大型民机扰流板对后缘襟翼载荷影响试飞研究  

Study on effect of spoiler on flap loads of large civil aircraft by flight test

作　　者：胡赞远[1] 符梁栋 Hu Zanyuan;Fu Liangdong(Shanghai Aircraft Design and Research Institute,Shanghai,201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《机械设计与制造工程》2023年第11期58-61,共4页Machine Design and Manufacturing Engineering

摘　　要：根据某大型民机襟翼载荷测压试飞数据,对不同扰流板偏度情况襟翼气动载荷特性进行了研究,将不同襟翼构型的襟翼部件力系数、襟翼剖面弦向压力分布随扰流板偏度的变化规律进行对比分析。结果表明,扰流板偏转产生的上洗效应使襟翼上表面前缘形成吸力峰从而增大襟翼部件力系数,该影响规律与襟翼偏度有关。此外还分析了扰流板满偏情况下襟翼气动载荷特性,结果表明,扰流板偏转对襟翼部件力系数的影响规律在一定的迎角范围内是一致的,襟翼部件力系数受迎角变化的影响较小。Based on the flap load test flight data of a large civil aircraft,the flap aerodynamic load characteristics with different spoiler deflection angles are studied.The force coefficient of flap components and the chord pressure distribution of flap profile with the spoiler deflection angle are compared and analyzed.The results show that the upwash effect caused by the spoiler deflection causes the leading edge of the upper surface of the flap to form a suction peak,which increases the force coefficient of the flap component.The results show that the influence of spoiler deflection on the force coefficient of flap components is consistent in a certain range of angle of attack,and the force coefficient of flap components is less affected by the change of angle of attack.

关 键 词：襟翼载荷 载荷试飞 扰流板 迎角 襟翼偏度 

分 类 号：V215.1[航空宇航科学与技术—航空宇航推进理论与工程]