The missile guidance law utilizing nonlinear variable structure control is proposed. The acceleration command input is determined considering the target acceleration as an uncertainty.
针对导弹拦截问题，在非线性系统滑模变结构控制理论的基础上，提计出一种新型滑模变结构导引律；
The missile guidance law utilizing nonlinear variable structure control is proposed. The acceleration command input is determined considering the target acceleration as an uncertainty.
针对导弹拦截问题，在非线性系统滑模变结构控制理论的基础上，提计出一种新型滑模变结构导引律；
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