中文摘要：

针对高超声速飞行器末段打击问题,提出了具有自适应能力的比例导引律,实现了高精度定点定向打击.通过纵向进入条件的分析,设计了一种提高比例导引进入时间的收敛策略,从而使飞行器有足够的时间进行横纵向调整,保证了落角落点约束的满足.由于制导参数直接影响落点和落角的精度,而飞行器动力学约束会导致无法理想响应制导指令,因此设计了一种闭环非线性自适应律,通过在线选择制导参数确保飞行器以高精度命中目标.仿真结果表明了该末制导方法的有效性和准确性.

英文摘要：

An adaptive proportional navigation guidance law is proposed for hypersonic vehicle terminal guidance. The vehicle could be guided to impact the target precisely in a specific direction with required circu- lar error probable. Based on the analysis of longitudinal flight, a convergence strategy was designed to make the proportional navigation guidance works earlier. The strategy allowed more time for the vehicle to meet the heading constraints at the impact. The precision of impact was affected by guidance parameters directly. How- ever, vehicle would not conduct guidance commands ideally because of dynamic constraints. A close-loop non- linear adaptive law was introduced to update guidance parameters online to improve the impact precision. Sim- ulation results demonstrate the affectivity and accuracy of the proposed method.