Helicopter performance improvement by rotor morphing technologies

HAN Dong; LIN Chang-liang; LI Jian-bo

doi:10.13224/j.cnki.jasp.2014.09.001

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Helicopter performance improvement by rotor morphing technologies

更新时间：2026-07-07

- Helicopter performance improvement by rotor morphing technologies
- Vol. 29, Issue 9, Pages: 2017-2023(2014)
- 作者机构：
  
  南京航空航天大学航空宇航学院直升机旋翼动力学国家级重点实验室,南京,210016
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.09.001
  CLC：
- Published：2014
- 稿件说明：
移动端阅览
韩东, 林长亮, 李建波. 旋翼变体技术对直升机性能的提升[J]. 航空动力学报, 2014, 29(9): 2017-2023.

doi: 10.13224/j.cnki.jasp.2014.09.001
韩东, 林长亮, 李建波. 旋翼变体技术对直升机性能的提升[J]. 航空动力学报, 2014, 29(9): 2017-2023. DOI： 10.13224/j.cnki.jasp.2014.09.001.

doi: 10.13224/j.cnki.jasp.2014.09.001 DOI：

摘要

为研究旋翼变体技术对直升机性能的提升作用，先建立旋翼模型，然后耦合机体模型，从而建立直升机需用功率计算模型.主要对比了几种不同旋翼变体技术，包括旋翼变直径、旋翼变转速、桨叶变弦长和桨叶变负扭转角在不同飞行状态时对直升机需用功率的影响.前飞速度为130km/h时，10%旋翼转速减小、10%旋翼直径减小、10%桨叶弦长减小和桨叶负扭转角由-12°变为-6°时，需用功率分别降低了15.7%，14.6%，5.8%和3.1%；前飞速度为250km/h时，10%旋翼转速减小和10%旋翼直径减小可分别降低14.5%和23.9%需用功率.结果表明，旋翼变转速明显优于桨叶变弦长和桨叶变负扭转角所取得的性能提升，高速前飞时旋翼变直径降低的需用功率大于旋翼变转速技术.

Abstract

To investigate the effect of rotor morphing technologies on helicopter performance improvement

a rotor model was derived. A fuselage model was coupled with this rotor model to establish the computational model of helicopter power. Several rotor morphing technologies

including varying rotor diameter

varying rotor speed

varying blade chord length and varying blade twist angle

were compared to investigate the influence on the helicopter power at different flight states. At the forward speed of 130km/h

10% reduction of the rotor speed

10% reduction of the rotor diameter

10% reduction of the blade chord length and the blade twist angle variation from -12 degree to -6 degree

the power can reduce by 15.7%

14.6%

5.8% and 3.1%

respectively. At the forward speed of 250km/h

10% reduction of the rotor speed and 10% reduction of the rotor diameter

can reduce the power by 14.5% and 23.9%

respectively. The results indicate varying rotor speed can achieve better performance improvement than varying blade chord length or varying blade twist angle. In high forward speed

varying rotor diameter can achieve better rotor power saving than varying rotor speed.

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Related Institution

南京航空航天大学直升机旋翼动力学国家级重点实验室

National Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics

China Helicopter Research and Development Institute, Aviation Industry Corporation of China, Limited

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics

School of Naval Architecture and Ocean Engineering, Jiangsu University of Science and Technology

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