舰面直升机旋翼瞬态气弹响应分析  

Aeroelastic Response Analysis of Helicopter Rotor During Shipboard Operation

作　　者：康浩[1] 高正[1] 

机构地区：[1]南京航空航天大学飞行器系,江苏南京210016

出　　处：《航空动力学报》2000年第1期67-70,共4页Journal of Aerospace Power

摘　　要：建立了舰面直升机起动和停车过程中的旋翼瞬态气弹响应分析方法,在桨叶结构建模中考虑了桨叶的挥舞、摆振、扭转和拉伸变形并计入了桨叶重量影响和因旋翼速度变化产生的惯性力。桨叶气动力计算采用时域非定常空气动力计算模型,包括非线性分离和动态失速的影响。用实验数据对分析方法进行了验证。最后。A method of transient aeroelastic rotor response analysis was developed and used to investigate shipboard engage/disengage sequences of the helicopter rotor.The blade was modeled as an elastic beam undergoing flap,lag torsion and axis deflections.The weight of blade and the inertia force due to the variation of rotation speed were taken into account.Blade element theory was used to calculate unsteady aerodynamic loads in linear and nonlinear regimes.The experimental data validated this analysis.The parameter effects on transient response were investigated.

关 键 词：直升机 旋翼 气动力弹性 响应分析 瞬态 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]