34 results about "Dual bus" patented technology

Vehicle (112), comprising: a pre-charging circuit designed to selectively couple a resistor (202, 302, 402) via either a first (206, 306, 406) or a second contactor (208, 308, 408) designed to selectively couple terminals of a battery (124) to a load bus (152); and a controller (220, 320, 420) programmed to couple the resistor (202, 302, 402) via the second contactor (208, 308, 408) in response to a pre-charge request in a case where the first contactor (206, 306, 406) is closed when commanded to open and the second contactor (208, 308, 408) is open, in order to pre-charge the load bus (152), characterized by the fact that The controller (220, 320, 420) is further programmed to, in response to the pre-charge request in a case where both the first contactor (206, 306, 406) and the second contactor (208, 308, 408) are open and following an immediately preceding pre-charge request that resulted in the resistor (202, 302, 402) being coupled via the first contactor (206, 306, 406), couple the resistor (202, 302, 402) via the second contactor (208, 308, 408) in order to pre-charge the load bus (152).

The invention discloses a spacecraft-oriented software on-orbit multi-bus fault-tolerant reconstruction system and method, and relates to the technical field of spacecraft electronic information. The system comprises a ground uploading subsystem, an on-satellite reconstruction management subsystem, a CAN and RS485 dual-bus redundant network and a load reconstruction client. The on-satellite reconstruction management subsystem segments software to be reconstructed according to 256KB, data packets in the segments are transmitted out of order, and transmission continuity is guaranteed through dual-bus hot backup and fault switching; and the load reconstruction client executes three-level verification of data packets, segments and files, and selectively retransmits the data packets, the segments and the files according to abnormal degrees. According to the scheme, through multi-bus redundancy, segmented transmission and a multi-stage fault-tolerant mechanism, multi-load collaborative updating is achieved, the space extreme environment is adapted, the reliability and efficiency of software on-orbit updating are greatly improved, algorithm iteration can be completed without changing hardware, and the spacecraft task life cycle is prolonged.

The invention provides a dual-bus redundant communication and switching method and device, electronic equipment and a storage medium, and the method comprises the steps: obtaining an industrial equipment parameter, and carrying out the packaging processing based on the industrial equipment parameter, and obtaining an Ethernet data frame and a CAN bus data frame; the Ethernet data frame and the CAN bus data frame are sent to a receiving end in parallel through two physical communication paths; receiving data frames from the two physical communication paths, and dynamically determining one of the physical communication paths as a current main communication path based on a monitoring result of transmission indexes of the two physical communication paths; and when it is monitored that the transmission index of the current primary communication path meets the fault condition, switching the data communication path from the current primary path to another physical communication path. According to the mode, intelligent parallel monitoring and rapid automatic switching of the Ethernet and the CAN bus are realized, the reliability and continuity of an industrial communication system are remarkably improved, and the data interruption risk caused by a single-path fault is reduced.

The invention discloses a general extensible digital beam forming chip design architecture and a method. The architecture comprises a chip control architecture which adopts a dual-bus master-slave control architecture of an AXI bus and an APB bus, a data source of a chip data stream architecture is external AD data or cascade beam forming dedicated chip sending end data, and the data is converted and sent in a stream form; according to the systolic array digital beam forming network architecture, a synthesis bandwidth, an input channel and an output channel are split to a plurality of beam forming chips, and the chips are connected in an interconnection topology form. The method is specifically a working method of the chip data stream architecture. According to the invention, the parameter reconfiguration of the chip is realized, the use expandability is realized, and the universality of the chip is ensured.

This invention discloses a communication gateway, data communication method, and vehicle control chip for inter-core collaboration, belonging to the field of vehicle diagnostic technology. The communication gateway is integrated into the diagnostic processing core. The diagnostic processing core and the bus communication core collaborate through the communication gateway. The communication gateway includes: an inter-core transparent transmission interface connected to the bus communication core, used to acquire the DoCAN data packet carrying the diagnostic request transmitted by the bus communication core when the CAN diagnostic instrument sends a diagnostic request via the CAN bus; and a first reassembly unit connected to the inter-core transparent transmission interface, used to parse the DoCAN data packet and reassemble it into a DoIP data packet; the reassembled DoIP data packet is sent to the diagnostic processing core for diagnostic processing. The beneficial effects of the above technical solution are: reliable transparent transmission of diagnostic data between dual cores in a multi-core heterogeneous SoC chip architecture, support for seamless conversion between dual bus protocols, and meeting the access requirements of diagnostic services under multiple protocols.

The invention relates to a load balancing method and device based on a space-ground integrated core network, and communication equipment. Wherein a data plane satellite-borne network element is newly added to each network node of the space-ground integrated core network, and the space-ground integrated core network is used for parallel transmission of a control plane link and a data plane link in an inter-satellite link based on a service interface (SBI) / data transmission interface (DTI) dual-bus link. The method comprises the following steps: a first network node receives a user task, wherein the user task is a task which is unloaded to a space-based network for execution after a ground data network performs a load balancing decision; the first network node makes a load balancing decision according to the geosynchronous orbit GEO node state information to obtain a first GEO node, and the first GEO node is used for executing a load balancing strategy to send a user task to a corresponding low earth orbit LEO node through an inter-satellite link for data processing. According to the invention, the average processing time delay of user tasks can be reduced.

A controller area network (CAN-FD) system and method with flexible data rate providing high availability, redundant process control I / O. A server device coupled to the dual CAN-FD bus generates a SYNC message that specifies one of the dual buses as an active bus and the other as a backup bus. The server device transmits the SYNC message on the active bus and then immediately transmits the SYNC message on the backup bus. A client device coupled to the dual bus transmits a process data frame on the bus in response to the SYNC message. Each process data frame includes a sequence number of a current communication cycle and indicates on which of the dual buses the process data frame is transmitted.

Controller Area Network with Flexible Data Rate (CAN-FD) system and method providing high availability, redundant process control I / O. A server device coupled to dual CAN-FD busses generates a SYNC message designating one of the dual busses as active and another one as backup. The server device transmits the SYNC message on the active bus and then immediately transmits the SYNC message on the backup bus. A client device coupled to the dual busses transmits process data frames on the busses in response to the SYNC message. Each of the process data frames includes a sequence number for the current communication cycle and indicates on which of the dual busses the process data frame is being transmitted.

The invention discloses a dual-bus self-switching display interface and a non-inductive backlight adjusting method and system, which integrate automatic identification of dual-bus MIPI DSI and LVDS, IOVDD level self-adaptive configuration, level self-switching matching and an integral non-inductive backlight adjusting method based on image acquisition, and realize plug and play and automatic compatibility of the display interface. The display module with different power supply levels and communication protocols can be adapted without manual intervention, electrical compatibility of reset, IC, interrupt and other signals under different IOVDD is ensured through the level self-switching circuit, the system robustness is improved, the ambient brightness is analyzed by using a camera image, real non-inductive backlight adjustment is realized, and the display quality is improved. The problem that a traditional photoresistor is prone to being affected by shielding or aging is avoided, the hardware cost and BOM complexity are reduced through the overall scheme, and meanwhile user experience and product universality are improved.

This invention discloses a redundant architecture method for a UAV flight control system, relating to the field of UAV control technology. It includes redundant design for four layers: flight sensor system, redundant flight control computer system, bus communication system, and actuator system. The bus communication system employs a three-bus redundant architecture consisting of a 1553B dual-bus, FlexRay bus, and CAN bus. The redundant flight control computer system features automatic switching between three modes: triple-mode redundancy, dual-mode redundancy, and single-mode redundancy, and possesses online fault channel repair and reconnection capabilities. The actuator system includes aerodynamic control surface segment redundancy, servo electrical dual-path redundancy, and dual-path access redundancy via the CAN bus main path and RS422 backup path. This invention, using the aforementioned redundant architecture method for a UAV flight control system, achieves long-endurance, highly reliable flight control with no awareness of single faults, return capability in the event of dual faults, and no degradation due to bus faults.

The embodiment of the invention provides a dwell pressure adjusting method, which is applied to an upper computer and a servo driver, and comprises the following steps that: the upper computer configures mapping parameters of a pressure value and an analog quantity value and issues the mapping parameters to the servo driver, and the servo driver calculates a dwell pressure value based on a linear calibration model; a servo motor is controlled to execute self-learning to determine a contact point origin machine of the pressing process; the upper computer issues a force control instruction to the servo driver through the EtherCAT bus; the servo driver converts an analog quantity signal fed back by the pressure sensor based on a linear calibration model to obtain a real-time pressure value, adjusts the torque of the servo motor by taking the original point of the contact point as a reference, and feeds back a state to the upper computer through an EtherCAT bus; an upper computer reads a process data packet through a Modbus bus and analyzes the process data packet to obtain a pressure-time relation oscillogram, complete and synchronous acquisition and tracing of process data are achieved through double-bus cooperation based on built-in high-precision calibration and closed-loop force control of a driver, and the precision, stability and analyzability of a pressure maintaining process are improved.

The invention discloses a dual-master control device and method for an instrument landing system, and the device comprises a first master control unit, a second master control unit and internal equipment, and the first master control unit and the second master control unit are electrically connected through a first bus, and are electrically connected with the internal equipment through a second bus and a third bus. When the first main control unit is in primary use, the first main control unit acquires operation data of internal equipment through the second bus, interacts data with the second main control unit through the first bus, communicates with external equipment to receive an operation instruction, issue a control instruction and feed back state data, and is switched to be standby when a communication link is abnormal; when the first main control unit is standby, the second main control unit obtains data through the third bus, interacts data with the first main control unit, communicates with external equipment and issues a control instruction; and the internal equipment receives the instruction to output heading channel and glide channel signals. Through the dual-master control and dual-bus redundancy design, the reliability of the system is improved, non-stop maintenance is supported, and the flight safety is guaranteed.

The invention discloses a plug-in panel and a dual-bus electric control device.The plug-in panel comprises a first bus and a second bus, and the first bus comprises an input end, a first output end and a first busbar set; the input end comprises at least two input components; the second bus comprises a second output end and a second busbar group, the second busbar group and the first busbar group are arranged at intervals in the first direction, and the second output end comprises a plurality of second output assemblies. According to the invention, the wiring work can be completed on the panel side, and conditions are provided for wiring in advance before the circuit breaker is connected to the panel, so that the circuit breaker can be matched with the plug-in panel to realize plug-and-play, and the installation and application convenience of the circuit breaker in the plug-in panel is improved; in addition, the trouble that additional wiring is needed after the circuit breaker is installed in the panel is omitted, and wiring on the side of the plug-in panel is beneficial to simplifying wiring of the distribution box.

The invention discloses a dual-bus register access device and method, and relates to the field of registers. The device comprises a register module which comprises a shared physical register and two read mapping buffer areas; the two bus interfaces are configured to be used for accessing the shared physical register and accessing the corresponding read mapping buffer areas, and the two bus interfaces are configured to be used for accessing the shared physical register and the corresponding read mapping buffer areas; an arbiter; and the synchronization unit is used for refreshing the address data of the written register unit stored in the read mapping buffer area corresponding to the two bus interfaces in response to the operation of writing data into the shared physical register by the two bus interfaces. In the write operation stage, the data is actively refreshed through the synchronization unit, hardware-level active guarantee of write-read consistency is achieved, and the requirement of an ARM M0 low-power-consumption scene for data real-time performance is met. Meanwhile, the read-write isolation design of the double-read mapping buffer area and the synchronization unit is matched with the access arbitration strategy of the arbiter to form a full read-write process conflict-free closed loop.

The invention relates to the technical field of flight simulation communication, and discloses a flight simulation hierarchical communication system and method based on cloud native dual-bus scheduling, and a communication architecture based on hierarchical decoupling, and the system comprises a component application module, a bus intelligent scheduling module, a data distribution module and a transmission adaptation module which are connected in sequence. The component application module is used for docking various flight simulation components; the bus intelligent scheduling module comprises a control bus unit and a data bus unit which are physically isolated from each other, and an intelligent scheduling unit which is in communication connection with the control bus unit and the data bus unit, and is used for realizing type identification of transmission data, branch and bus routing and dynamic scheduling of transmission resources based on a flight simulation scene; and the data distribution module comprises a cloud resource adaptation engine and a subscription relationship management unit, and is used for docking a cloud platform resource pool and realizing heterogeneous deployment resource matching and communication channel subscription management of various flight simulation components.

The application relates to the technical field of bus diagnosis, and discloses an ESPI and LPC bus diagnosis method and device. The method is as follows: the STRAP pin level of a master control chip is configured through a jump cap short circuit state, so that the master control chip enters an LPC bus working mode or an ESPI bus working mode; a target mainboard is connected; an I / O write operation initiated by the target mainboard in a POST self-checking stage is listened to; when a frame start signal is detected, a start field of a bus frame is analyzed and determined as an I / O write operation type; an address field in the bus frame of the I / O write operation type is analyzed and matched with a target listening address; when the address is matched successfully, a POST Code diagnosis code is acquired from the bus frame. The application realizes a dynamic switching mechanism of the LPC and ESPI double bus protocols through hardware jump cap configuration of the STRAP pin, solves the technical problem that a diagnosis card only supports a single bus protocol in the prior art, and enables a single diagnosis card device to be compatible with all X86 platform mainboards.

The present application relates to the technical field of data processing, in particular to a medical community business interconnection method and system based on platform and data double bus, through the double mode of timing and real-time collection and standardization of each institution heterogeneous business data, a unified data resource center is constructed; a double bus architecture of platform service bus and data exchange bus cooperation is established, respectively realizing intelligent scheduling of business service and reliable transmission of data; the core business capability is packaged as a standardized reusable service, and the business request is dynamically distributed through the intelligent routing mechanism; through the unified interface layer, the protocol and semantic double adaptive access with external systems are realized; finally, through full link monitoring and multi-modal intelligent diagnosis, abnormal early warning and root cause positioning are realized. The problems such as low data flow efficiency, slow business response, lack of unified scheduling and intelligent routing mechanism in the existing medical community system are solved, and the overall operation efficiency and service capability of the medical community are improved.

The invention discloses a power supply control circuit and method and a display device.The power supply control circuit comprises a processor 1, a PMIC2 and a DDIC3, the processor 1 is used for writing a matched DVDD voltage value into a register table of the PMIC2 through a first dual-bus interface 11, so that the PMIC2 supplies power to the DDIC3 according to the matched DVDD voltage value; and the DDIC3 is used for reading the register table of the PMIC2 through a fourth dual-bus interface 31 to control the PMIC2 to supply power to the display panel after being powered. The processor 1 can adaptively perform initialization configuration on the initial power supply voltage of the DVDD in the OLED PMIC for screens of different models, so that power supply to the DDIC3 is completed, and after the DDIC3 is powered, a digital circuit in the DDIC can work to send an instruction to control the OLED PMIC to supply power to a display panel, so that normal display of the screens is ensured.

This invention discloses a heterogeneous computing platform for underwater acoustic signal processing, belonging to the field of sensor architecture technology. The platform includes a VPX-standard-based chassis, backplane, and various functional boards plugged into it, including power boards, CPU boards, cache boards, switching boards, and three types of heterogeneous computing boards (A, B, and C). The platform adopts a dual-bus switching architecture of Ethernet and SRIO, and integrates a message middleware compliant with the DDSI-RTPS standard to realize data publishing and subscription between heterogeneous boards, shielding underlying hardware differences. Each board integrates a domestically produced chassis management and monitoring chip, supports the IPMI 2.0 standard, and has hot-swappable, remote monitoring, and dynamic reconfiguration capabilities. This invention achieves intelligent allocation and efficient utilization of computing resources, improves the modularity, intelligent algorithm compatibility, and system scalability of the underwater acoustic signal processing platform, and is suitable for various underwater acoustic detection and intelligent processing tasks.

This invention discloses a power regulator and its load circuit current abnormal fluctuation handling method in the field of circuit power regulation technology. It includes a built-in auxiliary heating PECVD reaction chamber and a dual-bus redundant power regulator. The built-in auxiliary heating PECVD reaction chamber includes a sealed water-cooled flange, an internal thermocouple, a support component, a graphite boat, an external thermocouple, a quartz tube, a resistance heating wire, an insulation layer, a support flange, an air inlet flange, and an auxiliary heating device. It implements RS485-based Modbus communication protocol and TCP / IP-based Modbus communication protocol through two communication ports, achieving redundancy of communication ports, as shown in Figure 3. Simultaneously, a shared memory mechanism is adopted to compare the communication data based on RS485 and TCP / IP, and then map it to shared memory, ensuring the reliability of the communication data.

The application provides a bidirectional Super buck-boost double bus power conversion circuit based on phase shift control, one end of a current collection circuit Rsense1 is connected with a high-voltage bus, the other end is connected with one end of an inductor L4, the other end of the inductor L4 is connected with the drain of a switch MOS tube Q1; one end of a current collection circuit Rsense2 is connected with a low-voltage bus, the other end is connected with the source of the switch MOS tube Q1 and the drain of a switch MOS tube Q2. The application has the advantages that energy can be bidirectionally supplied between different voltage buses of a space power supply, energy redundant resources are effectively utilized; the energy sharing of the high-voltage bus and the low-voltage bus in a "mobile phone direct connection satellite energy system" can be effectively solved, the redundant cost of the conversion circuit is reduced; meanwhile, the excess energy can be autonomously transmitted from one bus to another bus with insufficient energy; the current is continuous during the energy transmission process, which can effectively reduce the disturbance to the bus; and multiple buses can be connected in parallel for expansion.

The invention discloses a vehicle light decoding control system and method based on Lin / CAN dual-bus context awareness. The system comprises a power supply unit, a situation awareness device, a bus protocol decoding control unit, a main control unit and a multi-channel power driving module, the power supply unit is connected with a vehicle battery voltage to provide a power supply for the system, the situation sensing device obtains a face image, traffic road condition information, environment illumination intensity and rainfall data, and the bus protocol decoding control unit receives and analyzes a vehicle Lin / CAN bus signal to obtain vehicle state information. The main control unit fuses the vehicle state information and the situation awareness information to generate a light control instruction, and the multi-channel power driving module cooperatively drives the corresponding vehicle lamp according to the instruction. Through combination of multi-dimensional context awareness and dual-bus signal analysis, active recognition and dynamic regulation and control of vehicle lamplight are achieved, the problems that an existing lamplight system needs manual operation and cannot adapt to a complex driving environment and a driver state are solved, and driving safety and driving experience are effectively improved.

The invention relates to a reconfigurable double-bus power supply system of a spacecraft, which comprises two sets of bus power supply subsystems and a set of double-bus switching circuit, one set of bus power supply subsystem is arranged on a bus A, and the other set of bus power supply subsystem is arranged on a bus B; the two sets of bus power supply subsystems are the same in composition, and each bus power supply subsystem comprises a solar cell circuit, a shunt regulator, a charge-discharge regulator, a bus filter and a storage battery pack. The double-bus switching circuit realizes two-bus switching reduction through connection and disconnection of different relays. The invention solves the serious problems that the key load cannot supply power and the spaceflight task cannot be continued under the single bus fault condition of the traditional spacecraft power supply system, effectively improves the reliability of the spacecraft power supply system, and improves the success rate of the spaceflight task.

The application discloses a narrow-body folding building construction robot and a dynamic balance control method thereof. The robot adopts a layered body layout, and a battery pack is arranged at the bottom layer of the body. Four sets of supporting feet and two sets of working arms can be folded and collected, and the width of the folded and collected robot is 580-620 mm, so that the robot can be adapted to a standard entrance door. An AI control system adopts a distributed multi-rate control architecture of a cloud brain and a local cerebellum, and integrates functions of automatic walking and autonomous positioning, force-position hybrid control and construction quality closed loop, independent hardware safety protection and the like. The dynamic balance control method is executed by the local cerebellum, compensation instructions are issued to joint servo drivers through EtherCAT double buses at a communication period of 1 ms-2 ms, working disturbance is actively offset, and the body stability in dynamic working is maintained. The whole machine adopts a lightweight design, and after being connected to the ground through an extended pad, the whole machine meets the floor bearing requirement.

This invention relates to the field of power engineering technology and discloses an offshore wind power DC transmission system and its operation method and apparatus. The system includes an offshore station, an onshore station, and a DC submarine cable. The offshore station has two independent AC buses: a first AC bus and a second AC bus. The offshore station also includes a first converter branch, a second converter branch, and a first MMC converter valve. The onshore station has a second MMC converter valve, which is connected to the first and second converter branches via the DC submarine cable. This invention designs two independent AC buses connected to the wind farm group respectively, with the two converter branches sharing the first MMC converter valve and serving as backups for each other. The dual buses reduce electrical coupling between wind farms; in the event of a fault, only the wind farm connected to a single bus is affected, and the short-circuit current is reduced due to weakened impedance coupling. The shared core equipment between the two converter branches reduces hardware costs, and the backup design prevents system outages caused by single-branch faults.

The invention discloses a laser welding processing system and method based on dual-bus cooperation, and the system comprises an industrial personal computer which is used for generating process data according to a to-be-welded graph; the controller slave station is connected with the industrial personal computer so as to analyze the process data to generate preset process parameters; the PLC master station is connected with the controller slave station so as to transmit PDO data and enable signals to the controller slave station; the galvanometer is connected with the controller slave station so as to deflect according to the preset process parameters; and the laser is connected with the controller slave station so as to operate according to the preset process parameters. Separation of process data generation and real-time control instructions is achieved, the industrial personal computer focuses on graphic processing and data issuing, the PLC master station focuses on real-time synchronous control, the industrial personal computer and the PLC master station cooperatively work through the controller slave station, and resource competition and delay when a single controller processes multiple tasks are avoided.

The application provides a bus communication system and method based on a compound wing unmanned aerial vehicle power system, which comprises a bus repeater, a standard bus interface module, a double bus communication protocol module and a bus topology structure module; the bus repeater comprises a data transceiving module, a data processing module and a data storage module; the data transceiving module comprises a non-isolation unit and an isolation unit; the non-isolation unit is connected with a flight control navigation system; the isolation unit is connected with the standard bus interface module; the double bus communication protocol module comprises a bus competition processing protocol unit, a data analysis and distribution protocol unit and a fault processing protocol unit; the bus topology structure module adopts a tree topology and comprises a main bus and a plurality of branch buses; and the application can realize safe and efficient transmission of data between the power system and the flight control navigation system, improve the anti-interference ability, expandability and fault tolerance of the system.

The embodiment of the invention discloses a two-bus load capacity expansion circuit control system. According to one specific embodiment, the system comprises a control terminal which comprises a first detection assembly, a first adjustment assembly, a control chip and a power switch; a sensor group, wherein each sensor in the sensor group is provided with a second detection assembly; the control terminal is in communication connection with the sensor group through a two-bus; the control chip is configured to execute the following steps: in response to turning on the power switch, controlling the sensor group to start an intermittent working mode; turning off the power switch in response to the output current greater than or equal to the preset current; generating a line loss value in response to that the output current is smaller than the preset current; controlling the sensor group to switch between a first working mode and a second working mode in response to the condition that the line loss value is within a preset loss range; and adjusting the output voltage in response to the line loss value being outside the preset loss range. According to the embodiment, the system can be connected with more sensors through intermittent work.

The application discloses an extended IO module fault communication system and method based on a double-bus PLC, comprising a PLC controller, a plurality of extended IO modules and terminal modules; the PLC controller serves as a control port of the whole system and is used for acquiring input voltage and output voltage of a sampling resistor reported by each node of the extended IO modules, performing state monitoring of each module according to the input voltage and the output voltage, determining the number of fault extended IO modules and the positions of the fault extended IO modules, collecting analog and digital signals by the extended IO modules, receiving monitoring results output by the PLC commands, processing faults according to the monitoring results, determining the positions and the number of fault modules by processing voltage data in a communication process, switching a bus network through a control switch, and skipping the fault modules, so that subsequent extended IO modules can realize bus communication and do not affect normal functions.

The invention relates to an ETHERCAT-based equipment integrated control module and a control method, an EtherCAT communication circuit is connected with a CPU circuit through an SPI bus, an Ethernet communication circuit is connected with the CPU circuit through an SPI, and the CPU circuit is connected with an FPGA through an SPI bus and an FSMC bus; a constant current source circuit of the light source control unit is connected with an output pin of the FPGA, a multi-signal interface of the laser control unit is connected with a corresponding pin of the FPGA, and both the digital quantity input circuit and the digital quantity output circuit are connected with the FPGA. And the master station packages and sends instructions, analyzes and distributes the instructions, the FPGA generates control signals to drive each unit, and collects states and returns the states to the master station. High-speed cooperation is realized by utilizing ETHERCAT, multi-unit control is integrated, the precision and synchronism are improved, and precise synchronization of multiple links such as high-speed data transmission, low communication delay, light source control and laser control between a control module and a master station and between control units is realized.