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Ground validation method of main load-bearing structural member of fuselage under large load

A verification method and main load-bearing technology, which is applied in the testing of aircraft parts, ground devices, and aircraft components, etc., can solve the problems of long cycle time and high test cost, and achieve the goals of reducing use, simplifying the support structure scheme, and saving test cost and cycle time Effect

Active Publication Date: 2015-04-01
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method requires additional manufacturing of a large number of parts as an auxiliary, high test cost and long cycle time

Method used

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  • Ground validation method of main load-bearing structural member of fuselage under large load
  • Ground validation method of main load-bearing structural member of fuselage under large load
  • Ground validation method of main load-bearing structural member of fuselage under large load

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Embodiment Construction

[0016] The specific implementation manners of the present invention will be further described below in conjunction with the accompanying drawings.

[0017] 1) Analyze the deformation of the beam 1 inside the body: the structure of the beam with high-direction lugs and its installation method in the body see figure 1 , the crossbeam 1 is installed on the body structure 2 by screwing and riveting, and the nose landing gear 3 is installed on the lug 4 of the crossbeam 1 through bearings; according to the design drawings of the body structure, the finite element model of the cabin section where the crossbeam 1 is located is established, and according to the test The working conditions are loaded, and the deformation of the beam 1 under each test working condition is extracted.

[0018] 2) Simplify the support of the fuselage to beam 1 to form a preliminary simulation support structure scheme: on the basis of ensuring the transmission route of the concentrated load in beam 1, simpl...

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Abstract

The invention belongs to the technical field of structural strength of airplanes and relates to a ground validation method of a main load-bearing structural member of a fuselage under large load. The method comprises the steps: 1.1) analyzing the deformation situation of a transverse beam 1 in the fuselage; 1.2) simplifying the support of the fuselage to the transverse beam 1 and forming the scheme of primary simulation support structure; 1.3) analyzing the deformation situation of the transverse beam 1 under the primary simulation support structure; 1.4) matching the deformation situations of a test sample before simplification and obtaining the parameters of a final simulation support structure; 1.5) performing the manufacturing the final situation support structure and a test fixture and performing ground validation test. According to the ground validation method of the main load-bearing structural member of the fuselage, the scheme of the test sample (transverse beam 1) support structure is simplified, the usage of auxiliary parts in the test is reduced and the experimental cost and period can be saved greatly.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure strength, and relates to a ground verification method for main load-bearing structural parts of a fuselage under heavy load. Background technique [0002] see figure 1 , in the design process of a certain type of aircraft, a beam 1 with high-direction lugs is used on the frame where the front landing gear installation point is located, that is, the main load-bearing structural member. The beam 1 is made by titanium alloy laser forming method. This technology is installed for the first time, and it needs to be fully verified on the ground before it can be installed and used. [0003] There are many connection points between the main load-bearing structural parts and the fuselage, and the boundary conditions are complex, which is not conducive to carrying out ground verification tests. In this case, a fuselage section is usually fabricated as a supporting section of the main load-bearin...

Claims

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Application Information

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IPC IPC(8): B64F5/00B64F5/60
Inventor 金凤新丁庆东李光超
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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