CAJ | 학술논문

由于变结构控制的滑动模态具有完全的自适应性,不必全面研究系统的各种摄动及外干扰,只需根据高速度大机动目标的特点,对其实现自适应,将各种干扰及偏差的影响归入有关增益系数上加以考虑.应用变结构滑膜控制理论,推导了出一种适用于拦截高速大机动目标的空间制导规律,该制导规律能将系统引向滑动面并保持在其上运动.算例仿真证明,变结构项保证了对目标机动的鲁棒性,简单易行利于工程实现.
유우변결구공제적활동모태구유완전적자괄응성,불필전면연구계통적각충섭동급외간우,지수근거고속도대궤동목표적특점,대기실현자괄응,장각충간우급편차적영향귀입유관증익계수상가이고필.응용변결구활막공제이론,추도료출일충괄용우란절고속대궤동목표적공간제도규률,해제도규률능장계통인향활동면병보지재기상운동.산례방진증명,변결구항보증료대목표궤동적로봉성,간단역행리우공정실현.
Due to self-adaptability of the sliding model of the variable structure control, there is needless to total?ly study the system various perturbation and external interference, but only to realize the self-adaptability accord?ing to the characteristics of the high-velocity, high-maneuverable target. The effects of the various interference and deviation are considered in the design of the relative gain factor. Variable structure adaptive control theo?rem was used to obtain a three-dimensional guidance law which was suitable for the missile to intercept the tar?get of high velocity and maneuver. This guidance law would be led the system onto sliding plane and would be maintained it onto sliding plane. Simulation experiments indicated that variable structure item guaranteed the ro?bustness to target maneuverability.