industrial problem that high flame-retardant performance and excellent gas-blowing laying performance are difficult to consider at the same time is fundamentally solved, and the method is suitable for popularization and application of the flame-retardant gas-blowing micro-cable. And a series of products meeting requirements of different grades can be guided to be developed.

This invention relates to a multi-performance coordinated design method for planetary roller screws, belonging to the field of planetary roller screw technology. It includes the following steps: Step 1, establishing a calculation model for the thread engagement point slip ratio and maximum von Mises stress based on the kinematics and load distribution model of the planetary roller screw; Step 2, establishing equal and unequal structural constraints based on the correct meshing, non-interference, and contact boundary conditions of the planetary roller screw; Step 3, establishing a multi-performance optimization design model for the planetary roller screw based on the optimization objective and constraints; Step 4, using a multi-objective genetic algorithm to solve the multi-performance design model of the planetary roller screw, obtaining the Pareto front and corresponding structural design parameters; Step 5, obtaining the Pareto front range that satisfies the given limit trade-off cost. Based on the Euclidean norm and minimizing the dimensionless distance, the optimal trade-off solution and corresponding structural design parameters are obtained.

The invention belongs to the technical field of aircraft performance design, and particularly relates to a load range model research method for a transport aircraft, which comprises the following steps of: firstly, constructing a weight parameter model for aircraft load range evaluation by combining a typical mission profile according to the maximum takeoff weight of a transport aircraft and aircraft weight statistical data; then developing a flight distance performance model for load range evaluation based on the specific range parameter of each task section of the transport plane; and finally, inputting data of different load conditions of the transport aircraft by taking the load voyage calculation model as a carrier, and calculating a corresponding voyage result and an operation efficiency result. In this way, construction of a transport aircraft load range model and evaluation of a load range result are achieved. Through an overall weight model, a mission profile model and a flight performance model of the transport aircraft, a set of mathematical relationship between key design parameters and core capability indexes of the transport aircraft is established, and the mathematical relationship is used for evaluating voyage and operation efficiency results under different load conditions. The method is visual and clear, and the calculation process is convenient.

The invention belongs to the field of aircrafts, in particular to a disposable load transportation unmanned aerial vehicle, and aims at solving the problem that the existing transportation unmanned aerial vehicle technology lacks overall and performance design under the low-cost and assembly condition in a war area environment, the following scheme is provided: the disposable load transportation unmanned aerial vehicle comprises a fuselage, an equipment cabin is arranged in the fuselage, and a power system is arranged at the head of the fuselage; the power system comprises a propeller arranged at the head of the fuselage, and a direct-current brushless motor used for driving the propeller to rotate is arranged in the fuselage. According to the unmanned aerial vehicle, low-cost materials and foldable design are adopted, the manufacturing, transporting and deploying cost is reduced, the unmanned aerial vehicle becomes an economical and efficient choice, the system design is simple, and the unmanned aerial vehicle is suitable for popularization and application. Operators can quickly assemble in a war area, the time and labor cost is reduced, the response speed is increased, the propelling module and the flight control module can be repeatedly used, the maintainability and economical efficiency of the system are improved, and meanwhile resource waste is reduced.

The invention discloses an airfoil profile stability optimization method and system for inhibiting transonic buffeting, and relates to the technical field of aircraft safety. According to the method, the geometric morphology of the airfoil profile is accurately described through CST parameterization, the grid quality and the calculation precision after the airfoil profile is deformed are guaranteed by combining the radial basis function dynamic grid technology, the flow stability is quantified by relying on the pre-solution gain, efficient iteration is conducted through the nonlinear conjugate gradient method, transonic buffeting can be remarkably restrained, and the flow stability can be remarkably improved; and the aerodynamic performance can be optimized on the premise that engineering constraints such as no reduction of the airfoil thickness and no reduction of the lift force are met, experience trial and error and violent search of traditional optimization are avoided, the efficiency and reliability of transonic airfoil design are greatly improved, and the method is suitable for high-performance design requirements of core components such as aerospace vehicle airfoils.

The invention relates to a multi-performance coordination design method for a planetary roller screw, and belongs to the technical field of planetary roller screws. Comprising the following steps: step 1, based on planetary roller screw kinematics and a load distribution model, establishing a thread meshing point sliding-rolling ratio and maximum von * Mises stress calculation model; step 2, establishing equality and inequality structure constraint conditions according to the conditions of correct meshing, structure non-interference and contact boundary of the planetary roller screw; 3, according to the optimization target and the constraint condition, establishing a planetary roller screw multi-performance optimization design model; step 4, solving the planetary roller screw multi-performance design model by adopting a multi-objective genetic algorithm to obtain a Pareto frontier and corresponding structural design parameters; and step 4, obtaining a Pareto frontier range meeting the limit tradeoff cost according to the given limit tradeoff cost. And based on the Euclidean norm and minimizing the dimensionless distance, obtaining an optimal tradeoff solution and corresponding structural design parameters.

The invention relates to a control method, in particular to a motor adaptive preset performance asymptotic control method based on RISE. According to the characteristics of the motor position servo system, a motor position servo system model is established; according to the RISE-based motor preset performance adaptive asymptotic controller designed by the invention, unmodeled interference is suppressed by using a robust error symbol integral strategy, and system position parameters are estimated by using the adaptive controller, so that the problems of uncertain nonlinearity and uncertain parameters of a motor servo system can be effectively solved, and the motor preset performance adaptive asymptotic controller has the advantages of high reliability and high reliability. And a controller is designed by fusing a preset performance function, and finally, the overall stability of the system is illustrated through proving. Under the interference condition, the parameter convergence is good, and the system control precision meets the performance index; the design of the controller is simplified, and a simulation result shows the effectiveness of the method.

The invention provides a vehicle component performance design optimization method and device, equipment and a program product, and relates to the technical field of vehicles, and the method comprises the steps: obtaining a parameterized component finite element model established based on target model parameters related to static stiffness in a component, carrying out geometric kinematics and elastic kinematics performance analysis on the parameterized component finite element model to obtain geometric kinematics and elastic kinematics performance parameters of the component; performing static stiffness analysis on the parameterized component finite element model to obtain first static stiffness; according to geometric kinematics and elastic kinematics performance parameters, the first static stiffness is corrected, the corrected static stiffness is made to be more suitable for the actual working condition, and therefore component structure design is assisted; according to the method, the first static stiffness is corrected, screening of target model parameters related to the static stiffness, geometric kinematics and elastic kinematics performance analysis are carried out, automatic execution can be conveniently carried out by utilizing artificial intelligence, and the rigidity of the vehicle component is automatically corrected.

The application discloses a kind of mesh antenna electric performance weighting's form finding optimization method, comprising the following steps;Step (1): input the initial structure parameters of antenna and electric parameters in optimization model;Step (2): according to the initial force density input, solve mechanical model, obtain corresponding cable net node coordinates;Step (3): according to the aperture field distribution function of mesh reflector antenna, generate weighting function;Step (4): generate sensitivity matrix and vector;Step (5): find the optimal force density increment that meets the constraint condition;Step (6): when the solution accuracy of quadratic programming does not meet the requirement, one-dimensional line search is carried out, and the step length of next iteration is found;Step (7): update mechanical model, obtain next iteration value;Step (8): judge whether to meet convergence condition;Step (9): output force density design variable.The application improves calculation efficiency, effectively reduces antenna structure design and electric performance design iteration cycle time.

The invention discloses a method and a system for designing parameters of a shell type transformer, and relates to the technical field of electrical engineering, and the method focuses on three core targets of minimizing total loss, maximizing efficiency and minimizing volume. Key design parameters such as the thickness of an iron core lamination, the diameter of an iron core column, the number of turns of a high-voltage winding, the number of turns of a low-voltage winding, the sectional area of a high-voltage wire and the sectional area of a low-voltage wire can cover the requirements for operation economy, energy conversion efficiency and installation space of the shell type transformer, and multi-target balance of loss, efficiency and size is achieved; secondly, optimizing is achieved based on an NSGA-II algorithm, the diversity and reliability of an optimal solution can be guaranteed, and the problem that traditional leakage magnetic field calculation precision is insufficient is solved; the finite element method FEM of the shell-type transformer is established based on the finite element method, a leakage magnetic field simulation calculation result during normal operation can be obtained, and theoretical support and engineering reference are provided for subsequent high-performance design of the shell-type transformer.

The invention discloses a turbine characteristic calculation method for aero-engine overall performance high-precision design, and the method comprises the steps: capturing turbine performance demands and boundary constraints through an overall demand input interface, and forming a one-dimensional evaluation reference; then, a one-dimensional turbine parameterization model containing key optimizable parameters is established; then, pure one-dimensional optimization design is carried out, and optimal structure parameters are output; introducing a loss correction model to carry out all-condition characteristic calculation to obtain available characteristic data; and finally, outputting a result as required and establishing a rapid iteration adaptation mechanism. According to the method, a one-dimensional method is adopted to construct turbine optimization design and characteristic calculation integrated evaluation logic, and the technical effects of three progressive levels are achieved: firstly, seamless joint of turbine characteristic evaluation and an overall one-dimensional design process is completed; secondly, the evaluation precision of turbine characteristics in the overall design stage is remarkably improved; finally, the accuracy and iteration efficiency of the overall performance design of the aero-engine are guaranteed.

The application belongs to the technical field of aircraft performance design, and particularly relates to a method for designing an aircraft vertical flight path based on dynamic programming. First, fixed tasks are determined by sorting the scenes of the entire flight task, the approximate form of the entire vertical flight path is constructed according to the order, and the entire vertical flight path is decomposed into multiple local vertical flight paths. Then, the cruising altitude and the flight weight are marked, each flight process is divided into multiple stages through the change of the weight. The flight altitude of the aircraft at the beginning of each stage is set as a state, and the state is related to the flight segment. The flight altitude of the aircraft at the beginning of each stage is set as a state, and the state is related to the flight segment: the state value increases for climbing, the value is unchanged for cruising flight, and the value decreases for descending. In this way, the task process is processed into a multi-stage decision problem, and the method of dynamic programming is used to process the optimization problem of the vertical flight path.

The invention relates to the technical field of aero-engine performance simulation, and discloses an aero-engine overall performance simulation method and system based on a volume architecture, and the method comprises the steps: obtaining an initial working state of an engine through random initial assignment of undetermined state parameters of all parts of the engine; judging whether the engine overall matching error of the simulation model meets the condition of switching to the Newton-Raphson method or not; and if not, calculating the volume effect in the component by the reverse flow path, updating the working state of the component to ensure that the state of the overall performance simulation model of the engine is close to the convergent steady-state working point, and then switching to a classical Newton-Raphson solving method to realize model state convergence. According to the method, the problems of high initial value dependence, poor convergence and low convergence rate when a traditional Newton-Raphson solving method faces a complex-configuration engine simulation model with high nonlinearity are effectively solved, and the overall performance design evaluation requirements of various aero-engines can be met.

The invention discloses a turbofan engine aerodynamic thermodynamic cycle parameter and flow path geometric parameter coupling design method which is applied to the technical field of aero-engines. Comprising the following steps that total circulation parameters and initial constant value parameters of an engine are given, a fan pressure ratio initial guess value serves as a trial feeding amount, and the compressor pressure ratio is obtained through a given total supercharge ratio. Iterative design point calculation is carried out according to the overall circulation parameters, the initial constant value parameters, the fan pressure ratio and the air compressor supercharge ratio, compression system parameter calculation and turbine system parameter calculation are carried out according to a component coupling graph, and the iterative process is repeated until the total pressure difference of two air flows at an inlet of the mixing chamber is smaller than a given residual error. The method is high in universality, can guarantee certain precision, is suitable for the initial stage of overall performance design, can effectively avoid the subversive iteration in the later stage, and facilitates the shortening of the design period.

The present application relates to a kind of subsonic ramjet engine unsteady state performance estimation method, including the step of calculating and determining the design point parameter of ramjet engine inlet, transition section, combustion chamber and tail nozzle;According to the flow balance relationship of design point parameter and inlet and tail nozzle, the step of calculating and determining the non-design point of ramjet engine inlet, transition section, combustion chamber and tail nozzle;Establish actual inlet operating point beta residual equation step;Actual inlet operating point beta is obtained in the whole unsteady process point iteration, obtains the actual thrust Fn of engine 实 , finally obtains the unsteady state thrust curve of engine considering volume effect.The present application can accurately and quickly calculate the thrust of subsonic ramjet engine under unsteady state condition when carrying out subsonic ramjet engine unsteady state performance design, can shorten the design iteration cycle of overall design personnel when carrying out subsonic ramjet engine overall design, and guide component design personnel to carry out detailed design.

This invention relates to the field of ship design technology and discloses a rudder system optimization design method based on nonprobabilistic reliability theory, comprising the following steps: S1: Determine the mechanical performance design values ​​of key components of the rudder system based on nonprobabilistic reliability indices, conduct parameter sensitivity analysis to determine the sensitive variables affecting the rudder stock torque, construct a parameterized model library, and generate a sample space through automated simulation scripts; S2: Call the parameterized model library to generate a three-dimensional model, perform finite element calculations of the rudder-propeller combination, simulate the hydrodynamic performance of the rudder system under different rudder angle conditions, and compare and analyze the results with reference data and standard calculations. By integrating nonprobabilistic reliability theory and comparing nonprobabilistic reliability indices and convex set models, parameter uncertainties are effectively handled, the reliability of the rudder system design is improved, and the optimization ideas of portal frame structures are used to reduce design constraints and improve efficiency.

The invention discloses an optimized preparation method and system for an outer shielding material of a polypropylene cable, and relates to the technical field of functional preparation and optimization of the outer shielding material of the polypropylene cable, and the optimized preparation method comprises the following steps: obtaining performance data of a target material, generating a performance design constraint set, and screening a conductive phase type; according to the type of the conductive phase, constructing a spatial distribution topology of the conductive phase in the polypropylene matrix, forming a conductive network topology, and outputting spatial distribution; according to the conductive phase type and the spatial distribution, determining an interface regulation and control mode and outputting interface regulation and control data; according to the conductive network topology and the interface regulation and control data, determining the spatial distribution characteristics of the flexible connection structure for dispersing the stress, and forming a stress buffer layout; performing electric field simulation according to the spatial distribution of the conductive phase, the interface regulation and control data and the stress buffer layout, and dynamically correcting the spatial distribution of the conductive phase and the functional gradient of the outer shielding material in the thickness direction; through conductive network optimization and interface regulation and control, the problems of continuity and stress concentration of the shielding material are solved.

The invention discloses a frequency-oriented jacket repair structure and a design method, and belongs to the technical field of ocean engineering structure repair. The method aims to keep the natural vibration frequency of a repaired structure unchanged, and is characterized by comprising the following steps: firstly, establishing a dynamic model taking equivalent stiffness and equivalent mass of a restoration as variables, and reversely solving a stiffness and mass combination meeting the frequency change rate requirement; and furthermore, by actively regulating and controlling the mixing amount of the thermal expansion microspheres mixed with the grouting material and a thermal activation process, a performance lever is used, the final performance of the restoration body is accurately molded, and beneficial annular pre-tightening force is generated on a restoration interface while the light weight is realized, so that the restoration body is restored. Triple effects of repairing and reducing weight, prolonging the fatigue life and keeping the dynamic characteristic of the structure stable are synchronously achieved. According to the method, the crossing from passive repair to active performance design is realized, and the industrial problems that the additional mass is too large and the structural dynamic characteristics are easy to change in a traditional repair method are fundamentally solved.