基于风洞试验的非定常空气动力模型识别  

Identification of Unsteady Aerodynamic Model Based on Wind Tunnel Test

作　　者：杨勐[1,2] 黄达[1] 吴根兴[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016 [2]陆军航空兵学院机械系,北京101123

出　　处：《南京航空航天大学学报》2011年第2期149-153,共5页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金(11072111)资助项目

摘　　要：在某飞机模型大振幅风洞试验的基础上,分析讨论了单自由度叠加模型、动导数模型、混合模型和非定常模型的适用性。结果表明,单自由度叠加模型、动导数模型和混合模型在小攻角时均是可用的,在大攻角时都不能正确反映飞机的非定常迟滞特性;但与前两种模型相比,混合模型在中等攻角时仍然适用。对于非定常模型,无论在小攻角还是大攻角时,均能较好地反映耦合运动的非定常气动特性。The linear superposition model,dynamic derivative model,mixed model and unsteady aerodynamic model are established based on the wind tunnel test results of the large-amplitude motion.The applicability of four kinds of aerodynamic models is analyzed.The former three models are suitable for the test results at the small angle of attack,but not at the large angle.Compared with the former two models,the mixed model is still applicable to the medium angle of attack.As for the unsteady aerodynamic model,the aerodynamic characteristics of coupled-motion are reflected well to the test results in spite of any angle of attack.

关 键 词：非定常气动力 大攻角 大振幅 数学模型 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]