基于倾转翼飞机垂直起降阶段PID姿态控制器设计  

Design of PID Attitude Controller for Tilt Rotor in VTOL Mode

作　　者：江稳 王琦[1] 高硕[1] 

机构地区：[1]南昌航空大学飞行器工程学院,江西南昌

出　　处：《国际航空航天科学》2017年第2期81-89,共9页Journal of Aerospace Science and Technology

摘　　要：倾转翼飞机克服了倾转旋翼飞机垂直起降状态因固定机翼阻挡旋翼下洗气流而造成的效率降低的问题,但仍存在姿态控制难问题。然后针对倾转翼飞机垂直起降阶段的姿态控制提出相应的控制方案,并对俯仰和横滚姿态控制建立了数学模型和采用PID控制方法设计了相应的姿态控制器,最后使用Matlab软件平台的Simulink模块对该PID控制方法的可行性和有效性进行仿真验证。结果表明,俯仰和横滚姿态控制器均能满足要求。The tilt wing aircraft overcomes the problem that the efficiency of the wing rotor IS reduced due to the lower air flow caused by the fixed wing blocking rotor, but there are still problems of attitude control. Then the corresponding control scheme is put forward for the attitude of the tilt wing aircraft in VTOL mode, and focuses on the pitch and roll attitude control mathematical model are established and the attitude controller is designed by using PID control method. Finally, the simulink module of Matlab software platform is used to simulate the feasibility and validity of the PID control method.

关 键 词：倾转翼飞机 俯仰控制 横滚控制 PID 

分 类 号：V27[航空宇航科学与技术—飞行器设计]