基于机翼前缘绕流速度的大气参数测量方法
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摘要
利用安装在机翼前缘的声矢量传感器,给出了一种新型大气参数的估计方法。基于声矢量传感器敏感翼部绕流分布,建立大气参数求解模型。根据机翼后掠、对称的特点,对速度矢量进行分解来对模型的非线性方程进行解耦,从而求解了侧滑角、攻角和自由流速度的表达式。通过Fluent对机翼绕流进行仿真,验证了方法的可行性。
A new method measuring the atmospheric parameters was proposed based on acoustic vector sensors located at the wing leading edge, and the atmospheric parameters model was set up based on the airflow velocity distribution sensed by acoustic vector sensor over wing leading edge. According to the symmetric, swept character of wings, velocity vector was decomposed to solve the non-linear equation of model. The expressions of angle of sideslip, angle of attack and free stream velocity were derived. The feasibility of the expressions was verified by wing simulation data from Fluent.
A new method measuring the atmospheric parameters was proposed based on acoustic vector sensors located at the wing leading edge, and the atmospheric parameters model was set up based on the airflow velocity distribution sensed by acoustic vector sensor over wing leading edge. According to the symmetric, swept character of wings, velocity vector was decomposed to solve the non-linear equation of model. The expressions of angle of sideslip, angle of attack and free stream velocity were derived. The feasibility of the expressions was verified by wing simulation data from Fluent.
引文
[1]Stephen A Whitmore,Brent R Cobleigh.Design and calibration of the X-33 Flush Air-data Sensing(FADS)System[R]//NASA/TM 206540,1998.USA:NASA,1998.
[2]M Jost,F Schweg Mann,D T Kohler.Flush air data system an advanced air-data system for the aerospace industry[C]//AIAA Guidance,Navigation,and Control Conference and Exhibit,2004,Rhode Island,USA.USA:AIAA,2004:5028.
[3]J C Ellsworth,S A Whitmore.Reentry air-data system for a sub-orbital spacecraft based on X-34 design[C]//45th AIAA Aerospace Science Meeting and Exhibit,Reno Nevada,USA.USA:AIAA 2007:1200.
[4]Bau Mann J P,Keener J W.X-43A flush air-data sensing system flight-test results[J].Journal of Spacecraft and Rockets(S0022-4650),2010,47(1):48-61.
[5]Edward J Artz,Nicholas W Dona.NASA Orion flush air data sensing system feasibility determination and development[C]//52nd Aerospace Sciences Meeting.USA:AIAA,2014:1115.
[6]Whitmore Stephen A,Tobert E Curry.Experimental characterization of the effects of pneumatic tubing on unsteady pressure measurement[R].USA:NASA,1990.
[7]H-E de Bree,P Leussink,T Korthorst,et al.The Microflown:a novel device for measuring acoustic flows[J].Sensors and Actuators A(S0924-4247),1996,54(1):552-557.
[8]John D Anderson Jr.Fundamentals of aerodynamics[M].New York,USA:Mc Graw-Hill,2011.
[2]M Jost,F Schweg Mann,D T Kohler.Flush air data system an advanced air-data system for the aerospace industry[C]//AIAA Guidance,Navigation,and Control Conference and Exhibit,2004,Rhode Island,USA.USA:AIAA,2004:5028.
[3]J C Ellsworth,S A Whitmore.Reentry air-data system for a sub-orbital spacecraft based on X-34 design[C]//45th AIAA Aerospace Science Meeting and Exhibit,Reno Nevada,USA.USA:AIAA 2007:1200.
[4]Bau Mann J P,Keener J W.X-43A flush air-data sensing system flight-test results[J].Journal of Spacecraft and Rockets(S0022-4650),2010,47(1):48-61.
[5]Edward J Artz,Nicholas W Dona.NASA Orion flush air data sensing system feasibility determination and development[C]//52nd Aerospace Sciences Meeting.USA:AIAA,2014:1115.
[6]Whitmore Stephen A,Tobert E Curry.Experimental characterization of the effects of pneumatic tubing on unsteady pressure measurement[R].USA:NASA,1990.
[7]H-E de Bree,P Leussink,T Korthorst,et al.The Microflown:a novel device for measuring acoustic flows[J].Sensors and Actuators A(S0924-4247),1996,54(1):552-557.
[8]John D Anderson Jr.Fundamentals of aerodynamics[M].New York,USA:Mc Graw-Hill,2011.