Terminal guidance law based on adding a power integrator approach with autopilot lag

In this paper, a guidance law is proposed based on adding a power integrator approach for intercepting maneuvering targets in the presence of autopilot lag. Considering the missile autopilot as the first-order system, a new robust finite-time terminal guidance law is designed which can handle the targets maneuvering. In the design procedure, assumed that the acceleration of the target is bounded. It is proved that the system state i.e. the line-of-sight (LOS) angular rate and LOS angular acceleration can converge to a small neighborhood of zero in finite time under the designed terminal guidance law. Simulation demonstrate that this paper proposed the guidance law has a better robust performance against the maneuvers and the dynamics of the missiles autopilot.

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