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首页> 外文期刊>Journal of the American Helicopter Society >Performance and Loads of a Lift Offset Rotor: Hover and Wind Tunnel Testing
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Performance and Loads of a Lift Offset Rotor: Hover and Wind Tunnel Testing

机译：升举偏置转子的性能和负载：悬停和风洞测试

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摘要

The results of hover and wind tunnel tests of a reduced-scale, model rotor operating with lift offset are presented. The two-bladed rotor had a diameter of 2.03 m and constant cross section untwisted blades. Measurements include steady and vibratory hub loads, as well as control angles and pushrod loads. The rotor system was tested in hover and at advance ratios between 0.21 and 0.53, at collective pitches ranging from 3 degrees to 10 degrees, achieving blade loadings in excess of 0.10. At each forward flight operating condition, sweeps of lift offset up to 15% were performed. In forward flight, the rotor effective lift-to-drag ratio was found to increase with increasing advance ratio and lift offset, with a maximum increase of 40% compared to the zero lift offset case. Vibratory loads increased with advance ratio, with the largest loads in the two- and four-per-revolution harmonics. Lift offset is shown to modify vibratory hub forces and moments transmitted to the fixed frame, increasing vibratory rolling and pitching moments while decreasing vibratory thrust and torque.
机译：给出了带有升程偏移的缩小模型转子的悬停和风洞测试结果。两叶片转子的直径为2.03 m，横截面为不变的未扭曲叶片。测量包括稳定和振动的轮毂负载，以及控制角度和推杆负载。转子系统经过悬停测试，前进比在0.21到0.53之间，集体螺距在3度到10度之间，叶片负载超过0.10。在每个前向飞行操作条件下，都执行了升程偏移最大15％的扫掠。在前向飞行中，发现转子的有效升阻比随提前率和升程偏移的增加而增加，与零升程偏移的情况相比，最大增加了40％。振动载荷随提前传动比的增加而增加，最大的载荷是二次和四次谐波。升力偏移被显示为改变了传递到固定框架的振动轮毂力和力矩，增加了振动滚动和俯仰力矩，同时减小了振动推力和扭矩。

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