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A method of energy drive conversion

A drive conversion and energy technology, applied in the aviation field, can solve the problems of large engine life loss, heavy support tasks, poor support, etc., and achieve the effect of reducing loss and reducing demand

Active Publication Date: 2016-08-24
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention: the present invention mainly aims at the problems of large loss of engine life, high guarantee requirements, heavy guarantee tasks and poor guarantee in the two conventional hydraulic energy drive modes of the aircraft, and provides a method for converting the drive energy of the hydraulic system

Method used

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  • A method of energy drive conversion
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  • A method of energy drive conversion

Examples

Experimental program
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Effect test

Embodiment

[0025] Embodiment: this example is a certain aircraft, hydraulic energy drive system, see figure 1 . The DC-driven electric mechanism 1, the bow bracket 3, the spline clutch 2, and the gear assembly 4 are linked into the transmission chain of the aircraft accessory transmission casing to realize the energy drive system to be put into work or restore the link state of the aircraft accessory transmission casing after the work is completed. The design idea of ​​the system is as follows:

[0026] 1) Connect the transmission chain of the aircraft accessory transmission casing with the engine power branch shaft through the spline clutch and the transmission chain of the aircraft transmission casing and the power branch shaft of the hydraulic pump; drive the spline through the bow through the DC drive electric mechanism The clutch moves axially to realize the engagement and disengagement of the spline axial travel 27 -1 mm can realize the complete separation and full engagement of...

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Abstract

The invention discloses a converting method for energy source drive and belongs to the technical field of aircraft power plants. The converting method is characterized by consisting of a direct current drive electric mechanism, an arched support, a spline clutch and a gear assembly, wherein the direct current drive electric mechanism is connected with the spline clutch and the gear shaft in a gear train through the arched support; axial linear reciprocating motion is outputted by the direct current drive electric mechanism; the spline clutch and the gear assembly are driven by the arched support to do linear motion, so that the separation and communication of the spline clutch and reconstruction of a meshing gear of the gear assembly are realized. The converting method has the advantages that the reconstruction of a driving link is realized by simple linear drive of the direct current drive electric mechanism and the conversion of an energy source driving source is realized.

Description

technical field [0001] The invention belongs to the power plant system in the technical field of aviation, and relates to a conversion mechanism driven by energy. Background technique [0002] When the aircraft is inspecting the hydraulic system on the ground and driving the wings, it is necessary to drive the hydraulic pump of the hydraulic system to ensure the necessary output of the hydraulic source. In the past, two methods were used to drive the engine to drive the hydraulic pump and use the hydraulic source to drive the support equipment. Driver, both methods have some disadvantages: [0003] 1) In the working state of the aircraft engine, the gear chain in the transmission casing of the aircraft accessory drive is driven by the power split shaft to turn the hydraulic pump to output the hydraulic pressure source; in this way, when the hydraulic energy is needed, the engine must be started to work, which means The life of the engine is lost, and higher requirements are...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F16H37/02H02K7/116
CPCF16D28/00F16H37/02F16H61/32
Inventor 刘冬连永久李堃杨子仲
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA