Gimbal Angle Constrained PN Guidance Law

Homing head of missile or Seeker is having limited gimbal freedom due to physical constraints. For intercepting manoeuvring high speed target with different engagement scenario, it is essential to control and keep this gimbal angle requirement well within the gimbal freedom limit of seeker. This is proposed to be achieved by incorporating gimbal angle constraint in PN guidance law. The gimbal angle constrained PN guidance proposed in this paper avoids seeker track loss by protecting gimbal angle freedom within it's limit and without affecting guidance errors. The performances improvement of the proposed scheme over the basic PN are established through 6-DOF simulations for different engagement scenario and presented in this paper.