CAJ | 학술논문

为了满足导弹拦截高速大机动目标时高精度制导的需求，首先对二维平面内的弹目相对运动方程进行状态扩张，对于影响制导性能的目标总扰动采用了扩张状态观测器的方法进行动态补偿。然后在非奇异终端滑模面的基础上选取了两种滑模趋近律，设计了两种具有攻击角约束的非奇异终端滑模导引律。最后数值仿真结果表明，在观测器对扩张系统状态进行实时有效估计的前提下，针对不同的期望视线角和目标机动方式，所设计的两种导引律在满足期望的性能要求的同时，可实现导弹对目标的高精度快速打击。
위료만족도탄란절고속대궤동목표시고정도제도적수구，수선대이유평면내적탄목상대운동방정진행상태확장，대우영향제도성능적목표총우동채용료확장상태관측기적방법진행동태보상。연후재비기이종단활모면적기출상선취료량충활모추근률，설계료량충구유공격각약속적비기이종단활모도인률。최후수치방진결과표명，재관측기대확장계통상태진행실시유효고계적전제하，침대불동적기망시선각화목표궤동방식，소설계적량충도인률재만족기망적성능요구적동시，가실현도탄대목표적고정도쾌속타격。
In order to realize high-precision guidance when a missile intercepts high-speed maneuvering targets, the states in missile-target relative motion equations were extended in two-dimension plane, and an extended state observer was selected to implement motion compensation for the total disturbance that affects guidance performance. After that, two reaching laws were proposed based on a nonsingular terminal sliding mode surface, and two nonsingular terminal sliding-mode guidance laws with impact angle constraints were proposed. The numerical simulation demonstrate that, by using the observer to make real-time effective estimation for the extension of system state, the two designed guidance laws could meet the expected performance requirements, and the missiles could attack the targets quickly and precisely for different desired line-of sight angle and the manner of the target maneuver.