民机全机疲劳试验综合加速技术研究与验证

王育鹏; 田文朋; 宋鹏飞; 夏峰; 冯建民

doi:10.7527/S1000-6893.2020.24919

航空学报 >

2022 , Vol. 43 >Issue 5: 224919 - 224919

DOI: https://doi.org/10.7527/S1000-6893.2020.24919

固体力学与飞行器总体设计

民机全机疲劳试验综合加速技术研究与验证

王育鹏 ,
田文朋 ,
宋鹏飞 ,
夏峰 ,
冯建民

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1. 西北工业大学航空学院, 西安 710065;
2. 中国飞机强度研究所全尺寸飞机结构静力/疲劳航空科技重点实验室, 西安 710065

收稿日期: 2020-10-26

修回日期: 2020-10-28

网络出版日期: 2021-01-08

基金资助

国家自然科学基金（51601175）

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Research and verification of comprehensive acceleration technology for civil aircraft full-scale fatigue test

WANG Yupeng ,
TIAN Wenpeng ,
SONG Pengfei ,
XIA Feng ,
FENG Jianmin

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1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710065, China;
2. Aviation Technology Key Laboratory for Full-scale Aircraft Structures Static/Fatigue, Aircraft Strength Research Institute of China, Xi'an 710065, China

Received date: 2020-10-26

Revised date: 2020-10-28

Online published: 2021-01-08

Supported by

National Natural Science Foundation of China(51601175)

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摘要

民机全机疲劳试验关系到适航取证和服役使用，为缩短疲劳试验时间，从载荷谱简化和试验过程提速两方面进行综合性加速技术研究。对细节疲劳额定值（DFR）法改进使之适用于全寿命区间后，基于改进DFR法提出了以损伤比为判断标准的载荷谱等损伤折算方法，通过小试验件验证了载荷谱简化方法的正确性，并将其应用于全机疲劳试验。载荷谱简化后各任务段的总循环次数大幅减少，采用简化谱的后机身试验损伤结果与原谱全机试验基本相同，说明了该方法适用于全机试验。在试验设计和实施阶段，提出了快速载荷处理的载荷整体平衡优化方法和缩短每循环加载时长的分段等速率加载优化方法，载荷处理结果误差均满足设计要求，优化后的平均每日起落数由48提高到90。

关键词： 民机全机疲劳试验加速; 改进DFR法; 等损伤折算; 载荷整体平衡优化; 分段等速率加载

本文引用格式

王育鹏 , 田文朋 , 宋鹏飞 , 夏峰 , 冯建民 . 民机全机疲劳试验综合加速技术研究与验证[J]. 航空学报, 2022 , 43(5) : 224919 -224919 . DOI: 10.7527/S1000-6893.2020.24919

Abstract

The full-scale fatigue test of civil aircraft is related to airworthiness certification and service use. In order to shorten the fatigue test time, the comprehensive acceleration technology is studied from two aspects of load spectrum simplification and test process acceleration. The DFR method is improved to fit the whole life interval. The equivalent damage conversion method taking the damage ratio as the judgment basis is proposed based on improved DFR, and it's correctness is verified by a small test piece, and then it is applied to the full-scale fatigue test. The total number of cycles in each task segment is greatly reduced after the load spectrum simplification. The damage results of the rear fuselage test applied original load spectrum are basically the same as those of the full-scale aircraft test applied simplified load spectrum. It can be seen that the method is suitable for the full-scale fatigue test. For different stages of test implementation, the overall load balance optimization is proposed to quickly complete the load handing, and the subsection constant rate loading optimization is proposed to reasonably shorten loading time of each cycle. The error of load handling results meet the design requirements. The average number of daily landings increases from 48 to 90.

Key words： full scale fatigue test acceleration of civil aircraft; improved DFR; equivalent damage conversion; overall load balance optimization; subsection constant rate loading

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