强旋翼尾迹涡干扰对直升机空速测量的影响

doi:10.7527/S1000-6893.2024.29536

Abstract

Abstract:

Accurate airspeed measurement is crucial for helicopter flight safety. This article establishes a numerical simulation method for the rotor/fuselage aerodynamic interference flow field based on the unsteady momentum source theory and investigates the influence of rotor wake vortex interference on helicopter airspeed measurement. Using a reference helicopter as an example， we analyze the variation characteristics of airspeed values within the entire speed range for different rotor thrusts and airspeed probe locations. Due to factors such as rotor blade motion and fuselage blockage， there are differences in the static pressure phase and peak values at different airspeed probe locations. The phase difference is influenced by the impact of rotor blades， while the peak value difference is affected by the rotor disc load and fuselage blockage. The study also identifies and explains the “airspeed hysteresis” phenomenon caused by rotor tip vortices passing through the airspeed probe area within specific speed ranges. The variation of airspeed in the airspeed probe area can be divided into three regions： the downwash-dominated region， the hysteresis region， and the incoming-flow-dominated region. For conventional configuration helicopters， the hysteresis region occurs only at medium to low speeds. Further analysis of parameter effects suggests that the closer the airspeed probe is to the front of the fuselage and the smaller the rotor thrust， the further forward the speed range of the hysteresis region. When the airspeed probe is positioned near the nose， no significant hysteresis appears. Finally， the article provides recommendations for the placement of airspeed probes from the perspective of aerodynamical interference.

Key words: airspeed hysteresis, unsteady momentum sources, rotor/fuselage interaction, airspeed measurement, CFD

CLC Number:

V211.52

Yonghua LIU, Guohua XU, Yongjie SHI, Zhenyu DU, Huixin ZHANG, Zhiyuan HU. Effects of strong rotor wake vortex interference on helicopter airspeed measurement[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(14): 129536-129536.

Figures/Tables 27

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References 25

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部件	参数	数值
旋翼参数	旋翼半径	R=8.18 m
	根切	R₀=0.26R
	旋翼转速	ω=27.017 rad/s
	桨尖速度	V_tip=221 m/s
	桨叶弦长	c=0.51 m
	桨叶片数	b=5
	旋向	右旋
	桨毂中心	（0，0，0） m
机身参数	机身长	L=16.5 m
	机身高	H=2.5 m
	机身宽	W=1.5 m

参考位置	Ⅰ001	Ⅱ002
坐标值	（-3.5，0，-1.1）	（-5.25，0，-1.6）
机身轴向测点间隔	0.25	0.25
机身侧向测点间隔	0.25	0.5（0.25）
高度方向测点间隔	0.2	0.2

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Effects of strong rotor wake vortex interference on helicopter airspeed measurement

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