水陆两栖飞机静力试验优化机翼变形的载荷配平

田文朋; 夏峰; 宋鹏飞; 张柁; 杨鹏飞

doi:10.7527/S1000-6893.2020.23956

航空学报 >

2020 , Vol. 41 >Issue 11: 223956 - 223956

DOI: https://doi.org/10.7527/S1000-6893.2020.23956

固体力学与飞行器总体设计

水陆两栖飞机静力试验优化机翼变形的载荷配平

田文朋 ,
夏峰 ,
宋鹏飞 ,
张柁 ,
杨鹏飞

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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: 2020-03-10

修回日期: 2020-04-20

网络出版日期: 2020-12-01

基金资助

国家自然科学基金（51601175，51805041）

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Load balancing for wing deformation optimization in amphibious aircraft static test

TIAN Wenpeng ,
XIA Feng ,
SONG Pengfei ,
ZHANG Tuo ,
YANG Pengfei

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Aviation Technology Key Laboratory for Full-scale Aircraft Structures Static and Fatigue, Aircraft Strength Research Institute of China, Xi'an 710065

Received date: 2020-03-10

Revised date: 2020-04-20

Online published: 2020-12-01

Supported by

National Natural Science Foundation of China(51601175, 51805041)

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摘要

水陆两栖飞机全机静力试验的浮筒着水工况试验中，在试验允许的常规载荷配平方案下，压向大量级水载荷作用于浮筒结构引起机翼较大变形，影响试验精度，因此进行以减少机翼变形为目标的载荷配平研究。将机翼近似为悬臂梁结构，在构建的机翼力学模型基础上应用Green函数建立机翼的挠度曲线方程。首次以考核区域边界肋的挠度和转角为优化目标并建立多目标函数，通过层次分析法和极差变换标准化处理方法将其转化为单目标函数后，采用引入交叉和变异因子的改进蚁群算法进行载荷配平方案优化运算。有限元分析及试验结果显示，优化得到的载荷配平方案可以显著地减少机翼变形，配平载荷不影响考核区域的真实变形，证明了该优化方案的正确性和可行性。

关键词： 水陆两栖飞机; 静力试验; 机翼变形; 挠度; 多目标优化

本文引用格式

田文朋 , 夏峰 , 宋鹏飞 , 张柁 , 杨鹏飞 . 水陆两栖飞机静力试验优化机翼变形的载荷配平[J]. 航空学报, 2020 , 41(11) : 223956 -223956 . DOI: 10.7527/S1000-6893.2020.23956

Abstract

In the normal load balancing scheme allowed by the static test of amphibious aircraft buoy landing, compressive large-scale water load acting on the buoy structure causes large wing deformation which will affect the test accuracy. Therefore, load balancing research to reduce wing deformation is conducted. The deflection curve equation of the wing which is approximated to cantilever beam structure is established using Green’s function on the basis of the mechanics model. The deflection and the rotation angle of the boundary rib of the examined area are taken as the optimization targets, and a multi-objective function is established for the first time. The function is then transformed into a single objective one via the analytic hierarchy process and the standardized processing method of range transformation. The load balancing scheme is optimized by the ant colony algorithm with crossover and mutation factors. The results of both finite element analysis and the test showed that the optimized load balancing scheme can significantly reduce the wing deformation, and the balanced load does not affect the true deformation of the examined area, thus proving the correctness and feasibility of the optimization scheme.

Key words： amphibious aircraft; static test; wing deformation; deflection; multi-objective optimization

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