Slat load loading method in airplane full-size fatigue test

A fatigue test, full-scale technology, used in aircraft component testing, mechanical component testing, and machine/structural component testing. The cycle is controllable, the cost of manpower and time is reduced, and the effect of ensuring flight safety

Active Publication Date: 2021-07-02
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] However, the fatigue test at the component level of the slat wing, because the support boundary cannot truly simulate the deformation of the wing, the authenticity of the assessment is not high

Method used

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  • Slat load loading method in airplane full-size fatigue test
  • Slat load loading method in airplane full-size fatigue test
  • Slat load loading method in airplane full-size fatigue test

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Embodiment Construction

[0018] Referring to the accompanying drawings, the embodiment is a slat load loading scheme in a full-scale fatigue test of a certain type of aircraft. The wing 2 of the aircraft is connected to the fuselage 1. The structural parameters of the aircraft and the multiple slat structures connected to the wing 2 of the aircraft are known. Each slat structure contains the slat airfoil and the slide rail, and the slat load loading method includes the following contents:

[0019] 1) According to the aircraft structural parameters and the load of each slat structure, analyze and obtain the load transfer characteristics and damage characteristics of each slat structure;

[0020] For a certain type of aircraft, the slat structure on one side of the fuselage 1 is divided into five sections from the wing root to the wing tip of the wing 2: the inner slat 3, the middle 1 slat 4, the middle 2 slat 5, the outer slat 1st section slat 6 and outer 2nd section slat 7, see figure 2 , analyzed 3...

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Abstract

A slat load loading method in an airplane full-size fatigue test comprises the steps that airplane structure parameters and loads of a plurality of slat structures connected with an airplane wing are known, each slat structure comprises a slat wing surface and a sliding rail, and according to the airplane structure parameters and the loads of the slat structures, load transfer characteristics and damage characteristics of the slat structures are obtained through analysis; according to the load transfer characteristic and the damage characteristic of the slat structure, the slat structure is graded into a complete examination structure, an examination considering structure and a non-examination structure; in an airplane full-size fatigue test, a slat airfoil of a complete examination structure and a sliding rail are installed on a wing structure, a slat sliding rail of the examination considering structure is installed on the wing structure, and a slat structure of a non-examination structure is not installed; according to the grading result of the slat structures, the bending moment, the torque and the shear load of the slat are applied to the slat wing surface of the complete examination structure and;for the examination considering structure, the slat bending moment and shear load is applied to the slat slide rail; and the application method includes that the loading test is not carried out on the non-examination structure.

Description

technical field [0001] The invention belongs to the technical field of aircraft fatigue tests, and relates to a slat load loading method in an aircraft full-scale fatigue test. Background technique [0002] In order to solve the problems in the prior art, the object of the present invention is to provide a method for loading slat loads in the full-scale fatigue test of an aircraft. [0003] The slat is an important lift-increasing device in the aircraft structure. For large transport aircraft, in order to pursue a higher lift coefficient, the slat adopts multi-section slats, which are connected to the wings through a slide rail mechanism to transfer the slat load to the wings. Due to the different aerodynamic requirements in different stages such as takeoff, cruise, landing / go-around, etc., the slats need to swing in different positions. Therefore, the slat structure is complex and the load is very complex. [0004] Aircraft full-scale fatigue test is the core of aircraft ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00B64F5/60
CPCG01M13/00B64F5/60Y02T90/00
Inventor 雷晓欣纪露明张彦军彭航李小鹏薛海峰
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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