Field-of-View and Impact Angle Constrained Guidance Law for Missiles With Time-Varying Velocities

A novel nonlinear non-switching guidance strategy is proposed for missiles with time-varying velocities intercepting stationary targets, considering impact angle, seeker’s field-of-view, and input saturation constraints, simultaneously. A new nonlinear control oriented mathematical model is established, and the guidance design problem is converted to be the issue of tracking control of a nonlinear system with the partial state constraint. In the first step, a bounded virtual guidance law is designed based on hyperbolic tangent function. In the second step, the effect of the input saturation is compensated with a first-order filter. Integral barrier Lyapunov function based stability analysis shows that the tracking errors of the whole guidance system converge to zero uniformly, and the prescribed guidance constraints are not violated. Finally, the numerical simulations are performed to demonstrate the effectiveness of the proposed guidance law.