CAJ | 학술논문

为了解决滑翔式高超声速飞行器大攻角侧向机动时高精度高稳定性的控制要求，针对该过程中存在的多个不确定因素和控制耦合，对耦合特性进行分析，建立面向控制的滑翔式高超声速飞行器动力学模型。利用H∞回路成形设计方法设计了控制器，并提出了一种期望传递函数的选取方法。最后对所设计的控制系统进行三通道联合仿真。结果表明该控制系统满足滑翔式高超声速飞行器大攻角侧向机动的控制要求。
위료해결활상식고초성속비행기대공각측향궤동시고정도고은정성적공제요구，침대해과정중존재적다개불학정인소화공제우합，대우합특성진행분석，건립면향공제적활상식고초성속비행기동역학모형。이용H∞회로성형설계방법설계료공제기，병제출료일충기망전체함수적선취방법。최후대소설계적공제계통진행삼통도연합방진。결과표명해공제계통만족활상식고초성속비행기대공각측향궤동적공제요구。
In order to meet the high requirement of control and stability of gliding hypersonic vehicle when lateral maneuvering with high attack angle , we propose a new control method based on H∞ loop shaping .Focusing on the multi-indeterminate factors and control decoupling in lateral maneuvering and after analyzing the features of the decoupling , we establish the control oriented mathematical model of hypersonic vehicle .H∞loop shaping meth-od shows great predominance in conducting uncertainty research in model co-prime factorization .Based on the a-bove feature, we present an improved loop shaping method and selection method of expected shape .In the end, the proposed algorithm is simulated using MATLAB; the results and their analysis show preliminarily that the control system can satisfy the requirement of gliding hypersonic vehicle when doing lateral maneuvering with high attack an -gle.