Actuator of airplane electric braking device

A technology of electric brakes and actuators, applied in the direction of brakes, brake transmission devices, vehicle components, etc., can solve the problems of complex structure, low transmission efficiency, and inability to realize closed-loop control, etc., and achieve the effect of high transmission efficiency and simple structure

Active Publication Date: 2014-03-26
XIAN AVIATION BRAKE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to overcome the deficiencies in the prior art, such as low transmission efficiency, complex structure, inability to amplify the outpu

Method used

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  • Actuator of airplane electric braking device
  • Actuator of airplane electric braking device
  • Actuator of airplane electric braking device

Examples

Experimental program
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Embodiment Construction

[0032] This embodiment is an electric brake actuator for an aircraft, including a housing, an end cover 3, a motor 4, a ball screw assembly, a force sensor 6, a needle bearing 7, a reduction gear assembly 8, a guide rod 9, and a piston 11 , heat insulation pad 12, signal processor 13 and plug assembly 14.

[0033] The piston 11 is installed in the middle housing 2 and the lower housing 10 , and is sealed with the middle housing 2 and the lower housing 10 by a sealing ring 5 . The ball screw assembly is installed in the piston 11 , and the ball nut 19 in the ball screw assembly is in clearance fit with the inner surface of the piston 11 . The top end of the ball screw is located in the upper casing 1 and cooperates with the upper casing 1 through a bearing. Ball screws 18 are located inside ball nuts 19 and mesh with each other. The guide rod 9 is located in the upper housing 1, and is fitted into the inner hole of the ball screw 18, and the two are slidingly fitted. The hea...

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PUM

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Abstract

Disclosed is an actuator of an airplane electric braking device, a reduction gear assembly and a ball screw assembly are arranged in a shell. A second gear of the reduction gear assembly is meshed with a ball screw assembly gear of the ball screw assembly, and a first gear of the reduction gear assembly is meshed with an output shaft of a motor. A wire of the motor and a wire of the output end of a signal processor are led out through a plug assembly. A data line of a force sensor is connected with a data input port of the signal processor. A piston is arranged in a middle shell and a lower shell in a sealed mode. The ball screw assembly is arranged in the piston. By controlling the motor to produce corresponding rotating torque, amplifying the rotating torque through the reduction gear assembly, and converting rotating motion into linear motion to conduct outputting through a ball screw and then into a thrust force required by braking, the defects in the prior art are overcome, the structure is simple, transmission efficiency is high, and closed-loop control over an electro-mechanical actuator is achieved.

Description

technical field [0001] The invention relates to an aircraft brake device, in particular to an actuator for an aircraft electric brake device. Background technique [0002] Aircraft brakes provide braking torque for aircraft braking, mainly including hydraulic brakes and electric brakes. The electric braking device provides the braking thrust by the actuator. [0003] At present, domestic aircraft brake devices all use hydraulic brake devices, which generally provide hydraulic power through the centralized hydraulic system of the aircraft, and the hydraulic pistons connected in series on the brake device generate the required force for braking, but there will be brakes during use. The problem of fire caused by hydraulic oil leakage. [0004] Publication No. CN03249715.6 proposes an electromechanical actuator that converts rotary motion into linear reciprocating motion by a motor through a transmission drive mechanism and an executive mechanism. The electromechanical actuat...

Claims

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Application Information

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IPC IPC(8): B60T13/74
Inventor 丁斌李国胜乔勇李萍张耕靖吕雪赵文庆
Owner XIAN AVIATION BRAKE TECH
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