Lifting and propulsion devices for flight performance ,improvement of a compound helicopter

YANG Kelong; HAN Dong; SHI Qipeng

doi:10.13224/j.cnki.jasp.2020.11.020

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Lifting and propulsion devices for flight performance ,improvement of a compound helicopter

更新时间：2026-07-07

- Lifting and propulsion devices for flight performance ,improvement of a compound helicopter
- Vol. 35, Issue 11, Pages: 2429-2439(2020)
- 作者机构：
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2020.11.020
  CLC：
- Published：2020
- 稿件说明：
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杨克龙, 韩东, 石启鹏. 升推力装置对复合直升机飞行性能的提升[J]. 航空动力学报, 2020, 35(11): 2429-2439.

doi: 10.13224/j.cnki.jasp.2020.11.020
杨克龙, 韩东, 石启鹏. 升推力装置对复合直升机飞行性能的提升[J]. 航空动力学报, 2020, 35(11): 2429-2439. DOI： 10.13224/j.cnki.jasp.2020.11.020.

doi: 10.13224/j.cnki.jasp.2020.11.020 DOI：

摘要

为探讨升推力装置对常规复合式直升机的飞行性能影响

建立了一种复合式直升机性能分析模型。以加装机翼和螺旋桨的UH-60A直升机为样例

探讨了机翼和螺旋桨参数、升推力分配对全机性能的影响机理。结果表明:低速时

机翼和螺旋桨效率低

加装机翼和螺旋桨会降低全机升阻比;螺旋桨转速越高或桨叶负扭越大

导致螺旋桨的型阻功率越大

升阻比降低越明显。高速时

机翼和螺旋桨效率增加

螺旋桨承担绝大部分推力、机翼承担大部分升力

并降低旋翼转速

为旋翼卸载

降低了旋翼诱导和型阻功率

显著提升了全机性能;升阻比随升推力分配分别先增加后降低。300 km/h时

100%、90%、85%和80%旋翼转速时

对升推力进行优化分配后

将基准直升机的升阻比分别提升了40%、2133%、270%和306%。

Abstract

To analyze the effects of lifting and propulsion devices for flight performance improvement of a compound helicopter

a model of performance prediction was developed. Based on the UH-60A helicopter equipped with a wing and a propeller

the influence mechanism of parameters of the wing and propeller

lift and propulsive force shares on the performance was analyzed. At low speeds

due to the low efficiency of the wing and propeller

equipping the wing and propeller decreased the lift-to-drag ratio of the helicopter. The higher rotor speed or blade twist of the propeller led to larger profile power of the propeller

and further reduced the lift-to-drag significantly. At high speeds

the efficiency of the wing and propeller was higher; the performance was significantly improved when the wing and propeller offloaded most of the lift and propulsive force with the decrease of the main rotor speed; the lift-to-drag ratio increased first and then decreased as increasing the lift and propulsive force shares. At a speed of 300 km/h

optimizing the lift and propulsive force share

at 100%

95%

85% and 80% of main rotor speed

increased the lift-drag ratio by 40%

2133%

270% and 306%

respectively.

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Related Institution

Aerospace Technology Institute，China Aerodynamics Research and Development Center

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

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics

School of Aeronautics, Northwestern Polytechnical University

General Design Department, China Helicopter Research and Development Institute

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