民用飞机机身壁板复杂试验载荷优化技术  

Optimization technology for complex test load of civil fuselage panel

作　　者：郭瑜超[1] 王立凯[1] 孙喜桂 聂小华[1] GUO Yuchao;WANG Likai;SUN Xigui;NIE Xiaohua(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi’an 710065,China)

机构地区：[1]中国飞机强度研究所,强度与结构完整性全国重点实验室,西安710065

出　　处：《航空学报》2023年第17期159-170,共12页Acta Aeronautica et Astronautica Sinica

基　　金：工信部民用飞机专项(MJZ3-2N21);陕西省重点研发计划(2022ZDLGY02-03)。

摘　　要：针对民用飞机复合材料机身壁板强度试验中的载荷预计问题,构造了基于应变误差矩阵的壁板试验载荷优化模型,并利用多维极小值优化算法预计了壁板试验载荷。首先,基于机身壁板在试验装置中的受载形式,建立了机身壁板及试验装置有限元模型,并计算了各试验基准载荷作用下的机身壁板应变矩阵;其次,基于机身壁板在全机身受载状态下和试验受载状态下的应变矩阵之差,同时考虑矩阵中各元素的加权系数,构建了机身壁板应变误差矩阵,并以应变误差矩阵所有项的平方和最小为目标,以各基准载荷的系数为优化变量,以各基准载荷系数的上下限为约束,构建了基准载荷系数优化函数;基于罚函数法对优化函数进行了无约束处理,并利用最速梯度法进行了载荷系数优化;最后,基于优化得到的载荷,计算了机身壁板在试验复合载荷作用下的应变,并与机身壁板在全机身受载状态下的应变相对比,应变的分布趋势基本一致,应变误差在10%以内,证明该方法可以为机身壁板试验载荷的确定提供支持。Aiming at the problem of load prediction in the strength test of composite fuselage panel of civil aircraft,we construct an optimization model of the test load based on the strain error matrix,and predict the test load using the multi-dimensional minima optimization algorithm.Firstly,based on the load form of the fuselage panel in the test de⁃vice,the finite element model of the fuselage panel and the test device was established,and the strain matrix of the fuselage panel under each test reference load calculated.Secondly,the fuselage panel strain error matrix was con⁃structed based on the difference between the strain matrices of the fuselage panel under the full fuselage load state and the test state,and considering the weighting coefficients of each element in the matrix.With the minimum sum of squares of all terms in the strain error matrix as the objective,each reference load coefficient as the optimization vari⁃able,and the upper and lower limits of each reference load coefficient as the constraints,the reference load coefficient optimization function was constructed.The optimization function was then processed unconstrained based on the pen⁃alty function method,and the reference load coefficients obtained by the steepest gradient method.Finally,based on the optimized load,the strain of the fuselage panel under the composite load of the test was calculated.Compared with the strain of the fuselage panel under the full fuselage load,the distribution trend of the strain was basically the same with the strain error within 10%,proving that this method can provide support for the determination of the test load of the fuselage panel.

关 键 词：复合材料 机身壁板 试验装置 应变误差矩阵 试验载荷系数 多维极值优化 

分 类 号：V223[航空宇航科学与技术—飞行器设计]