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首页> 外文会议>AHS Specialists Conference on Aeromechanics Design for Transformative Vertical Flight >Nonlinear Aeroelastic Modeling of Cycloidal Rotor in Forward Flight
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Nonlinear Aeroelastic Modeling of Cycloidal Rotor in Forward Flight

机译：向前飞行中系环转子的非线性空气弹性建模

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In this paper, detailed development of a nonlinear aeroelastic model of a cycloidal rotor in forward flight is presented. Towards this, effect of forward flight on several aerodynamic phenomena such as virtual camber, inflow characteristics as well as effects of several unsteady phenomena such as leading-edge vortices, near and shed wakes are rigorously modeled. It is shown that forward flight velocity changes curvilinear geometry of flow associated with cycloidal rotor, which changes chord-wise variation of incident flow velocity angle on the blade and hence the dynamic virtual camber and incidence. The magnitude and direction of forward velocity along with phasing of cyclic blade pitch is shown to determine induced flow velocity magnitude and direction. The aerodynamic model is validated with in-house experimental data and CFD results. Once validated, the aerodynamic model is coupled with a geometrically exact beam-based blade structural model to develop a fully nonlinear aeroelastic model. Based on a systematic analysis performed using the validated model, it was observed that the dynamic nature of virtual camber and incidence plays an important role in production of net vertical and propulsive force by a cycloidal rotor in forward flight. It is important for a cycloidal rotor to have a backwards rotation with respect to forward speed (blade moving away from the flow in the upper half) for generating an upward vertical force; whereas, the propulsive force is insensitive to the direction of rotation. The vertical force increases with increase in advance ratio, while net propulsive force decreases.
机译：本文介绍了向前飞行中环形转子的非线性空气弹性模型的详细发展。对此，向前飞行对几种空气动力学现象的影响，如虚拟露角，流入特性以及几种不稳定现象的效果，如前沿涡旋，靠近和棚锯都是严格建模的。结果表明，前进的飞行速度改变与摆线转子相关的流动的曲线几何形状，这改变了刀片上的入射流速角的弦变化，因此动态虚拟弯曲和入射。向前速度以及循环叶片间距的分阶段的幅度和方向被示出为确定诱导的流速幅度和方向。空气动力学模型用内部实验数据和CFD结果验证。经过验证，空气动力学模型与基于几何精确光束的刀片结构模型耦合，以开发完全非线性空气弹性模型。基于使用验证模型进行的系统分析，观察到虚拟弯曲和发病率的动态性质在向前飞行中的循环转子产生净垂直和推进力的产生重要作用。对于向前速度（刀片远离上半部的流动的刀片移动）来产生向后旋转，非常重要的是，对于向前垂直力，重要的是，对于向前速度（刀片远离流动的流动）来说是重要的。虽然，推进力对旋转方向不敏感。垂直力随着预先比率的增加而增加，而净推进力降低。

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