CAJ | 학술논문

针对旋转靶弹低空飞行姿态难以快速调整以及参数摄动的问题，基于内外环的双滑模变结构方法，设计了旋转靶弹的双通道控制器。基于非线性模型，对靶弹快速变化的攻角和侧滑角以及慢速变化的高度和偏航距离分别设计了一种积分型滑模面，并采用指数趋近律减轻系统的抖振，利用Lyapunov稳定理论证明其稳定性。非线性仿真结果表明，该设计控制方法能快速准确响应控制指令，且在参数摄动时表现出较强的鲁棒性。
침대선전파탄저공비행자태난이쾌속조정이급삼수섭동적문제，기우내외배적쌍활모변결구방법，설계료선전파탄적쌍통도공제기。기우비선성모형，대파탄쾌속변화적공각화측활각이급만속변화적고도화편항거리분별설계료일충적분형활모면，병채용지수추근률감경계통적두진，이용Lyapunov은정이론증명기은정성。비선성방진결과표명，해설계공제방법능쾌속준학향응공제지령，차재삼수섭동시표현출교강적로봉성。
Aimming at flight attitude difficult to quickly adjust and parameter perturbation problems when rotating target missile fly at low altitude, inner and outer rings of the method of double SMVSC is adopted to design dual?channel controller for rotating target missile. Based on the nonlinear model of rotating target missile, the paper designs an integral sliding surface for rapidly changing attack angle and sideslip angle and slowly varying height and yaw distance respectively, buffeting is reduced by using index reaching law. It is proved to be stable by using Lyapunov stability theory. The designed control method is proved that it can quickly and accurately respond to control commands and exhibit strong robustness when parameter perturbate.