摘要
80年代兴起的高次谐波主动控制技术是直升机抑振技术领域中十分活跃的研究课题。本文从控制观点阐述高次谐波控制(HHC)基本原理,提出HHC中的旋翼系统及机体振动的数学模型,提供自适应HHC方法,并辅以仿真验证。
This paper, in the view of control theory, interprets, the bagic principles of the higher hamonic control(HHC)for the helicopter, proposes the vibration mathematical models of the rotor blade and the airframe in forward flight. The designs of control law and controller, the methods of system identifiention discussed specifically for the self-adaptive HHC. The effectiveness reducing the vibration level has been shown by the mumerical simulation.
出处
《直升机技术》
1996年第1期1-7,共7页
Helicopter Technique
