摘要
针对自旋弹存在的非线性耦合特性,研究了以时标分离方法进行分段设计的动态逆理论解决途径。根据系统的变量快慢区分子系统,采取层叠结构设计控制器对分系统进行单独设计,并考虑实际应用中存在的具体实现问题,得到了过载驾驶仪控制器的基本结构。引入实际系统延迟及噪声等因素由dSpace与三轴转台进行了验证性试验,得出了具有工程应用价值的控制器设计方法。
The solution to dynamic inversion theory with time scale artifice was studied based on nonlinear coupling characteristics exist in spinning missile. The subsystems were designed separately according to cascade structure method. Considering problems occurred in application, the control structure of overload autopilot was obtained. Then, the control system design method for spinning missile was obtained by introducing real-time simulation system of dSpace and three-axis rotating platform.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第5期83-86,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
自旋弹
动态逆理论
半实物仿真
spinning missile
dynamic inversion
hardware-in-the-loop simulation
