Abstract：A new measuring airdata algorithm is put forward.A vector sensor is applied to the flush airdata sensing(FADS) system to measure the airdata, the mathematics model of particle velocity, sound velocity and airspeed is established, the mach number can be computed, then impact-static pressure can be solved by the mach number. The less computational load and the real-time measurement can be achieved. The simulation shows this method is effective.
［1］Siemers P M, Martin W, Henry J R. Shuttle Entry Air Data System (SEADS) Advanced Air Data System Results:Air Data Across the Entry Speed Range［C］//Orbiter Experiments (OEX) Aerothermodynamics Symposium. NASA,1995.
［2］While D M. Shuttle Entry Air Data System (SEADS) Hardware Development［R］.NASA-CR-166044, 1983.
［3］Larson T J,Whitmore S A,Ehernberger L J.Qualitative Evaluation of a Flush Air Data System at Transonic Speeds and High Angles of attack［R］.NASA-TP-2716,1987.
［4］Larson T J, Moes T R, Siemers P M. Wind-Tunnel Investigation of a Flush Airdata System at Mach Numbers From 0.7 to 1.4［R］.NASA-TM-101697,1990.
［5］Whitmore S A, Cobleigh B R, Haering E A. Design and Calibration of the X-33 Flush Airdata Sensing (FADS) System［R］.NASA-TM-206540,1998.
［6］Bahm C,Baumann E,Martin J.The X-43A Hyper-X Mach 7 Flight 2 Guidance,Navigation,and Control Overview and Flight Test Results［R］.AIAA-3275,2005.
［7］张斌,于盛林.嵌入式飞行参数传感系统的神经网络算法［J］.航空学报,2006,27(2):294-298.
［8］Zheng C J, Lu Y P, He Z.Improved Algorithms for Flush Airdata Sensing System［J］.Chinese Jounal of Aeronautics,2006,19(4):334-339.
［9］邵笑杰.嵌入式飞行数据传感系统的算法研究［D］.南京:南京航空航天大学,2004.
［10］郑成军.嵌入式大气数据传感系统及其算法研究［D］.南京:南京航空航天大学,2005.
2011, Vol. 32 
