A Novel Sliding Mode Guidance Law with Impact Angle and Time Constraints

A Novel sliding mode guidance law with impact angle and time constraints is proposed in this paper. In order to solve the problem, the equations of the missile motion and the engagement kinematics take the downrange of the missile as the independent variable instead of time. What's more, the desired LOS angle is designed as a quartic polynomial function and the coefficients are determined by the boundary conditions. To widely broaden the range of the impact angle, a new reference frame by rotating an appropriate angle is introduced to realize the application with an arbitrary desired impact angle. Finally, Numerical simulations are used to determine the guidance parameters and various scenarios simulations validate the effectiveness and accuracy of the proposed guidance law.