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作 者:陈峰[1] 何广军[1] CHEN Feng;HE Guang-jun(Air and Missile Defense College,Air Force Engineering University,Xi'an 710051,Shaanxi,China)
机构地区:[1]空军工程大学防空反导学院,陕西西安710051
出 处:《兵工学报》2018年第9期1741-1748,共8页Acta Armamentarii
基 金:国家自然科学基金项目(61703424)
摘 要:当雷达导引头俯视探测超低空目标时,受多径干扰的影响,跟踪精度严重降低。为了最大限度地降低干扰,需要将弹目视线角约束至布儒斯特角。基于终端滑模控制的方法,设计了一种非奇异快速终端滑模制导律;针对该制导律中目标加速度难以准确获得的问题,设计了滑模扰动观测器来估计目标加速度;在非奇异快速终端滑模制导律中引入观测器的估计值和带开关系数的符号函数,设计出一种复合非奇异快速终端滑模制导律。通过Lyapunov理论证明,该复合制导律可保证弹目视线角在有限时间内快速收敛至布儒斯特角,同时视线角速率收敛至0附近的小邻域内。仿真结果表明:当该复合制导律应用于对超低空目标拦截时,可使脱靶量减少至杀伤半径之内;相比于传统滑模制导律,可使系统状态的收敛时间减少4 s左右。When the radar seeker overlooks and detects an ultra-low altitude target,the tracking precision is greatly reduced because of the existence of multipath interference.In order to minimize the interference,the line-of-sight(LOS)angle must be constrained to Brewster’s angle.A nonsingular fast terminal sliding mode guidance law is designed based on the terminal sliding mode control method.Aiming at the problem that the target acceleration is difficult to be accurately obtained using the guidance law,a sliding mode disturbance observer(SMDO)is designed to estimate the target acceleration.A composite nonsingular fast terminal sliding mode guidance law is designed by introducing the estimated value of the observer and the sign function with switches coefficient into the nonsingular fast terminal sliding mode guidance law.It is proved by Lyapunov theory that the proposed composite guidance law enables the LOS angle to converge quickly to the Brewster angle and the LOS angular rate to converge to a small neighborhood near zero in finite time.Simulated results show that the miss distance is reduced within the kill radius when the proposed guidance law is used in the ultra-low altitude target interception.Compared with the traditional sliding mode guidance laws,the convergence time of the system state can be reduced about 4 s by the proposed guidance law.
分 类 号:TJ765.331[兵器科学与技术—武器系统与运用工程]
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