A Near Optimal Midcourse Guidance Law for Air-to-Air Missile

Abstract

Dynamic inversion and singular perturbation methods are employed for medium-range air-to-air missile to obtain a near-optimal midcourse guidance law. The midcourse guidance stage is separated into two phases. In phase 1, which the rocket engine working, a dynamic inversion guidance law is used to guide the missile flight along a nominal trajectory. In the second gliding phase, singular perturbation technique is employed to develop a guidance law which maximum terminal specific energy. A terminal correction is made to ensure the seeker intercept the target. The result obtained from numerical simulation shows that, the guidance law can conserve energy for terminal interception, and the flight path error is small enough at the end of midcourse stage.