As an improved guidance method,the attitude head pursuit guidance （AHPG） law enables the attitude pursuit guidance （APG） law to be more suited to transition guidance of air-to-ground missiles. By adding a head ang...As an improved guidance method,the attitude head pursuit guidance （AHPG） law enables the attitude pursuit guidance （APG） law to be more suited to transition guidance of air-to-ground missiles. By adding a head angle into the attitude angle of APG,AHPG directs the missile axis onto the line of sight （LOS）. The maximum range trajectory simulation shows that the elevator deflection angle reaches the saturated value of 10° at the outset and the impact angle is less than 60° when APG is used as transi-tion guidance law. However,the elevator deflection angle on the whole trajectory is reduced to under 5° and the impact angle increased to over 60° when AHPG is used. The formulae to calculate head angles are derived for different target distributions. The simulation of multiple trajectories shows that with the help of the formulae based on AHPG law,the same performance could be achieved.展开更多
针对BTT导弹飞行控制系统的自适应鲁棒控制问题,基于反馈线性化控制和自适应RBF(radical base function)神经网络控制系统设计方法,设计了高精度鲁棒飞行控制器。提出在线权值修正算法,使RBF神经网络能实现对飞行控制系统动态逆误差的...针对BTT导弹飞行控制系统的自适应鲁棒控制问题,基于反馈线性化控制和自适应RBF(radical base function)神经网络控制系统设计方法,设计了高精度鲁棒飞行控制器。提出在线权值修正算法,使RBF神经网络能实现对飞行控制系统动态逆误差的在线逼近,进而实现对系统不确定性和外界扰动的实时补偿。通过数值仿真,对所设计的飞行控制器进行了有效性验证。仿真结果表明,相比仅采用反馈线性化控制的飞行控制器,文中提出的飞行控制器能较好地跟踪期望的指令角度信息,鲁棒性能更优。展开更多
文摘As an improved guidance method,the attitude head pursuit guidance （AHPG） law enables the attitude pursuit guidance （APG） law to be more suited to transition guidance of air-to-ground missiles. By adding a head angle into the attitude angle of APG,AHPG directs the missile axis onto the line of sight （LOS）. The maximum range trajectory simulation shows that the elevator deflection angle reaches the saturated value of 10° at the outset and the impact angle is less than 60° when APG is used as transi-tion guidance law. However,the elevator deflection angle on the whole trajectory is reduced to under 5° and the impact angle increased to over 60° when AHPG is used. The formulae to calculate head angles are derived for different target distributions. The simulation of multiple trajectories shows that with the help of the formulae based on AHPG law,the same performance could be achieved.
文摘针对现有剩余时间估计方法在导弹前置角较大时精度不高的问题,采用分段求解的方法,推导了一种大前置角情况下比例导引律的剩余时间估计算法.首先,对比例导引的闭环运动方程进行变形,得到弹目距离和飞行时间关于前置角的一阶非线性微分方程.然后对前置角的变化区间适当分段,在每段区间内保证前置角的增量为小角度,从而利用一阶泰勒展开求解每段区间内的微分方程.最后,通过分段迭代求解,推导大前置角下的剩余时间估计.仿真结果表明,在典型背景下,该算法能够将大前置角下剩余时间的估计精度由1.2 s提高到0.1 s.
文摘针对BTT导弹飞行控制系统的自适应鲁棒控制问题,基于反馈线性化控制和自适应RBF(radical base function)神经网络控制系统设计方法,设计了高精度鲁棒飞行控制器。提出在线权值修正算法,使RBF神经网络能实现对飞行控制系统动态逆误差的在线逼近,进而实现对系统不确定性和外界扰动的实时补偿。通过数值仿真,对所设计的飞行控制器进行了有效性验证。仿真结果表明,相比仅采用反馈线性化控制的飞行控制器,文中提出的飞行控制器能较好地跟踪期望的指令角度信息,鲁棒性能更优。
