169 results about "Reliability design" patented technology

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 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 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 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 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 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 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 provides a random point collocation method for solving global sensitivity of an augmented failure probability of a turbine blade structure, and belongs to the technical field of reliability design. Comprising the following steps: constructing an expected density function of an n-dimensional random input variable of a turbine blade structure to obtain an n-dimensional expected density function; calculating an unconditional augmentation failure probability of the turbine blade structure based on the n-dimensional expected density function and the performance function; a Gauss-Hermite integral quadrature node of the n-dimensional expected density function is determined; constructing an expected density function of (n-1)-dimensional random input variables except the i-th dimension of the turbine blade structure to obtain an (n-1)-dimensional expected density function except the i-th dimension; based on the (n-1)-dimensional expected density function and the conditional performance function, the conditional augmentation failure probability of the turbine blade structure corresponding to the Gauss-Hermite integral quadrature node is calculated; and determining the augmented failure probability global sensitivity of the turbine blade structure. According to the invention, the calculation efficiency of the global sensitivity of the augmentation failure probability of the turbine blade structure can be improved.

The invention provides a reliability index distribution method and device for a power system, and is applied to the technical field of reliability design of the power system, and the method comprises the steps: obtaining the working condition characteristics and structure information of each part of the power system; inputting the working condition characteristics of each component into a trained severity quantification model based on a gradient boosting tree model to obtain a severity score of each component; inputting the component attribute and the connection relation of each component of the power system into a trained influence degree quantification model based on a graph neural network model to obtain an influence degree score of each component; and adopting a preset optimization algorithm to determine a reliability index distribution result of the power system based on the severity score of each component and the influence degree score of each component under a target constraint. According to the invention, the reliability design efficiency and accuracy of the system can be improved.

The invention discloses a multi-chip module (MCM) interconnection reliability optimization method based on a WOA-GRNN. The method comprises the steps of MCM three-dimensional automatic modeling, load condition application, interconnection reliability WOA-GRNN modeling, and WOA-GRNN modeling result and analysis. According to the core of the method, an ANSYS parameterized language is adopted to construct a three-dimensional (3D) model and interconnection reliability analysis, a WOA-GRNN technology is adopted to quickly construct a nonlinear model of MCM input and output based on collected data, a reliability database is generated according to the nonlinear model, and key guidance is provided for MCM reliability design and analysis. The MCM interconnection reliability prediction method can greatly improve the MCM interconnection reliability prediction efficiency, further provides important reference for the layout design of the chip, and is an important measure for guaranteeing the MCM chip reliability.

The invention provides a karst tunnel excavation support pressure reliability design method based on threshold gradient. According to the method, aiming at three random variables in an HB constitutive model, firstly, center composite sampling is carried out in a standard normal space to obtain seven test points, coordinates of the test points are converted into an original parameter space, a failure threshold value of each test point is obtained through calculation by establishing a numerical model, then a secondary response surface agent model without cross terms is established, and the failure threshold value of each test point is calculated. And establishing a tunnel face support force dominant threshold function by solving a linear equation set and determining seven coefficients of the proxy model, on this basis, proposing a standard normal space target reliability isoline checking point iteration method, performing checking point iteration on a sphere with the radius being the target reliability, and updating checking points in a gradient manner by adopting the threshold function. And calculating the collapse load of the design point during iterative convergence, so that the collapse load meets the requirement of a target reliable index. According to the method, the design complexity is reduced, and the design efficiency is improved.

The invention belongs to the technical field of metallurgy, and particularly relates to a 420 MPa-grade wind power steel welded joint with the fatigue grade of DC112 and a preparation method. According to the 420 MPa grade wind power steel welded joint, under the tension-tension fatigue test condition that the stress ratio R is equal to 0.5, after 2 * 106 times of cyclic loading, the fatigue strength of the 420 MPa grade wind power steel welded joint reaches 112 MPa, and the strict requirement for the DC112 grade fatigue grade in the international standard DNV-ST-0126 is completely met. The performance index is obviously superior to the prior art level, and key technical support is provided for high-reliability design and light-weight manufacturing of a wind power tower tube structure.

The present application relates to a kind of spot I type nugget fracture failure constitutive model construction method, belong to the fracture mechanics and numerical simulation method technical field of spot welding joint.The technical scheme of the present application is: the parameter construction of constitutive model is carried out, parameter is directly used for spot welding joint related finite element simulation;Spot welding joint is bonded with uniaxial tensile fixture, and the tensile experiment of nugget fracture form is completed under tensile testing machine and the load-displacement curve and maximum load are recorded;Finite element model is constructed and tensile displacement is calculated;Convert and correct stress-displacement curve in combination with measured nugget area, solve maximum tensile stress and fracture energy, parameter is substituted into model and the precision of replacement connection mode is verified.The beneficial effects of the present application are: the accurate construction of spot I type nugget fracture failure constitutive model is realized, which provides standardized mechanical parameter support for spot welding joint structure reliability design and welding process optimization, and significantly improves the accuracy and engineering application value of finite element simulation.

The application relates to an integrated circuit electrostatic protection reliability design in the field of semiconductor technology, in particular to an H-shaped fin silicon structure ESD protection device applied to an SOI-FinFET process; a longitudinal fin silicon, a transverse fin silicon, a dielectric and a gate electrode are prepared based on an SOI substrate; the longitudinal fin silicon comprises longitudinal fin silicon one and longitudinal fin silicon two; the longitudinal fin silicon one comprises two kinds of doped regions of first and second semiconductor types, the longitudinal fin silicon two is of the second semiconductor type, the transverse fin silicon is of the second semiconductor type, the longitudinal fin silicon one, the longitudinal fin silicon two and the transverse fin silicon three jointly form an H-shaped fin silicon structure and are electrically connected, and a carrier control region is only a part of the longitudinal fin silicon one, the longitudinal fin silicon two and the transverse fin silicon; a novel ESD protection device can be implemented under the SOI-FinFET process, the device is different from a substrate under an insulating layer which must be used in the electrostatic protection technology related to the Bulk-FinFET process, and a good electrostatic protection method is provided for the SOI-FinFET process.

The invention discloses an accelerated life test device and method for an MEMS inertial device. A test board of the device is fixed on a middle bracket at the bottom in a damp-heat test box; the damp-heat test box is mounted on a cantilever of the three-axis turntable; the direct-current power supply and the signal collector are respectively connected with the test box through a low-frequency electric connector; the control computer is connected with the three-axis turntable, the damp heat test box, the direct-current power supply and the signal collector; determining the highest stress level and the multi-stress level of the test sample; determining test sample groups, and constructing a test sample multi-stress acceleration model; determining a test point and a test truncation of the test sample; setting the test device to each stress level for testing, and after a specified test interval is reached, controlling a computer to acquire performance parameters and test stress of a test sample until the step test truncation requirements are met; according to the method, the research and development period is shortened, the test cost is reduced, and a theoretical and experimental basis closer to reality is provided for reliability design and life evaluation of the device.

The invention relates to the technical field of reliability design analysis of mechanical products, in particular to a non-parametric reliability analysis method for a high-speed driving roller, which comprises the following steps of: S1, acquiring fault data of the high-speed driving roller, and combining the same fault time in the fault data into a fault time point ti; s2, calculating a risk value of each fault time point ti according to a Nelson-Aalen estimation method, and performing continuous accumulation to obtain an accumulation risk function # imgabs0 #; S3, calculating a reliability function # imgabs2 # according to the accumulation risk function # imgabs1 # to obtain reliability; s4, non-parametric reliability degree confidence evaluation based on Nelson-Aalen estimation is carried out; the problem of reliability calculation when the theoretical distribution of the fault time of the high-speed driving roller is uncertain in engineering practice can be solved.