Differentiator-Based Output-Feedback SlidingMode Control for Angle Constrained Midcourse Guidance

A new guidance law with terminal angle constraint is presented for the midcourse guidance of anti-hypersonic missiles, thus to realize a near head-on scenario at the start of terminal phase. The proposed differentiator-based output feedback sliding mode guidance law is derived from supertwist based differentiator and prescribed convergence law for secondorder sliding mode controller. Considering nonlinear dynamics of planar engagement, relative range and its derivative, line-of-sight angle and a guess of maximum target maneuverability is required for the implementation of new guidance law, information can always be available through data link from ground-based or air-based platforms. Fast convergence of line-of-sight angular rate as well as flight path angle can be expected. Simulation results validate the effectiveness of new guidance law against various target maneuvers and also illustrate the superiority when compared to conventional guidance laws.