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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.
In order to deal with the final hovering problem of hypersonic vehicle, a self-adaptive proportional guidance law is proposed to achieve high-precision fixed-point directional strike. By analyzing the longitudinal entry conditions, a convergence strategy is proposed to improve the time- So that the aircraft has enough time to make horizontal and vertical adjustment to ensure the satisfaction of the falling point constraint.As the guidance parameters directly affect the accuracy of the falling point and the falling angle and the aircraft dynamics constraints can not lead to the ideal response to the guidance command, A closed-loop nonlinear adaptive law ensures that the aircraft can hit the target with high accuracy by selecting guidance parameters online.The simulation results show the validity and accuracy of the final guidance method.