[1] LAN C E, WU K Y, YU J. Flight characteristics analysis based on QAR data of a jet transport during landing at a high-altitude airport[J]. Chinese Journal of Aeronautics, 2012, 25(1):13-24. [2] North Atlantic Treaty Organization. Dynamic stability parameters:AGARD-CP-235[R]. London:Technical Editing and Reproduction Ltd., 1978. [3] North Atlantic Treaty Organization. Dynamic stability parameters:AGARD-LS-114[R]. London:Technical Editing and Reproduction Ltd., 1981. [4] GRAFTON S B. Dynamic stability derivatives of a twin-jet fighter model for angles of attack from -10° to 110°:NASA TN D-6091[R]. Hampton:Langley Research Center, 1971. [5] OWENS D B, BRANDON J M, CROOM M A, et al. Overview of dynamic test techniques for flight dynamics research at NASA LaRC:AIAA-2006-3146[R]. Reston:AIAA, 2006. [6] ALTENKIRCH D. Flight mechanics analysis of the dynamic derivatives of the Dornier variable wind tunnel model:ESA-TT-854[R]. Hampton:Langley Research Center, 1984. [7] CHRISTOPHE J. New rig for flight mechanics studies:AIAA-1980-0464[R]. Reston:AIAA, 1980. [8] JANSSON T, TORNGREN L. New dynamic testing technique and related results at FFA:AD-P005024[R]. Goteborg:The Aeronautical Research Institute of Sweden, 1983. [9] GOMAN M G, GREENWELL D I, KHRABROV A N. The characteristic time constant approach for mathematical modeling of high angle of attack aerodynamics[C]//ICAS 2000 Congress, 2000. [10] 孙海生. 96型低速大攻角动导数试验系统[J]. 流体力学实验与测量, 1999, 13(1):31-37. SUN H S. The development of 96-test system for measuring dynamic derivatives at high angle of attack[J]. Experiments and Measurements in Fluid Mechanics, 1999, 13(1):31-37(in Chinese). [11] 卜忱, 杜希奇, 王学俭. 飞行器纵向阻尼动导数直接测量实验研究[J]. 实验流体力学, 2005, 19(1):31-34. BU C, DU X Q, WANG X J. Investigation of longitudinal damping derivative of aircraft by direct measurement tests[J]. Experiments and Measurements in Fluid Mechanics, 2005, 19(1):31-34(in Chinese). [12] 史志伟, 吴根兴. 大迎角非定常气动力建模与模型比较[J]. 空气动力学学报, 1999, 17(4):454-461. SHI Z W, WU G X. The comparison of several unsteady aerodynamics models at high angle of attack[J]. Acta Aerodynamica Sinica, 1999, 17(4):454-461(in Chinese). [13] 孙海生. 飞行器大迎角非定常气动力试验研究[D]. 西安:西北工业大学, 2011. SUN H S. Experimental study on unsteady aerodynamics of aircraft at high angle of attack[D]. Xi'an:Northwestern Polytechnical University, 2011. [14] 李周复. 风洞特种实验技术[M]. 北京:航空工业出版社, 2010:249. LI Z F. The special experimental technology in wind tunnel[M]. Beijing:Aviation Industry Press, 2010:249(in Chinese). [15] GRAFTON S B, PARLETT L P, CHARLES C S. Dynamic stability derivatives of a jet transport configuration with high thrust-weight ratio and an externally blown jet flap:NASA TN D-6440[R]. Hampton:Langley Research Center, 1971. [16] 孙海生, 张晖, 汤更生, 等. 8 m×6 m风洞特大迎角试验设备研制[J]. 实验流体力学, 2009, 23(1):70-73. SUN H S, ZHANG H, TANG G S, et al. The development of high angle of attack test equipment in the 8 m×6 m low speed wind tunnel[J]. Experiments and Measurements in Fluid Mechanics, 2009, 23(1):70-73(in Chinese). [17] 张征宇, 喻波, 黄诗捷, 等. 风洞试验中模型迎角的视频测量及精度研究[J]. 实验流体力学, 2013, 27(1):88-90. ZHANG Z Y, YU B, HUANG S J, et al. Videogrammetric measurement of attack angle and its precision investigation in wind tunnel tests[J]. Experiments and Measurements in Fluid Mechanics, 2013, 27(1):88-90(in Chinese). [18] 顾艺, 岑飞, 温渝昌, 等. 基于非接触测量技术的低速风洞连续扫描试验技术研究[J]. 实验流体力学, 2013, 27(5):98-104. GU Y, CEN F, WEN Y C, et al. Research about continuous scanning test technique based on non-contact measurement technique in low speed wind tunnel[J]. Experiments and Measurements in Fluid Mechanics, 2013, 27(5):98-104(in Chinese). [19] 章克来, 朱海明. 微弱信号检测技术[J]. 航空电子技术, 2009, 40(2):30-36. ZHANG K L, ZHU H M. Weak signal detection technology[J]. Avionics Technology, 2009, 40(2):30-36(in Chinese). [20] 彭长英, 沈志洪, 段丕轩. 动导数试验数据测量与处理系统[C]//全国空气动力测控技术会, 2005. PENG C Y, SHEN Z H, DUAN P X. Development of measurement and data processing system for dynamic derivative test[C]//Chinese Aerodynamics Experimental Measurement and Control Technology Conference, 2005(in Chinese). [21] North Atlantic Treaty Organization. Cooperative programme on dynamic wind tunnel experiments for manoeuvring aircraft:AGARD-AR-305[R]. Hull:Canada Communication Group, 1996. [22] DAN D V, THOMOS D L, ANDRES S. SACCON forced oscillation tests at DNW-NWB and NASA Langley 14×22-foot tunnel:AIAA-2010-4394[R]. Reston:AIAA, 2010.