大型整流罩分离动力学简化建模及仿真分析  

Simplified finite element modeling method and separation dynamics of large scale fairing structure

作　　者：李哲[1] 范学领[1] 孙秦[1] 万小朋[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《固体火箭技术》2012年第5期583-587,共5页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(11002104);陕西省自然科学基金(2011JQ1019);中央高校基本科研业务费专项资金(xjj2011053;GCKY1004)

摘　　要：为有效简化大型整流罩分离过程的数值分析工作,采用柔性多体动力学分析软件———ADAMS/Flex对大型整流罩结构进行了有限元建模简化技术研究,并在离散化简化模型的有效性验证基础上探讨了大型整流罩分离过程中质心运动、罩内可用空间包络及铰链力的变化规律;同时,对比分析了分离面解锁前因弹簧作用导致的整流罩初始装配弹性变形对整流罩分离动力学行为的影响。结果表明,给出的大型薄壁加筋整流罩结构的简化建模方法合理可行,可作为整流罩简化建模基本依据;忽略初始弹性变形的抛罩动力学分析可用作整流罩分离运动规律研究的基准工况;整流罩分离过程中的"呼吸运动"对柱段角点处影响最为严重,而越靠近罩体顶端其影响越小。To improve the effectiveness of the numerical study of fairing separation dynamics,simplified finite element modeling method as well as the separation dynamics of large scale fairing structure were investigated.The commercial software ADAMS/Flex was adopted to construct the simplified finite element model of large scale fairing structure.The proposed simplified finite element modeling technique was validated for different examples.Furthermore,the effects of initial elastic deformation of fairing on the translation of center of mass,the envelope of available inner space,and the hinge force were presented as well as the evolution of characteristic separation parameters.Based on the numerical results,it is concluded that（i） the proposed simplified finite element modeling technique is accurate and effective;（ii） it is reasonable to neglect the initial elastic deformation while predicting the dynamical response of the fairing system;（iii） during fairing separation,the trailing point of the cylinder is the most possible place where collision between the separated fairing section and core vehicle may occur.

关 键 词：整流罩 分离 柔性多体系统 ADAMS 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程]