Aircraft wing determination method, aircraft wing and aircraft

Abstract

The invention relates to an aircraft wing determinantion method. The method comprises: designing an aircraft wing model, determining a main wing, a single-slit flap, a first connecting rod L1 and a second connecting rod L2, wherein a point A at the rear edge of the bottom of the main wing is fixedly connected with one end of the first connecting rod L1; an included angle alpha is formed between the first connecting rod and the vertical direction, the length of the first connecting rod is 1, an O point at the other end of the first connecting rod is hinged to one end of a second connecting rodL2, the other end of the second connecting rod L2 is fixed below the single-slit flap, the second connecting rod is configured to rotate around the O point, and the maximum rotation angle is an included angle beta; performing mesh generation on the aircraft wing model based on finite element software; calculating aerodynamic parameters of the single-slit flap; and screening aircraft wings meetingset aerodynamic force parameter conditions according to task requirements. According to the determination method, the structure and pneumatic problems are combined and analyzed, and comprehensive consideration is achieved; the problem that the structure is not matched with the aerodynamic configuration is avoided; aircraft wing control parameters are few, and logic is clear.

Description

technical field [0001] The invention belongs to the field of aircraft design, in particular to a method for determining an aircraft wing for a single-slot flap, an aircraft wing and an aircraft determined according to the method. Background technique [0002] When designing the wing aerodynamics of an aircraft, on the one hand, the performance during cruising flight should be considered; on the other hand, when taking off and landing, the flight speed should be reduced as much as possible to shorten the running distance, which usually means that the wing should have a larger Therefore, the wing needs to be equipped with a movable surface during design, that is, a lift device. [0003] High-lift devices are usually divided into leading-edge high-lift devices and trailing-edge high-lift devices according to their positions on the wing. The research direction of this patent is trailing edge high-lift devices. Common trailing edge high-lift devices include simple flaps, split f...

AI Technical Summary

Problems solved by technology

This design approach sometimes produces structural and aerodynamic mismatch results, resulting in reduced aerodynamic efficiency of the wing, structural interference during deflection, etc.

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