Homing missile guidance using LOS rate and relative range measurement

In this paper, a technique for missile guidance using line-of-sight (LOS) angular rate measurement and measurement of relative range between target and missile by suitable sensors on-board the missile is proposed. A simple system of non linear equations formulated from proportional navigation guidance geometry is used for the control problem. The target acceleration information is generally not available and hence is considered as an unknown quantity to be estimated by a disturbance observer. Sliding mode control (SMC) is used for design of the control law. The stability of the proposed controller is then established using Lyapunov function. The effectiveness of the new missile guidance law in making the miss distance near zero is proved through simulations under various target conditions.