On influence of kinematics to equivalent linear damping of helicopter blade hydraulic damper |
| |
| Authors: | Hu Guo-cai Xiang Jin-wu Zhang Xiao-gu |
| |
| Affiliation: | Institute of Aircraft Design and Research, Beijing University of Aeronautics and Astronautics, Beijing 100083, P. R. China |
| |
| Abstract: | An analytical model of hydraulic damper was presented in forward flight accounting for pitch/flap/lag kinematic coupling and its nonlinear force_velocity curve. The fourth order Runge_Kutta was applied to calculate the damper axial velocity in time domain. Fourier series based moving block analysis was applied to calculate equivalent linear damping in terms of transient responses of damper axial velocity. Results indicate that equivalent linear damping will be significantly reduced if pitch/flap/lag kinematic coupling introduced for notional model and flight conditions. |
| |
| Keywords: | nonlinear damping hydraulic damper equivalent linear damping helicopter rotor blade kinematic coupling |
| 本文献已被 CNKI 万方数据 SpringerLink 等数据库收录！ |
| 点击此处可从《应用数学和力学(英文版)》浏览原始摘要信息 |
|
点击此处可从《应用数学和力学(英文版)》下载全文 |
