The invention relates to a leading edge lift augmentation layout for an aircraft, comprising a leading edge slat disposed at the leading edge of a wing of the aircraft, the leading edge slat being interrupted by an engine suspension equipped with a propulsion device and divided into an inboard slat near the fuselage of the aircraft and an outboard slat remote from the fuselage of the aircraft. The leading edge slat further comprises a hanging slat arranged at the intersection of the wing leading edge of the aircraft and an engine hanging, and the inner side slat, the outer side slat and the hanging slat located between the inner side slat and the outer side slat jointly form a leading edge lift augmentation component with continuity. The leading edge lift augmentation layout can reduce airflow separation on the inner side of the wing and eliminate the discontinuity of each leading edge lift augmentation component, so that the aerodynamic characteristics of the aircraft are improved.
本发明涉及一种用于飞行器的前缘增升布局,包括设置在飞行器的机翼前缘的前缘缝翼,前缘缝翼被配装有推进装置的发动机吊挂中断并分成靠近飞行器的机身的内侧缝翼和远离飞行器的机身的外侧缝翼。前缘缝翼还包括设置在飞行器的机翼前缘与发动机吊挂相交处的吊挂缝翼,其中,内侧缝翼、外侧缝翼以及位于内侧缝翼与外侧缝翼之间的吊挂缝翼共同构成具有连续性的前缘增升部件。该前缘增升布局能够减少机翼内侧的气流分离,消除各前缘增升部件的不连续性,从而改善飞行器的气动特性。
Leading edge lift augmentation layout
前缘增升布局
2021-11-23
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |