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某小型边条翼无人飞机的气动参数估算及风洞试验分析
引用本文:刘斌,刘沛清,王亮.某小型边条翼无人飞机的气动参数估算及风洞试验分析[J].飞机设计,2010,30(3):1-5,22.
作者姓名:刘斌  刘沛清  王亮
作者单位:1. 北京航空航天大学航空科学与工程学院,北京,100191;中国航天空气动力技术研究院,北京100074
2. 北京航空航天大学航空科学与工程学院,北京,100191
摘    要:根据自主飞行技术要求,对试验载荷飞机的气动布局进行设计论证。在低雷诺数下,通过风洞试验对所设计的微小型边条翼飞行器进行气动性能的评估,得到有效的气动参数。针对风洞对阻力系数测量偏大的弊端以及在低雷诺数下风洞数据在绝对量值上的不精确,利用前人已有的经验公式与处理方法创新性的对风洞数据进行处理,从小迎角范围中选用一些相对合理的参数,对经验公式及结果进行修正,得到更为合理的控制辨识参数,为无人飞行器提供可靠的参数保障,以实现小型飞机的自主飞行。

关 键 词:风洞试验  边条翼  气动参数  低雷诺数

A Small Trim-wing Unmanned Aircraft Aerodynamic Parameter Estimation and Analysis of Wind Tunnel Test
LIU Bin,LIU Pei-qing,WANG Liang.A Small Trim-wing Unmanned Aircraft Aerodynamic Parameter Estimation and Analysis of Wind Tunnel Test[J].Aircraft Design,2010,30(3):1-5,22.
Authors:LIU Bin  LIU Pei-qing  WANG Liang
Institution:1. School of Aeronautic Science and Technology Beijing University of Aeronautics and Astronautics, Beijing 100191, China) (2. China Academy of Aerospace Aerodynamics, Beijing 100074, China)
Abstract:According to the technical requirements of autonomous flight, the aircraft's aerodynamic loads on the experimental design of the layout are studied In the low Reynolds number, through wind tunnel tests designed miniature streak wing aircraft for aerodynamic performance evaluation, obtained aerodynamic parameters. Drag coefficient for wind-tunnel measurements of the defects is too large, and the low Reynolds number, wind tunnel data on the inaccuracy in absolute value. Previous experience of using the existing formula and innovative approach to the wind tunnel data processing, use small angle of attack range of parameters that are relatively reasonable, the results of the empirical formula and the correction. Be more reasonable control of identification parameters in order to achieve autonomous flight of small aircraft.
Keywords:wind tunnel test  trim wing  aerodynamic parameters  low Reynolds number
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