飞行速度可调导弹三维制导律研究

Three-dimensional Guidance Law of Flight Velocity Adjustable Missiles

摘要:

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。

Abstract:

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