Reliability analysis of composite sandwich structure for fuselage skin based on surrogate model

基于代理模型的机身蒙皮复合材料夹层结构可靠性分析

¹ College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
² Beijing Institute of Power Machinery, China Aerospace Science and Industry Corporation, Beijing 100074, China

Received: 15 July 2021

Abstract

Composite structures are characterized by multiple source uncertainties in mechanical properties, geometric dimension, etc., and multiple failure modes, which bring challenges to their design and application. In order to explore the reliability analysis method of composite sandwich structures with multi-source uncertainties and multi-failure modes, a parametric finite element model and an acoustic boundary element model were established for deterministic analysis of a fuselage skin sandwich structure. Considering the randomness of the mechanical properties of composite materials and the laminate thickness, the structural reliability models were established for three typical failure modes of sandwich structures: static strength failure, global buckling and vibration noise. In order to reduce the computational effort, the Kriging surrogate models of failure modes were constructed, and the subset simulation method was used to predict the system failure probability of the sandwich structure of fuselage skin. The proposed computational framework provides support and tool for the fine design of composite sandwich structure.

摘要

复合材料结构具有力学性能、几何尺寸等的多源不确定性和失效模式多样化的特点，给其设计与应用带来了挑战。为了探索多源多失效模式下复合材料夹层结构的可靠性分析方法，以机身蒙皮夹层结构为研究对象，建立了参数化有限元分析模型和声学边界元模型进行确定性分析。考虑复合材料的力学性能参数和铺层厚度的随机性，为夹层结构的静强度失效、整体屈曲和振动噪音3种典型失效模式建立结构可靠性分析模型。为了减少计算量，构造3种失效模式的Kriging代理模型，并结合子集模拟方法预测机身蒙皮夹层结构的系统失效概率。为复合材料夹层结构精细化设计提供支撑和工具。