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Control method of data stream of avionics system of civil light airplane

A technology for avionics systems and small aircraft, applied in transmission systems, digital transmission systems, data exchange networks, etc., to achieve real-time transmission, low cost, and good scalability

Active Publication Date: 2011-05-04
AVIC NO 631 RES INST
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  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The present invention aims to provide a data flow control method for civil small aircraft avionics system to solve the problems of real-time and fault-tolerant control of internal data flow control in the integrated avionics system in the prior art

Method used

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  • Control method of data stream of avionics system of civil light airplane
  • Control method of data stream of avionics system of civil light airplane
  • Control method of data stream of avionics system of civil light airplane

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Embodiment Construction

[0019] Below the utility model is described in further detail. see figure 1 , the civil avionics system of the present invention comprises a main flight display (PFD), a multi-function display (MFD), two integrated processors (integrated processor 1 and integrated processor 2), and some sensor devices . The main flight display and the multi-function display, the main flight display and the integrated processor 1, and the multi-function display and the integrated processor 2 are all connected through Ethernet; the plurality of sensor devices all have four signal output terminals, and are connected through IEEE The -422 interface or the ARINC429 interface is connected with the integrated processor 1, the integrated processor 2, the main flight display, and the multi-function display; the integrated processor 1 and the integrated processor 2 are also connected through the IEEE-422 interface or the ARINC429 interface.

[0020] The operation of the avionics system adopts error co...

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Abstract

The invention aims to provide a control method of data streams of an avionics system of a civil light airplane to solve the problems in the aspects of control real-time, fault-tolerant control and the like of internal data streams of an integrated avionics system in the prior art. The control method comprises the following steps of: firstly, classifying the data streams inside the avionics system of the light airplane into four types, and defining functions and data types of each data field inside the data streams; secondly, according to different attributes of transmission events, dividing each data frame into a periodic type and a conditional type; thirdly, determining different communication cycles, rates and error correction modes; and finally, establishing a standard framework of network transmissions among a main flight display, a multifunctional display, a first integrated processor, a second integrated processor and a plurality of sensors. The control method not only meets requirements on system real-time and reliability, but also has high expandability, supports data channel compounding and data fusion of a plurality of sensors, is low in cost and high in universality, and is widely applied to various integrated display control unit configurations.

Description

technical field [0001] The invention relates to a real-time and fault-tolerant control mode of data in an avionics system, in particular to a data flow control method of an avionics system of a civil small aircraft. Background technique [0002] With the continuous development of civil aircraft avionics systems, more and more electronic devices are integrated, the devices are interconnected and the amount of data transmitted is huge, especially after the comprehensive design is adopted, the amount of data interacted between devices is in series Ascending, how to ensure the real-time performance of such massive data transmission, and how to ensure the reliability of data between devices, these problems need to be solved urgently. [0003] Civil avionics systems generally include a primary flight display (PFD), a multi-function display (MFD), and two integrated processors (the first integrated processor corresponding to the PFD, the second integrated processor corresponding to...

Claims

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Application Information

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IPC IPC(8): H04L12/56H04L1/00H04L29/06H04L12/801
Inventor 张磊张双刘文刘硕朱朝
Owner AVIC NO 631 RES INST
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