20 results about "Functional failure" patented technology

According to the semiconductor packaging structure and the preparation method thereof provided by the invention, the diffusion barrier layer is formed on the upper surface of the first packaging chip, and the diffusion barrier layer is only ground in the process of grinding and thinning the first packaging layer, so that a Cu metal column and the first packaging chip are prevented from being ground at the same time, and therefore, Cu metal can be prevented from remaining on the first packaging chip; therefore, the first packaging chip is prevented from being polluted by diffusion of Cu metal, and the problems of function failure, such as breakdown voltage reduction and electric leakage, of a chip sensitive to Cu caused by diffusion of Cu metal are avoided.

The invention relates to a reliability acceleration factor calculation method and device and computer equipment. The method comprises the following steps: acquiring a first test parameter of a to-be-tested electronic device in a first test environment and a second test parameter of the to-be-tested electronic device in a second test environment; the test parameters comprise function test parameters and interconnection test parameters; the environmental severity of the second test environment is higher than that of the first test environment; based on the first function test parameter, the second function test parameter and a preset physical model, determining a function failure acceleration factor of a component of the to-be-tested electronic equipment; determining an interconnection failure acceleration factor of the to-be-tested electronic equipment based on the first interconnection test parameter and the second interconnection test parameter; and calculating a reliability acceleration factor of the to-be-tested electronic equipment according to the function failure acceleration factor and the interconnection failure acceleration factor. By adopting the method, the reliability test time of the electronic equipment can be shortened.

The present disclosure relates to an aero-engine stator crack critical size comprehensive judgment method and system, belonging to the field of aviation technology, the method comprising: obtaining the typical hot end stator component geometric model of the aero-engine, material parameters, and carrying out static strength analysis for the flow-thermal-solid coupling load characteristics in the actual working condition; inserting an initial crack in the first principal stress plane of the real component dangerous position and carrying out crack propagation simulation to determine the crack propagation path and calculate the critical crack size of the dangerous point; analyzing the critical crack size under different failure modes such as cooling failure and buckling failure; integrating the analysis results under multiple failure modes to determine the comprehensive critical size as the final judgment standard. The present disclosure realizes accurate judgment of crack critical size by combining fracture failure and functional failure analysis, breaks through the limitations of traditional single fracture criterion, comprehensively analyzes functional failure, significantly improves the accuracy of maintenance decision, and provides a scientific basis for condition-based maintenance decision.

This utility model relates to a shockproof and accident-proof panel latch lock, which addresses the technical problems of existing similar products being prone to component damage, functional failure, and difficulty in pre-tightening or opening operations when applied in vibration scenarios. The key feature is that one end of the handle fork of this panel latch lock extends out or protrudes above the bottom of the panel and is equipped with a touch head. The touch head of the handle fork is aligned with the first unlocking head at the latch fork protruding from the latch assembly below. The first unlocking head is a triangular protrusion located on one side of the outer diameter of the latch fork. When the handle is rotated and lifted within the handle groove of the panel, it drives the handle fork to rotate. The touch head of the handle fork abuts against the first unlocking head at the protruding end of the latch fork, driving the latch fork inside the latch assembly to rotate. The other side protrusion of the latch fork inside the latch assembly disengages from the side groove of the protrusion on one side of the movable latch inside the latch assembly, unlocking it. When the handle drives the handle fork to rotate and lift less than 15 degrees, the handle fork to the latch fork has a free travel.

A comprehensive safety analysis system and method integrating FTA and FMEA is disclosed. The system includes an input module, a functional safety requirements management module, an FTA analysis module, a functional failure mode management module, and an FMEA analysis module. The functional failure mode management module analyzes whether each functional safety requirement has a corresponding component and removes duplicate functional safety requirements. The functional failure mode management module analyzes whether each functional safety requirement corresponds to a specific functional failure mode; if not, it adds the corresponding functional failure mode. By combining FTA and FMEA safety analysis methods, it is possible to identify unconsidered functional safety requirements or add functional failure modes, leveraging the advantages of both FTA and FMEA for a comprehensive safety analysis.

The invention provides a civil aircraft airborne equipment reliability data verification scheme selection method. Obtaining an I, II and III type function failure state list of the target system; determining the influence level of each airborne device of the target system on safety and reliability; analyzing the reliability data conformity verification method of the system airborne equipment to form a preliminary verification method list; for equipment which needs to be subjected to a necessary reliability test in the preliminary verification method list, preliminarily judging reliability test items which need to be carried out by the equipment; selecting a reliability identification test or a durability / life test according to product characteristics and fault reasons of fault modes having great influence on safety, and obtaining a preliminary reliability test item list of the system airborne equipment; and forming a test item list based on the preliminary reliability test item list of the system airborne equipment. According to the method, the problem of reliability data verification scheme selection of the civil aircraft airborne equipment can be efficiently solved.

The invention relates to the technical field of quality management, and discloses a fault tree analysis method and device, equipment and a medium, and the method comprises the steps: extracting hierarchical architecture information which comprises the function description of each hierarchical component, a non-functional failure factor and a superior-subordinate dependency relationship; determining a top event based on the hierarchical architecture information, and mapping the hierarchical architecture information into a tree analysis hierarchy; screening components related to the top event according to the function description, and identifying a bottom event from the non-functional failure factors according to a preset guide word; and determining a logic gate type between the top event and the bottom event according to the superior-subordinate dependency relationship, and upwards connecting the bottom event to the top event according to the logic gate type and the mapped tree-shaped analysis hierarchy to obtain a target fault tree containing a failure propagation path so as to obtain a fault tree analysis result according to the target fault tree. According to the technical scheme provided by the invention, the accuracy and efficiency of function security analysis can be improved.

The application discloses a failure diagnosis method of a steer-by-wire device. The working states of various functional units in the steer-by-wire device are monitored by a plurality of function monitoring sensors in a sensor network. When a failure of a functional unit is monitored, the functional unit is identified in the form of failure identification data, and the working state of the steer-by-wire device is evaluated according to a steering function failure evaluation parameter obtained from the failure identification data of the functional unit, so as to give a prompt for repairing or maintaining the steer-by-wire device. The failure identification data of the functional unit is obtained according to a unique mass value of each function monitoring sensor that discovers the failure. The failure identification data can not only identify the failure state of each functional unit of the steer-by-wire device, but also identify the failure position, so that the failure identification mode is greatly simplified, and the failure position of the function unit with a redundant design can be accurately identified.

The invention discloses a fuse storage circuit and a fault detection method thereof, and two detection paths are added on the basis of an original branch of a storage unit. In a normal working mode, the two detection paths are in a turn-off state, and the normal read-write function of an original circuit is not affected. When the circuit has a function failure and needs fault detection, the fault position is quickly positioned by selectively conducting the detection path, so that the fault detection efficiency is improved.

This invention discloses a method and system for diagnosing temperature compensation faults in inertial measurement units (IMUs). The method achieves highly reliable fault detection by introducing a redundant temperature source T2 and a functional safety-oriented diagnostic logic. Instead of directly comparing temperature signals, the method substitutes the primary temperature T1 and the redundant temperature T2 into the IMU error compensation model to calculate two sets of compensation results B. compT1 and B compT2 The difference between residual offset Only if the difference is residual offset A functional failure is only identified when the threshold is exceeded by reverse engineering based on application safety requirements. This method effectively solves the shortcomings of traditional diagnostic methods, such as high cost, cold start failure, and high false alarm rate, and meets functional safety requirements.

This invention belongs to the field of safety and reliability of complex equipment, and relates to a method and system for rapidly determining key safety items of complex equipment. The method includes the following steps: Step 1: For complex equipment, based on the system safety assessment report of each system of the complex equipment, and after a system-wide safety assessment of the complex equipment, obtain n fault trees with functional failure states as top events and their critical importance of bottom events; Step 2: Calculate the critical importance factor; Step 3: Multiply the critical importance of the bottom events of the n fault trees by the critical importance factor, and sum the products of the critical importance of the same type of bottom events and the critical importance factor to obtain the final critical importance; Step 4: Sort the final critical importance of each bottom event, and focus on improving and monitoring the set of bottom events corresponding to the top final critical importance. This set of bottom events is the corresponding list of key safety items.

The application relates to an aero-engine system testability design and evaluation method and device, and relates to the engine technical field.The method comprises the following steps: acquiring a requirement document and a function to-be-tested item list of an aero-engine; performing requirement decomposition according to the requirement document and the function to-be-tested item list, acquiring a function failure mode, influence and hazard analysis report and a function design report; performing implementation through component design according to the function design report, and acquiring a hardware failure mode, influence and hazard analysis report; and performing integrated and verified testability evaluation according to the function failure mode, influence and hazard analysis report, the hardware failure mode, influence and hazard analysis report and the function to-be-tested item list, so as to meet the requirements of the aero-engine. The method can be used for performing system testability design and evaluation on the aero-engine from the perspective of aero-engine forward design, and improving the quality and performance of the product.

The invention relates to a testability modeling and analysis method based on closed-loop control system architecture design. The method comprises the following steps: decomposing system-level functions of the closed-loop control system into component functions according to a composition structure and function definition of the closed-loop control system, and forming a function list; determining a function fault mode, a fault rate and a fault influence level based on the function list; forming a fault transmission path; a testability model is established, and after simulation analysis and calculation, the detection rate of the fault mode is obtained; sorting the function fault modes from high to low according to the fault rates, and calculating an accumulated detection rate based on the corresponding detection rate; optimization is carried out based on the indexes; and based on the initial test set, comprehensively considering the fault influence and the test cost, and adjusting and optimizing the initial test set to obtain an optimized test set. The problem that system testability design and analysis cannot be carried out at the initial stage of closed-loop control system design in the prior art is solved.

The invention discloses an interface test circuit, a judgment method and test equipment, and relates to the field of interface test, and the interface test circuit comprises a connection module, a switch module, a test module and a control module. And the connection module is connected with a to-be-tested pin of the Type-C interface. The switch module connects or disconnects the test path of each to-be-tested pin. And the test module performs function test on each to-be-tested pin to obtain a test result. And the control module determines whether all the to-be-tested pins are successfully tested according to the test result and sends the test result to the to-be-tested equipment for display. Based on the scheme of the invention, all the pins of the Type-C interface can be tested, so that the function failure phenomenon of the untested pins is avoided. And meanwhile, whether all the to-be-tested pins are successfully tested or not is determined and sent to the to-be-tested equipment to be displayed, so that the problems of missing detection and error detection can be prevented, the test personnel can conveniently watch, and the test efficiency is relatively high.

This invention relates to a software architecture for an electromechanical braking control system for commercial vehicles. It employs a safety redundancy mechanism with two independent control units. The system is implemented with dual redundancy, allowing each control unit to operate independently. Each control unit includes a functional layer and a functional monitoring layer. The functional layer includes functions such as vehicle state estimation, brake coordination control, actuator control, and fault handling. The functional monitoring layer performs real-time monitoring of the functional layers, monitoring the braking demand calculation, anti-lock braking module, and vehicle stability control module processes to ensure signal integrity and rationality, pinpoint the causes of brake failure or ABS / ESC malfunctions, and detect functional anomalies. This architecture can monitor defects in real time and handle them quickly. Furthermore, in the event of a functional failure, another control unit can be used for braking, ensuring the safety of the EMB system.

Aspects of the present disclosure relate to performance monitoring for AI / ML inference. In an aspect, a configuration about resource settings is received from a base station via the transceiver, the configuration including one or more sets of non-zero power channel state information reference signal (NZP CSI-RS) resources for operation of a UE associated with an artificial intelligence (AI) / machine learning (ML) model or AI / ML function. In a case where the UE determines a fault event based on differential reference signal received power (RSRP)-based performance monitoring for the AI / ML model or the AI / ML function, the UE sends an indication of the fault event for the AI / ML model or the AI / ML function to the base station. In this way, based on the obtained differential RSRP, the UE may determine whether to report an AI / ML model / function failure event to the base station.

This disclosure provides a user-based service isolation method, apparatus, device, and medium. One specific implementation of the method includes: in response to a target user's login, constructing a user object corresponding to the target user, constructing a service container, binding the user object to the service container, and creating a service instance corresponding to the target user within the service container; in response to a target user's logout, destroying the user object and the service container. This method can solve the functional failure problem caused by untimely user switching.

This application discloses a method and related equipment for predicting the functional failure probability of shield tunnels based on multiple variables. The method includes: constructing an integrated damage-function index system covering multiple scales and quantifying the mapping relationship between damage and function; optimizing the probabilistic seismic demand model using interval estimation methods and selecting the best vibration intensity index by combining fuzzy multi-criteria decision-making; introducing the Copula function to accurately characterize the nonlinear correlation between multidimensional damage / function parameters; and finally establishing a multivariate vulnerability analysis model that can output the failure probability of each function of the tunnel and the overall failure probability of the system. This provides reliable technical support for the seismic design, post-earthquake assessment, and operation and maintenance decisions of shield tunnels. It can accurately assess the seismic risk of shield tunnels under non-uniform liquefaction development, improve the reliability and robustness of the results, and can be widely applied in the field of computer technology.

The invention discloses a method, device and equipment for improving FDP function accuracy of an SSD, and a medium, and relates to the field of solid state disks, and the method comprises the following steps: receiving a query command sent by a host; executing the query command, and determining identities of one or more recovery units corresponding to the logic block address range; counting the number of the recovery units occupied by the logic block address range based on the identity labels of the one or more recovery units; and returning the quantity information of the recovery units to the host. In the invention, the host can accurately verify whether the data is expected to be placed according to the FDP strategy, and the write strategy can be adjusted in time once the deviation is found, so that the problem of function failure caused by information asymmetry is fundamentally solved, and the technical span from passive dependency event recording to active accurate management and control is realized; and the accuracy and the reliability of the FDP function are obviously improved.

The application discloses a kind of high acceleration life test fast test method, first find the operating limit of product, then find the destruction limit of product, find the operating limit of product: simultaneously to product temperature and vibration test, temperature and vibration condition are with the fixed increment mode of continuous change to product with the temperature and vibration stress of continuous change, until product occurs functional failure, start to confirm operating limit, determine high temperature operating limit, low temperature operating limit and vibration operating limit;Find the destruction limit of product: with (S1) in the high temperature operating limit, low temperature operating limit and vibration operating limit obtained by testing in starting setting value, temperature and vibration condition are with the fixed increment mode of continuous change to product with the temperature and vibration stress of continuous change, until product cannot work normally, start to confirm destruction limit, determine high temperature destruction limit, low temperature destruction limit and vibration destruction limit.