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首页> 外文期刊>Journal of the American Helicopter Society >Performance and Loads Study of a High-Speed Compound Helicopter
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Performance and Loads Study of a High-Speed Compound Helicopter

机译：高速复合直升机的性能和载荷研究

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摘要

An aeromechanics analysis was conducted of a large-winged, single main rotor, compound helicopter modified from the AH-56A Cheyenne, in cruise and high-speed flight (250 kt) at sea level and high-altitude (20,000 ft) conditions. Performance and representative loads were evaluated with the comprehensive code RCAS to show the effect of compound configuration decisions. Validation of compound performance prediction was shown with AH-56A test data. An assessment of the role of compound configuration, collective setting, wing pitch, rotor speed, altitude, and trim control strategy on performance and loads was made. The study shows how reducing collective, for a constant wing pitch, is beneficial for peak L/D-e and reducing loads. Increasing wing pitch, at a constant collective, improves peak L/D-e, but can reduce L/D-e at high airspeeds and limit maximum airspeed. A 30% reduction in rotor speed achieved significant performance increases, while larger reductions limited high airspeed and high-altitude trim due to stall. High-altitude flight improves L/D-e at all airspeeds if stall on the propeller can be prevented. Ailerons and horizontal stabilizer trim control does not adversely affect L/D-e, but does allow use of rotor cyclics to trim for reduced flap-bending loads. The final compound configuration achieved a peak L/D-e = 8.5 around 140 kt and L/D-e 5.0 at the maximum airspeed considered of 250 kt.
机译：对从AH-56A夏安改装而成的大型机翼单主旋翼复合直升机进行了航空力学分析，在海平面和高空（20,000 ft）条件下进行巡航和高速飞行（250 kt）。使用综合代码RCAS对性能和代表性负载进行了评估，以显示复合配置决策的效果。 AH-56A测试数据显示了化合物性能预测的有效性。评估了复合构型，整体设置，机翼俯仰，旋翼速度，高度以及调整控制策略对性能和载荷的作用。研究表明，对于恒定的机翼螺距，减小总和对于峰值L / D-e和减小载荷是有好处的。以恒定的总和增加机翼螺距可以改善峰值L / D-e，但可以降低高空速时的L / D-e并限制最大空速。转子速度降低30％可以显着提高性能，而较大的降低则限制了高空速和由于失速而引起的高海拔调整。如果可以防止螺旋桨失速，则高空飞行可在所有空速下提高L / D-e。副翼和水平稳定器微调控制不会对L / D-e产生不利影响，但允许使用转子周期进行微调，以减少襟翼弯曲载荷。最终的化合物构型在140 kt附近达到了峰值L / D-e = 8.5，在250 kt的最大空速下L / D-e> 5.0。

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  • 来源
    《Journal of the American Helicopter Society》 |2018年第3期|032004.1-032004.15|共15页
  • 作者

    Bowen-Davies Graham; Yeo Hyeonsoo;

  • 作者单位

    Sci & Technol Corp, Ames Res Ctr, Moffett Field, CA 94035 USA;

    US Army, Aviat & Missile Res Dev & Engn Ctr, Res Dev & Engn Command RDECOM, Ames Res Ctr,Aviat Dev Directorate, Moffett Field, CA USA;

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