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An angular displacement sensor installation structure and its zero position adjustment method

An angular displacement sensor and installation structure technology, which is applied to instruments, measuring devices, etc., can solve the problems that the actuator is difficult to realize, the zero position adjustment of the aircraft cannot be adjusted, and the installation space of the aircraft actuator is limited. Simple, good processing effect

Active Publication Date: 2019-12-10
LANZHOU FLIGHT CONTROL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, due to the limited installation space of the aircraft actuator, it is difficult or impossible to adjust the zero position of the actuator on the aircraft

Method used

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  • An angular displacement sensor installation structure and its zero position adjustment method

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Embodiment Construction

[0017] The present invention will be described in further detail below in conjunction with the accompanying drawings. see figure 1 , a mounting structure for an angular displacement sensor, comprising an actuator body 1, an angular displacement position sensor assembly 2, a taper head fastening screw pin 5, an outer cover 6, and an external thread pressure block 7; The mounting port of the displacement position sensor assembly 2 is used to place the fixed angular displacement position sensor assembly 2; the angular displacement position sensor assembly 2 includes an angular displacement position sensor and an adjustment ring, the adjustment ring is fixedly connected to the angular displacement position sensor, and the rotation adjustment ring can drive The angular displacement position sensor rotates integrally;

[0018] The outer cover 6 is fixedly connected with the actuator body 1, and the angular displacement position sensor assembly 2 is located in the space between the ...

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Abstract

The invention, which belongs to the actuator structure design technology, relates to a structure for installing an angular displacement sensor and a zero position adjusting method thereof. The structure comprises an angular displacement position sensor assembly, a position sensor cover and a special-purpose nut. The angular displacement position sensor assembly is fixed by the special-purpose nutto realize axial constraint; after the special-purpose nut is loosened, a rotating handle installed at the periphery of an angular displacement position sensor mounting rack in the angular displacement position sensor assembly rotates to realize electrical zero position adjustment of an actuator. Therefore, a problem that the existing angular displacement actuator can not realize zero position adjustment or adjusts the zero position difficulty due to the small axial mounting space is solved.

Description

technical field [0001] The invention belongs to the structure design technology of an actuator, and relates to an installation structure of an angular displacement sensor and a zero position adjustment method thereof. Background technique [0002] The electric servo actuator is an important executive part of the flight control system. After the actuator is installed in the aircraft, the mechanical zero position and the electrical zero position need to be adjusted according to the needs. After the mechanical zero position of the actuator output mechanism meets the requirements, the rotation angle The housing of the position sensor is used to adjust the electrical zero position of the angular position sensor so that the mechanical zero position of the actuator coincides with the electrical zero position. The position sensor of the electric actuator is mechanically fixed to the actuator shell after the actuator is assembled and debugged. There must be a certain space in the axi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01B21/22
Inventor 任省伟张华张强朝李建
Owner LANZHOU FLIGHT CONTROL
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