The problem of terminal precision guidance for missiles with vertical attack angle constraint is considered. A sliding mode disturbance observer and enhanced adaptive proportional guidance law are applied to improve the robustness. Considering the constraints of target location and attack angle, the guidance parameters selections in longitudinal and lateral planes are analyzed. The uncertainties of the dynamics are estimated by using a second-order sliding mode disturbance observer, and then compensated to ensure high accuracy in the realization of guidance commands. Simulation results demonstrate the robustness and accuracy of the proposed approach. Compared with the conventional adaptive proportional guidance approach, the guidance precision of proposed approach is obviously improved in the present of aerodynamic dispersions.
Key words
control and navigation technology of aerocraft /
missile /
terminal guidance /
proportional guidance /
vertical attack /
sliding mode disturbance observer
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Footnotes
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