翼身融合民机典型PRSEUS受压壁板屈曲及渐进损伤分析

张永杰; 吴莹莹; 朱胜利; 王斌团; 谭兆光; 袁昌盛

doi:10.7527/S1000-6893.2019.23185

航空学报 >

2019 , Vol. 40 >Issue 9: 623185 - 623185

DOI: https://doi.org/10.7527/S1000-6893.2019.23185

翼身融合民机技术专栏

翼身融合民机典型PRSEUS受压壁板屈曲及渐进损伤分析

张永杰 ,
吴莹莹 ,
朱胜利 ,
王斌团 ,
谭兆光 ,
袁昌盛

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1. 西北工业大学航空学院, 西安 710072;
2. 航空工业第一飞机设计研究院, 西安 710089;
3. 上海飞机设计研究院, 上海 201210

收稿日期: 2019-05-24

修回日期: 2019-06-24

网络出版日期: 2019-07-29

基金资助

国家自然科学基金（11972301）

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Buckling and progressive damage analysis of representative compressed PRSEUS panel in blended-wing-body civil aircraft

ZHANG Yongjie ,
WU Yingying ,
ZHU Shengli ,
WANG Bintuan ,
TAN Zhaoguang ,
YUAN Changsheng

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1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. AVIC The First Aircraft Institute, Xi'an 710089, China;
3. Shanghai Aircraft Design and Research Institute, Shanghai 201210, China

Received date: 2019-05-24

Revised date: 2019-06-24

Online published: 2019-07-29

Supported by

National Nature Science Foundation of China (11972301)

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摘要

由NASA和波音公司共同提出的拉挤杆缝合高效一体化结构（PRSEUS），由于具有优异的抗压稳定性和止损/止裂等承载优势，已成为解决翼身融合布局民机非圆截面机身结构承载效率低和稳定性差等问题的主要途径。本文针对典型PRSEUS受压壁板结构，开展了线性/非线性屈曲及渐进损伤分析；提出了综合考虑蒙皮、止裂带、长桁翻边、隔框翻边等一体化缝合元件贯穿支撑构型几何关系和偏置参考面的建模方法，提高了PRSEUS受压壁板有限元模型的精度；提出了综合考虑屈曲特征值、非线性屈曲载荷等多影响因素的网格收敛性分析方法，提高了PRSEUS受压壁板屈曲分析的计算效率；提出了最小屈曲特征值、几何节点偏移以及最小屈曲特征值-几何节点偏移组合式等3种初始缺陷引入方法，提高了PRSEUS受压壁板损伤分析的计算精度；完成了基于纤维与基体损伤本构关系的典型PRSEUS受压壁板非线性屈曲损伤分析，通过与试验结果对比，给出了针对PRSEUS结构的非线性屈曲渐进损伤演化分析方法。为翼身融合布局民机PRSEUS结构的稳定性/损伤分析和设计提供了方法和技术支撑。

关键词： 翼身融合民机; PRSEUS结构; 非线性屈曲; 网格收敛性; 渐进损伤

本文引用格式

张永杰 , 吴莹莹 , 朱胜利 , 王斌团 , 谭兆光 , 袁昌盛 . 翼身融合民机典型PRSEUS受压壁板屈曲及渐进损伤分析[J]. 航空学报, 2019 , 40(9) : 623185 -623185 . DOI: 10.7527/S1000-6893.2019.23185

Abstract

Due to the excellent loading advantage of stability under compression and damage arrest/crack arrest, the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS), put forward by NASA and the Boeing Company, has become the major solution to solve low efficiency and poor stability problems caused by non-circular fuselage cross section in civil aircraft. This paper carries out linear/nonlinear buckling and progressive damage analysis for representative compressed PRSEUS panel structure. The methods of modeling the geometric relationship of the support configuration and offset reference surface of skin, tears-trap, stringer flange, frame flange integrated stitched supporting configuration are put forward, improving the accuracy of the finite element model of PRSEUS compressed panel. A mesh convergence analysis method that takes buckling eigenvalue, nonlinear buckling load and other factors into account is proposed to improve the computational efficiency of PRSEUS compressed panel buckling analysis. Three initial imperfection introduction methods including the minimum buckling eigenvalue, geometrical node offset, and combination of the minimum buckling eigenvalue and geometrical node offset are presented to improve the calculation accuracy of the finite element model of PRSEUS compressed panel. Finally, the nonlinear buckling progressive damage analyses of representative PRSEUS compressed panel based on the damage constitutive relation between fiber and matrix are completed. By comparing the experimental results, the nonlinear buckling progressive damage evolution analysis methods for PRSEUS structure are presented. This paper provides the methods and technical support for the stability/damage analysis and design of the PRSEUS structure in blended-wing-body civil aircraft.

Key words： blended-wing-body civil aircraft; PRSEUS structure; nonlinear buckling; mesh convergence; progressive damage

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