All-electric aircraft brake system and aircraft electric brake redundancy control method

A control method and electric braking technology, applied in aircraft braking arrangements, brakes, vehicle components, etc., can solve the problems of redundant design of control units, difficult system reliability, etc., and achieve the effect of ensuring independence

Active Publication Date: 2015-07-22
东莞市三航军民融合创新研究院
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  • Application Information

AI Technical Summary

Problems solved by technology

The patent "A Double Redundancy Electric Braking Device and Control Method for Aircraft" (publication number CN 102700542 A) only makes a redundant design for the electromechanical actuator, but does not carry out a redundant design for the weak control unit, so it is difficult to guarantee The system is reliable enough

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  • All-electric aircraft brake system and aircraft electric brake redundancy control method
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  • All-electric aircraft brake system and aircraft electric brake redundancy control method

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Embodiment Construction

[0022] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0023] The all-electric braking system of the present invention includes a Brake Control Unit (BCU), an Electro-Mechanical Actuator Controller (EMAC) and an Electro-Mechanical Actuator (EMA). Among them, the BCU is used to notify the EMAC to turn off the stop switch before starting to brake, the electromagnetic clutch is unlocked, and perform normal braking; after the brake is completed, the BCU notifies the EMAC to turn on the stop switch, and the electromagnetic clutch is locked to prevent the aircraft from moving; Generate antiskid control command. The EMAC includes a control unit (DSP+CPLD) and a drive circuit for controlling and driving the motor in the EMA. The EMA includes a motor, a force sensor, and a Hall position sensor, which are used to convert the rotational motion of the motor into linear motion, generate brake pressure, and collect the brake pres...

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Abstract

The invention discloses an all-electric aircraft brake system and an aircraft electric brake redundancy control method. Redundancy design is performed for elements, easy to damage, of a brake system, and drive control can simultaneously drive EMAs (electro-mechanical actuators) of four channels to actuate; a core control unit including DSPs (digital signal processors) and CPLDs (complex programmable logic devices) adopts double-redundancy design, and an electric circuit adopts four-redundancy design; power-driven circuits, motors, force sensors and Hall position sensors of a channel A and a channel B are divided into one group, and a 1#DSP and a 1#CPLD are taken as primary control units; power-driven circuits, motors and force sensors of a channel C and a channel D are divided into the other group, and a 2#DSP and a 2#CPLD are taken as secondary control units; the primary and secondary control units simultaneously drive the EMAs of the four channels to actuate. Double redundancy of the control units and four redundancy of the drive units are realized; the 1#DSP and the 2#DSP communicate with each other through an SPI (serial peripheral interface).

Description

technical field [0001] The invention belongs to the field of automatic control, and in particular relates to an aircraft all-electric braking system and an aircraft electric braking redundancy control method. Background technique [0002] The aircraft braking system is a subsystem with relatively independent functions on the aircraft. Its function is to absorb the kinetic energy of the aircraft during landing and taxiing, so that the aircraft can brake quickly and safely. The all-electric brake system is to use the motor drive device to drive the brake actuator, and use the electronic transmission line to replace the original oil pipeline to realize the brake control function of the brake. The all-electric braking system has better maintainability and excellent potential braking performance, which can greatly reduce the weight of the system. However, due to the addition of many components, the system must be designed redundantly to ensure its safety and reliability. [000...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/42B60T13/74B60T8/17
Inventor 相里康马瑞卿张庆超韩伟健
Owner 东莞市三航军民融合创新研究院
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