基于经典层合板理论的运载火箭动特性梁模型研究  

Research on Dynamic Characteristic Beam Model of Launch Vehicle Based on Classical Laminate Theory

作　　者：罗震宇 邱静宇 周遇仁 刘建 狄文斌 冀宾 LUO ZhenYu;QIU JingYu;ZHOU YuRen;LIU Jian;DI WenBin;JI Bin(Land Space Technology Co Ltd,Shanghai 201109,China)

机构地区：[1]蓝箭航天空间科技股份有限公司,上海201109

出　　处：《强度与环境》2025年第1期1-8,共8页Structure & Environment Engineering

摘　　要：针对不同蒙皮加筋结构的运载火箭动特性快速预测问题,基于经典层合板理论,建立一种考虑火箭筒段细节尺寸的运载火箭等效梁模型,用于快速预测运载火箭的动特性。该梁模型中,不同的筋条形式(正交筋、三交筋、桁条)被当作不同刚度的铺层,在蒙皮上进行“平铺堆叠”。使用典型筒段的有限元模型和全箭试验结果验证该等效梁模型的计算偏差。结果表明,该梁模型在一阶弯曲、扭转、纵向模态频率计算上均具有较高的精度。最后,通过有限元模型反推梁截面属性发现,该梁模型的主要误差来源为箭体几何尺寸的偏差和刚度系数矩阵的精度。a simplified equivalent beam model is established base on the classical sandwich panel theory for rapid predicted the dynamic characteristics of launch vehicle,which considering the detailed dimensions of the launch vehicle structure.In the beam model,different types of ribs(orthogonal ribs,triple crossbars,stringer) are treated as layers with different stiffness and are "stacked" on the skin.The calculation deviation of the equivalent beam model are verified by using the finite element model of typical segments and the experiment results of the whole launch vehicle modal test.The results show that the beam model has high accuracy in the frequency calculation of first-order bending,torsional and longitudinal modal.Finally,by using the finite element model to invert the beam section properties,inferred that the main source of the calculation deviation of the beam model is the deviation of the geometrical dimension and the accuracy of the stiffness coefficient matrix.

关 键 词：运载火箭 动特性 梁模型 蒙皮加筋 蒙皮桁条 

分 类 号：V421[航空宇航科学与技术—飞行器设计]