论文部分内容阅读
导引头侧窗探测技术的采用和大气层内气动力的存在要求针对该空域内目标的拦截弹于中制导末端,在零攻角的情况下将目标收入侧窗视场内,并针对目标的预测脱靶量为0,以满足中末制导交班和末制导弹道平直性的要求。基于此,本文从中制导末端的视场角约束和预测脱靶量为0出发,分析拦截弹中制导末端应达到的理想位置和运动状态,并据此设置虚拟目标和终端约束,运用最优控制原理设计针对虚拟目标的优化导引律。Matlab仿真结果验证了该方法能有效地保证交班条件和脱靶量要求的满足。
The introduction of the seeker side-window detection technique and the presence of aerodynamic forces in the atmosphere require that the interception missile aimed at the target in the airspace be centered on the mid-guided end and the target is to be received within the side-field of view at a zero angle of attack and directed against the target The predicted miss distance is 0, so as to meet the requirements of mid-to-final guidance and final guidance trajectory straightness. Based on this, this paper analyzes the ideal position and motion state to be achieved at the guidance end of the interception missile from the angle-of-view constraint and the prediction of the miss distance in the guidance end, and sets the virtual target and terminal constraints accordingly. Using the principle of optimal control Design optimization guidance law for virtual target. Matlab simulation results verify that this method can effectively meet the requirements of shift conditions and miss distance.