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Whole dimension fatigue test fuselage lateral load loading design method

A lateral load and fatigue test technology, which is applied in the field of aviation fatigue damage tolerance test, can solve problems such as limitations, achieve the effect of reducing impact, clear engineering concept, and correct theoretical basis

Inactive Publication Date: 2019-03-26
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Regarding the research on the full-scale fatigue test of aircraft, there are few researches on domestic public data, which are limited by the current domestic technical level and contain other factors. There are more researches on foreign public data, but most of them are on the airframe configuration and test hardware matching , a brief introduction to the state of implementation of the test and the load situation, but failed to give a practical design method for the fatigue test in terms of the force and load characteristics of the fuselage structure itself

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  • Whole dimension fatigue test fuselage lateral load loading design method
  • Whole dimension fatigue test fuselage lateral load loading design method
  • Whole dimension fatigue test fuselage lateral load loading design method

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Embodiment Construction

[0021] The present invention will be described in further detail below in conjunction with accompanying drawing, please refer to Figure 1 to Figure 5 .

[0022] Such as figure 1 As shown, it is a schematic diagram of side load loading of the fuselage structure, in which the left side load is applied to the left lug of the frame, and the right side load is applied to the right side lug of the frame.

[0023] Such as figure 2 As shown in , it is an isometric schematic diagram of the lateral loading arrangement of the fuselage. The joint in the figure is a connection form of co-riveting by connecting the belt plate with the frame, skin, and long stringer. The joint and the frame, stringer, and skin are Or it can be connected with frame and skin together.

[0024] Such as image 3 , 4 , 5 are the front view, top view, and side view of the laterally loaded joint, respectively.

[0025] A design method for lateral load loading of a full-scale fatigue test fuselage, comprisin...

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Abstract

The invention belongs to the field of aviation fatigue damage tolerance tests, and particularly relates to a whole dimension fatigue test fuselage lateral load loading design method. The method comprises the following steps of analyzing a whole airplane structure of an airplane; building a whole airplane finite element model; performing whole airplane load solution to obtain the fuselage lateral load Fjy under each load work condition; then, determining the loading scheme; combining the characteristics of connection between fuselage frames, the connection between the frames and the skin and the connection between the skin and a stringer; performing primary calculation to obtain the connector load under each work condition; according to the obtained connector load under all work conditions,performing finite element solution in the whole airplane load implementation state with the loads of the airplane structure in other directions; according to the structure form after the reinforcingand optimization, completing the fatigue test machine matching catalogue and supplementing processing requirements; finally completing the machine body lateral load arrangement. The invention providesthe method for solving the problems that a fuselage lateral load loading system is complicated, and the design is difficult; the lever system arrangement is simplified; the influence on loads exertedin other directions is greatly reduced.

Description

technical field [0001] The invention belongs to the field of aviation fatigue damage tolerance test, in particular to a design method for lateral load loading of a full-scale fatigue test fuselage. Background technique [0002] The assessment and verification of aircraft full-scale fatigue test is the most direct and effective method to obtain the service life of the airframe structure and reflect the weak parts of fatigue. It represents the highest technical level in the field of durability damage tolerance test. The test load application method determines the implementation scale of the full-scale fatigue test. . Before formulating the test implementation plan, the designer needs to do a lot of theoretical analysis and calculation to ensure that the test loading design can not only truly simulate the loading state of the aircraft in the air and on the ground, but also consider the scale of the test implementation and balance the loads of the whole aircraft in all direction...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/32
CPCG01N3/32G01N2203/0073
Inventor 闵强王亚芳王新波张彦军
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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