Method for determining tightening torque value of aircraft canopy mounting lock

A tightening torque, aircraft cockpit technology, applied to measure the direction of torque/torsion force during tightening, to achieve the effect of improving service life and reducing cracking time

Active Publication Date: 2021-12-24
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

[0004] The purpose of this application is to provide a method for determining the tightening torque value of the installation lock of the aircraft canopy, so as to solve or alleviate at least one problem in the background technology

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  • Method for determining tightening torque value of aircraft canopy mounting lock
  • Method for determining tightening torque value of aircraft canopy mounting lock

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Embodiment Construction

[0029] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application.

[0030] In order to overcome the problem pointed out in the prior art that cracks are easily produced in the bolt hole of the canopy canopy installation lock, the application provides a method for determining the tightening torque value of the canopy canopy installation lock, and the fixing bolt is locked with a reasonable tightening torque. Thereby reducing the probability of cracks in the mounting lock bolt hole of the aircraft canopy and improving its service life.

[0031] Such as figure 1 As shown, the determination method of the aircraft canopy installation lock tightening torque value provided by the application comprises the following steps:

[0032] First, determine the range value of the tightening...

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Abstract

The invention provides a method for determining the tightening torque value of an aircraft canopy mounting lock. The method comprises the steps that: the range value of tightening torque of a fixing bolt is determined according to the diameter of the fixing bolt; a test type is determined as a fatigue test, a test group at least comprises three groups of test pieces with different tightening torques, and a test load is the maximum use load of the aircraft canopy mounting lock; test pieces and test fixtures for contrast tests under different tightening torques are constructed according to a load transfer route and a boundary condition requirement; supporting and loading modes of test equipment and the test pieces are determined according to the load transfer route and boundary conditions in a full-size aircraft structure; the mechanical property influence of the bolt hole of the aircraft canopy mounting lock under different tightening torques is obtained through contrast test results under the different tightening torques; and according to the longest median life of the bolt hole of the canopy mounting lock under the different tightening torques, the optimal tightening torque value of the canopy mounting lock isdetermined.

Description

technical field [0001] The application belongs to the technical field of aircraft structure maintenance, and in particular relates to a method for determining the tightening torque value of an aircraft canopy installation lock. Background technique [0002] During the use of the canopy side profile of a certain type of aircraft, cracks frequently appeared in the mounting lock bolt holes, which were analyzed as fatigue cracking. In the repair process, in order to suppress the initiation of cracks, the method of installing reinforcements and reducing the stress in use can be used to increase the initiation period of cracks. The side profile of the canopy bears the normal concentrated load transmitted by the lock ring, and the side profile is attached to the lock ring mounting seat. When the actual load is loaded, the lock ring mounting seat provides rigidity support for the side profile, and the tightness of the mounting lock fixing bolt directly affects the use process. The ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01L5/24
CPCG01L5/24Y02T90/00
Inventor 隋福成解放刘汉海于淼单兴业
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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