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本文对在发射时导引头无法捕获目标的超视距空对空战术导弹的中制导进行了研究。改进后的中制导规律是在最佳控制理论的基础上导出的。中制导的方程按照末段截获条件使飞行时间达到最短,控制的最佳条件归结为一个两点边界值问题。而这对于采用目前计算机技术实现实时在线控制是太复杂了。本文利用奇异扰动技术及工程近似方法使得完全不需要求解两点边界值问题。最后得到的改进的导引规律是一种近似最优且实现起来又足够简单的方法。通过计算机仿真,对该导引律与目前使用的线性最佳制导和比例导引方法进行了比较。后面两种方法为了形成所需的中制导弹道均按照指定条件用垂直g偏置指令进行了修正。本文所给出的先进中制导导引规律相对另外两种导引规律,在扩展外部发射边界方面有了明显的改善。
This paper studies the guidance of over-the-horizon air-to-air tactical missiles that seeker can not capture at launch. The improved Guidance Law is derived on the basis of the best control theory. The guidance equation in the final interception conditions to minimize the flight time, the optimal control conditions attributed to a two-point boundary value problem. And this is too complicated for real-time online control using current computer technology. In this paper, using the singular perturbation technique and the engineering approximation method, we do not need to solve the boundary value problem of two points at all. The resulting improved guidance law is a near optimal and easy to implement method. Through computer simulation, the guidance law is compared with the currently used linear optimal guidance and proportional guidance method. The latter two methods were modified with the vertical g-offset command in accordance with the specified conditions in order to form the required medium-to-heavy missile trajectory. Compared with the other two guiding laws, the guidance law of advanced middle guidance given in this paper has obvious improvement in extending the external emission boundary.