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Method for determining fatigue load of refitted part of aircraft fuselage

An aircraft fuselage and fatigue load technology, applied in geometric CAD and other directions, can solve problems such as insufficient sample size, inability to effectively reflect the dispersion of fatigue loads, affecting the reliability of load data reliability and life assessment conclusions, etc., to improve effectiveness. , The effect of expanding the load sample library and saving the cost of load measurement

Pending Publication Date: 2021-06-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0004] Fatigue load measurement is a common method to determine the fatigue load of aircraft fuselage modification parts. The advantage of this method is that the load history actually occurs. The disadvantage is that the load measurement work is limited by factors such as time and manpower. It can only be used in combination with the actual use of the aircraft. Obtaining a limited number of flight parameter data and local strain data, the sample size is seriously insufficient, and cannot effectively reflect the dispersion of fatigue loads, which seriously affects the reliability of load data and the credibility of life assessment conclusions

Method used

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  • Method for determining fatigue load of refitted part of aircraft fuselage
  • Method for determining fatigue load of refitted part of aircraft fuselage
  • Method for determining fatigue load of refitted part of aircraft fuselage

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Embodiment Construction

[0013] This invention method has been applied to the fuselage modification part 4 fatigue load determination work of a certain type of aircraft, such as figure 1 As shown, the aircraft fuselage includes a front fuselage 1 and a rear fuselage 2, and the wings 3 are connected to the aircraft fuselage. The embodiment refits the fuselage structure, and the fuselage modification part 4 is located on the rear fuselage 2. According to The inventive idea of ​​the present application, to the method for determining the fatigue load of aircraft fuselage modification part 4, the original design parameters and refitting structural parameters of the known aircraft fuselage, and the historical flight parameter data after known modification of the aircraft, it is characterized in that it includes the following content :

[0014] 1) Add strain gauges 5 to the refitting part 4 of the aircraft fuselage, and obtain the measured strain data of the part through actual flight measurement;

[0015] ...

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Abstract

The invention relates to a method for determining a fatigue load of a refitted part of an aircraft fuselage, which comprises the following steps: obtaining actual measurement strain data of the part through flight actual measurement by knowing original design parameters and refitted structure parameters of the aircraft fuselage and knowing historical flight parameter data after the aircraft is refitted; acquiring flight parameter data in flight actual measurement through a flight parameter recorder; subjecting the two types of data to correspondence in the time and frequency relation, and forming fatigue load actual measurement data of the fuselage refitted part; carrying out correlation analysis on the average strain data of the refitted part and the flight parameter of the aircraft to obtain a relationship between the average strain data of the refitted part of the aircraft and the flight parameter data of the aircraft; calculating average strain data of an extended refitted part by applying historical flight parameter data after the airplane is refitted, combining the historical flight parameter data after the airplane is refitted and fatigue load measured data of a fuselage refitted part to form fatigue load data of the refitted part, and forming a strain accumulation transcendental curve or a parameter accumulation transcendental curve, which can be spectrally compiled, via data processing.

Description

technical field [0001] The invention belongs to the technical field of aircraft fatigue tests, and relates to a method for determining the fatigue load of aircraft fuselage modification parts. Background technique [0002] The fuselage structure is the main loading part of the aircraft. During the design of the aircraft, the layout design was carried out according to the requirements of the aircraft. Refitting will inevitably lead to changes in the fatigue load of the aircraft fuselage structure, which will change the service life of this part and affect the flight safety of the aircraft. Therefore, life assessment after modification must be carried out. [0003] As the basis of the fatigue load spectrum, the fatigue load is the design input for the structural life assessment. The biggest difficulty in the life assessment of the aircraft fuselage modified structure is to obtain the fatigue load. The accuracy of the fatigue load directly affects the reliability of the life re...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15
Inventor 雷晓欣秦剑波朱亮张彦军史志俊王新波
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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