196 results about "Reliability design" patented technology

The invention belongs to the technical field of reliability-based design optimization, and particularly relates to a reliability design optimization method combining transfer learning and a physical information neural network. Comprising the following steps: constructing a physical information neural network model by adopting training data of a source domain, and evaluating the reliability of the source domain. A physical information neural network model constructed by adopting training data of a source domain is updated by utilizing a layer freezing and fine tuning technology in transfer learning, so that the reliability of a target domain with different statistical attributes is evaluated, the calculation overhead is saved, and the calculation efficiency is improved. A first-order scoring function is utilized to carry out random sensitivity analysis on the failure probability so as to ensure normal operation of design optimization. And finally, providing estimation reliability, an objective function value and corresponding sensitivity information for an optimizer to obtain a corresponding updated design point. And repeating the iterative design process until the optimal design is realized. The training speed of the physical information neural network model is increased, and the precision of the physical information neural network model is improved.

The invention relates to the field of mechanical fatigue simulation, and discloses a method for simulating and deducing the number of torsion cycles. Comprising the steps that a component three-dimensional parameterized model is constructed, and material fatigue characteristics are defined; applying a periodic torsion load spectrum containing a harmonic component; adopting a stress influence coefficient matrix method to execute quasi-static finite element analysis, and extracting a multi-axis stress state; calculating the maximum alternating shear stress and the average shear stress based on a critical plane recognition technology; converting into a single-axis equivalent stress amplitude through a gradient enhanced multi-axis correction rule; calculating node fatigue damage by combining an S-N curve and a damage accumulation theory; and when the damage reaches a threshold value, outputting a failure cycle number and a position. The innovation points are as follows: the prediction error is controlled within 10% by a critical plane and multi-axis correction technology; a stress matrix method realizes ten thousand times of cycle-level efficient simulation, and the efficiency is improved by 10 times; the risk early warning accuracy rate is improved to 96% by integrating a process correlation defect model; and the research and development period is shortened by 40% through a life cloud picture and an automatic optimization closed loop. The method is suitable for transmission shaft system reliability design.

The invention discloses a multi-scale wear fatigue joint simulation method and system for a valve element and a valve sleeve of a servo valve, and relates to the technical field of hydraulic control. A geometric model is designed according to structural parameters of a valve structure, and the geometric model is divided into multiple assemblies; defining material parameters of each component, and correspondingly associating the material parameters with each component; defining a wear model of the contact surface of the valve core and the valve sleeve; defining a nonlinear mechanism of the fatigue model; defining a coupling model of a coupling relationship between the wear model and the fatigue model; performing grid division on the geometric model by adopting a dynamic grid updating model, and taking all grid units as simulation analysis objects; performing simulation analysis on the coupling model; according to the simulation result, the wear fatigue coupling failure behavior of the valve element and the valve sleeve is predicted, and the design of the valve element and the valve sleeve is optimized. According to the method, the submicron wear depth prediction precision can be realized, the service life prediction error is reduced compared with that of a traditional method, and a quantitative basis is provided for reliability design and condition-based maintenance of a high-precision servo valve.

The invention discloses a face gear planetary transmission system dynamic uniform load test platform and test method, and belongs to the field of gear transmission, and the test platform comprises a rack, a drive motor, a step-up gear box, a face gear planetary transmission system, a magnetic powder brake, a torque sensor, a slip ring, a stress strain test system and the like. The face gear planetary transmission system comprises an input face gear, a planet wheel, a planet carrier, a fixed face gear and the like. According to the dynamic uniform load test, stress values at the tooth root of the face gear and the tooth root of the planetary gear are measured mainly through strain gauges, and the corresponding relation between the tooth root stress and the meshing force at the gear meshing point is obtained through finite element simulation. And calculating the dynamic uniform load coefficient according to the dynamic meshing force root-mean-square values and the average values obtained at the tooth roots of the face gear and the planetary gear. By testing and analyzing the dynamic uniform load coefficient, the load distribution characteristic of the face gear planetary transmission system can be accurately revealed, a scientific basis is provided for structural parameter optimization, meshing performance improvement and reliability design of the face gear planetary transmission system, and then accurate and high-performance design of the transmission system is achieved.

The invention belongs to the field of system reliability design analysis, and particularly relates to a common cause failure parameter-based fault analysis method, which comprises the following steps: acquiring a fault tree model of an analysis object, and fusing the fault tree model with a common cause failure parameter model; constructing a fault tree model with a common cause failure parameter model; performing common cause failure analysis by using the common cause failure parameter model; expanding the constructed fault tree model with the common cause failure parameter model into an explicit expression common cause failure fault tree model by adopting a universal parameter model expansion method; solving the extended explicit expression common cause failure fault tree model to obtain a top event occurrence probability; according to the method, the implicit common cause failure parameter model is expanded into explicit expression, the automation of the reliability analysis process of the complex system considering the common cause failure influence is realized, the modeling difficulty is reduced, and the reliability analysis working efficiency is improved.

The invention discloses a mechanical part reliability digital twin model construction method and computer equipment. According to the method, a mechanical part digital twinborn model based on a failure mechanism model, a mechanical part digital twinborn model based on an empirical model, a mechanical part digital twinborn model based on a simulation model and a mechanical part digital twinborn model based on a structural performance function are constructed according to a mechanical part digital twinborn model based on a failure mechanism model, a mechanical part digital twinborn model based on an empirical model, and on the basis of the priority sequence of the mechanical part digital twinborn body models of the data model, the reliability digital twinborn body models of the mechanical parts are constructed in sequence, so that the complete mechanical part reliability digital twinborn body model can be constructed. Simulation, monitoring, diagnosis, prediction and control of reliability indexes such as failure rate, reliability, service life and residual service life of the mechanical part are achieved, reliability design analysis, test evaluation and diagnosis prediction of the mechanical part are achieved through a digital means, the product iteration upgrading period is greatly shortened, and the research, development and use cost of the mechanical part is greatly reduced.

The invention discloses a gear pair life prediction method based on dynamic stress, belongs to the technical field of reliability design of mechanical transmission systems, and aims to solve the problem of inaccurate life prediction caused by neglecting a dynamic effect and a real surface topography in an existing gear design method. The method comprises the following steps: firstly, acquiring gear pair interface mechanical property parameters considering shafting vibration, dynamic load and surface roughness, wherein the parameters comprise transient oil film pressure, friction coefficient, oil film thickness and shear stress; solving a three-dimensional subsurface stress field by adopting an algorithm and calculating von Mises equivalent stress distribution; stress volume integration is conducted on different rough surfaces, the honed surface is used as the reference, the relative fatigue life of other surfaces is calculated based on the Zaretsky life prediction theory, and accurate prediction and process optimization of the contact fatigue life are achieved; meanwhile, the dynamic bending stress of the tooth root is calculated based on the dynamic normal load, and the bending fatigue safety coefficient is checked.

The invention discloses a piezoelectric ceramic fatigue life analysis method based on macro and micro multi-scale. The method comprises the following steps: firstly, automatically establishing a microcosmic unit cell model based on a Python script, realizing automatic assignment of material parameters and application of periodic boundary conditions, and calculating microcosmic unit cell homogenization mechanical parameters; then constructing a macroscopic driver model, inputting microscopic parameters as material attributes, and performing macroscopic fatigue life prediction and damage distribution simulation in combination with a Miner linear damage accumulation theory; and finally, through macro-micro coupling analysis, transmitting the strain of the macroscopic maximum stress unit to the micro model, and researching the intergranular stress distribution characteristics and the interface damage evolution law of the piezoelectric ceramic. According to the method, a multi-scale modeling strategy is adopted, cross-scale fatigue performance prediction from the micro grain scale to the macro structure scale is achieved, and an effective means is provided for reliability design and service life evaluation of the piezoelectric ceramic driver.

The invention relates to a satellite-borne electronic hardware design guarantee method and system. The method comprises the following steps: determining a satellite-borne hardware guarantee level (SHL) of satellite-borne electronic hardware; integrating a fault mode injection FM I into a design process of satellite-borne electronic hardware, and adjusting the execution depth of the FM I based on the SHL level; and providing a process cutting engine, and realizing adaptive process cutting based on a DO-254 standard according to the SHL level and in combination with the execution depth of the FM I. The system comprises an SHL evaluation module; an FM I management module; a space environment effect knowledge base; and a process cutting engine. According to the method, the problem that the DO-254 standard is insufficient in adaptability in the aerospace field is solved, the reliability design and verification efficiency of satellite-borne electronic hardware is remarkably improved, and the method is suitable for aerospace tasks such as various satellites and deep space probes.

The invention relates to an engine component reliability modeling method based on a reliability unit, which comprises the following steps: (1) carrying out engine body external field fault statistics: carrying out statistics on aero-engine fault data, and determining a reliability index distribution object; (2) engine reliability unit division is carried out, and the reliability units have physical independence and comprise structures with large safety influences; and (3) carrying out hierarchical division and reliability modeling on the whole engine system. And (4) based on the established hierarchical division relationship of the complete engine system, carrying out reliability distribution based on a cost function from left to right. According to the method, aero-engine part reliability modeling and system reliability distribution considering reliability improvement cost can be realized, and a method basis is provided for aero-engine reliability design.

The invention relates to the technical field of integrated circuit reliability analogue simulation, in particular to an analogue simulation system and method applied to an integrated circuit. The method comprises the following steps: acquiring an integrated circuit layout and carrying out circuit topological structure datamation on the integrated circuit layout to obtain an oxide layer area grid chart; performing stress distribution mapping generation on the integrated circuit according to the oxide layer region grid chart to obtain a region stress state matrix; performing electric field-temperature collaborative analysis according to the regional stress state matrix to obtain a random fluctuation factor matrix; performing time sequence damage accumulation calculation according to the random fluctuation factor matrix to obtain a time sequence damage state set; and performing damage state feedback adjustment on the time sequence damage state set to obtain a time-varying damage evolution graph. According to the method, the fragile performance indexes and areas of the integrated circuit are identified, and the comprehensive circuit performance degradation characteristic spectrum is generated, so that a scientific basis is provided for reliability design and performance optimization of the integrated circuit.

The invention discloses a quantitative FMECA-based six-property integrated design method for a weapon station. The method comprises the following steps: step 1, carrying out system definition on the weapon station; step 2, fault mode analysis; step 3, fault reason analysis; step 4, fault influence and severity analysis; step 5, a fault detection method; step 6, design improvement and use compensation measure analysis; step 7, analyzing harmfulness; determining the scope of reliability design according to the step 7; determining the scope of maintainability design according to the steps 2 to 4; determining the scope of the supportability design according to the steps 5-6; determining the category of testability design according to the step 5; determining a security design category according to the step 2 and the step 5; and determining the scope of the environmental adaptability design according to the step 2. According to the method, quantitative FMECA analysis is firstly carried out on the weapon station, design is improved and optimized based on the quantitative FMECA analysis result, and performance and six properties are integrally and synchronously carried out.

The embodiment of the invention discloses a GBIC-based multi-electric aircraft starting power generation system DBN model lightweight method, and relates to the technical field of reliability design and modeling of an equipment complex system.The GBIC-based multi-electric aircraft starting power generation system DBN model lightweight method comprises the steps that a DBN model of a starting power generation system is established, nodes in the DBN model correspond to key components and working states of the starting power generation system, and the nodes in the DBN model correspond to the key components and the working states of the starting power generation system; directed edges in the DBN model are used for describing the mutual relation between the nodes, a redundant structure in the DBN model is recognized, lightweight processing is carried out, and the fault state of the starting power generation system is recognized through the DBN model subjected to the lightweight processing. Aiming at the problems of complex reasoning calculation and low efficiency in the use process of the dynamic Bayesian analysis method of the equipment complex polymorphic system, the grey system theory and the Bayesian information criterion are introduced, the lightweight of the dynamic Bayesian network of the complex polymorphic system is realized, the redundant structure is eliminated, and the accuracy of the result is ensured.

The invention discloses an offshore wind power structure corrosion fatigue life reliability calculation method and system considering a fan operation effect. The method comprises the steps of external load determination, structure corresponding calculation, stress time history calculation, statistical parameter calculation and reliability calculation. According to the method, the operation effect of the offshore wind power fan in the service state can be considered, the influence of load randomness, material performance randomness and corrosion degree randomness is reflected, and then the corrosion fatigue reliability analysis of the offshore wind power structure considering the operation effect of the fan is achieved. The method and the system can be used for evaluating the reliability of the residual life of the corrosion fatigue of the existing offshore wind power structure after service, and can also provide effective reference for the reliability design process of the offshore wind power structure with the corrosion fatigue problem.

The invention belongs to the technical field of electronic packaging board level interconnection, and particularly relates to a DIC-based surface-mounted component welding spot vibration strain non-contact test method and system. The testing method comprises the following steps: testing the amplitude of a welding spot by adopting a laser displacement sensor method through carrying out a vibration test, or carrying out calculation and analysis on the vibration amplitude of a welding spot area by establishing a finite element model; carrying out the type selection of telecentric / double telecentric lenses, and selecting the lens with the smallest field of view under the condition that the depth of field is close to the amplitude of the welding spot; further determining erection angles of a high-speed camera and a lens; speckles of the welding spots to be detected are manufactured; carrying out speckle quality evaluation by adopting DIC analysis software; assembling a three-dimensional strain test system, completing the setting of shooting parameters of a high-speed camera, and completing the calibration of the three-dimensional strain test system by adopting DIC analysis software; setting control parameters of a vibration table, carrying out a vibration test of the board-level assembly welding spot, and synchronously collecting a vibration image of the welding spot; and carrying out strain calculation on the welding spots under the vibration working condition by adopting DIC calculation and analysis software. According to the DIC-based non-contact test method and system for the vibration strain of the welding spot of the surface-mounted component, the strain response process of the surface-mounted welding spot can be accurately obtained, quantitative analysis and research on the vibration reliability of the welding spot are supported, and key data support is provided for reliability design of board-level interconnection products of the surface-mounted component.

The invention discloses a gear tooth surface wear prediction method based on interface characteristics, and belongs to the technical field of gears. According to the gear tooth surface wear prediction method based on the interface characteristics, the tooth surface morphology evolution is dynamically represented through the fractal theory, and the roughness change in the wear process is quantified; contact interface parameters and interface characteristics are introduced, a time-varying friction model and a translation-torsion coupling dynamic model are combined, the coupling effect of tooth surface morphology, lubricating conditions and dynamic loads is comprehensively considered, the limitation that a traditional model ignores multi-factor coupling is broken through, and a scientific basis is provided for reliability design and service life prediction of a gear system; and the method has important engineering application value.

The invention discloses a test device for evaluating the multi-dimensional service life of a high-bearing-resistance supporting rod. The device comprises a cyclic load loading device which realizes accurate loading and measurement through a loading actuator cylinder, a counter-force support and a sensor; the guide rail control device is used for simulating an actual complex motion form by utilizing a guide rail, a sliding block and a joint bearing; the abrasion checking device achieves the function of simulating abrasion at the piston end and the fixed end in an actual complex motion form; the temperature control system is used for accurately controlling the environment temperature and the working temperature by virtue of a high and low temperature environment box and a hydraulic oil temperature machine; and the MTS structure test loading system is used for controlling oil inlet and outlet of a loading actuating cylinder and a resistance supporting rod and displaying sensor data in real time. According to the invention, multi-physics coupling conditions such as cyclic load, compound wear and high and low temperature environment can be simulated through tests, the wear resistance, sealing performance, fatigue performance and overall reliability of the resistance stay bar can be comprehensively evaluated, and effective technical support is provided for life prediction and reliability design of the resistance stay bar.

The invention provides a motor stator potting structure failure risk assessment and optimization design method. The method comprises the following steps: firstly, establishing a simplified numerical calculation domain based on a potting structure, carrying out grid and time step length independence verification, carrying out parameter sensitivity analysis and experimental measurement, and establishing a high-precision thermal-mechanical coupling numerical calculation model; then, in combination with the simulation result and the temperature change constitutive characteristics of the ultimate strength of the material, a node-level failure risk calculation method is provided, failure risk indexes of different stress forms are obtained, and a weighted comprehensive failure risk evaluation standard is determined according to the contribution degree of the stress forms to failure behaviors; and finally, proposing a parameterized structure optimization scheme according to a dangerous area and a dominant failure mechanism, carrying out quantitative evaluation and optimization on the candidate scheme under a weighted comprehensive failure risk evaluation standard, and determining a final structure optimization scheme. The method has the advantages of closed flow loop and quantifiable indexes, and is suitable for reliability design and life evaluation of the motor encapsulation structure.

The invention provides an automatic weapon automaton fault criterion construction method based on design parameter association, and relates to the technical field of computer simulation. The method comprises the steps of constructing a sample matrix based on design parameter distribution and statistics of an automatic weapon, inputting the sample matrix into an automatic weapon automaton dynamics simulation model, extracting motion parameter response, and fitting the motion parameter response into a proxy model; establishing an association relationship of the design parameters, calculating the contribution degree of each design parameter based on the association relationship, and determining the design parameters of which the contribution degrees are greater than a contribution degree threshold value as key design parameters; and constructing a Bayesian network based on the key design parameters and the proxy model, further performing forward and reverse reasoning to trace the design parameters influencing the fault, obtaining a design parameter constraint range and a motion parameter constraint range, and establishing an automaton fault criterion. The method can be used for quickly positioning fault reasons, improving design parameters and further guiding automatic weapon reliability design.

The invention discloses an electronic component reliability digital design method based on multi-physics field coupling simulation, and belongs to the technical field of reliability analysis, and the method comprises the following steps: S1, obtaining a working environment index and a reliability design index of an electronic component; s2, constructing a component reliability digital evaluation model; s3, obtaining an electrical parameter and a temperature parameter of the electronic component; s4, constructing an overall reliability evaluation model for the electronic component; and S5, constructing an optimization model for the overall reliability evaluation model of the electronic component, and completing the reliability digital design of the electronic component. According to the method, the reliability of the electronic component can be accurately evaluated through multi-physical field coupling simulation and a digital evaluation technology under the condition of insufficient data, and reliability design optimization is realized under constraint conditions of other design factors; therefore, the stability and the long-term reliability of the electronic component in a complex environment are improved under a limited design condition.

The invention provides a high-temperature fatigue life prediction method based on EIFS, and relates to the technical field of reliability design. The method comprises the following steps: acquiring first test data for performing a crack propagation test and a high-cycle fatigue test on a smooth component, and second test data for performing a test on a notched component; according to the first test data and the second test data, the equivalent initial defect size of the smooth component and the equivalent initial defect size of the notched component are determined; according to the second test data, the equivalent stress strength factor difference value and the fatigue crack propagation rate of the notched component under the high-temperature condition are obtained; fitting a function relationship among the fatigue crack propagation rate, the equivalent stress strength factor difference value and the crack size to obtain a crack propagation function; and based on the crack propagation function and the equivalent initial defect size and the limit crack size of the notched component, the predicted fatigue life of the notched component under the high-temperature condition is determined. According to the invention, accurate high-temperature fatigue life prediction can be realized.

The invention discloses a service life prediction and reliability evaluation method for a DC-DC converter. The method comprises the following steps: carrying out consistency screening on test samples; determining the type and level of acceleration stress; screening pre-test and stress sensitive parameters; the implementation of the life test is accelerated; and constructing a life model and evaluating reliability. According to the method provided by the invention, by establishing the voltage-temperature dual-stress acceleration model, the degradation process of the device under the actual working condition is reflected more accurately; an analysis framework suitable for scenes containing failure data and non-failure data at the same time is provided, and point estimation and confidence intervals of parameters for reliability evaluation under the non-failure data condition can be provided; the method realizes accurate evaluation of the service life and reliability of the DC-DC converter before installation, has the characteristics of high prediction precision, high engineering practicability, wide application range and the like, can be widely applied to the field of reliability evaluation of various DC-DC converters, and provides data support for installation type selection, maintenance strategy formulation and system reliability design of devices.

The invention relates to a torque sensor failure probability function estimation method, which combines two stages of improved cross entropy important sampling ICE-IS and adaptive Kriging to carry out failure probability function estimation, in the first stage, a small number of Monte Carlo simulation MCS samples are generated in an augmented space, a performance function of a torque sensor is replaced by a Kriging model, an initial Kriging model is constructed, and the initial Kriging model is used as an initial Kriging model; an MCS sample is adopted to train the model, and an initial Kriging model after training is obtained; in the second stage, ICE-IS is executed on the Kriging model constructed in the first stage to generate candidate sample points, after sampling training, the initial Kriging model predicts the candidate sample points and calculates learning function values for training, and retraining of the Kriging model is completed; the trained Kriging model can replace a real performance function to estimate a torque sensor failure probability function. The calculation efficiency is effectively improved, and the method has important reference value and guiding significance for reliability design of the torque sensor.

The invention relates to a structure for protecting focal plane electronics to realize installation in different postures. A tool structure comprises a base installation platform, a frame installation plate, a box installation plate, an overturning fixing frame A, an overturning fixing frame B, an overturning arm and an installation plate connecting block. According to the invention, the installation deformation is controlled within a safety threshold through an integrated tool structure, the posture adjustment of a complex electronic assembly is realized, the installation efficiency is effectively improved, the damage probability of a flexible product (a flexible circuit board) is greatly reduced, and a key technical support is provided for the miniaturization and reliability design of high-density electronic equipment.

The application provides a long-distance slag conveying numerical self-adaptive control method based on CFD, relates to the technical field of slag conveying pipeline analysis, and comprises the following steps: constructing a pipeline real-time data set; generating a calculation grid; combining a mathematical model and a dynamic boundary condition to construct a CFD dynamic simulation system of a pneumatic conveying pipeline; performing solution calculation on the CFD dynamic simulation system to obtain a flow parameter distribution model in the slag conveying pipeline; performing feature extraction on the pipeline real-time data set and the flow parameter distribution model, mining the correlation between features and fault types through a weight matrix and a cross-term weight matrix, obtaining a multi-modal fault diagnosis judgment result, and generating a slag conveying pipeline self-adaptive control strategy. The technical problems that the simulation accuracy is limited, it is difficult to support high-reliability design, a multi-physical field data fusion mechanism is missing, accurate fault diagnosis cannot be achieved, dynamic self-adaptive analysis capability is lacked, and the timeliness of fault early warning and regulation strategies is insufficient in the prior art are solved.

The invention belongs to the technical field of reliability design analysis, and particularly discloses a complex system reliability distribution method based on an optimization algorithm and a fault tree model, and the method comprises the steps: building a fault tree model containing common cause failure events based on the composition and function principle of a target system and common cause events which may occur in the target system; based on preset equipment reliability data, endowing a top event occurrence probability value to the fault tree model; and based on the fault tree model, constructing a constrained optimization problem, and solving the constrained optimization problem to obtain a reliability allocation result of each device in the target system. According to the method, the reliability distribution result is closer to the actual situation, and the reliability distribution precision is improved.

The invention belongs to the technical field of satellite-borne computer high-reliability design, and particularly relates to a high-reliability satellite-borne computer master control module circuit which comprises a CPU board, an FPGA board and a watchdog circuit. Wherein the CPU board is composed of two identical CPU minimum systems, namely a CPU-A and a CPU-B, and the two CPUs are in a master-slave relationship; the FPGA board is composed of two identical FPGA minimum systems of FPGA-A and FPGA-B, and the two FPGAs are in a master-slave relation and are respectively connected with the master CPU and the slave CPU to serve as arbitration boards; and the two watchdogs are respectively connected with the master FPGA and the slave FPGA, and mutually perform state monitoring with the master FPGA and the slave FPGA.

The invention discloses a joint reliability analysis method suitable for a satellite multi-task system, which comprises the following steps: decomposing a system task into a plurality of independent sub-task units, introducing a task weight parameter Ci to quantify the importance of each sub-task, and calculating the reliability of the system through a formula RS = sigma CiRi. The model comprises a basic type and a double-layer structure, wherein the basic type is directly suitable for an independent subtask system; according to the double-layer structure, for a sub-task containing a plurality of same units, the calculation complexity is reduced by simplifying the sub-task as a single unit and simplifying the sub-task into a basic type. A reliability mathematical model reflecting task weight influence is established, the model is expanded to a double-layer structure, and an equivalent processing method is provided. The model can accurately describe the reliability of the satellite multi-load system, avoids over-design or under-design caused by a traditional model, is adaptive to systems with different complexities, provides a scientific basis for reliability distribution and prediction, and improves the accuracy and practicability of reliability design of the multi-task system.

The present invention provides a strength-based structural reliability design method, device, cab and medium, belonging to the technical field of structural reliability design. The method includes: performing static strength analysis on a measured structure subjected to at least one working condition to obtain stress results; acquiring the risk parameters and remaining life of the measured structure; determining a static strength working condition combination in the at least one working condition based on the stress results and the risk parameters; determining the strength value of the static strength working condition combination, and constructing a correlation model between the strength value and the remaining life; acquiring the target strength value of a structure to be designed, and determining the reliability of the structure to be designed based on the target strength value and the correlation model. The present invention improves the accuracy and efficiency of structural reliability design.

The invention relates to the technical field of passenger car suspension systems, in particular to a C-shaped suspension arm mounting structure which comprises a mounting seat assembly, a connecting plate assembly and an underframe beam. The chassis beam is fixedly installed on a passenger car chassis, and the installation base assembly is installed at the lower end of the chassis beam and fixed through the connecting plate assembly. And the C-shaped suspension arm is mounted on the mounting seat assembly through a bolt, so that the purpose of mounting and fixing the C-shaped suspension arm is achieved. The overall combination of the bilateral C-shaped suspension arm is considered, the mounting structure is optimized, the mounting seat assembly and the underframe beam are connected together by using a plurality of flat special-shaped connecting plates, and then the stress of the mounting seat assembly is partially dispersed upwards by using the upper cross beam and the middle cross beam, so that the structural safety is improved; and meanwhile, the reliable design of a small space structure is realized.