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FADEC and avionic component distributed architecture

A technology for avionics and components, applied in the field of avionics systems, can solve the problems of education and development lag, high development, integration and maintenance costs, and achieve the effect of optimizing development and maintenance time and cost

Active Publication Date: 2010-08-18
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

however, the advent of these new technologies, concepts, and new avionics systems has resulted in education and development lags, and high development, integration, and maintenance costs

Method used

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  • FADEC and avionic component distributed architecture
  • FADEC and avionic component distributed architecture
  • FADEC and avionic component distributed architecture

Examples

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Embodiment Construction

[0022] According to the method of the invention, it is possible to distribute the functions traditionally implemented in the FADEC between the avionics module and the FADEC, so as to simplify the FADEC and its software. This approach can focus on the exchange of avionics data between the FADEC and the avionics assembly.

[0023] In particular, the object of the invention is to transfer the power supply functions, the avionics data transfer functions to the FADEC, and the engine-related data transfer functions to the avionics package, and the functions related to thrust reversing from the FADEC to the avionics Component transfer.

[0024] FADEC is mainly composed of the following two components,

[0025] -Engine Control Unit, also known as ECU (an acronym for the Old English term Engine Control Unit), or Engine Electronic Controller, also known as EEC (an acronym for the Old English term Electronic Engine Control). In the following description, this element is generally refer...

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PUM

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Abstract

The invention relates to a device for motorized aircraft comprising at least one avionic component (300) positioned in the said aircraft, at least one engine interface (310) positioned in the said aircraft and at least one engine controller (315) positioned in or near an engine (320) of the said aircraft. According to the device of the invention, the said at least one engine interface (310) is designed to exchange data between the said at least one avionic component (300) and the said at least one engine controller (315). The said at least one engine interface (310) is generic and able to communicate with engine controllers (315) of various types that may be mounted on said aircraft. The said at least one engine controller is specific to a particular engine.

Description

technical field [0001] The present invention relates to avionics systems, and more particularly to an arrangement according to which the functionality of a FADEC is distributed between the FADEC itself and the avionics assembly. Background technique [0002] The electronic equipment and avionics systems currently carried are becoming more and more complex, with better performance, integrating many advanced functions, and increasing the interconnection between systems. [0003] These on-board avionics systems are highly integrated, based on hardware, software and a shared transmission network, which intensifies and complicates the constant pace of technological progress and opens up new prospects for aircraft manufacturers. However, the advent of these new technologies, concepts, and new avionics systems has resulted in education and development lags and high development, integration, and maintenance costs. [0004] In particular, the avionics system can be distinguished fro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D31/00
CPCB64D31/00B64D43/00
Inventor L·圣马克L·布吕内尔P·扎卡里亚M·亚历山大J·费奥F·勒博尔纳T·伊莫尔迪诺J-F·贝尔卡迪N·迪朗
Owner AIRBUS OPERATIONS GMBH
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