ARINC429 Bus Research Articles

VHDL Design of ARINC 429 Bus Protocol

ARINC 429 is a data transfer standard for aircraft avionics which is also known as the Mark 33 DITS Specification (Digital Information Transfer System). It makes use of self-clocking and self-synchronizing techniques. ARINC-429 bus interface is used as a controlling function. It is a two-wire point-to-point serial data bus for control communications in avionics. The bus operates at the speed of 100kb/sec; the ARINC429 is developed to provide interchangeability and interoperability of line replaceable units (LRUs) in commercial aircraft. File transfer of ARINC 429 protocol is bit oriented, handshake between the transmitter and receiver units is necessary at the initial condition. Predefined codes are sent from the source initiates communication with the receiver to determine compatibility between the units required for successful transmission. FPGA implementation of bus protocol can be done , for this purpose SRAM memory is used to sort the data into the buffer and make use of the information whenever needed. In order to enhance the security during transmission converters and key can be used. It is one of the modern techniques used in aircrafts and military. Keywords: ARNIC429, LRU, independent transmitter and receiver Cite this Article J. Joshua Bapu, I.J. Divya Prasanna, M. Sheela Merlin . VHDL Design of ARINC 429 Bus Protocol. Journal of Aerospace Engineering and Technology. 2016; 6(2): 21–27p.

Architecture Design of Aviation Fault-tolerant Computer Based on ARINC659 Bus Technology

The ARINC659 backplane bus is suitable for high safety and high reliability requirements of aircraft on-board computer communication systems. This paper analyzes the structure of ARINC 659 serial backplane bus and the bus fault tolerance mechanism. On the basis of backplane bus, a 4 degree of aviation fault-tolerant computer is designed. Moreover, the computer architecture and computer system of the instruction branch and monitoring branch are designed in the computer channel. The fault-tolerant management of the computer is realized by bus fault tolerance, redundancy voting between computers and the monitoring of the instruction and monitoring branches.

ARINC659总线接口组件抗单粒子翻转加固设计及试验验证

ARINC659是一种标准的多点串行通信总线，具有通用、高效、高可靠等优点，已经越来越多地成为航天器综合电子系统计算机背板总线的理想选型。本文在对ARINC659总线架构和工作机制研究的基础上，对ARINC659总线标准背板总线组件在空间环境应用下的单粒子翻转效应敏感环节进行识别，并提出了有针对性的抗单粒子翻转加固设计措施，最后通过地面模拟试验对抗单粒子翻转加固措施的正确性和有效性进行了验证。试验表明进行单粒子翻转加固设计后的ARINC659总线接口组件满足辐照环境下的应用要求，为ARINC659总线应用于航天领域奠定了基础。 ARINC659 as a standard multipoint serial communication bus, and with the advantage of more general, high efficiency and reliability, has increasingly become the idea selection of backplane bus within the computer of spacecraft avionics system. This paper based on the study of ARINC659 bus architecture and underlying communication mechanism, identifies the sensitive of single event upset for ARINC659 bus interface components applied to space radiation environment, and a set of targeted reinforcement design is put forward for single event upset hardened. Finally, the correction and validity of the reinforcement design are verified by ground simulation experiment, which shows that ARINC659 bus interface components after reinforcement design meet the application in the radiation environment and provide the basis for the application of ARINC659 bus in aerospace.

Design of Civil Aircraft Avionics System Bus Excitation System

The avionics system is a core component of the civil aircraft. To reduce the risk and cost of developing avionics system, shorten the development cycle, through the development process of avionics systems, variety of simulation and verification must be done. The bus excitation signals need to be provided for each avionics unit and the signals from each avionics unit need to be received and processed. The multilayer abstract model and organizational structure model of the bus excitation system was established. And a complete bus excitation system was designed. In this system, the ARINC429 bus signals and discrete signals for communication and navigation equipments were provided, and the signals from the equipments were received and processed. This system has been tested, and one practical application example of the system was given.

Design of Flight Data Signal Generator System

Aiming at the problem that flight data recorder taken aircraft directly as testing signal resource in the process of development and debugging of the flight data recorder is very difficult, the flight data signal generator based on embedded system is designed, which purpose is to simulate the status signal of aircraft and each component of aircraft during flight, providing test signal source for flight data recorder. Interactive interface was designed on PC by LabVIEW, which was used for setting parameter values of each signal; STM32 microcontroller received the parameter value and controlled each generating module to generate electric signal. All generating modules link with the Bus network, and the network will be easy to increase or decrease generating module. Experiment results show that the flight data signal generating system can simultaneously generate 138 signals, including analog, digital, synchronous, frequency, ARINC429 bus signals etc, and can work stably.

Designing and Realizing of Universal Test and Analysis System of Avionics Data Bus

In modern combat aircrafts, avionics integrated systems play an increasingly important role. Bus test and analysis system is used as a testing platform for the testing, debugging, maintenance and monitoring of airborne electronic equipment, which could rapidly detect and identify the working status of the bus. This paper discusses the general avionics data bus test system design and implementation, which focuses on the test system design, system management, software development, and the bus information flow management of the whole system. The universal test and analysis system is based on the bus test analysis platform of ICD database that can effectively test ARINC429 bus and 1553B bus. Through integrating the platform into the simulation system, it can complete the closed-loop test of the integrated avionics simulation test system, analyze the state changes of various information flows during the process of bus communication, test and verify the active status and logical sequence of avionic fire control test systems, which has achieved very good results in the practical engineering applications.

한국형기동헬기 임무컴퓨터 비행필수기능 설계

Avionics system tends to be designed to have the integrated architecture, and it is getting difficult and complex to verify the flight-critical function because of sophisticated structure. In Korean Utility Helicopter, mission computer acts as the MUX Bus Controller to handle the data from both communication, identification, mission/display and survivability equipment inside Mission Equipment Package and aircraft subsystems such as fuel system and electrical system while it is interfacing with Automatic Flight Control System and Full-Authority Digital Engine Control via ARINC-429 bus. The Flight Displays which is classified as flight-critical function in aircraft is implemented on Primary Flight Display after mission computer processes data from AFCS in order to generate graphics. This paper defines the flight-critical function implemented in mission computer for KUH, and presents the static and dynamic test procedures which is performed on System Integration Laboratory along with Playback Recorder prior to flight test.

Research of the CCD Aerial Camera Manipulator System

Manipulator is the corollary equipment of the CCD aerial camera, which is mainly used to manage and control the main system of the aerial camera, receive the feedback information of the main system, and display the video image of the land object almost real time, and its performance will directly influence the working state of the CCD camera. The applications of the PC104 bus technology and the ARINC429 bus technology in the subsystem of the aerial camera manipulator are concisely introduced in this article, and the working flow of the display manipulator, the composing and working principle of the system are mainly discussed. Through the test-fly, the manipulator system could run stably, with advantages such as strong anti-jamming and high reliability.