摘要
针对大气层外拦截器在中制导结束后还需要长时间无控飞行的情况,基于零控脱靶量思想采用最优控制理论,对拦截器和目标的相对运动关系进行了理论推导,以脱靶量和中制导加速度为性能指标,设计了一种拦截器发动机固定推进时间的中制导策略,研究了拦截器制导精度与零控脱靶量预测精度的关系,提出了调节拦截器机动过载大小的实现途径。仿真结果表明,设计的中制导律精度高、可靠性好、形式简单,在脱靶量计算得足够精确时,中制导结束后的零控脱靶量可控制在百米量级内,为拦截器以动能碰撞方式拦截目标创造了优良的末制导条件。
Aiming at the situation that the extra-atmospheric interceptor still needs to fly without control for a long time after the midcourse guidance,the relative motion relationship between interceptor and target is theoretically deduced by using the optimal control theory based on the zero effort miss.Then a midcourse guidance strategy with a fixed propulsion time of the interceptor engine is proposed,which is taking miss distance and midcourse guidance acceleration as performance indexes.Finally,the relationship between the guidance accuracy of the interceptor and the prediction accuracy of zero effort miss is studied,and the way to adjust the maneuver overload of interceptor is proposed.The simulation results show that the designed midcourse guidance law has high precision,good reliability and simple form.When the miss distance calculation is accurate enough,the zero effort miss after midcourse guidance can be controlled within 100 meters,which creates excellent terminal guidance conditions for the interceptor to intercept the target by kinetic energy collision.
作者
赵蒙
端军红
王明宇
殷双斌
鲁娜
ZHAO Meng;DUAN Junhong;WANG Mingyu;YIN Shuangbin;LU Na(Air and Missile Defense College,Air Force Engineering University,Xi’an 710051,China;Unit 93792 of the PLA,Langfang 065000,China)
出处
《系统工程与电子技术》
EI
CSCD
北大核心
2023年第2期538-545,共8页
Systems Engineering and Electronics
基金
国家自然科学基金(62173340)资助课题。
关键词
制导律
中制导
拦截器
零控脱靶量
guidance law
midcourse guidance
interceptor
zero effort miss
