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首页> 外文期刊>Aeronautical journal >Interactional Aerodynamics And Acoustics Of A Hingeless Coaxial Helicopter With An Auxiliary Propeller In Forward Flight
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Interactional Aerodynamics And Acoustics Of A Hingeless Coaxial Helicopter With An Auxiliary Propeller In Forward Flight

机译：带有辅助螺旋桨的无铰链同轴直升机在向前飞行中的相互作用空气动力学和声学

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The aerodynamics and acoustics of a generic coaxial helicopter with a stiff main rotor system and a tail-mounted propulsor are investigated using Brown's Vorticity Transport Model. In particular, the model is used to capture the aerodynamic interactions that arise between the various components of the configuration. By comparing the aerodynamics of the full configuration of the helicopter to the aerodynamics of various combinations of its sub-components, the influence of these aerodynamic interactions on the behaviour of the system can be isolated. Many of the interactions follow a simple relationship between cause and effect. For instance, ingestion of the main rotor wake produces a direct effect on the unsteadiness in the thrust produced by the propulsor. The causal relationship for other interdependencies within the system is found to be more obscure. For instance, a dependence of the acoustic signature of the aircraft on the tailplane design originates in the changes in loading on the main rotor that arise from the requirement to trim the load on the tailplane that is induced by its interaction with the main rotor wake. The traditional approach to the analysis of interactional effects on the performance of the helicopter relies on characterising the system in terms of a network of possible interactions between the separate components of its configuration. This approach, although conceptually appealing, may obscure the closed-loop nature of some of the aerodynamic interactions within the helicopter system. It is suggested that modern numerical simulation techniques may be ready to supplant any overt reliance on this reductionist type approach and hence may help to forestall future repetition of the long history of unforeseen, interaction-induced dynamic problems that have arisen in various new helicopter designs.
机译：使用布朗的涡流传输模型研究了具有刚性主旋翼系统和尾部安装推进器的通用同轴直升机的空气动力学和声学特性。特别是，该模型用于捕获在配置的各个组件之间出现的空气动力学相互作用。通过将直升机的完整配置的空气动力学与其子组件的各种组合的空气动力学进行比较，可以隔离这些空气动力学相互作用对系统行为的影响。许多交互遵循因果之间的简单关系。例如，摄入主旋翼尾流会对推进器产生的推力不稳定产生直接影响。发现系统内其他相互依存关系之间的因果关系更加模糊。例如，飞机的声学特征对尾翼设计的依赖性源于主旋翼上载荷的变化，该载荷变化是由于需要修整尾翼上的载荷而引起的，该载荷是由于其与主旋翼尾翼的相互作用而引起的。用于分析对直升机性能的相互作用影响的传统方法依赖于根据其配置的各个单独组件之间可能存在的相互作用的网络来表征系统。这种方法虽然在概念上很吸引人，但可能会使直升机系统内某些空气动力相互作用的闭环性质模糊。建议现代数值模拟技术可能已准备好取代对这种简化派方法的任何过分依赖，因此可能有助于防止未来重复出现在各种新型直升机设计中的不可预见的，相互作用引起的动态问题。

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