以提高低动压着舰时动态跟踪及抑制舰尾气流扰动的性能为期望 ,基于线性矩阵不等式 (LMI)的 H∞ 控制理论 ,提出了保持由地速构成的迎角 αd 恒定的 H∞ 飞行 /推力综合控制增广模型结构。使飞机在接近舰尾处于雷达导引系统关闭的关键时刻 ,该系统仍有姿态保持及抑制气流扰动的优良性能 ,从而改变了传统设计需由导引系统纠正气流扰动而引起的轨迹偏离。基于工程应用 ,文中提出了 H∞ 控制器的降阶方法 ,进行了离散化实时仿真验证。仿真表明 ,本文开发的系统能够很好地满足设计要求 Based on the H∞ control theory of linear matrix inequality (LMI), it is proposed to keep the H∞ flight with αd constant angle of attack, which is composed of the ground speed, and to improve the performance of dynamic tracking and suppression of airstream disturbances. / Thrust Composite Control Extended Model Structure. As the aircraft approaches the stern at the critical moment when the radar guidance system is shut down, the system still possesses the excellent performance of attitude retention and suppression of airflow disturbance, thus changing the trajectory deviation caused by the disturbance of airflow caused by the guidance system in the conventional design. Based on the engineering application, a reduction method of H∞ controller is proposed in this paper, which is verified by discrete real-time simulation. Simulation shows that the system developed in this paper can well meet the design requirements