CAJ | 학술논문

为提高脉冲推冲器的弹道修正效能，通过理论分析的方法分析了脉冲推冲器在不同弹道段的内弹道修正能力分布情况。数值仿真和分析结果表明，在弹道上升段脉冲推冲器的横向修正能力大于纵向，而在弹道的下降段横向和纵向修正能力相当。提出了上升段只进行横向修正和下降段进行综合修正的修正策略，并优化了脉冲推冲器点火相位。采用122 mm火箭弹对优化后的脉冲点火控制方法进行了数值仿真。结果表明：该控制方法能有效提高脉冲推冲器的修正效果。
위제고맥충추충기적탄도수정효능，통과이론분석적방법분석료맥충추충기재불동탄도단적내탄도수정능력분포정황。수치방진화분석결과표명，재탄도상승단맥충추충기적횡향수정능력대우종향，이재탄도적하강단횡향화종향수정능력상당。제출료상승단지진행횡향수정화하강단진행종합수정적수정책략，병우화료맥충추충기점화상위。채용122 mm화전탄대우화후적맥충점화공제방법진행료수치방진。결과표명：해공제방법능유효제고맥충추충기적수정효과。
In order to improve the correction efficiency of impulse j et,the correction ability of impulse j et was analyzed and calculated in theory.The simulation and analysis results show that the correction distance at the same point in the cross range direction is longer than the range direction before the apogee of the traj ectory,and the distance is almost the same in both direction after the apogee.A method was put forward that the across direction was corrected during the ascend phase and the across and vertical direction was corrected at the same time after the apogee,and then an optimization strategy for the firing phase angle was presented.The control method was verified by the simulation.The results show that the method can improve the correction ability of rocket proj ectile greatly.