速度可调空空导弹鲁棒末制导律

Robust Terminal Guidance Law for Air-to-Air Missile of Adjustable Velocity

针对采用变流量固体火箭冲压发动机的空空导弹速度可调的特点,提出了一种非线性鲁棒末制导律。将弹目相对速度与视线角速度一起作为被控状态,基于准平行接近原理,通过选择合适的李雅普诺夫函数,在保证了制导系统大范围渐近稳定的同时,结合非线性H∞鲁棒控制理论,推导出了鲁棒末制导律的表达式。数字仿真结果表明,该制导律不仅对目标的大范围机动具有较强的鲁棒性,命中精度较高,并且与传统末制导律相比,能够明显缩短导弹拦截时间,具有较大优势。

According to adjustable character of the velocity of air-to-air missile with variable-flow ducted rockets, a nonlinear terminal guidance law with robustness was proposed. The relative velocity of the missile and the target was taken as controlled state as well as the line-of-sight angular-velocity. Based on the principle of quasi constant bearing navigation, a proper Lyapunov function was chosen. The global asymptotic stability of the guidance system was ensured, and the expression of the robust terminal guidance law was obtained by means of the nonlinear H ∞robust control theory. Simulation results show that, for the missile intercepting a target with high ma- neuverability,the proposed terminal guidance law not only has strong robustness and excellent guidance precision, but also can shorten the interception time compared with the traditional one.