Rotor Wake Modeling for Flight Dynamic Simulation of Helicopters
Rotor Wake Modeling for Flight Dynamic Simulation of Helicopters
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DOI：
10.2514/2.922
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发表时间：
2000
期刊：
影响因子：
2.5
通讯作者：
Richard Brown
中科院分区：
文献类型：
--
作者：
Richard Brown
本文建立了一个计算直升机旋翼尾流的数学模型，该模型基于控制涡量产生和对流的非定常流体动力学方程的数值解。该模型解决了几个问题的具体利益的背景下，直升机飞行动力学建模。涡结构的过度数值耗散的问题，最常见的基于网格的计算技术，克服使用涡守恒方法结合适当的涡通量限制器功能。使用时间因子分解型算法可以使尾流模型避免在飞行动力学应用中由于旋翼和机身时标之间的差异而引入的刚度，并对直升机尾流的时变涡流结构产生快速的解。该模型被证明产生有效的解决方案，叶片载荷和尾流结构的孤立和相互作用的转子在悬停和前飞
A computational helicopter rotor wake model, based on the numerical solution of the unsteady fluid-dynamic equations governing the generation and convection of vorticity through a domain enclosing the helicopter, has been developed. The model addresses several issues of specific interest in the context of helicopter flight dynamic modeling. The problem of excessive numerical dissipation of vortical structure, common to most grid-based computational techniques, is overcome using a vorticity conservation approach in conjunction with suitable vorticity-flux limiter functions. Use of a time-factorization-type algorithm allows the wake model to avoid the stiffness that is introduced in flight dynamic applications by the disparity between the rotor and fuselage timescales and to generate rapid solutions to the time-varying vortical structure of the helicopter wake. The model is demonstrated to yield valid solutions to the blade loading and wake structure for isolated and interacting rotors in both hover and forward flight