Transfer matrix method for determination of the natural vibration characteristics of elastically coupled launch vehicle boosters  

作　　者：Laith K.Abbas Qinbo Zhou Hossam Hendy Xiaoting Rui 

机构地区：[1]Institute of Launch Dynamics, Nanjing University of Science and Technology

出　　处：《Acta Mechanica Sinica》2015年第4期570-580,共11页力学学报（英文版）

基　　金：supported by the Research Fund for the Doctoral Program of Higher Education of China(Grants 20113219110025,20133219110037);the National Natural Science Foundation of China(Grants 11102089,61304137);the Program for New Century Excellent Talents in University(NCET-10-0075)

摘　　要：The analysis of natural vibration characteristics has become one of important steps of the manufacture and dynamic design in the aerospace industry. This paper presents a new scenario called virtual cutting in the context of the transfer matrix method of linear multibody systems closed- loop topology for computing the free vibration characteristics of elastically coupled flexible launch vehicle boosters. In this approach, the coupled system is idealized as a triple-beam system-like structure coupled by linear translational springs, where a non-uniform free-free Euler-Bemoulli beam is used. A large thrust-to-weight ratio leads to large axial accelera- tions that result in an axial inertia load distribution from nose to tail. Consequently, it causes the development of significant compressive forces along the length of the launch vehicle. Therefore, it is important to take into account this effect in the transverse vibration model. This scenario does not need the global dynamics equations of a system, and it has high computational efficiency and low memory requirements. The validity of the presented scenario is achieved through com- parison to other approaches published in the literature.The analysis of natural vibration characteristics has become one of important steps of the manufacture and dynamic design in the aerospace industry. This paper presents a new scenario called virtual cutting in the context of the transfer matrix method of linear multibody systems closed- loop topology for computing the free vibration characteristics of elastically coupled flexible launch vehicle boosters. In this approach, the coupled system is idealized as a triple-beam system-like structure coupled by linear translational springs, where a non-uniform free-free Euler-Bemoulli beam is used. A large thrust-to-weight ratio leads to large axial accelera- tions that result in an axial inertia load distribution from nose to tail. Consequently, it causes the development of significant compressive forces along the length of the launch vehicle. Therefore, it is important to take into account this effect in the transverse vibration model. This scenario does not need the global dynamics equations of a system, and it has high computational efficiency and low memory requirements. The validity of the presented scenario is achieved through com- parison to other approaches published in the literature.

关 键 词：Transfer matrix method of linear multibodysystems Free vibration characteristics Coupled launchvehicle boosters 

分 类 号：V475.1[航空宇航科学与技术—飞行器设计] V430