固液捆绑火箭星箭耦合分析技术研究  

Research on Coupled Load Analysis Technology for Launch Vehicles with Strap-on Solid Rocket Boosters

作　　者：刘佳俊 毛玉明 博伟 李鑫 狄文斌 LIU Jiajun;MAO Yuming;BO Wei;LI Xin;DI Wenbin(Shanghai Aerospace System Engineering Institute,Shanghai 201109,China)

机构地区：[1]上海宇航系统工程研究所,上海201109

出　　处：《上海航天（中英文）》2022年第5期66-70,共5页Aerospace Shanghai（Chinese&English）

摘　　要：新一代中型固液捆绑火箭频率低、模态密、全箭动力学特性复杂,助推与芯级之间的力的传递特性在纵横扭方向存在耦合,传统纵横向分离的星箭耦合分析方法无法准确预示星箭界面力学环境。本文针对固液捆绑火箭的特点,建立了星箭耦合系统纵横扭一体化有限元模型;根据火箭飞行特定设计工况建立具有时变飞行特征的外力函数,对火箭特征工况进行了瞬态响应分析;通过子结构内力恢复对固液捆绑火箭的星箭界面力学环境进行了准确预示,具有较高的工程应用价值。Medium size launch vehicles with a liquid core level and several strap-on solid rocket boosters(SRBs)have complex dynamic characteristics. The fundamental frequency is low,the mode is dense,and the loads of the core level and boosters are coupled in the longitudinal,lateral,and torsional directions. Traditional coupled load analysis(CLA)methods cannot accurately foreshow the mechanical environment of the satellite-launch vehicle interface. Based on the characteristics of launch vehicles with SRBs,this paper establishes a longitudinal-lateral-torsional integrated satellite-launch vehicle finite element model and a set of time-varying force functions. The CLA is conducted by using modal transient analysis. With the substructure force recovery technique,the mechanical environment of the satellitelaunch vehicle interface is shown. The CLA method has high value in the design of launch vehicles with SRBs.

关 键 词：固液捆绑火箭 星箭耦合分析 纵横扭一体化 时变外力函数 子结构内力恢复 

分 类 号：V214.3[航空宇航科学与技术—航空宇航推进理论与工程]