多功能火箭弹进行二维弹道末端修正时,同时需满足落点多角度约束,采用优化比例导引律存在导引精度低、指令过载大、稳定性差等缺陷.提出了一种基于滑模变结构的多功能火箭弹末制导律,能够满足小脱靶量,预定落角和水平入射角多约束条件.推导了制导律计算公式,给出了稳定性证明.最后通过数学仿真,比较比例制导和基于滑模变结构的末制导律性能差异,证明了提出方法的有效性.%Multi-purpose rockets need to meet terminal multi angle constraints when correcting two dimensional trajectory.Aiming at the problems of low guidance accuracy,overload,and poor stability by adopting optimal proportional guidance law,a terminal guidance law based on sliding mode variable structure theory is proposed to meet the small miss distance and the predetermined angle of fall and level of incident angle constraints.The formula of the guidance law is derived,and the stability validation is given.Finally,the performance of the proportional guidance law and the terminal guidance law are compared through mathematical simulation based on the sliding mode variable structure and the validity of the proposed method is verified.
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