基于Bézier曲线的碰撞角约束多项式制导方法

Polynomial Guidance with Constrained Impact Angle Based on Bezier Curve

研究了一种基于Bézier曲线的碰撞角约束的制导律。通过模型转化将制导指令设计的问题转化为二次Bézier曲线形式的航迹角设计问题。首先,利用Bézier曲线的性质设计了导弹速度大小不变的制导律;然后进一步对导弹速度时变的末端角度约束的制导律进行了研究,同时对导弹速度时变情形下的剩余飞行时间进行了估计;最后通过不同情况下的数值仿真,验证了所提出的制导律的有效性。

The work presented investigates a polynomial guidance law with impact angle constraint based on Bézier curve.The problem of guidance command design is transformed into the design of the flight path angle,which is proposed in a quadric Bézier curve form,through mathematical model transformation.First,a guidance law is proposed with constant velocity by using the property of Bézier curve.Then,a guidance law of terminal angle constraint with time-varying velocity is studied;and then the time-to-go estimation under this strategy is obtained.Different simulations are carried out to verify the performance of the proposed guidance law.