针对大型特殊布局飞机开口结构刚度强度设计难点，结合力学原理与数值仿真方法，开展了大跨距开口承载边梁稳定性分析方法研究，建立了大跨距多弹性支撑隔框作用下开口边梁失稳特性分析方法，给出了隔框刚度设计要求；开展了开口边梁-隔框结构布置与刚度协同优化研究，通过算例揭示了隔框间距与边梁、隔框剖面参数耦合作用规律；开展了机体开口结构失效及承载能力预测分析，建立了基于Nastran-Abaqus跨平台的多层级非嵌入式模型耦合失效分析方法，并通过典型大开口结构破坏试验进行试验与仿真对比。对比结果显示有限元仿真结果能够较好反映试验过程载荷与变形非线性历程，最大载荷及变形预测误差分别为8.8%和7.1%，且有限元仿真结果能够与试验件失稳现象和失效模式较好吻合。

The present study addresses the challenges of stiffness and strength design for large-opening structures in special configuration aircraft such as blended wing-body aircraft. By combining mechanical principles and numerical simulation methods， this research investigates the stability analysis of long-span opening load-bearing beams. A method for analyzing the buckling characteristics of opening beams under the influence of multiple elastic supports from frames is established， providing design requirements for frame stiffness. Additionally， the study explores the collaborative optimization of structural arrangement and stiffness for opening beams and frames. Through case studies， the interaction between frame spacing and cross-sectional parameters of beams and frames is revealed. Furthermore， the research conducts failure analysis and load-bearing capacity prediction for aircraft opening structures， developing a coupled failure analysis method using a Nastran-Abaqus based multi-level non-intrusive model coupling analysis. Experimental validation is performed using typical large-opening structure failure tests. Comparative results show that finite element simulation effectively captures the nonlinear load and deformation behavior during testing， with maximum errors of 8.8% and 7.1% in load and deformation predictions， respectively. The simulation results also demonstrate good agreement with experimental buckling phenomena and failure modes.