Self-adaptive wing with variable wing surface curvature and control manner of aircraft thereof

Abstract

The invention provides a self-adaptive wing with a variable wing surface curvature. The self-adaptive wing is connected with a control system of an aircraft where the self-adaptive wing is installed and comprises a metal wing framework arranged at the lower part and a support structure arranged on the framework, wherein an adjustable curved surface is arranged on an upper wing surface of the wing; an actuation device is arranged at the interior of the wing and is connected with the adjustable curved surface; the actuation device is connected with a control system of the wing. Through the wing structure replacing the conventional flaperon structure and a control manner of the aircraft thereof, the high-speed performance and the low-speed performance of the aircraft can be balanced; the rising force of the wing is adjusted by changing the curvature of the upper wing surface of the wing so as to adapt to various flight situations.

Description

technical field [0001] The invention relates to the technical field of aircraft wing design, in particular to an adaptive wing with variable curvature of the wing surface and a control method for the aircraft. Background technique [0002] Modern aircraft can operate over a wide range of speeds and altitudes, requiring modification and control of the aerodynamic characteristics of the aircraft's wing lifting surfaces. Traditional aircraft generally use conventional trailing edge flaps to meet the lift requirements during takeoff and landing. But it is not enough to finely adjust and optimize the aerodynamic performance of the aircraft in the cruising state and the aerodynamic performance of the aircraft in other states (such as take-off and landing). In the 1960s, the variable-sweep wing technology, which allowed the aircraft to change the wing-sweep angle by pivoting during flight to adapt to different flight conditions, was once considered to be the best way to balance hi...

AI Technical Summary

Problems solved by technology

At present, the roll control surface of traditional aircraft is generally a partial chord length aileron, which has the advantage of simple mechanism, but it occupies a large space in the span of the wing, which limits the traditional lift performance of the aircraft

In addition, in order to meet the stall characteristic requirements of the aircraft, the wing with a partial chord-length aileron needs a larger wing twist angle, which will cause the aircraft to increase the induced drag during cruise and reduce the lift-to-drag ratio of the aircraft.

Moreover, the deflection of partial chord length ailerons is relatively inefficient for aircraft roll control, especially when the aileron deflection angle is large, its control efficiency drops sharply

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