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The proposed robust guidance control law can attain satisfactory robust performance for pursuing an unpredictable maneuvering target. Sufficient condition analysis is also carried out for the proposed guidance control law with tunable parameters. The proposed method not only need not touch the hard-solved Hamilton-Jacobi partial differential inequality but also guarantees that the line-of-sight distance between homing missile and maneuvering target can quickly converge to zero. A previously-implemented simulation discussed elsewhere is performed using the guidance control law to illustrate the efficiency of the proposed design.