摘要
研究了伺服惯性力发生器的基本特性及其在直升机振动控制中的应用。首先,建立了由电液伺服控制器、电液伺服阀、液压作动筒、弹性元件和惯性元件组成的伺服惯性力发生器的数学模型;接着,确定了设计电液伺服控制器的准则,分析了伺服惯性力发生器的特性;进而研究了基于自适应前馈控制的振动控制器的设计;最后,将伺服惯性力发生器和振动控制器应用于直升机振动控制。仿真表明,伺服惯性力发生器可提供良好的减振效果。
Deals with the feature and application of a servo inertial force generator (SIFG). The SIFG is an electro hydraulic servo apparatus with two states: passive absorber and active vibration reductor, and includes an inertial mass, a spring, a hydraulic cylinder controlled by a servo valve and a servo controller. Firstly, the mathematical mo del of the SIFG is derived. The criteria for designing the servo controller are determinated. The features of the SIFG with or without the controller are analysed. Then, based on the principle of adaptive filtering, an adaptive controller is built. Lastly, the SIFG is installed in a helicopter fuselage. The vibration reduction of the passive absorber and the SIFG is compared, it can be concluded that the SIFG with adpative controller can provide better vibration reduction.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
1998年第4期366-370,共5页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
直升机
结构振动
伺服系统
自适应控制
SIFG
helicopters
structural vibration
electro hydraulic servo system
adaptive control