运载火箭姿控系统三通道Simulink建模与仿真分析  

Simulink Modeling & Simulation Analysis of the Attitude Control System on Three-channel of the Launch Vehicle

作　　者：孙志兵[1] 戴金海[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2004年第3期20-23,共4页Journal of National University of Defense Technology

基　　金：国家部委基金资助项目

摘　　要：以某运载火箭为例,介绍了将姿控系统数学模型转化为Simulink三通道仿真模型的方法和过程;在仿真过程中涉及到时变系数的瞬时时间固化法,分析由此引起的计算数据局部振荡,并提出解决办法;分析了用Simulink为该大型系统建模时所遇到的代数循环问题,并加以解决。Exampled by a certain launch vehicle, the modeling method and modeling process with Simulink to mathematical simulation on three-channel for the vehicle attitude control system are described.The problem of the local surge of the calculated data due to the so-called freeze time method during the simulation process is analyzed and the resolvent is given. Algebraic loop problem encountered in Simulink modeling of this large scale system is discussed and the resolvent is given.

关 键 词：运载火箭 系统仿真 SIMULINK 数据振荡 代数循环 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]