Widespread fatigue damage analysis method of fuselage wallboard lap joint structure

A widely distributed fatigue damage and analysis method technology, applied in the field of civil aircraft structure design, can solve problems such as endangering structural integrity, reducing aircraft residual strength, and affecting structural use safety

Inactive Publication Date: 2017-11-17
AVIC SAC COMML AIRCRAFT
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Problems solved by technology

Some data show that widespread fatigue damage can reduce the remaining strength of the aircraft by about 25%
Widely d

Method used

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  • Widespread fatigue damage analysis method of fuselage wallboard lap joint structure
  • Widespread fatigue damage analysis method of fuselage wallboard lap joint structure
  • Widespread fatigue damage analysis method of fuselage wallboard lap joint structure

Examples

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Embodiment Construction

[0062] Calculation example: Take the longitudinal lap structure of the rear fuselage of a certain type of aircraft as an example. This type of aircraft requires LOV to be 60,000 flight cycles, the initial inspection interval of the structure is 30,000 flight cycles, and the repeated inspection interval is 7,500 flight cycles. The material is 2024-T42, the ultimate tensile strength is F tu = 427MPa, the nominal stress of the net section of the structural analysis part is 100MPa, and the extensive fatigue damage analysis is carried out on the typical lap joint structure, and the analysis methods all adopt the method of the present invention.

[0063] Below in conjunction with accompanying drawing, the specific implementation process of the present invention is described in further detail, and the specific step description process takes the analysis of the lap joint structure of the rear fuselage of a certain type of aircraft as an example, and its realization process is as follow...

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Abstract

The invention provides a widespread fatigue damage analysis method of a fuselage wallboard lap joint structure, which makes a new request according to conventional widespread fatigue damage assessment. The analysis of the fuselage wallboard lap joint structure comprises three aspects: firstly, a detail fatigue analysis of a row of rivet holes of the lap joint structure is conducted based on a fatigue lifetime analysis; secondly, a damage tolerance analysis of any of the row of rivet holes of the lap joint structure is conducted; and thirdly, when the row of rivet holes of the lap joint structure have leading cracks, it is considered that all hole edges have initial damages of material defect, it is assumed that the initial damage dimension is 0.127 mm, crack expansion of the structure is performed, and the residual intensity is calculated so that the inspection interval requirement is satisfied. According to the method, the application space is wide in the initial stage and later stage of the design of civil airplanes, the accuracy and the reliability of analysis can be greatly improved, the structural service security can be guaranteed from the perspective of durability, and the expansibility is achieved with the expansion of a test database.

Description

technical field [0001] The invention relates to a widely distributed fatigue damage analysis method for fuselage wall panel lap joint structures, which belongs to the technical field of civil aircraft structure design. Background technique [0002] The term wide-spread fatigue damage (WFD) first appeared in the analysis of the catastrophic accident at Aloha Airlines. Subsequent investigations showed that the cause of the accident was the initiation of many small cracks in the rivet holes at the overlapping joints of the fuselage skins. accident. Widely distributed fatigue damage produces multi-point or multi-position damage on the body structure. The damage generally occurs at the edge of the hole, and the force is uniform. It is difficult to detect the tiny cracks initiated at the edge of the hole of the overlapping structure. Widely distributed fatigue damage usually refers to numerous cracks of arbitrary length and random distribution, which is a typical damage form in ...

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Application Information

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IPC IPC(8): G01M13/00
CPCG01M13/00
Inventor 贾大炜刘旭陈瑞钰周龙超孟维宇刘磊
Owner AVIC SAC COMML AIRCRAFT
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