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Zero limit structure of dual-redundancy gear transmission angular displacement sensor

An angular displacement sensor and gear transmission technology, applied in instruments, measuring devices, etc., can solve problems such as performance degradation and product output changes, and achieve the effects of increasing safety and reliability, improving performance stability, and expanding market share.

Active Publication Date: 2017-05-31
JINCHENG NANJING ELECTROMECHANICAL HYDRAULIC PRESSURE ENG RES CENT AVIATION IND OF CHINA
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Problems solved by technology

[0003] The purpose of the present invention is to provide a zero-position limiting structure of a double-redundancy gear rotation angular displacement sensor, which solves the problems of product output changes and performance degradation due to zero-position changes during the assembly and disassembly of the product on the aircraft, and improves Product performance stability, increasing the safety and reliability of product use

Method used

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  • Zero limit structure of dual-redundancy gear transmission angular displacement sensor
  • Zero limit structure of dual-redundancy gear transmission angular displacement sensor
  • Zero limit structure of dual-redundancy gear transmission angular displacement sensor

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[0013] In order to better illustrate the present invention, it will be described in detail below in conjunction with the accompanying drawings.

[0014] see image 3 , Figure 4 , which is an embodiment of a zero-position limit structure of a double-redundancy gear rotation angular displacement sensor of the present invention.

[0015] A zero-position limit structure of a double-redundancy gear transmission angular displacement sensor, comprising an angular displacement sensor housing 1, a cylindrical pin 2, a front end cover 3, an angular displacement sensor shaft 4, a gear assembly 5, a lower bearing 6, and a lower base Assembly 7, output gear 8, pinion 9, upper bearing 10 and upper base assembly 11. The angular displacement sensor housing 1 is fixed on the upper base assembly 11 by four screws, the cylindrical pin 2 is fixed on the angular displacement sensor shaft 4 through a drill, and the front end cover 3 is fixed on the angular displacement sensor by four countersunk...

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Abstract

The invention relates to the field of gear transmission angular displacement sensor design, and relates to a zero limit structure of a dual-redundancy gear transmission angular displacement sensor. According to the invention, the consistency of the zero position of a dual-redundancy angular displacement sensor in multi-gear installation is realized; the phenomenon of difficult zero position consistency of a traditional gear transmission dual-redundancy angular displacement sensor is overcome; the problems of changed product output and declined performance, which are caused by zero position change in the process of loading and unloading of the product on an aircraft are solved; the performance stability of the product is improved; and the product safety and reliability are increased.

Description

technical field [0001] The invention belongs to the design field of angular displacement sensors for gear transmission, and relates to a zero-position limiting structure of a double-redundancy gear transmission angular displacement sensor. Background technique [0002] figure 1 It is a traditional double-redundancy gear rotation angle displacement sensor zero position limit structure, including cylindrical pin 2, output gear 8 and lower base assembly 7, etc., wherein output gear 8 is fixed on the lower base through lower bearing 6 and upper bearing 10 On the seat assembly 7, the cylindrical pin 2 is pressed on the output gear 8 through interference fit. The disadvantage of this traditional structure is: on the one hand, there is a zero limit, when the lower base assembly 7 has an annular groove 7a at the corresponding position of the cylindrical pin 2, since the annular groove 7a is limited by parts, this makes the output gear 8 work Corners are limited, such as figure 2...

Claims

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Application Information

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IPC IPC(8): G01B21/22
CPCG01B21/22
Inventor 徐华
Owner JINCHENG NANJING ELECTROMECHANICAL HYDRAULIC PRESSURE ENG RES CENT AVIATION IND OF CHINA
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