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针对某些导弹在对目标进行打击时需要满足零脱靶量和攻击角度约束的要求,首先基于终端滑模控制和有限时间控制理论,改进了一种快速收敛的非奇异终端滑模函数,用于设计滑模面,结合自适应指数趋近律,提出了一种自适应非奇异终端滑模控制方法,解决了传统终端滑模控制中存在的奇异问题,并使状态变量在有限时间内快速收敛到平衡点。然后将所提方法用于导引律的设计,提出了一种带攻击角度约束的自适应非奇异和有限时间收敛导引律,实现了导弹对脱靶量和攻击角度约束的要求;采用有限时间控制理论对该导引律的收敛特性进行了分析,证明了制导系统状态的全局有限时间快速收敛特性。与传统的非奇异终端滑模导引律相比,本文所提导引律能够在更短的时间内以更小的脱靶量和更高精度的攻击角度对目标实施打击。最后进行了大量的对比仿真实验,仿真结果验证了所提导引律的有效性。
In order to meet the requirement of zero miss distance and attack angle constraint, some missiles need to meet the requirements of target misspecification. Firstly, based on terminal sliding mode control and finite-time control theory, a fast convergent non-singular terminal sliding-mode function is proposed for An adaptive non-singular terminal sliding mode control method is proposed based on the adaptive sliding-mode sliding mode. The singularity problem in traditional terminal sliding mode control is solved and the state variables converge rapidly in finite time To balance. Then, the proposed method is applied to the design of the guidance law. An adaptive non-singular and finite time convergence guidance law with attack angle constraints is proposed, which realizes the requirements of missiles for the miss distance and attack angle constraints. The control theory analyzes the convergence property of the guidance law, and proves the global finite time fast convergence of the guidance system. Compared with the traditional non-singular terminal sliding-mode guidance law, the guidance law proposed in this paper can attack the target in a shorter time with a smaller miss distance and more accurate attack angle. Finally, a large number of comparative simulation experiments were carried out, and the simulation results validated the validity of the guidance law.