A guidance law design with terminal impact angle constraint based on nonlinear generalized predictive control

In this paper, a kind of reference trajectory of line-of-sight (LOS) angle based on the optimal control theory is given. Then, the corresponding nonlinear generalized predictive control law is designed to make the missile´s actual LOS angle track the reference LOS angle. Simulation results show that the proposed nonlinear generalized predictive control law can make the missile hit the ground stationary target accurately and meet the demand for terminal impact angle constraint.