Nonlinear control for missile terminal guidance

Variable Structure Control (VSC) technique is applied to the design of robu st homing missile guidance laws. In the design procedure, the target's mane uver is assumed to be unpredictable and is considered as disturbances. Guid ance laws are then proposed to achieve the interception performance for bot h cases of longitude-axis control being available and unavailable. The prop osed guidance laws are continuous which alleviate chattering drawback by cl assic VSC design. Results are obtained and compared with those by realistic true proportional navigation design to illustrate the benefits of the prop osed decision. [S0022-0434(00)00604-3].