舰载飞机着舰航迹角控制器设计  

Design of Carrier Landing Flight Path Angle Controller

作　　者：李冀鑫[1,3] 侯志强[1,2] 徐彦军[3] 林正[3] 

机构地区：[1]海军航空工程学院研究生管理大队,山东烟台264001 [2]海军航空工程学院飞行器工程系,山东烟台264001 [3]海军飞行学院教研部,辽宁葫芦岛125001

出　　处：《海军航空工程学院学报》2010年第3期303-306,共4页Journal of Naval Aeronautical and Astronautical University

摘　　要：为提高舰载飞机的着舰精度,基于总能量控制理论设计了着舰下滑航迹角控制器。频域分析结果表明,该控制系统使航迹角的响应带宽为1.21rad/s,满足了设计要求。基于非线性模型的仿真结果表明,该系统不但能够使航迹角快速地响应阶跃输入指令和保持飞行速度基本不变,且对于气动参数的摄动具有较好的鲁棒性。In order to increase the carrier landing precision,carrier landing flight path angle controller was designed based on total energy control theory. The analytical results in frequency domain show that the bandwidth of the control system is 1.21 rad/sec which achieves the design requirements. And the simulation results based on the nonlinear mathematical model prove that the step response is quick and good,and at the same time the flight velocity is unchanged. What＇s more,the robust performance is good when the aerodynamic coefficients are uncertain.

关 键 词：舰载飞机 总能量控制 着舰 航迹角控制 

分 类 号：V249[航空宇航科学与技术—飞行器设计]