Considering the guidance problem of relative motion of missile target without the dynamic characteristics of missile autopilot in\nthe interception planar, non-homogeneous disturbance observer is applied for finite-time estimation with respect to the target\nmaneuvering affecting the guidance performance. Two guidance laws with finite-time convergence are designed by using a\nfast power rate reaching law and the prescribed sliding variable dynamics. The non singular terminal sliding mode surface is\nselected to improve dynamic characteristics of missile autopilot. Furthermore, the finite-time guidance law with dynamic delay\ncharacteristics is designed for the target maneuvering through adopting variable structure dynamic compensation. The simulation\nresults demonstrate that, for different target maneuvering, the proposed guidance laws can restrain the sliding mode chattering\nproblem effectively and make the missile hit the maneuvering target quickly and accurately with condition of corresponding\nassumptions.
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