Distributed large airplane flap control computer system

A control computer, distributed technology, applied in aircraft control, aircraft parts, aircraft transmissions, etc., can solve the problem that the shape of the inner and outer sections of the wing is very different, cannot achieve modularization and reuse, and increase the system design and efficiency. Installation difficulty, etc.

Active Publication Date: 2015-04-22
AVIC NO 631 RES INST
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The synchronization of the movement of the left and right airfoils is ensured by the method of sharing the mechanical transmission shaft. However, the shape of the inner section and the outer section of the wing is very different. Design and Installation Difficulty
In addition, in order to adapt to the deformation of the wing, the transmission

Method used

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  • Distributed large airplane flap control computer system
  • Distributed large airplane flap control computer system
  • Distributed large airplane flap control computer system

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Embodiment Construction

[0017] The system of the present invention consists of flap slat control computer (abbreviated SFCC), actuator control electronic unit (abbreviated ACE), power drive unit (abbreviated PDU), flap control handle sensor, flap position sensor, slat position sensor, It consists of flap tilt sensor, slat tilt sensor and other components. The system adopts a distributed fault-tolerant and management system architecture. The flaps and slats control computer collects the control handle sensor instructions and the information of the wing surface tilt sensor. The actuator control electronic unit collects the position information of the controlled airfoil. The flaps and slats control computer and the operating The data communication between the actuator control electronic units is carried out through the high-integrity data bus. The flap and slat control computer collects the position information of the control handle and the relevant airfoil position information, and after the control la...

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Abstract

The invention provides a distributed large airplane flap control computer system. The system includes a flap and slat control computer, an actuator control electronic unit, a power drive device, a flap and slat control handle sensor, a flap position sensor, a slat position sensor, a flap inclination sensor and a slat inclination sensor; and the flap and slat computer acquires the instruction of the flap and slat control handle sensor and information of the slat inclination sensor, the actuator control electronic unit acquires the position information of a controlled slat surface, and the flap and slat control computer is in data communication with the actuator control electronic unit via a high integrity data bus. The distributed large airplane flap fly-by-wire control fault-tolerant computer system meets different large airplanes' needs of control calculation and execution mechanism configurable management, and has the advantages of high reliability, configurability and upgradability.

Description

technical field [0001] The invention belongs to the field of aircraft avionics system design, and relates to the design of a large-scale aircraft flight control system flap and slat telex control computer system. Background technique [0002] Modern large aircraft are equipped with high-lift devices, including slats on the leading edge of the wing and flaps on the trailing edge. In low-speed states such as take-off and landing, the leading-edge slats and trailing-edge flaps protrude outward, bend downward to increase the surface area of ​​the wing, change the airfoil, and improve the lift of the aircraft to ensure a reasonable sliding distance and Safe take-off speed, while improving aircraft climb rate, approach speed and approach flight attitude. [0003] The closed-loop control of the flaps and slats of the aircraft is carried out by the computer system to realize the automatic flaps and slats function, which improves the control accuracy and the robustness of the system...

Claims

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Application Information

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IPC IPC(8): B64C13/50B64C13/00
Inventor 徐奡林坚夏德天解文涛郑久寿康晓东
Owner AVIC NO 631 RES INST
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