Dual-redundancy aircraft fuel remaining amount measuring system

A measurement system and dual-redundancy technology, applied in the direction of relative volume flow measurement, measurement devices, aircraft parts, etc., can solve the problem of affecting the execution of aircraft tasks, the failure of the electromechanical management computer to receive and display the remaining fuel of the whole machine, and the remaining fuel of the whole machine Quantity display errors and other issues

Pending Publication Date: 2021-01-12
JIANGXI HONGDU AVIATION IND GRP
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  • Abstract
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  • Application Information

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Problems solved by technology

[0003] If there is a flow sensor failure, a fuel computer failure, or a communication failure between the fuel computer and the electromechanical management computer, the electromechanical management computer cann

Method used

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  • Dual-redundancy aircraft fuel remaining amount measuring system

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Embodiment Construction

[0013] The following will combine figure 1 , clearly and completely describe the technical solutions in the embodiments of the present invention.

[0014] Such as figure 1 As shown, the left oil flow sensor 3 and the right oil flow sensor 4 installed on the left and right main oil supply pipelines, when the fuel flows through the left oil flow sensor 3 and the right oil flow sensor 4, the flow sensor The turbine rotates, and the internal signal conversion device converts the turbine rotation into a pulse signal output. The fuel computer 2 first receives the preset data of the whole machine fuel quantity, and then collects the output signals of the left fuel flow sensor 3 and the right fuel flow sensor 4, and obtains the aircraft fuel remaining value through calculation and data processing. Simultaneously, the fuel balance value of the aircraft is transmitted to the electromechanical management computer 1 through the RS-422A serial communication interface, and finally display...

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Abstract

The invention provides a dual-redundancy aircraft fuel remaining amount measuring system. The dual-redundancy aircraft fuel remaining amount measuring system comprises an electromechanical managementcomputer (1), a fuel computer (2), a left oil way flow sensor (3), a right oil way flow sensor (4), a comprehensive display (5), a left engine fuel flow meter (6), a right engine fuel flow meter (7) and an electronic control device (8), the fuel computer (2) collects and calculates the numerical values of the left oil path flow sensor (3) and the right oil path flow sensor (4), and obtains the aircraft fuel remaining amount value through comprehensive calculation; when the loop breaks down, subsequent airplane fuel remaining amount values are obtained through comprehensive calculation of the electromechanical management computer (1) after the numerical values measured by the left engine fuel flow meter (6) and the right engine fuel flow meter (7) are subjected to signal conversion of the electronic control device (8). The system is correct in principle and simple in composition, and the safety redundancy of the system is effectively improved.

Description

technical field [0001] The invention belongs to the field of aviation machinery control, in particular to a dual-redundancy aircraft fuel residual measurement system. Background technique [0002] The fuel in the aircraft fuel tank is directly supplied to the engine through the fuel supply pipeline, and each fuel supply pipeline is equipped with a flow sensor to receive and transmit the fuel consumption of the engine. The set value calculates the remaining oil quantity of the whole machine and sends it to the electromechanical management computer for display on the multi-function display. [0003] If there is a flow sensor failure, a fuel computer failure, or a communication failure between the fuel computer and the electromechanical management computer, the electromechanical management computer cannot receive and display the remaining fuel volume output by the fuel computer, resulting in an error in the display of the remaining fuel volume in the cockpit, and eventually af...

Claims

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Application Information

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IPC IPC(8): B64D37/00B64D43/00G01F9/00
CPCB64D37/005B64D43/00G01F9/00
Inventor 谢艳娇彭克顺古远康黄华陈雄昕雷明章韩亦俍罗敏
Owner JIANGXI HONGDU AVIATION IND GRP
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