几何耦合对直升机桨叶液压减摆器等效线性阻尼的影响研究

On Influence of Kinematics to Equivalent Linear Damping of Helicopter Blade Hydraulic Damper

Institute of Aircraft Design and Research, Beijing University of Aeronautics and Astronautics, Beijing 100083, P.R.China

摘要: 建立了直升机前飞时,计入变距/挥舞/摆振几何耦合和力-速度非线性关系的液压减摆器分析模型;用4阶龙格-库塔法在时域内计算减摆器的轴向速度;根据减摆器轴向速度的瞬态响应成分,利用基于富里叶级数的移动矩形窗方法计算了减摆器等效线性阻尼。结果表明,存在变距/挥舞/摆振几何耦合的液压减摆器,在直升机前飞时其等效线性阻尼将大幅度下降。
- 非线性阻尼 /
- 液压减摆器 /
- 等效线性阻尼 /
- 直升机旋翼桨叶 /
- 几何耦合
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.
- nonlinear damping /
- hydraulic damper /
- equivalent linear damping /
- helicopter rotor blade /
- kinematic coupling

[1]	Twomey C B, Wereley N M. Review of engine/airframe/drive train dynamic interface development problem[R]. ADA057932,1978,111-124.
[2]	Niebanck C, Girvan W. Sikorsky S-76 analysis, design, and development for successful dynamic characteristics[A]. In:AHS Ed. The American Helicopter Society 34th Annual Forum Proceedings[C]. American: Washington DC,1978,78-23-1-17.
[3]	Tarzanin F J, Panda B. Development and application of nonlinear elastomeric and hydraulic lag models[R]. AIAA-95-1449,1995.
[4]	Wang J M, Challenges in rotor dynamics correlation[A]. In:AHS Ed. The American Helicopter Society 54th Annual Forum Proccedings[C]. America: Washington DC,1998.
[5]	Johnson W. 直升机理论[M]. 孙如林译. 北京:航空工业出版社,1991.
[6]	Bousman W G, Winkler D J. Application of the moving-block analysis[R]. AIAA-81-0653,1981.
[7]	Tasker F A, Chopra I. Assessment of transient analysis techniques for rotor stability testing[J]. Journal of the American Helicopter Society,1990,35(1):39-50.
[8]	Smith C B, Wereley N M. Damping identification in helicopter rotor system[A]. In:AHS Ed. The American Helicopter Society 54th Annual Forum[C]. America: Washington DC,1998.