Missile-Attitude-control

代码说明：

  1、利用simulink中sfunction方法建立航天器姿态动力学模型和运动学模型； 2、利用linmod对非线性模型线性化； 3、姿态模型线性化后，利用极点配置（pole）方法求取控制参数； 4、将控制参数带入非线性模型仿真控制效果。(One using simulink sfunction method to establish the dynamic model and kinematic model of the spacecraft attitude 2, the use of linmod linearization of the nonlinear model Attitude model linearization, the use of pole configuration (pole) is used to obtain the control parameters 4, the control parameters into the nonlinear model simulation control effect.)

文件列表：

ode45_linmod
............\Attitude7.m,1610,2011-03-16
............\Attitude_ode.m,856,2011-04-01
............\ode_main.m,1783,2011-04-01
............\pole.m,439,2011-04-01
............\zitai.mdl,20618,2011-04-03
新建 文本文档.txt,296,2012-04-11