大型客机柔性后缘增升装置气动机构一体化优化设计

增升装置的设计对于大型客机来说是十分重要的,柔性可变弯的增升装置是未来大型客机的发展趋势,也是当前的研究热点。以某大型宽体客机内段翼型为研究对象,在襟翼内部的柔性变弯机构的带动下,可以使襟翼的后50%部分实现柔性变弯。在原始刚性襟翼的基础上,柔性变弯后的襟翼可使襟翼后缘增加8°的偏角。之后在三维后缘铰链襟翼机构的带动下,同时襟翼内部使用柔性变弯机构,采用"前缘下垂+后缘襟翼柔性变弯+后缘简单铰链襟翼联合扰流板下偏",进行起飞和着陆构型的二维气动/机构一体化优化设计,优化出来的结果与原始不柔性变弯的翼型相比,起飞构型的最大升力系数的增加量为0.119,着陆构型的最大升力系数的增加量为0.162,且着陆最优构型推迟1°迎角失速。

The aerodynamic and mechanical integrated optimization design of morphing trailing high-lift devices of large passenger aircraft

The design of high-lift devices is very important for large commercial aircraft.Variable camber high-lift devises are the development trend of large passenger aircraft in the future,and is also the current research hot spot.The inner airfoil of a large wide body aircraft is taken as the research object.Driven by the flexible bending mechanism inside the flaps,the last 50%of the flaps can be flexibly bent.Based on the original rigid flap,the optimal configuration can increase the camber of the trailing edge of the flap by 8°.Then,driven by the three-dimensional trailing edge hinge flap mechanism,and using the flexible bending mechanism inside the flap,the"droop nose+trailing edge flap of variable camber+simple hinged trailing edge flap combined with spoiler downward de-flection"is adopted to optimize the two-dimensional aerodynamic/mechanical integration of take-off and landing configuration.Compared with the original airfoil with inflexible bending,the optimized results showed that the increase of the maximum lift coefficient of the takeoff configuration and the increase of the maximum lift coefficient of the landing configuration was 0.119 and 0.162 respectively,and the optimal landing configuration delayed stall at an angle of attack by 1°.