摘要
提出了一种适用于空间拦截的离散脉冲式的最优标准轨道中制导律。首先,基于摄动方程建立了一种连续形式的最优标准轨道中制导律;其次,设计了拦截航天器助推器的开关机控制规律,提出了离散脉冲式最优标准轨道中制导律;最后,通过仿真验证了该中制导律的有效性。结果表明,所提出的中制导律制导精度较高,制导控制简单,易于工程实现,适用于普遍的空间拦截问题。
An optimal standard orbital guidance law for discrete impulse form of space intercept is presented.First,a continuous optimal nominal trajectory guidance law based on the perturbation equation of remote orbital transfer is put forward.Secondly,the on-off control law of the interceptor's booster is designed,and then the discrete impulse form of the guidance law is built up.Finally,an experiment is conducted,the results of which validate the effectiveness and advantages of the proposed midcourse guidance law.The proposed midcourse guidance law is of high precision and easy implementation,and is applicable to universal space interception.
作者
端军红
刘跃峰
DUAN Jun-hong;LIU Yue-feng(Air and Missile Defense College,Air Force Engineering University,Xi'an 710051,China;Science and Technology on Electro-optic Control Laboratory,Luoyang Institute of Electro-Optical Devices,Luoyang 471000,China)
出处
《飞行力学》
CSCD
北大核心
2018年第6期69-73,共5页
Flight Dynamics
基金
国家自然科学基金资助(11502300)
航空科学基金资助(20165196018)
关键词
空间拦截
转移轨道
摄动方程
标准状态轨迹
space interception
transfer orbit
perturbation equation
nominal state trajectory
