航天运载器局部连接刚度对振型斜率的影响  

Mode shape slopes prefigure analysis of aerospace vehicle structure

作　　者：芦旭[1] 王平[1] 关振群[1] 李宁 马上 

机构地区：[1]大连理工大学工程力学系工业装备结构分析国家重点实验室,大连116024 [2]北京宇航系统工程研究所,北京100076

出　　处：《强度与环境》2014年第1期10-16,共7页Structure & Environment Engineering

基　　金：国家自然科学基金10872040;11272074;国家科技重大专项2011ZX02403

摘　　要：振型斜率一直是姿态控制系统关心的首要问题。通过等效梁模型结合局部三维有限元精细模型的混合建模的方法,研究了结构局部刚度变化对惯性部件安装位置振型斜率的影响。基于模态分析,在多种工况下提取了振型与惯性部件的振型斜率并进行对比研究,讨论了舱体开口加强圈梁刚度变化、载体十字梁截面变化、连接固定支座刚度变化以及壳体壁厚变化对振型斜率的影响,为航天运载器结构动力学模型简化与姿态控制系统相关结构设计提供了参考依据。Vibration mode Attitude Control System for mode shape slope has been a primary issue of con- cern. In this paper, we propose a hybrid modeling method of combination equivalent beam with three-dimensional finite element. This approach exposits a conclusion, where local stiffness of structure have effects on mode shape slope of Inertial components installation location. Based on modal analysis in multiple conditions, the stiffness of opening cabin reinforcing beam, section geometry parameter of cross beam, stiffness of fixed support and shell thickness which are discussed the effects on mode shape and mode shape slope of Attitude Control System. The conclusion of this article may be bentfit to simplification of dynamic models and design of Attitude Control System.

关 键 词：有限元 简化模型 振型 振型斜率 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]