The invention relates to a lift assembly (300) in an aircraft. The lift assembly (300) includes a wing (102) and at least one vertical rotor (118) disposed below the wing (102). The vertical axis (121) of the vertical rotor (118) is located within the span of the wing (102). The vertical rotor (118) is operable during forward flight of the aircraft. A placement distance (122) between the leading edge (108) and the vertical axis (121) of the vertical rotor (118) is a factor of the RPM of the rotor (118), the angle of attack (116) of the wing, and the chord (117). The lift assembly (300) produces a higher lift than the sum of lift produced individually by the wings (102) and the rotors (118), so that small wings can be provided and thus reduced drag can be produced.
本发明涉及一种飞行器中的升降组件(300)。所述升降组件(300)包括机翼(102)和设置在所述机翼(102)下方的至少一个垂直旋翼(118)。所述垂直旋翼(118)的垂直轴(121)位于所述机翼(102)的翼展内。所述垂直旋翼(118)在所述飞行器向前飞行期间可运行。前缘(108)和所述垂直旋翼(118)的所述垂直轴(121)之间的放置距离(122)是旋翼(118)的RPM、所述机翼的攻角(116)和翼弦(117)的因数。所述升降组件(300)产生的升力高于由所述机翼(102)和所述旋翼(118)单独产生的升力之和,这样可以设置小机翼并因此产生减小的阻力。
Lift enhancement assembly for aircraft with fixed wings
具有固定翼的飞行器的升降增强组件
2022-05-27
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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