Integrated control valve assembly-actuating cylinder separated hydraulic servo actuator

A hydraulic servo and actuator technology, which is applied in aircraft transmission, aircraft power transmission, aircraft power devices, etc., can solve problems such as the influence of control system and structure life, large installation space, etc., to improve design efficiency and reduce cost. Effects of small torsional moments

Active Publication Date: 2016-04-27
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

The two actuators arranged in the same direction require a large installation space, and at the same time, the actuators installed in the same di

Method used

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  • Integrated control valve assembly-actuating cylinder separated hydraulic servo actuator
  • Integrated control valve assembly-actuating cylinder separated hydraulic servo actuator
  • Integrated control valve assembly-actuating cylinder separated hydraulic servo actuator

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Embodiment Construction

[0016] In order to overcome the arrangement of high-power hydraulic servo actuators in a small space and improve the maintainability of the product, a hydraulic servo actuator with door cylinder separation is designed, including integrated control valve assembly 1, first actuator cylinder 2 and The second cylinder 3. Among them, the integrated control valve assembly 1 includes a first servo valve 101, a first solenoid valve 102, a first bypass valve 103, a second servo valve 104, a second solenoid valve 105, a second bypass valve 106, and a centering valve 107. , switching valve 108 and centering mechanism 109, wherein the first servo valve 101, the first solenoid valve 102, the first bypass valve 103, the switching valve 108 and the first actuator 2 form the No. 1 channel; the first servo valve 101 is the main control valve, and the first solenoid valve 102 controls the on-off of the hydraulic oil. After the first solenoid valve 102 is powered on, the hydraulic oil enters the...

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Abstract

The present invention relates to the field of aircraft actuation systems, more particularly to the field of actuation system actuator design and layout. According to the present invention, the integrated control valve assembly-actuating cylinder separated hydraulic servo actuator is designed for meeting of the installation requirement of the limited space, wherein an integrated control valve assembly and two actuating cylinders are respectively adopted as the separate LRU so as to be installed on the aircraft, the integrated control valve assembly and the actuating cylinders are connected through hydraulic soft pipes and electric cables, a command signal is input into the integrated control valve assembly, and the integrated control valve assembly receives the command and controls the corresponding part to move so as to control the movement of the actuating cylinder; and the push-pull arrangement is that the two actuating cylinders are arranged in a push-pull movement manner, such that the installation space requirements can be effectively reduced, and the fatigue torques of the actuation system and the structure can be reduced.

Description

technical field [0001] The invention relates to the field of aircraft actuation systems, in particular to the field of design and arrangement of hydraulic servo actuators in the actuation system. Background technique [0002] The actuator of the aircraft actuation system is the executive component in the flight control system, which is related to the safety of the aircraft. Therefore, the design, layout and installation of high-power hydraulic servo actuators are particularly important. However, high-power hydraulic servo actuators often have a large volume and have certain requirements for installation space. Therefore, it is very necessary to design a high-power hydraulic servo actuator that can be installed in a small space. The hydraulic servo actuator in the existing actuation system generally adopts the integrated control valve assembly and the actuating cylinder to be integrated and installed as a whole. In this way, the actuator will have greater requirements for i...

Claims

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Application Information

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IPC IPC(8): B64C13/40
Inventor 董骥喻杰刘波张家盛
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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