适合机动飞行的旋翼气动模型研究  

Study of aerodynamic model for the maneuvering rotor

作　　者：徐进[1] 高正[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学实验室,南京210016

出　　处：《航空动力学报》2008年第1期94-99,共6页Journal of Aerospace Power

摘　　要：为改善对旋翼空气动力他轴响应的预测,在旋翼气动模型中引入时变的尾迹弯曲参数KR,以体现机动旋翼的尾迹畸变效应.与已有方法相比,该模型的计算结果更为接近实验数据.还建立了动态尾迹畸变模型,并分析了计入尾迹收缩效应的必要性.结果表明,为了正确计算机动飞行中的旋翼气动力,特别是操纵的他轴响应,应当在模型中采用随状态变化的尾迹弯曲参数KR.To improve the prediction of the rotor＇s off-axis aerodynamic response, the wake distortion effect of maneuvering rotor was studied with the introduction of time-accurate wake curvature parameter （KR） into the maneuvering rotor model. As compared with existing approaches, the computed results from this model are more close to the test data. Besides, a dynamic wake distortion model was constructed, while the necessity of incorporating the wake contraction effect was analyzed. The research results show that： the operatingstate-dependent （KR） shall be applied to aerodynamic models in order to calculate accurately the rotor aerodynamic forces and moments, especially for off-axis response.

关 键 词：航空 航天推进系统 机动飞行 旋翼 尾迹畸变 尾迹弯曲参数 他轴响应 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程] V249.1