攻击时间控制的动态逆三维制导律

Dynamic inversion three-dimensional guidance law for impact time control

为使导弹按照指定的攻击时间攻击目标,在俯仰通道采用增广比例导引,而在偏航通道采用机动控制,该机动控制的作用为调整导弹的攻击时间使其趋于标称值.用剩余时间误差来表示当前剩余时间和标称剩余时间的差值,这里的当前剩余时间按照当前时刻弹目距离与速度的比值来计算.由弹目相对运动关系可知,偏航通道的控制量通过前置角间接控制当前时刻的弹目距离,因此,该控制量通过前置角间接控制剩余时间误差.对此控制系统,采用时标分离的方法设计了期望的慢子系统和快子系统,对这两个子系统分别进行动态逆控制设计,得到了导弹偏航通道的机动控制指令.仿真结果表明,这种制导方法最终使剩余时间误差趋于0,实现了导弹的攻击时间控制,并在导引后期能够获得直线弹道.

In order to hit a stationary target at a designated time, a missile guidance system was developed with an augmented proportional navigation guidance （APNG） system in the pitch channel, and a maneuver control system in the yaw channel. Maneuver control was able to adjust the impact time to a designated value. Time-to-go error was introduced, which is the difference between actual time-to-impact and the designated time-to-impact. The cur- rent time-to-go was calculated as current range-to-go over velocity. According to the kinematics of missile-to-target, current range-to-go can be indirectly altered by the yaw control command through the yaw lead angle. This means that time-to-go error could also be indirectly controlled by this command. For the proposed two part control system, the low speed subsystem and the fast one were designed using the time-scale separation method. Two nonlinear dy- namic inversion controllers were designed for the two subsystems and a yaw maneuver control command was provid- ed. Simulation results showed that this guidance approach allowed time-to-go errors to be ultimately reduced to ze- ro, with missile impact time accurately controlled. The final phase of flight can still be a straight trajectory.