一种连续修正速度方向的导引方法

考虑制导炮弹由身管武器发射，其飞行控制能力和导引信息量有限，基于预测落点位置偏差量来修正速度方向并在控制时间内连续分配导引指令的思想，提出了一种新的三维末制导方法。根据非线性弹道方程组的级数解预测弹丸落点位置，得到落点与目标的偏差，并提出了两种通过此偏差解算当前速度方向修正量的方法。取剩余飞行时间为修正时间，通过将速度方向修正量分配到整个剩余导引段建立了加速度修正公式，以减小导引指令饱和的可能性。通过连续地预测落点和分配加速度指令来实时地导引飞行。仿真结果表明：该导引方法简单可行，精度高，对控制能力要求较低，且具备较好的制导效果和毁伤效果，为该体制制导炮弹的应用提供参考依据。

A guidance law based on correcting velocity direction continuously

Taking the limited control authority and guidance information of a gun-launched guided projectile into account, a novel three-dimensional terminal guidance law based on the combination of the correction of the velocity direction via impact point prediction and continuous distribution of acceleration command is proposed. The deviations between the impact point of the projectile and the target are predicted based on the series solutions of the nonlinear ballistic equations. According to the deviations, the paper addresses two methods to calculate the direction angles corrections of the current speed. Design the remaining flight time as the correction time. The acceleration correction formulas are established through sharing the direction angles corrections of the current speed into the whole remaining guided flight to reduce the possibility of command saturation. By predicting the impact point and distributing acceleration corrections continuously to shape the trajectory in real time. The simulation results show that the proposed guidance law is feasible and effective, and provides the performances of high precision and little requirements of control authority and great guidance and damage effects, which provides a reference for the application of the guided projectile.