Method for obtaining and protecting piston position of aircraft electric brake actuator

A piston position and actuator technology, applied in the direction of brakes, brake transmissions, vehicle components, etc., can solve the problems of piston jamming, errors, and failure to guarantee the output of actuators, etc., to achieve the effect of avoiding jamming

Inactive Publication Date: 2014-04-09
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the inevitable error in the controller's acquisition of the feedback signal of the pressure sensor, it is difficult to determine the given value of the braking force at zero.
If the given value is too large, the output of the actuator cannot be guaranteed to be zero; if it is too small, the piston will also be stuck in the actuator due to continuous backward movement

Method used

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  • Method for obtaining and protecting piston position of aircraft electric brake actuator
  • Method for obtaining and protecting piston position of aircraft electric brake actuator
  • Method for obtaining and protecting piston position of aircraft electric brake actuator

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Embodiment Construction

[0035] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0036] The structure of the electromechanical actuator in the aircraft electric braking system is as follows: figure 2 As shown, the actuator is mainly composed of a brake disc, a brake static disc, a piston, a ball screw, a reduction gear and a brushless DC motor. The number of pole pairs of the motor is 3, and its Hall position sensor is located at the rear end of the motor. .

[0037] The structure of the brushless DC motor drive controller is as follows: image 3 As shown, the main power part adopts a three-phase full-bridge inverter, the DC bus voltage is 160V, the power switch tube adopts N-channel power MOSFET, the switching frequency is set to 20kHz, and the driver chip adopts IR2130. The control unit is powered by 28V, uses TMS320F2812 as the main control chip, uses its on-chip analog-to-digital converter to collect the feedback signal of the pressure...

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Abstract

The invention relates to a method for obtaining and protecting the piston position of an aircraft electric brake actuator. According to the method, position information of a piston can be obtained in real time in the working process of an aircraft brake system, and therefore the problems that the piston easily exerts force in the reverse direction to be stuck when the actuator is in the zero alignment process and the deep skid resistance process can be effectively solved, and the strong support is provided for stable and reliable running of the aircraft electric brake system.

Description

technical field [0001] The invention relates to an aircraft electric brake system, in particular to a method for obtaining and protecting the position of a piston of an aircraft electric brake actuator. Background technique [0002] The brake system is an important subsystem of the aircraft, and its function is to ensure the safety of the aircraft's take-off and landing, and on this basis to shorten the taxiing distance of the aircraft as much as possible when landing. [0003] The all-electric braking system is a new generation of aircraft braking system developed domestically and internationally. It replaces the hydraulic actuating mechanism of the existing braking system with an electromechanical actuating mechanism. Both control signals and power signals are transmitted through electricity, and no hydraulic pipelines, Hydraulic components such as pumps and valves. [0004] In the aircraft electric braking system, the output and unloading force of the electromechanical a...

Claims

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Application Information

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IPC IPC(8): B60T13/74B60T17/22
Inventor 马瑞卿韩伟健张庆超相里康刘青
Owner NORTHWESTERN POLYTECHNICAL UNIV
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