44 results about "ARINC 429" patented technology

The invention discloses an automatic testing device and an automatic testing method of ARINC 429 bus signal performance parameters; the device comprises a test unit, a test adapter and corresponding software program, wherein the test unit consists of a power control box, a PXI test case, a signal conditioning box, a test interface array and an input-output device; all resource modules in the test unit can be used for running a test program of the test unit by testing software under the control of a PXI control computer through a PXI bus; the adapter is meshed with an RCV end by an ITA end of a test array, and is connected with test resource modules on the test unit; and the testing software comprises two parts including testing software of the test unit and testing software specially used for the adapter. After the invention is adopted, the quality level of an ARINC 429 bus signal module product can be improved, the development of a special test device is omitted, and the development cost and the maintenance cost of the test device can be greatly lowered.

An ARINC429 data bus simulation test system belongs to the technical field of simulation test. It is characterized in that the ARINC429 data bus simulation and test environment is formed by the simulation controller [1], the data transmission and control bus [2], the ARINC 429 communication interface [3] and the ARINC 429 interface adapter [4], and the simulation controller [ 1] Through data transmission and control bus [2] control ARINC429 communication interface [3] to realize the transmission and reception of data information, simulate the generation and transmission process of information flow of airborne equipment such as airborne flight control system and avionics system, and receive Other airborne equipment information flow and display. The invention has the advantages of complete system function, reasonable layout, compact structure, reliable operation, convenient use, good expansibility and tailorability.

An optical communications link for an electrical communications system, e.g., an ARINC 429 protocol system, includes a first logic device to convert an input signal of a given level to a first electrical signal of a duration corresponding to such level, a first optical device (transmitter) presenting an optical signal of a duration corresponding to such first electrical signal, a second optical device (receiver) to convert the optical signal to a second electrical signal of a duration representative of the duration of the optical signal, an optical coupling between the optical devices, and a second logic device to convert the second electrical signal to an output electrical signal having a level representative of the duration of the optical signal. A communications system including electrical communications input and output devices, the optical and an optical communications link coupled between those devices. A method of coupling electrical signals includes converting or encoding electrical signals that are provided at multiple levels in an electrical communications system to optical signals that have a duration respectively representative of the corresponding electrical signal level, transmitting the optical signals, and decoding the optical signals. The converting / encoding and the decoding may be accomplished using hardware logic without the need for a processor and associated software.

The invention relates to an aircraft CFDS (Centralized Fault Display System) data analyzer and an implementation method thereof. Firstly, the CFDS monitoring status of a line replaceable unit on an aircraft is simulated in an infield workshop; secondly, the LRU (Least Recently Used) workshop test is completed in the infield test, and after the decoding analysis and verification, the test data aretransplanted into an aircraft CFDS data analyzer which consists of an ARINC (Aeronautical Radio Inc) 429 data analyzer and an industrial control mechanism and is communicated with a tested airborne system through an ARINC 429 channel and a discrete I / O channel, and thus the aircraft CFDS analysis is realized. The price of the aircraft CFDS data analyzer is low, the aircraft CFDS data analyzer is provided with a second development interface, and thus the aircraft CFDS data analyzer is easy to independently upgrade by the technicist, and the cost for software upgrading is greatly lowered. The aircraft CFDS data analyzer complies with a modern ATS design standard and can be conveniently transplanted into different automatic test systems, the maintenance resource is saved, abroad technical monopoly is broken, the cost of return for repair and the turnover time of aeronautical materials are effectively reduced, the abroad maintenance rate of part of aircraft components is lowered, and the enterprise competitiveness is improved.

The invention relates to the technical field of avionics, in particular to a multi-channel ARINC (aeronautical radio incorporated) 700 bus monitoring device and a realizing method thereof. The device comprises an industrial personal computer, a bus adapter and bus access equipment, wherein a multi-channel ARINC 429 bus module is arranged in the industrial personal computer; the bus adapter comprises a main board, a self-checking module, a power supply management module and a switch matrix module; and the bus access equipment comprises an aviation bus distribution frame and a ZIF (zero insertion force) interface. Control data and bus data are switched between the industrial personal computer and the bus access equipment through the bus adapter; the industrial personal computer transmits an instruction package to the bus adapter to finish instruction loading through the ZIF interface; a monitoring circuit is mounted on an aviation bus, so that the bus data can be read; when other buses need to be monitored, by only updating the loading instruction, the switching of the channel can be finished, which is convenient and rapid; the speed requirements in an automatic measuring and monitoring system can be fully satisfied; the testing time is greatly reduced; and the problem of wasting a large amount of bus channels in a complex avionics system is solved.

The invention provides methods, systems, and products for communicating between engine computers without the participation of a flight deck computer. The invention allows the engine computers to coordinate activities for real-time control of the engines for improved efficiency using an existing ARINC 429 communications bus. The invention facilitates cross-engine communications over the same ARINC 429 communications bus used for communicating with the Flight Deck Computer, without installation of a second, dedicated communications bus for cross-engine communications. The invention thus provides a cost effective way to allow the engines to coordinate activities without expensive installation and recertification of airframe modifications.

The invention discloses a navigation and interface computer based on dual-DSP and CPLD. The navigation and interface computer is applied to a rotary inertial navigation system constructed by a gyroscope taking RS-422 as the output, an accelerometer and an angular measurement device taking quadrature coding pulse as the output as well as other inertial navigation systems. The navigation and interface computer mainly comprises a DSP1 module, a DSP2 module, a CPLD module, a dual-port RAM module, an Ethernet interface module, a MIL-STD-1553B interface module, an ARINC-429 interface module and an expanded RS-422 interface module. The DSP1 module is mainly used for synchronous acquisition of inertial sensors and synchronous reading of the signal of the angular measurement device; the DSP2 module is mainly used for coordinated communication of the external MIL-STD-1553B, ARINC-429 and expanded RS-422; and the CPLD module is mainly used for signal acquisition of the angular measurement device and assistance of the DSP2 module. The navigation and interface computer disclosed by the invention is compact in circuit structure and high in expandability and can be widely applied to various inertial navigation systems.

The invention is applicable to the field of communication technology and provides a communication method based on an ARINC 429, a device thereof and an expansion interface. The method comprises a step of receiving a data sending request sent by an X86 system bus, a step of obtaining a data package bit number preset by an ARINC 429 transceiver and packaging the data to be sent to be a data package to be sent according to the data package bit number, a step of obtaining the identification number of the buffer area of the data package, obtaining a buffer area corresponding to identification number from a plurality of preset buffer areas according to the identification number, and storing the data package into the obtained buffer area, and a step of sending the data package into the obtained buffer area to the ARINC 429 transceiver. According to the communication method, the device and the expansion interface, the distinction of the buffer area by the identification number of the buffer area is realized, the isolation of buffer related in a data sending process and buffer related in a data receiving process of the ARINC 429 transceiver is realized at the same time, and the efficiency of data communication and communication reliability are improved.

The invention discloses an interface adaptation method and a circuit used for an airborne collision avoidance system, relates to an air collision avoidance technology, and aims to provide a data conversion method and a circuit based on an aerialcarrier platform. The technical note of the circuit provided by the invention is as follows: the circuit comprises an atmosphere height acquiring and coding module, a radio altitude acquiring and coding module, and a fly parameter data conversion module, wherein the atmosphere height acquiring and coding module is used for acquiring current atmosphere height value, and the atmosphere height value is changed into an ARINC 429 data format so as to be finally output to the airborne collision avoidance system; the radio altitude acquiring and coding module is used for acquiring current radio altitude value, and the radio altitude value is changed into the ARINC429 data format so as to be finally output to the airborne collision avoidance system; and the fly parameter data conversion module is used for collecting alarm information generated by the airborne collision avoidance system, the alarm information is subjected to digital-analog conversion so as to be finally output to an airplane reference record instrument. By using the method and the circuit provided by the invention, a compatible problem of the existing airplane and digital airborne collision avoidance system following a Russian-made protocol can be solved.

The invention discloses an ARINC 429 communication redundancy method based on a vxworks operation system, mainly solving the problems of unreliability, low instantaneity and complex design of the redundancy method in the existing instant communication system. The method of the invention has the follow realizing procedures: in an upper computer and a CPU communication system, the upper computer communicates with CPU via two independent ARINC 429 channels, namely a main channel A and a spare channel B; the working sequence and the transmitted data of the two channels are identical; CPU stores data received from the two channels via two different circular buffer zones; before receiving data each time, CPU calls a channel choice function; firstly, the channel choice function judges the number of bytes in the two buffer zones, and detects and chooses a channel according to different situations of the number of bytes in the two buffer zones. The method fully utilizes the circular buffer zone operation function in vxworks, and simplifies the process of anomaly detection and information synchronization to treat faults in time, so that the reliability and the instantaneity of the system can be ensured in software.

A protocol converter that translates the ARINC-429 protocol output of an Inertial Navigation System to the National Marine Electronics Association 0183 protocol. The protocol converter includes an ARINC-429 interface board with cable and software operating in a computer with at least one serial communications port. The software includes a protocol conversion program which is capable of outputting the NMEA-0183 protocol to as many as four serial communications ports simultaneously.

The invention provides a double-receiving double-emitting programmable ARINC 429 communication interface chip, and aims to provide a double-receiving double-emitting HT 429 communication chip which is fast in data transmission, stable and reliable in work and higher in universality. The technical scheme of the invention is that a controller CPU (Central Processing Unit) performs data communication with the HT 429 interface chip through a bothway tristate data bus and a three-bit address bus, and the controller CPU carries out read and write operation on a transmitting controller, a receiving control register, a bumper occupancy state register, a work state register and four data registers of a communication interface unit in the HT 429 chip through the address bus and the data bus; the HT 429 chip carries out odd-even check and volume label check on received data, and data in accordance with requirements are input into an ARINC 429 received data storage; the CPU carries out write operation on two ARINC 429 transmitting data storage FIFO through the communication interface unit of the HT 429 chip respectively, data emitting of two channels is finished, data receiving of the two channels is finished by reading the FIFO data, and the double-receiving double-emitting HT 429 communication chip is formed.

A protocol converter that translates the ARINC-429 protocol output of an Inertial Navigation System to the National Marine Electronics Association 0183 protocol. The protocol converter includes an ARINC-429 interface board with cable and software operating in a computer with at least one serial communications port. The software includes a protocol conversion program which is capable of outputting the NMEA-0183 protocol to as many as four serial communications ports simultaneously.

The invention provides methods, systems, and products for communicating between engine computers without the participation of a flight deck computer. The invention allows the engine computers to coordinate activities for real-time control of the engines for improved efficiency using an existing ARINC 429 communications bus. The invention facilitates cross-engine communications over the same ARINC 429 communications bus used for communicating with the Flight Deck Computer, without installation of a second, dedicated communications bus for cross-engine communications. The invention thus provides a cost effective way to allow the engines to coordinate activities without expensive installation and recertification of airframe modifications.

The invention discloses a high-speed ARINC429 data processing method based on FPGA. The method comprises steps that a CPU and FPGA coding and decoding unit and a transceiver driver unit are included,a channel of a transmission code, the rate and the transmission information are controlled by a CPU through a bus, the rate of receiving and decoding, odd-even check and LABEL number filtering are controlled, moreover, received data is extracted from the bus for analysis; encoding and decoding are performed by an FPGA encoding and decoding unit according to CPU setting, and LABEL hardware filtering is performed; a standard ARINC 429 signal is converted to a 3.3V TTL signal by the transceiver driver unit, and the 3.3V TTL signal is converted to the standard ARINC 429 signal. The method is advantaged in that CPU processing speed requirements are reduced, performance is improved by 1111 times, a system interface is simple and is convenient to control and use; a main body is implemented by theFPGA, configuration is flexible, and upgrade and expansion are convenient.

The invention provides a special-purpose comprehensive quality evaluation system for an aircraft ARINC429 bus. The system comprises a controller, a protocol layer test module, an electrical layer testmodule and a physical layer test module, wherein the protocol layer test module, the electrical layer test module and the physical layer test module are respectively connected to the controller. Theprotocol layer test module is used for detecting a bit error rate and a packet loss rate of an ARINC 429 bus signal based on an interface control file database; the electrical layer test module detects the electrical parameters of the ARINC 429 bus signal based on relevant clauses of the ARINC 429 specification; and the physical layer test module is used for testing connectivity of the ARINC 429 bus cable based on an spread spectrum time-domain reflectometry.

The invention discloses a multiprotocol isolation-type digital signal excitation source, which belongs to the technical field of embedded measurement. A control signal and a data signal are connected to bus signal transceivers (RS232(103), RS422(104), RS485(105), CAN bus transceiver (106) and ARINC-429 bus transceiver (108)) via input interfaces. The CAN bus transceiver (106) outputs the signals to a CAN bus driver (107). The ARINC-429 bus transceiver (108) outputs the signals to an ARINC-429 bus driver (109) via a signal isolation circuit (110). Output ends of the RS232(103) bus signal transceiver, the RS422(104) bus signal transceiver, the RS485(105) bus signal transceiver, the CAN bus driver (107) and the ARINC-429 bus driver (109) are connected onto an FPGA (111) via a level conversion circuit (112), the FPGA (111) is internally provided with a data processing circuit and an embedded soft core processor, the processor caches the data to an SDRAM, the data are transmitted to a host terminal (113) via the RS485 transmitting and receiving circuit (105) from the SDRAM, and the core processor is an nios processor. Signal parameters are programmable, signals are mutually electrically isolated, and the data transmission stability can be improved.

The invention discloses integrated multi-channel DVI video distribution equipment. The equipment comprises an ARINC 429 bus controller, an FPGA overall control module, a DVI interface protection unit, an equalization adjustment unit, a DVI selection and distribution unit, a DVI distribution unit, and a power conversion unit, wherein the DVI interface protection unit comprises 14 independent DVI interface protection modules; the equalization adjustment unit comprises 7 independent equalization adjustment modules; the DVI selection and distribution unit comprises 5 independent DVI selection and distribution modules; the DVI distribution unit comprises 2 independent DVI distribution modules; and the power conversion unit comprises a power conversion module and a secondary power conversion module. The equipment is additionally mounted between a DPU and an airborne display, and has the advantages that the requirement for video signal extraction of a 5-channel airborne flight display and a 2-channel head-up display of a certain airplane model is satisfied, the function of multi-channel DVI video distribution is achieved, and a same DVI video signal can be simultaneously displayed and acquired at a back end.

The invention belongs to a touching-type simulator for a store management system, which is used during ground power-on check of a helicopter avionics system. The simulator comprises a DC / DC conversion module (1), a touch screen (2), a PC 104 module (3), an ARINC 429 communication board (4), an RS 422 communication board (5) and a KVM external member (6). The simulator can simulate ARINC 429 and RS 422 signals of various external store devices crosslinked with a store management unit, receive ARINC 429 and RS 422 signals from the store management unit, and can replace various external store devices and special testers to participate in the ground power-on test of the system.

The invention, which belongs to the technical field of electronic communication, relates to an integrated-packaging-based multifunctional interface circuit. The circuit comprises a level conversion unit, a switching value control unit, an optocoupler signal isolation unit, an LVDS transceiver unit, an RS-422 communication interface transceiver unit, an ARINC 429 bus interface transceiver unit, anda 1553B bus communication control unit. On the basis of the integrated packaging, single-cavity multi-layer wiring integration of a plurality of components is realized; because all function units arepackaged into one cavity, compared with the existing packaging system structure, the circuit is integrated with multiple functions with a reduced circuit packaging dimension; and the requirement of the H standard military quality level in the GJB2438A-2002 "hybrid integrated circuit general specifications" can be met.

The invention belongs to the technical field of computers, specifically belongs to the field of embedded one-board computers and particularly relates to a one-board computer integrated with various bus multifunction modules. The one-board computer comprises a shell, a processor, a complex programmable logic device, a local bus and a peripheral interface, wherein the processor, the complex programmable logic device, the local bus and the peripheral interface are arranged on a circuit board in the shell; the complex programmable logic device and the local bus are mutually connected and are respectively connected with the processor; the local bus is also connected with a 1553B bus and an ARINC-429 bus; the local bus is connected with the peripheral interface through the 1553B bus; one end of the ARINC-429 bus is connected with the peripheral interface, and the other end of the ARINC-429 bus is connected with the local bus through a field-programmable gate array. According to the one-board computer provided by the invention, on the basis that combination functions of three computer integrated boards are realized, by matching a storage element and interface equipment, the three computer integrated boards are integrated, and therefore, the 3UCPCI multifunctional one-board computer is realized; meanwhile, the goals that the power consumption is reduced, space is saved and the cost is reduced are achieved.

The invention belongs to the technical field of avionics, and relates to a comprehensive protection type audio / video recorder which comprises a main control module, a power supply module and an anti-crash protection component, wherein the power supply module is connected with the main control module and is used for supplying power to the main control module; the main control module is connected with the anti-crash protection component; the main control module is further connected with a plane bus through an AFDX (Avionics Full-Duplex Ethernet) bus and an ARINC-429 (Aeronautical Radio Incorporation) bus; the AFDX bus is connected with a plane digital camera, ground maintenance equipment and a software loader respectively, and is connected with a plane digital sound picker through a cabin sound data wire. The comprehensive protection type audio / video recorder has an AFDX bus interface, so that digital voice data can be acquired; due to the ARINC-429 bus, UTC (Universal Time Code) time can be acquired, the Beijing time and the UTC time are recorded in each data frame, and thus multi-channel data synchronism can be conveniently achieved; meanwhile, the system is capable of acquiring audio data and video data which are both digital signals; in addition, the universality is improved as power is supplied through 115AC and 28VDC; lightning protection circuits are designed for external interfaces, so that lightning indirect effects can be prevented.

A flight data recorder (FDR) may include a script engine configured to run an algorithm in order to obtain, analyze and use FDR and Cockpit Voice and Data Recorder (CVDR) data for non-Technical Standard Orders (TSO) applications. The script engine may be configured, by the algorithm, to analyze flight data received by the FDR and use the flight data to output a trigger via an Ethernet port or an ARINC 429 output. The script engine may also analyze the flight data and stream at least a portion of the flight data via the Ethernet port or the ARINC port.

The invention belongs to the technical field of avionics and relates to a miniature caching recorder for civil aviation. The miniature caching recorder comprises a case part, an aviation connector, a data management module and a battery, wherein the aviation connector is mounted at the physical center of the back of the case part, is used for being connected with aircraft equipment and plays a structural support role; the data management module and the battery are mounted in the case part, and the data management module is connected with the aviation connector. The miniature caching recorder has the advantages that the miniature caching recorder is connected with a universal computer through a USB interface, the miniature caching recorder can become a removable storage medium, and accordingly direct data reading is achieved; the battery is designed in the miniature caching recorder, and the battery can supply power for the miniature caching recorder when external power supply fails; the ARINC-717 and ARINC-429 interfaces used by the miniature caching recorder are directly connected with an ARM microprocessor through a SPI interface, an situation that originally the ARINC-717 and ARINC-429 interfaces can only be connected with the ARM microprocessor through FPGA is changed, part module volume is reduced, and circuit design is simplified.

The invention provides a self-checking system and method for an Arinc 429 communication system. The method comprises detecting the hardware part of the Arinc 429 communication system, monitoring the hardware configuration of the Arinc 429 communication system, and monitoring the interface communication data of the Arinc 429 communication system. The system and method may achieve complete Arinc 429 communication system monitoring and hardware configuration recovery, rapidly and online eliminate restorable faults of the Arinc 429 communication system, position the faults of the Arinc 429 communication system in detail, enhance the reliability and the maintainability of the Arinc 429 communication system, and satisfy requirements of avionics system integration.

The present invention provides a system and method for improving Arinc 429 communication system reliability. The system comprises a first Arinc 429 communication system and a second Arinc 429 communication system that are independent of each other. The method comprises: monitoring in real time whether a currently used communication system among the two independent Arinc 429 communication systems encounters a fault; if a fault occurs, online recovering the faulty Arinc 429 communication system; if the recovery is successful, terminating the process; and if the recovery is unsuccessful, starting the other Arinc 429 communication system. According to the present invention, the reliability of the Arinc 429 communication system in a traffic alert collision avoidance system II (TCAS II), the problem that after an Arinc 429 communication system encounters a hardware fault and theus the TCAS II communication fails is solved, and further the problem that the TACS loses its normal functions when the configuration region of the Arinc 429 communication system fails in a complicated electromagnetic environment or under the single particle reverse effect is solved.

The invention provides a data format conversion device and an airborne electronic mission system. The data format conversion device comprises: a data collection unit; a flow control unit connected with the data collection unit; and an interface conversion unit connected with the flow control unit, wherein the data collection unit is used for collecting and obtaining ARINC-429 format downlink data of an inertial navigation system, the flow control unit is used for obtaining the ARINC-429 format downlink data from the data collection unit and converting the ARINC-429 format downlink data into RS-232 format downlink data, and the interface conversion unit is used for obtaining the RS-232 format downlink data from the flow control unit and converting the RS-232 format downlink data into RS-422 format downlink data.

The invention discloses a distributed air data system, which includes left and right multifunctional probe sensors, left and right L-shaped pressure sensor components, up and down angle of attack sensors, sideslip angle sensors and a total temperature sensor; , the right multi-function probe sensor provides a set of total, static pressure and local angle of attack signals to the left and right L-shaped pressure sensor components, and provides dynamic and static pressure signals in the form of analog quantities and two sets of angle of attack to the flight control computer signal, the left and right multi-function probe sensors receive the slip angle signals from the left and right L-shaped pressure sensor components for parameter correction; the left and right L-shaped pressure sensor components receive the slip angle signals from the upper and lower angle-of-attack sensors Calculate the angle of attack from the pressure signal, collect the side-slip angle signal from the side-slip angle sensor, calculate various atmospheric parameters through voting and correction, and provide them to the airborne transponder, inertial navigation system, electromechanical management computer and Flight parameter collector. Compared with the independent sensor solution, the present invention can reduce two pieces of equipment, improve the system integration degree, and reduce the total amount of the system.

The invention belongs to the technical field of avionics, and particularly relates to a triaxial accelerometer and an impact detecting switch. The triaxial accelerometer and the impact detecting switch comprise a power module, an acceleration collecting board, and a data collecting board. The power module is connected with an external power source and an external button reset switch, and externally outputs power, and is connected to the acceleration collecting board and the data collecting board. The acceleration collecting board is connected to the data collecting board through a parallel busand outputs an acceleration signal to the data collecting board. The data collecting board comprises a microprocessor circuit and an A / D conversion circuit. According to the triaxial accelerometer and the impact detecting switch, the collected aircraft lateral, bus and normal acceleration can be output through an analog quantity, and can also be converted into a digital signal and output throughthe ARINC-429 bus and the AFDX bus which can adapt to multiple aircraft requirements, so that the maintainability of the equipment is improved; and two airborne devices are integrated, so that the total weight of the products is reduced.

The invention discloses a test platform of a bleed air monitoring computer, which comprises a test platform body and control software, wherein the software is matched with the test platform and accords with an ARINC (Aeronautical Radio Incorporated) 429 protocol; a panel of the test platform body is provided with discrete signal switches, test holes, status indicator lamps, a socket and a connector; and the test platform body provides a power supply signal, analog input, discrete signal input and input of an ARINC 429 data signal, converts a discrete signal output by a UUT (Unit Under Test) and the ARINC 429 data signal into output signals of the status indicator lamps and the socket for output, and performs an electrical test on a transmission channel. Compared with the existing test platform, the test platform is very simple in overall structure; since the test platform adopts a digital technology, and the related electronic devices are ordinary electronic components, the manufacturing cost and the maintenance cost of the test platform are very low, and are lowered greatly in comparison with the prior art.