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飞机相比于攻击导弹,在飞行速度和机动性能等方面存在着劣势。为了提高其生存几率,设计了一种发射防御导弹协同对抗攻击导弹的自适应滑模制导律。该制导律本质是一种视线(Line of Sight,LOS)制导方法,通过对飞机与防御导弹和防御导弹与攻击导弹间的LOS调整以满足特定的几何关系,从而实现对攻击导弹的主动防御。最后,将所设计的制导律与比例导引进行了仿真比较。结果表明,由于与目标间的协同,所设计的制导律在机动性能和拦截性能方面具有明显的优势,且对于三方的飞行速度变化与攻击导弹的机动具有较强的鲁棒性。
Compared to the attacked aircraft, the aircraft have disadvantages in terms of flight speed and maneuverability. In order to improve its chances of survival, an adaptive sliding mode guidance law was developed to launch a defensive missile synergetic attack missile. The essence of the guidance law is a Line of Sight (LOS) guidance method, which proactively defends attack missiles by adjusting the LOS between aircraft and defensive missiles and defensive missiles and attacking missiles to meet certain geometric relationships. Finally, the designed guidance law is compared with the proportional guidance. The results show that due to the synergy with the target, the designed guidance law has obvious advantages in maneuverability and interception performance, and has strong robustness to the flight speed change of three parties and the maneuver of attacking missile.