Aircraft load spectrum curve calculation method

By dynamically adjusting the conservative coefficient and correcting the load spectrum curve, the problem of overly conservative load spectrum curves in existing technologies is solved, achieving lightweight and economical improvements in aircraft structural design and ensuring a balance between safety and economy.

CN121413201APending Publication Date: 2026-01-27BAI JING HANG XIAN (CHANG ZHOU) KE JI YOU XIAN GONG SI
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Patent Information

Application Number
CN202511465455.5
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-10-14
Publication Date
2026-01-27

AI Technical Summary

Technical Problem

Existing methods for calculating aircraft load spectrum curves are sometimes too conservative, especially for long-life aircraft, leading to excessive structural weight, increased fuel consumption, and higher operating costs, making it impossible to balance safety and economy.

Method used

By combining the standard spectrum curve with the target aircraft's flight distance of one lifetime, the limiting incremental load factor is calculated, the conservative coefficient is dynamically adjusted, and the load spectrum curve is corrected to match the actual service load of the aircraft, thus avoiding the over-conservative problem caused by ignoring design differences in traditional methods.

Benefits of technology

The revised load spectrum curve more accurately reflects the load characteristics of the aircraft throughout its entire life cycle, avoids structural weight redundancy, reduces fuel consumption and operating costs, improves payload capacity, and achieves a balance between safety and economy.

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Abstract

The invention relates to the technical field of aircraft structure design, in particular to an aircraft load spectrum curve calculation method, which comprises the following steps: calculating a double-life spectrum curve of a target aircraft, and then calculating a double-life accumulated exceeding frequency corresponding to an incremental load coefficient ratio of 1; according to the design parameters of the target aircraft, calculating the limited increment load coefficient of the target aircraft to obtain a load coefficient spectrum curve of the target aircraft, and defining the aircraft limited load as a judgment reference based on the numerical relationship of the limited increment load coefficient and the numerical relationship of the one-time life cumulative exceeding times; and calculating a conservative coefficient of the load spectrum curve of the target aircraft, and correcting the load coefficient spectrum curve of the target aircraft to form a corrected load spectrum curve. The corrected load spectrum curve is used for fatigue and damage tolerance design of the target aircraft structure, especially for the target aircraft with the long service life, the aircraft design can be optimized, the structural weight can be reduced, the maintenance cost can be reduced, and the commercial value can be improved.
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