Guidance of solid propellant missile based on functional guidance

In this paper a new method for guidance of solid propellant and aerodynamic control missile is introduced. In proposed method after achieving maximum acceleration, flight path angle of missile changes in order to impact to target. In this method flight information such as time history of magnitude of velocity and position vectors are saved in the table before firing. For calculating difference of nominal and disturbed parameters new concepts are used. Corrected values of nominal parameters are used in guidance after firing to guaranty impact to target. The flight simulation of proposed method is compared with functional guidance method and the effect of the proposed method is shown. Design verification is done in base of simulation in presence of flight disturbances.