106 results about "Hardware redundancy" patented technology

Methods of generating heat maps of assets using clustering of assets are disclosed. Some methods include receiving a list of assets, assigning the assets to one or more heat range categories based on the status of the assets, assigning assets operating within a zone to a zone cluster, assigning the assets of the zone cluster to category clusters based on the heat range categories assigned to the assets. The positions of the clusters may be calculated for mapping, and may be displayed on a map. Some embodiments of these methods allow a user to quickly detect and locate non-standard assets on a map while standard assets are consolidated to clusters that are less prominent to the user. This leads to minimizing the time required to form responses to de-load hotspots in an electrical grid, minimizing the cost of assets by reducing the need for hardware redundancy, and minimized equipment outages.

The invention discloses an automobile steering-by-wire system SBW with a redundancy and fault tolerance structure and control method, wherein the system comprises a main control chip, a heavy-current circuit, a detection module, a treatment module and an execution motor, characterized in that the system also comprises a standby chip and a standby heavy-current circuit, when fault occurs, the treatment module screens the main control chip and the standby chip and the standby heavy-current circuit are started. The automobile steering-by-wire system also comprises a standby sensor circuit, and the sensor circuit is directly connected with a plurality of sensors of the automobile by the standby connection. The hardware redundancy is combined with the software redundancy to ensure the completeness of the SBW and the entire car loaded CAN communication gives the fault treatment communication and alarm way, thereby the system can be maintained when the fault occurs. The SBW system reliability, safety, real-time communication performance can be increased and optimized, therefore the structure is simple and the industrialization benefit is high.

The invention discloses an unmanned helicopter flight control system with a fault diagnosis ability. The hardware device is composed of a navigation/flight control computer system, a sensor system, an execution mechanism system, a remote control and remote measurement system and a power supply system, wherein the navigation/flight control computer system is an active/standby dual-redundancy system; the sensor system provides sensor information for the navigation/flight control computer system; the remote control and remote measurement system is directly connected with an actuator system through remote control autonomous conversion; and the power supply system provides power for the sensor system, the navigation/flight control computer system and the remote control and remote measurement system. The software structure comprises a bottom operation system, a data I/O module, system management software, redundancy management software, flight control software, navigation control software and task execution software. Through adding the hardware redundancy to the flight control system of the invention, thereby enhancing the reliability; the retention of the remote control system can handle emergency states and non routine tasks; and due to the adding of the fault diagnosis method, the fault identifiability is enhanced.

A method and system are provided for enabling replacement of a failed processor without requiring redundancy of hardware. The system is a multiprocessing computer system that includes one or more processor chips. Each processor chip may include one or more logical processors. During system initialization, one or more logical processors may be reserved in an inactive state. In the event an error is detected on a logical or physical processor, one or more reserved logical processors may have execution context transferred from the processor experiencing the error. Thereafter, the active processor is designated as inactive and replaced by the inactive processor to which the execution context has been transferred.

The invention relates to a plug-and-play smart vehicle domain controller with a redundant structure and a method. The domain controller is provided with a power supply redundancy structure, a microcontroller redundancy structure, a microprocessor redundancy structure, a communication redundancy structure, a data redundancy structure and a redundancy management module through a hardware redundancymethod. The microcontroller redundancy structure comprises more than two microcontroller MCUs which realize intelligent control and an auxiliary chip. The microprocessor redundancy structure is a multi-embedded microprocessor structure. The communication redundancy comprises multiple redundant buses. The data redundancy structure comprises more than two data storage units. The redundancy management module is used to isolate, switch and reconstruct input and output channels and signals of the domain controller when faults or attacks are discovered. The domain controller is connected with the whole vehicle to complete safe deployment, and is suitable for smart vehicles of the L3 class and above or link smart vehicles. Compared with the prior art, the domain controller provided by the invention has the advantages of high security, high reliability, high adaptability, good cross-platform versatility and the like.

The invention relates to an electrical system of an electric intelligent vehicle, for a centralized architecture controller and electricity supply redundancy. The electrical system comprises a high-voltage battery, a battery management system (1), a key switch (16), an electricity supply unit, an intelligent decision-making and control unit, a sensor unit and an actuator unit, wherein the high-voltage battery is connected with the battery management system (1) through an electrical circuit; the key switch (16) is provided with an OFF gear, an ACC gear, an ON gear and a START gear; the electricity supply unit comprises a main accumulator (12) and an auxiliary accumulator (11); the electrical circuit comprises a main ACC circuit, an auxiliary ACC circuit, an ON circuit, a START circuit and a constant electric circuit which is connected with a positive pole output terminal of the main accumulator (12). Compared with the prior art, the electrical system disclosed by the invention has the advantages that requirements of a control unit and a wire-controlled system of the electric intelligent vehicle for redundancy are met, hardware redundancy and electricity supply redundancy are designed for critical components including a steering unit, a braking unit, a central control unit and the like in the driving of vehicles, and the safety of autonomous vehicles is improved.

The unit includes HH-OP to interexchage data of platforms in communication system, interruption interface and abnormal trigger device to process interrupting application and abnormal trigger signal, HA-OA to monitor local task and line operation and to carry out heartbeat detection, HA-ARB cosisting of platform decision device to decide abnormal trigger signal that can not be processed by HA-OP, task decision device to decide to switch or restart as per detected result of HA-OA. The present invention provides hardware redundant resource and handling method of data and state consistancy at standby time of software management redundance to realize HA requirement of telecommunication system.

The invention discloses a remote control key, tire pressure monitoring and engine anti-theft locking system, which comprises an automobile body controller, a tire pressure monitoring module, a remote control key module and an engine anti-theft locking module, wherein on the basis of the system integration technology, an automobile remote control entry system, an engine anti-theft locking system and a tire pressure monitoring system are combined into a whole, and the hardware redundancy is reduced. The remote control key module and the tire pressure monitoring module are connected with the automobile body controller in a wireless way of 434MHz, and the engine anti-theft locking module is connected with the automobile body controller in a low-frequency wireless way of 125MHz. Wireless data emitted by the remote control key and the tire pressure monitoring module adopts a 434MHz frequency range, a frequency shift keying modulation mode and a Manchester data encoding mode. The remote control key data after the Keeloq rolling code encryption is distinguished from the tire pressure monitoring data through matching codes. The system has the advantages that the hardware redundancy is reduced, the cost is low, the failure rate is low, and the space size is small.

The invention relates to a dual-redundant unmanned ship ship-borne control system and method based on an ARM. The system comprises an information collection system, a first arbitration switching system, a second arbitration switching system, an execution mechanism, a first ARM processor, a second ARM processor, a communication system and a power supply. The task level synchronization is realized by the two ARM processors. The dual-redundant designs of all sensors are made. The data of two paths of sensors are transmitted to two ARM processors at the same time to carry out comparison, correct data is selected to carry out task operation, and a comparison point is set in the task operation. The corresponding data is subjected to consistency judgment, if the corresponding data is inconsistent, the arbitration switching systems carry out fault diagnosis on the two ARM processors, a failed ARM processor is isolated, and at the same time an ARM processor with normal operation is selected to control output. According to the dual-redundant unmanned ship ship-borne control system and method, with hardware redundancy as a basis, with software redundancy, information redundancy and time redundancy as a supplement, the reliability, stability and safety of the unmanned ship ship-borne control system are effectively improved, the safe and stable operation of an unmanned ship is ensured, and various complex tasks are smoothly completed.

The invention discloses a method for testing an SOC (System On Chip) based on a reference vector and a bit mask, relating to a method for testing the SOC and solving the problem of lower compression rate when the traditional testing method s used for testing an IP core. The method comprises the steps of: 1, compressing test data corresponding to a circuit; 2, transmitting compressed data and storing in ATE (Automatic Test Equipment); 3, decompressing the compressed data through a decompression structure on a chip, reducing into test data; and 4, testing the IP core by using the test data. Themethod has high compression efficiency higher than that of the similar products by above 20 percent, has no additional hardware redundancy, and is used for testing the SOC based on a reusable IP coredesign.

The invention discloses a multi-fault diagnosis and fault-tolerant control method of a wind turbine system. The method comprises the following steps: firstly, establishing a global fuzzy model of the wind turbine system by utilizing the T-S fuzzy algorithm; converting an actuator fault into a sensor fault by utilizing the characteristic of combining the sensor hardware redundancy technology with the actuator fault, and establishing a multi-fault diagnosis logical table to realize multi-fault detection; then, introducing a filter, converting the sensor fault into the actuator fault, establishing a virtual actuator fault, and realizing simultaneous reconstitution of two faults through reconstitution of the virtual actuator fault; finally, revising input and output of a controller based on a fault reconstitution value to realize active fault-tolerant control. The method has the following advantages: diagnosis and reconstitution of the wind turbine system with concurrent actuator and sensor faults can be simultaneously realized, accurate fault information is obtained in a real-time and on-line manner, fault-tolerant control is realized, the capacity of processing unknown faults of the system is enhanced, and the wind energy conversion efficiency under the fault is improved.

The invention discloses a control method of a nuclear power steam generator. The control method comprises the steps of (a) mechanism modeling in which a high-temperature gas-cooled-reactor steam generator model is established according to thermotechnical waterpower principle; (b) data collection; (c) state estimation; (d) fault diagnosis and reconstruction; and (e) control according to reconstructed values. Tolerance control design is carried out on the steam generator based on a traceless Kalman filter; and on the basis of a lumped parameter model, tolerance control with stable water level and flow of the steam generator is achieved by detecting and separating sensor faults in real time and reconstructing output values of the sensor. Even if detection faults occur in the sensor, the control effect is good, the cost of hardware redundancy is reduced, tracking control for a multivariable nonlinear system can be realized, the possibility of nuclear power safety accidents caused by detection faults is effectively reduced, the safety level is high, the control effect is good, and computers are easy to control.

The invention discloses a PLC (programmed logic controller)-based redundancy system implementation method, wherein the method comprises the following steps: a. at least two CPUs (central processing unit) with different address codes and at least two I/O (input/output) modules with different address codes are connected through a CAN (controller area network) bus; b. after electrification is performed, a main CPU is determined after electrification, and other CPUs are spare CPUs; and c. the main CPU receives data from the I/O modules and sends a broadcast frame, and the spare CPUs only monitor the broadcast frame sent by the main CPU on the CAN bus. The PLC-based redundancy system implementation method provided by the invention has the beneficial effects that according to the invention, redundancy configuration is not required to be adopted for all important components in a PLC system, the system redundancy property can achieve or be close to that of a hardware redundancy PLC system, thus the cost of hardware is saved; the main and auxiliary switching is smooth; automatic fault recognition and positioning can be carried out, and the fault module switching supports hot plug; and the system has high reliability, is easy to implement and is low in cost.

The invention relates to a flight control system fault diagnosis method and belongs to the fault diagnosis technology field of a flight control system. The method comprises steps that 1), components and a connection structure of the flight control system are determined; 2), a distributed flight control computer structure and redundancy configuration are determined; 3), an aircraft object model is determined; 4), a performing mechanism and model fault observers of an airborne sensing system are designed according to the object model determined in the step 3), and typical faults are identified; 5), according to the distributed flight control computer structure, the corresponding model fault observer is configured in each distributed unit; 6), fault diagnosis of the flight control system is carried out according to hardware redundancy and the model fault observers; and 7), the fault diagnosis effect of the system is tested, and the system structure is further optimized. The method is advantaged in that fault diagnosis of the flight control computer, the airborne sensing system and the performing mechanism in the flight control system can be realized.

Disclosed is an automatic failure handling and protection method of a deep space probe global navigation chart (GNC) system base on a layered structure. The automatic failure handling and protection method of the deep space probe GNC system base on the layered structure comprises the steps of carrying out hardware protection to avoid a failure which can result in permanent damage or invalidation of other parts or other parts inside a part according to a result of failure mode and effects analysis (FMEA), judging whether the data of measuring points are normal with an infrared ray method for other failures, marking the states of parts and handling the data and state information to a controller for analyzing of system-level failures; carrying out failure analyzing according to the state information and the data of the measuring points handed to the controller: if hardware redundancy or analysis redundancy exists, a failure part is switched to a normal redundancy part; if the hardware redundancy or the analysis redundancy dose not exist, the next step is carried out; switching to a counter-glow orientation mode when the prior step can not position a failure source or no redundant backup can replace the failure source and gesture is pretty poor and directing is out of control, switching off equipments not necessary for flying of a deep space probe to reduce power consumption, and switching off a self-locking valve and switching to a control-stop mode to reduce propellant consumption of the probe when the probe is out of control, a pushing system spray gas at random and star bodies roll.

The invention discloses a design method of a scanning unit based on partial scanning of an improved test vector set, relating to the technical field of SOC (system-on-a-chip) test of digital integrated circuits, and solving the problems of delayed test, hardware redundancy and large required capacity of a memory in the conventional online test method. The method comprises the following steps of: firstly, obtaining an important equivalent output pin which is important to fault detection by stimulating a fault of an equivalent output pin in a combined part of a sequence circuit; secondly, obtaining the improved test vector set by stimulating a fault of an equivalent input pin in the combined part of the sequence circuit; and finally, according to the improved test vector set and an equivalent output pin which is unimportant to the fault detection, dividing triggers into fixed-input triggers and important triggers, and serially connecting the important triggers to form a partial scanningchain. By the method, the obtained scanning unit has a relatively high fault coverage rate and can reduce the hardware redundancy of a test circuit, the digit of bits of the test vector and the memory space.

The present invention relates to a satellite control system fault diagnosis method based on multiple layer state estimators. With the method, fault isolation of an optical sensor and an inertial sensor can be achieved under the circumstance that hardware redundancy conditions are not met. The method comprises the following basic process: firstly establishing a analytical model for describing an output relationship between the optical sensor and the inertial sensor; secondly respectively designing two layers of state estimators based on the model, wherein residual error generated by the first layer state estimator is sensitive to the optical sensor fault and the inertial sensor fault, and residual error generated by the second layer state estimator is not affected by the inertial sensor fault; finally detecting the residual error generated by the first layer state estimator, and comparing with the preset threshold value to determine whether the fault occurs, wherein the optical sensor fault and the inertial sensor fault can be distinguished based on the residual error generated by the second layer state estimator if the fault occurs.

The invention provides an aerodynamic parameter measurement method for an aircraft, which is used for measuring key data in three aspects of an airflow angle, dynamic pressure and an aerodynamic force. The method comprises the following steps: the airflow angle is calculated, the airflow angle is acquired through an embedded atmospheric data sensing system or a trajectory reconstruction mode, andthe above two modes are in mutual backup; the dynamic pressure is calculated, data are outputted according to pressure sensors configured by the embedded atmospheric data sensing system on the aircraft, the dynamic pressure is calculated and input is provided for calculating an aerodynamic coefficient; and the aerodynamic coefficient is calculated, the output is measured by using accelerometers, the aerodynamic force, that is, the lift force and the drag force, is calculated, and in combination of the dynamic pressure data, an aerodynamic calculation formula is used to directly determine the lift force coefficient and the drag force coefficient of the aircraft. The embedded atmospheric data sensing system is equipped with two sets of pressure sensors and multiple sets of accelerometers andgyroscopes. A hardware redundancy design and an algorithm redundancy design are adopted, and the aerodynamic parameter measurement reliability is improved.

The invention relates to a method for realizing a DDS service on an embedded sensor access platform, and the method comprises the steps: taking embedded hardware as the sensor access platform, carrying an embedded real-time operation system, and carrying out the message communication with a data processing unit through employing the DDS service. According to the invention, the sensor access platform is constructed based on an embedded manner, so that low-cost hardware redundancy backup can be realized; meanwhile, DDS service is realized based on an embedded mode, complete DDS service is formedwith the data processing unit, and a perfect abnormal recovery mechanism is provided.

The invention relates to the technical field of a battery management system, aims to solve a problem of incomplete fault processing in a battery management system in the prior art and provides a battery management system fault FDIR system and method based on double redundancy. The system includes a first data acquisition module, a second data acquisition module, a resolution redundancy module, a hardware redundancy module and a fault reconstruction module, wherein the first data acquisition module is connected with the analysis redundancy module, the second data acquisition module is connectedwith the hardware redundancy module, and the fault reconstruction module is respectively connected with the hardware redundancy module and the analysis redundancy module. The battery management system is detected, isolated and reconstructed through hardware redundancy and analytical redundancy, not only can faults of a battery pack be detected accordingly, but also hardware faults of the batterymanagement system can be processed, comprehensive fault processing of the battery management system is achieved, and the method is suitable for the battery management system.

The invention discloses a redundancy communication method among nodes based on multiple networks. The method includes that sender nodes send data to a receiver node through N Ethernet channels simultaneously, and the sender nodes give different frame numbers to data sent each time. The receiver node extracts a data frame from a receive data frame list and judges whether the current extracted data frame is processed according to a current extracted data frame number and a sender node which the current extracted data frame number belongs to. On no judgment, data processing is conducted, and the current extracted data frame number and the sender node which the current extracted data frame belongs to are related. The redundancy communication method is achieved mainly through software, requirements for hardware are reduced, a common network device can achieve the method, and cost of a hardware redundancy device is reduced. In addition, the redundancy communication method avoids repeated processing on the same data by introducing a judging mechanism, and processing speed is increased.

Transient faults in a combinational logic become a major challenge for the VLSI (very large scale integrated circuit) design. As a typical component in the combinational logic, an adder is widely applied to an arithmetic unit. The invention discloses a low-overhead transient fault automatic correction circuit for a high speed adder. According to the structure, through developing the abundant inherent hardware redundancy and time redundancy existing in the adder circuit, automatic correction on the transient faults in the high speed adder can be realized with lower overhead, thus the fault-tolerant area and performance overheads can be obviously reduced; and through combining a fault correction technology based on a C unit and the inherent hardware redundancy and time redundancy, the transient fault correction capacity of the adder can be further enhanced. The adder provided by the invention has preferably compromised area-delay overhead compared with other structures.

The invention discloses an aero-engine sensor fault diagnosing and isolating method based on a fuzzy membership degree. For the defects in the prior art, a solving idea of the aero-engine sensor faultdiagnosing and isolating method is that analytic redundancy and hardware redundancy are fused based on fuzzy logic and a fault threshold value; sensor fault analysis is performed based on a fused signal; once a signal membership degree is lower than an average value, a proportion of a signal of the signal membership degree in the fused signal decreases; after the signal membership degree exceedsthe fault threshold value, the signal is completely expelled out of the fused signal; thus, self-adaption fault tolerant and fault isolation are achieved. Compared with the prior art, the aero-enginesensor fault diagnosing and isolating method disclosed by the invention can achieve self-adaption fault tolerant and fault isolation under the single channel situation of a dual-channel sensor.