A novel terminal guidance law based on stochastic fast smooth second-order sliding modes control theory was proposed to handle the track imprecision mainly caused by stochastic maneuvering of the target, inertial lag, and model uncertainties.It is assumed that the target acceleration term was a zero mean Gaussian white noise and the missile-interceptor guidance system became a stochastic uncertain nonlinear system driven by additive noise, which did not have any equilibrium.So a concept of finite-time second-order mean-square practical convergence was presented and the finite-time convergence property of proposed control was proved.Then the direct hit sliding mode manifold was chosen and the guidance law was designed.The applicability of the new guidance law was illustrated through simulations of a guided missile intercepting a stochastic maneuvering target in tail chase and head-on intercepts case, respectively.Results show the validity and effectiveness of the proposed method, while a comparison is made with the augmented proportional navigation guidance law, the traditional sliding mode guidance law and smooth second order sliding mode guidance law.%针对目标随机机动、惯性延迟、参数变化等因素降低导弹末制导精度的问题,提出新型随机快速光滑二阶滑模控制方法.将目标机动简化为零均值高斯白噪声过程,制导系统成为带加性噪声随机不确定非线性系统.考虑到该系统不存在平衡点,提出有限时间二阶均方实用收敛概念,并基于此证明了所设计控制律的收敛特性.根据直接命中条件设计滑模面,得到随机快速光滑二阶滑模制导律.在尾追和迎头两种态势下,将该新型制导律与扩展比例导引、一般滑模制导律及确定性光滑二阶滑模制导律进行仿真比较,验证了该方法的正确性和有效性.
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