Double-slit flap with flap body fixedly connected with additional wing

Abstract

The invention belongs to the technical field of aircraft wings, and particularly relates to a double-slit flap with a flap body fixedly connected with an additional wing. The double-slit flap comprises the additional wing and the flap body, the additional wing and the flap are fixedly connected through a connecting rod, and the fixedly-connected additional wing and flap are taken as a whole to beretracted and released under the effect of a driving connecting mechanism; when the double-slit flap is in a put-down state, a gap exists between the main wing and the additional wing, a gap exists between the additional wing and the flap, and the high lift effect of the double-slit flap is achieved. According to the double-slit flap, through the additional wing flap structure in rigid connection,the high lift effect of the double-slit flap is achieved when the flap body is put down, meanwhile, the structural complexity of the double-slit flap is kept to be equivalent to that of a single-slit / fullerene flap, lift force is improved under the condition of the same structural complexity, and therefore the area requirements of wings and flaps are reduced, the weight of an airplane is reduced,and the aircraft performance is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft wings, and in particular relates to a double-slit flap in which the flap is fixedly connected to an additional wing. Background technique [0002] The flying speed of the aircraft is high during cruising flight, and the required wing area and airfoil camber are small, while the flying speed is small during the take-off and landing stage, and the required wing area and airfoil camber are large. In order to solve the contradictory needs of the two types of situations, contemporary aircrafts adopt flaps of different complexity. The flaps are retracted during cruising flight and lowered during takeoff and landing to increase lift. See the main trailing edge flap devices figure 1 . [0003] The lift-enhancing effect of the flaps is measured by the increment ΔCLmax of the maximum lift coefficient generated by the flaps down state relative to the retracted state. In two-dimensional terms, the ΔCLmax ...

AI Technical Summary

Problems solved by technology

[0004] For small fixed-wing aircraft, single-slot flaps or Fuller flaps with relatively simple structures are usually used. The problem caused by this is that ΔCLmax is small. In order to obtain sufficient lift during take-off and landing, it is only possible to increase Large wing and flap area, resulting in increased structural weight, increased cruise flight resistance and other costs

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