运载火箭大姿态调姿段全数值飞行仿真  

Numerical Simulation of Attitude Regulation of Launch Vehicle

作　　者：周游[1] 王茂芝[1] 毛万标[2] 佘春东[3] 

机构地区：[1]成都理工大学信息管理学院,四川成都610059 [2]西昌卫星发射中心技术部,四川西昌651000 [3]中国科学院软件研究所,北京100080

出　　处：《计算机仿真》2007年第3期54-57,共4页Computer Simulation

基　　金：数字化火箭仿真系统总装试验技术项目

摘　　要：以国产CZ系列运载火箭为研究对象,建立了大姿态飞行段全量数学模型,包括控制方程、箭体运动以及数字校正网络和非线性开关函数。并利用Matlab/Simulink仿真环境对大姿态调姿系统进行了全数值仿真研究。在仿真过程中,采用模块化思想建模,先将系统分解为一系列功能相对独立的子系统,再进行仿真模型集成,构建出大姿态调姿系统的总体模型。还对仿真模型进行了验证,分析了其在给定输入条件下的输出情况,仿真结果表明:模型建立正确,调姿系统的性能指标均满足技术要求,能够较好的完成调姿功能。最后对仿真模型进行了精度分析并提出了进一步研究方向。Adapting the CZ series Launch Vehicle as research object, the paper proposes a mathematical model of attitude regulation system of Launch Vehicle, including control equation, rocket movement and digital corrective network. The simulation model of the subsystem is established in Matlab/Simulink. In simulation, the system is divided into a series of independent functional units. The sub simulation models of these units are built in Matlab/Simulink. The model of attitude regulation of Launch Vehicle is acquired by means of integration. Then the simulation model is validated and its output under given condition is analyzed. The simulation shows that the model is valid and its performance can meet the technical requirement.

关 键 词：运载火箭 大姿态调姿 建模与仿真 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]