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.

Figures/Tables 27

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References 25

1	熊亮，刘义明，黄巧平. 武装直升机大气数据传感器技术研究进展［J］. 传感器与微系统， 2015， 34（2）： 5-8.
	XIONG L， LIU Y M， HUANG Q P. Research progress in air data sensor technology for attack helicopter［J］. Transducer and Microsystem Technologies， 2015， 34（2）： 5-8 （in Chinese）.
2	KNIGHT C G. Low airspeed measuring devices for helicopter usage monitoring systems： DSTO-TN-0495 ［R］. Melbourne： DSTO Platforms Sciences Laboratory， 2003.
3	COYLE S. The art and science of flying helicopters［M］. Ames： Iowa State University Press， 1996.
4	龙彦志，梁应剑，黄巧平，等. 基于多普勒频移的光学大气测速系统设计［J］. 北京航空航天大学学报， 2018， 44（12）： 2521-2527.
	LONG Y Z， LIANG Y J， HUANG Q P， et al. Design of optical airspeed measurement system based on Doppler shift［J］. Journal of Beijing University of Aeronautics and Astronautics， 2018， 44（12）： 2521-2527 （in Chinese）.
5	JOST M， SCHWEGMANN F， KOHLER T. Flush air data system-an advanced air data system for the aerospace industry［C］∥Proceedings of the AIAA Guidance， Navigation， and Control Conference and Exhibit. Reston： AIAA， 2004.
6	AUGERE B， BESSON B， FLEURY D， et al. 1.5 μm lidar anemometer for true air speed， angle of sideslip， and angle of attack measurements on-board Piaggio P180 aircraft［J］. Measurement Science and Technology， 2016， 27（5）： 054002.
7	O’BRIEN D M， SMITH M J. Improvements in the computational modeling of rotor/fuselage interactions using unstructured grids［C］∥61st American Helicopter Society International Annual Forum. 2005.
8	NAM H J， PARK Y M， KWON O J. Simulation of unsteady rotor-fuselage aerodynamic interaction using unstructured adaptive meshes［J］. Journal of the American Helicopter Society， 2006， 51（2）： 141-149.
9	WILSON J C， MINECK R E. Wind-tunnel investigation of helicopter-rotor wake effects on three helicopter fuselage models： NASA-TM-X-3185［R］. Washington， D. C.： NASA， 1975.
10	LIOU S G， KOMERATH N M， MCMAHON H M. Velocity measurements of airframe effects on a rotor in a low-speed forward flight［J］. Journal of Aircraft， 1989， 26（4）： 340-348.
11	BRAND A G， MCMAHON H M， KOMERATH N M. Surface pressure measurements on a body subject to vortex wake interaction［J］. AIAA Journal， 1989， 27（5）： 569-574.
12	BI N P， LEISHMAN J G. Analysis of unsteady pressures induced on a body by a rotor［J］. Journal of Aircraft， 1991， 28（11）： 756-767.
13	MINECK R E， GORTON S A. Steady and periodic pressure measurements on a generic helicopter fuselage model in the presence of a roto： NASA/TM-2000-210286［R］. Washington， D. C.： NASA， 2000.
14	LIU C， THOMAS J， TUNG C. Navier-Stokes calculations for the vortex wake of a rotor in hover［C］∥Proceedings of the 16th Fluid and Plasmadynamics Conference. Reston： AIAA， 1983.
15	RAJAGOPALAN R G， MATHUR S R. Three dimensional analysis of a rotor in forward flight［J］. Journal of the American Helicopter Society， 1993， 38（3）： 14-25.
16	TADGHIGHI H， ANAND V. Simulation of rotor-body interactional aerodynamics： A time accurate rotor model［C］∥61st American Helicopter Society International Annual Forum. 2005.
17	KIM Y H， PARK S O. Navier-Stokes simulation of unsteady rotor-airframe interaction with momentum source method［J］. International Journal of Aeronautical and Space Sciences， 2009， 10（2）： 125-133.
18	RENAUD T， O’BRIEN D， SMITH M， et al. Evaluation of isolated fuselage and rotor-fuselage interaction using computational fluid dynamics［J］. Journal of the American Helicopter Society， 2008， 53（1）： 3-17.
19	谭剑锋，王浩文. 直升机旋翼/机身非定常气动干扰数值分析［J］. 空气动力学学报， 2014， 32（3）： 320-327.
	TAN J F， WANG H W. Numerical analysis of helicopter rotor/fuselage unsteady aerodynamic interaction［J］. Acta Aerodynamica Sinica， 2014， 32（3）： 320-327 （in Chinese）.
20	PARK Y M， KIM T， LEE D Y， et al. Computations of multicopter aerodynamics using OpenFOAM［C］∥Proceedings of the AIAA Scitech 2022 Forum. Reston： AIAA， 2022.
21	PARK Y M， JEE S K. Computations of multicopter aerodynamics in vertical flight with overset grids in OpenFOAM［C］∥Proceedings of the AIAA Aviation 2023 Forum. Reston： AIAA， 2023.
22	MCKEE J W， NAESETH R L. Experimental investigation of the drag of flat plates and cylinders in the slipstream of a hovering rotor： NACA-TN-4239［R］. Washington， D. C.： NASA， 1993.
23	CARADONNA F X， TUNG C. Experimental and analytical studies of a model helicopter rotor in hover［J］. Vertica， 1981， 5（2）： 149-161.
24	HAN S Q， SONG W P， HAN Z H. A novel high-order scheme for numerical simulation of wake flow over helicopter rotors in hover［J］. Chinese Journal of Aeronautics， 2022， 35（5）： 260-274.
25	樊枫，林永峰，黄水林，等. 基于混合网格的直升机旋翼/机身非定常干扰流场数值模拟方法［J］. 南京航空航天大学学报， 2015， 47（2）： 180-188.
	FAN F， LIN Y F， HUANG S L， et al. Numerical simulation on rotor/fuselage unsteady interaction flowfield based on hybrid grid［J］. Journal of Nanjing University of Aeronautics & Astronautics， 2015， 47（2）： 180-188 （in Chinese）.

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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