大气层外动能拦截器末段导引规律设计  

Design of Guidance Law for Exoatmospheric Interceptor During Its Terminal Course

作　　者：田源[1] 任章[1] 

机构地区：[1]北京航空航天大学自动化科学与电气工程学院,北京100083

出　　处：《宇航学报》2009年第2期474-480,共7页Journal of Astronautics

摘　　要：研究了末制导段轨控发动机开机和关机时拦截器与目标的相对运动规律,给出了零控脱靶量的近似表达式。定量分析了轨控发动机分别处于常值力和脉冲力工作状态时的作用效果,以及影响末制导律对视线转率修正能力的因素,并给出了末制导段发动机能够修正的初始视线转率上限。结合相对运动规律的特点,基于抑制视线转率的思想设计了末段的导引规律。根据轨控发动机所具有的两种工作状态,将末制导拦截过程分为三个阶段来设计,特别设计了轨控发动机在两种工作状态之间的过渡过程,让拦截器以近似于平行接近的方式拦截目标。通过仿真,证明了该导引规律的有效性。The relative motion law between the target and the interceptor during the terminal course was deeply analyzed when the divert thruster was on or off. An approximate expression of zero effort miss was given. The effect of the divert thruster was quantitatively analyzed in the constant-value and impulse states. The factors to the divert ability that corrected the LOS rate were researched on, and then the upper limit of the initial LOS rate was obtained. According to the relative motion law, a terminal guidance law was designed based on the method that restrained the line-of-sight rate. Since the divert thruster had two working states, the terminal course was divided into three phases and the transition phase from constant thrust to impulsive thrust was accurately designed, making the interceptor fly to the target in an approximate parallel approaching method. A simulation was given to prove the validity of the guidance law.

关 键 词：大气层外动能拦截器 轨控发动机 运动规律 末制导律 

分 类 号：V448[航空宇航科学与技术—飞行器设计]