微型导弹命中角度和时间受控的制导方法研究

Study on Impact Angle and Impact Time Control Guidance Law for Micro Missiles

为提高微型导弹的杀伤力,研究了一种空中发射微型导弹命中角度和时间受控的制导律。建立了微型导弹和目标的相对运动方程组,用变结构控制理论设计了一种对终端命中角度约束的制导律。为保证微型导弹以特定角度命中目标的同时,命中时间也满足要求,在变结构制导律基础上加入了命中时间受控的制导项。在单发导弹和3发导弹同时攻击地面运动目标的两种场景中,对设计的制导律与修正比例导引律进行了仿真,结果表明:设计的制导律弹道曲线更平直,更易适应导弹末段转弯速率有限的条件,在目标有机动干扰时其制导精度更高,且攻击角度满足约束要求;在多弹协同攻击时,设计的制导律可实现多枚导弹在给定时间内以一定命中角度协同打击同一目标。

To improve the killability of micro missile, a control guidance law for the impact angle and the impact time of air-launched micro missiles was studied in this paper. The guidance law with constraints on terminal attacking angle was designed by utilizing the variable structure control theory according to relative dynamic equations of the micro missile and the target. The influence of impact time constraints was also added into the guidance equation, since the demand that the micro missile hit the target with specified angle as well as the impact time would be ensured. The simulation was carried out using control guidance proposed and modified proportional guidance law in two scenarios in which one was only one micro missile and the other was three micro missiles cooperatively. The results showed that the trajectory of the proposed guidance law was smoother than that of modified proportional guidance law, which was suitable to the situation that the turning speed of the missile was limited in the terminal phase. The proposed law had high guidance accuracy for maneuvering target and attacking angle met the constraint requirement. And the proposed guidance law could realize the cooperative attacking the same target with the required impact angle in certain time for many missiles.