摘要
研究了基于自适应滤波技术、采用伺服惯性力发生器（ＳＩＦＧ）的直升机结构响应主动控制；比较了被动动力吸振器和ＳＩＦＧ的减振效果。研究表明，ＳＩＦＧ在直升机前飞速度和旋翼转速及前飞速度改变的情况下均能保持良好的减振效果。
An active control system for helicopter structure response is studied, which includes a servo inertial force generator (SIFG), an electro hydraulic servo controller and an adaptive controller. Following the modelling of the SIFG and the design of the electro hydraulic controller, an adaptive controller is built using RLS algorithm. The response induced by the disturbance is reconstructed and used as the reference signal required by adaptive filtering algorithm, and a method for measuring and recovering the stability of the algorithm is made.The vibration reduction of a passive absorber and the SIFG is compared for a forward flight helicopter with a constant rotor speed and variant rotor speeds. It is concluded that the SIFG with adaptive vibration controller can provide better results for different flight conditions.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1997年第3期359-362,共4页
Acta Aeronautica et Astronautica Sinica
关键词
自适应控制
结构振动
直升机
adaptive control, structural vibration, helicopter
