摘要
采用变后掠翼技术实现战术巡航导弹多任务低能耗飞行,导弹的动力学与控制特性因为弹翼的运动更加复杂化,给出了包含弹翼运动的整弹动力学模型,基于小扰动法和系数"冻结"法,得出了导弹包含弹翼运动参数的三通道数学模型,充分考虑了气动参数摄动和弹翼运动参数时变特性,将其视为标称值与已知上下界的摄动量的和。采用变结构控制理论设计自动驾驶仪,仿真结果表明,设计的控制器具有强鲁棒性,能够抑制参数变化的影响,满足导弹控制性能指标要求。
The tactical cruise missile with morphing swept wings can have the ability of multi - mission flight. By considering the interaction between the motion of the morphing swept wings and the body, the multi - body dynamic model for the whole missile is given. The simple three - channel mathematical models are gotten with linear disposal. using the variable structure control theory, the autopilot designs are finished. The control laws are based on the disturbances of the parameters of the model. The results of the simulation shows that the controller meets the need of performance of the control system and has the capabilities of celerity and robustness.
出处
《计算机仿真》
CSCD
2008年第6期62-65,共4页
Computer Simulation
基金
航天科技创新基金资助项目(07XE0153)
关键词
变后掠翼
巡航导弹
动力学
变结构控制
Morphing swept wing
Tactical cruise missile
Dynamics
Variable structure control
