Sliding-mode-control-based Differential Geometric Guidance Law using Mild Sliding Manifolds

Based on sliding mode control, this paper presents a novel differential geometric guidance law for a homing missile against maneuvering targets. The three-dimensional guidance problem is reduced to two-dimensions by an engagement plane rotation reference frame. In the design of guidance law, two well-constructed mild sliding manifolds are introduced to decrease control efforts. Moreover, target maneuver is treated as a disturbance with known upper bound and no algorithm is required to estimate the maneuver. Simulation results illustrate that the mild sliding manifolds can be fast arrived at in finite time and the proposed differential geometric guidance law yields better performance by contrast with other existing guidance laws.