Abstract
A method of a SMC (sliding mode control)-based guidance law design is proposed for an exoatmospheric missile with constant positive acceleration. By analyzing the nonlinear kinematic equations of the missile, a class of nominal motions that requires no maneuver effort can be defined. The unique time-to-go, the corresponding nominal heading angle and the nominal heading angular rate can be solved from the equations that are derived from the properties of the nominal motions to guarantee a perfect interception with a desired impact angle. A nonsingular SMC-based guidance law is designed for the disturbed heading angle tracking system such that the tracking is guaranteed in finite time.
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