A Sliding Mode Variable-structure Guidance Law with Terminal Impact Angle Constraint

Aiming at the maneuvering target interception and having built the equation of motion between the missile and the target. The sliding mode variable-structure guidance law with terminal impact angle constraint is established by employing the sliding mode variable-structure control theory. The exponential approach law is used to weaken the chattering, while the stability and time limitations of the guidance law model are proved. Simulation results of the designed guidance law: the missile accurately hit the target, the guidance law with terminal impact angle constraint can track the expected angle of sight q
_d
accurately; in simulation, the sliding surfaces can quickly converge to zero without any noticeable chattering; the missile has no fluctuation in the longitudinal and lateral overload during the conception, and the trajectory curvature is small. The simulation results show the effectiveness of the proposed guiding law model.