Wang Peng, Jin Xin. Study on artificial neural network modeling and wind tunnel test for the FADS system applied to the vehicle with sharp nosed fore-bodies[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(5): 57-63. doi: 10.11729/syltlx20180125
Citation: Wang Peng, Jin Xin. Study on artificial neural network modeling and wind tunnel test for the FADS system applied to the vehicle with sharp nosed fore-bodies[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(5): 57-63. doi: 10.11729/syltlx20180125

Study on artificial neural network modeling and wind tunnel test for the FADS system applied to the vehicle with sharp nosed fore-bodies

doi: 10.11729/syltlx20180125
  • Received Date: 2018-09-11
  • Rev Recd Date: 2019-06-13
  • Publish Date: 2019-10-25
  • The solving model and its accuracy for the Flush Air Data Sensing (FADS) system applied to the vehicle with sharp nosed fore-bodies are studied. Firstly, the pressure ports configuration for sharp nosed fore-bodies is determined based on the theoretical model of the FADS system applied to the blunt fore-bodies. Secondly, a typical wind tunnel test for the FADS pressure ports is implemented, and CFD results and wind tunnel test are analyzed systematically. Finally, the solving model and algorithm are developed for the FADS system based on the Radial Basis Function (RBF) neural network modeling, and the neural network model solving accuracy for the FADS system is analyzed. The results show that, the solving accuracy of the RBF neural network model for the FADS system is high enough. The neural network outputs agree well with the wind tunnel test data, and the testing error distributions (absolute error distribution) for the angle of attack, angle of sideslip, free stream static pressure and Mach number are less than 0.1°, 0.1°, 50.0 Pa and 0.01, respectively. The results also present that the artificial neural network modeling for the FADS system can be further developed in the future.
  • loading
  • [1]
    Ellsworth J C, Whitmore S A. Simulation of a flush air-data system for transatmospheric vehicles[J]. Journal of Spacecraft and Rockets, 2008, 45(4):716-732. doi: 10.2514/1.33541
    [2]
    Siemers P M III, Wolf H, Henry M. Shuttle Entry Air Data System (SEADS)-flight verification of an advanced air data system concept[R]. AIAA-88-2014, 2014.
    [3]
    Larson T J, Siemers P M III. Use of nose cap and fuselage pressure orifices for determination of air data for Space Shuttle Orbiter below supersonic speeds[R]. NASA TR-1643, 1980.
    [4]
    Whitmore S A, Cobleigh B R, Haering E A Jr. Design and calibration of the X-33 Flush Airdata Sensing (FADS) system[R]. NASA/TM-1998-206540, 1998.
    [5]
    Larson T J, Whitmore S A, Ehernberger L J, et al. Qualitative evaluation of a flush air data system at transonic speeds and high angles of attack[R]. NASA TP-2716, 1987.
    [6]
    Larson T J, Siemers P M III. Subsonic tests of an all-flush-pressure-orifice air data system[R]. NASA TP-1871, 1981.
    [7]
    Terry L J, Timothy R M, Siemers P M III. Wind-tunnel investigation of a flush airdata system at Mach numbers from 0.7 to 1.4[R]. NASA TM-101697, 1990.
    [8]
    Westhelle C H. X-38 backup Air Data System(AeroDAD)[R]. AIAA 2002-0007, 2002.
    [9]
    Ellsworth J C, Whitmore S A. Reentry air data system for a sub-orbital spacecraft based on X-34 design[R]. AIAA 2007-1200, 2007.
    [10]
    Crowther W J, Lamont P J. A neural network approach to the calibration of a flush air data system[J]. The Aeronautical Journal, 2011, 105(1044):85-95. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=cb3d4fbbfee5264c0a7aa7990ca5627b
    [11]
    Calia A, Denti E, Galatolo R, et al. Air data computation using neural networks[J]. Journal of Aircraft, 2008, 45(6):2078-2083. doi: 10.2514/1.37334
    [12]
    Rohloff T J, Whitmore S A, Catton I. Fault-tolerant neural network algorithm for flush air data sensing[J]. Journal of Aircraft, 1999, 36(3):541-549. doi: 10.2514/2.2489
    [13]
    Samy I, Postlethwaite I, Gu D W. Neural-network-based flush air data sensing system demonstrated on a mini air vehicle[J]. Journal of Aircraft, 2010, 47(1):18-31. doi: 10.2514/1.44157
    [14]
    王鹏, 胡远思, 金鑫.尖楔前体飞行器FADS系统驻点压力对神经网络算法精度的影响[J].宇航学报, 2016, 37(9):1072-1079. doi: 10.3873/j.issn.1000-1328.2016.09.006

    Wang P, Hu Y S, Jin X. Effect of stagnation pressure on the neural network algorithm accuracy for the FADS system applied to the vehicle with sharp wedged fore-bodies[J]. Journal of Astronautics, 2016, 37(9):1072-1079. doi: 10.3873/j.issn.1000-1328.2016.09.006
    [15]
    王鹏, 金鑫, 张卫民, 等.钝头机体用FADS系统的校准[J].实验流体力学, 2016, 30(2):97-102. http://www.syltlx.com/CN/abstract/abstract10924.shtml

    Wang P, Jin X, Zhang W M. Calibration for the FADS system applied to the vehicle with blunt fore-bodies[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(2):97-102. http://www.syltlx.com/CN/abstract/abstract10924.shtml
    [16]
    王鹏, 金鑫, 张卫民. FADS系统测压孔配置对攻角校准的影响[J].战术导弹技术, 2013, (2):51-55. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=zsddjs201302011

    Wang P, Jin X, Zhang W M. The effect of configuration of pressure ports on calibration for angle of attack in FADS system[J]. Tactical Missile Technology, 2013, (2):51-55. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=zsddjs201302011
    [17]
    Li Y, Sundararajan N, Saratchandran P. Analysis of minimal radial basis function network algorithm for real-time identifi-cation of nonlinear dynamic systems[J]. IEE Proceedings-Control Theory and Applications, 2000, 147(4):476-484. doi: 10.1049/ip-cta:20000549
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Figures(13)  / Tables(1)

    Article Metrics

    Article views (274) PDF downloads(14) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return