基于标准弹道点的最优制导方法

由于基于需要速度的显式制导方法要确定虚拟目标点,虚拟目标点的确定要对地球扁率和再入阻力的影响进行修正,存在着百米以上的修正误差,为此提出了基于标准弹道点的最优制导方法,即将标准弹道的某点作为目标点进行需要椭圆轨道计算及最优入轨控制。提供了采用弹上迭代制导方法实现最优控制,同时给出了预测关机参数的需要椭圆轨道终端约束校正方法。该制导方法无需进行地球扁率和再入阻力的影响修正,可以减少方法误差,仿真计算证明了这一点。

The Optimal Guidance Method Based on Standard Ballistic Point

Making a certain virtual target is needed in the explicit guidance based on the required velocity,the earth oblateness and reentry aerodynamic resistance effects are revised in making a certain virtual target,which causes the error of 100 m.So the optimal guidance method based on standard ballistic points is put forward,that is,some point in standard trajectory is regarded as a target to calculate the required ellipse trajectory and optimal control injection of the missile.In this article the iterative explicit guidance is put forward for the optimal control issue when the missile is flying,at the same time the correction method about the required ellipse trajectory termination constraint of the forecasted shut down point parameter is given.The method error of the optimal guidance gets less by the simulation calculation.