飞行速度可调导弹三维制导律研究

Three-dimensional Guidance Law of Flight Velocity Adjustable Missiles

为获得更好的制导性能,针对一类采用流量可调发动机的导弹,利用其所增加的飞行速度控制自由度,提出一种三维空间下比例导引+飞行速度控制的双重控制滑模制导律;以比例导引作为基础,在对二维、三维零控脱靶量分析的基础上,以零控脱靶量为跟踪目标选取合适的滑模面,并进一步使用辅助滑模面和有限时间超螺旋干扰观测器对滑模面中的不确定项进行估计,推导了减少脱靶量的速度控制制导律;仿真结果表明,相比于经典的比例导引,在考虑空气阻力的场景下,所设计的制导律脱靶量更小,弹道更平滑,滑模面收敛情况理想,实现了导弹飞行速度的主动控制。

In order to obtain better guidance performances,a dual-control sliding mode guidance rate of proportional guidance and flight speed control in three-dimensional space was proposed for a class of missile with flow-adjustable engines by using the increased freedom of flight speed control.On the basis of proportional guidance and analysis on two-dimensional and three-dimensional zero-control miss distance,the suitable sliding mode surface is selected with the zero-control miss distance as the tracking target,and the auxiliary sliding mode surface and finite-time super-twisting interference observer are used to estimate the uncertainties of sliding mode surface.The simulation results show that compared with the classical proportional guidance,the designed guidance rate has smaller miss distance,smoother trajectory,and ideal convergence of the sliding mode surface under the consideration of air resistance,which achieves the active control of missile flight speed.