碰撞角约束最优导引律关键问题的研究

Research on Key Problems of Optimal Guidance Law with Impact Angle Constraints

导弹的初始发射角度、剩余飞行时间估计精度对制导性能有较大的影响。以具有落角约束的空地导弹最优导引律为基础,研究了对于特定的落角如何选择初始发射角度,从而避免制导指令被限幅,并给出了关于初始发射角度和终端碰撞角度的成功打击区域。另外,具有角度约束的最优导引律弹道往往非常弯曲,利用传统的剩余飞行时间估计方法会造成较大的估计误差。本文提出了两种剩余飞行时间估计方法,可以有效克服传统方法的不足。仿真结果证明了所提出方法的有效性。

The initial heading angle of missile and the estimate accuracy of time-to-go considerably influence the missile＇s guidance performance. Based on angle-of-fall control optimal guidance law of air-to-surface missile, some in-depth research work was carried out. For a specified angle-of-fall, how to select initial heading angle to avoid command saturation was studied. The launch envelope of initial heading angle and terminal impact angle were given. In addition, since the optimal guidance law with angle constraint often achieves a curving ballistic trajectory, the traditional estimate method of time-to-go may bring about large error. Two new methods are proposed in this paper, which can overcome the shortcomings of traditional methods. Simulation results demonstrate the effectiveness of the proposed methods.