Field-of-View and Impact Angle Constrained Guidance Law for Missile with Reducing Sensitivity on Initial Errors based on optimal Error Dynamics

This paper presents a comprehensive terminal homing guidance law for stationary ground targets, derived from the optimal error dynamics (OED) technique. The synthesized guidance law addresses a wide range of constraints, with a primary focus on reducing sensitivity to the initial guidance error, resulting in lower required acceleration command at the initial homing phase. Incorporating an input weighting function effectively distributes the guidance command throughout the homing phase. Simultaneously, the guidance law ensures compliance with the terminal impact angle and field-of-view (FOV) constraints. To meet the FOV constraint, the paper integrates a saturation function mapping method. The guidance law ensures that the acceleration command approaches zero at the terminal phase, achieving precise control of the impact angle. Furthermore, the missile’s trajectory generated by this guidance law remains unaffected by variations in missile velocity, enhancing its applicability in real-world scenarios. Numerical simulations are conducted to illustrate the effectiveness of the synthesized guidance law.