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首页> 外文期刊>Journal of the American Helicopter Society >Using Control Redundancy for Power and Vibration Reduction on a Compound Helicopter at High Speeds
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Using Control Redundancy for Power and Vibration Reduction on a Compound Helicopter at High Speeds

机译：使用控制冗余来高速降低复合直升机的功率和减振

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This study examines a compound helicopter with an articulated main rotor, focusing on the high advance ratio, low disk loading environment attained at a flight speed of 225 kt. The objective of the study is to examine how aircraft power and hub vibrations can be minimized through the use of redundant controls available on a compound configuration. The compound model is based on a UH-60A derivative with 20,110 lb of gross weight with simulations performed using the Rotorcraft Comprehensive Analysis System. Untwisted blades are compared against -8 degrees linearly twisted blades. It was observed that for the rotor with -8 degrees twist, the minimum power and minimum vibration states corresponded to very different redundant control settings and main rotor behavior. The low-power state occurs at lower RPM, lower stabilator pitch, and higher auxiliary thrust, with lower forward flapping of the main rotor. At a state with reduced vibrations, main rotor forward tilt is higher, resulting in weaker blade-vortex interactions over the aft section of the rotor disk. For an untwisted rotor, it was shown that the controls for minimum power and minimum vibrations are more similar, and the rotor operates best with lower rotor speed and reduced flapping relative to the rotor with twist. Untwisting the rotor and providing proper control settings can reduce the power requirement by 7-16% and the hub vibrations by 50-80%, relative to a -8 degrees twisted blade with proper control settings. Control of lift offset through the use of ailerons did not provide any further reductions for either twist case.
机译：这项研究研究了具有铰接式主旋翼的复合直升机，重点研究了以225 kt的飞行速度实现的高推进比，低磁盘加载环境。该研究的目的是研究如何通过使用复合结构上可用的冗余控制来最大程度地降低飞机的动力和轮毂的振动。复合模型基于UH-60A衍生产品，毛重为20,110磅，并使用Rotorcraft综合分析系统进行了仿真。将未扭曲的刀片与-8度线性扭曲的刀片进行比较。已观察到，对于-8度扭转的转子，最小功率和最小振动状态对应于非常不同的冗余控制设置和主转子性能。低功率状态发生在较低的RPM，较低的稳定器螺距和较高的辅助推力下，同时主转子的前向摆动较小。在振动减小的状态下，主旋翼向前倾斜较高，从而导致在旋翼盘的后部部分上较弱的叶片涡旋相互作用。对于未扭转的转子，已显示出最小功率和最小振动的控制更为相似，并且转子在较低的转子速度下运行最佳，并且相对于带有扭转的转子，其拍打减少。相对于采用适当控制设置的-8度扭曲叶片，解开转子并提供适当的控制设置可以将功率需求降低7-16％，将轮毂振动降低50-80％。通过使用副翼来控制升程偏移并不能进一步降低任一扭转情况。

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