Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods

Abstract

Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.

Description

technical field [0001] The present invention is generally directed to aircraft trailing edge devices, including devices having forward hinge lines, and related methods. Background technique [0002] Modern high-speed aircraft basically have thin wings that provide a low-drag curve during high-speed flight or cruise. The wings of these aircraft typically include various movable surfaces to provide aircraft control and / or to configure the aircraft for low-speed operation (eg, takeoff and landing). For example, in addition to carrying fuel, the wings of high speed transport aircraft typically include aileron surfaces, spoiler surfaces, leading edge devices, and trailing edge flap surfaces. These moveable surfaces are typically located at or adjacent to the leading and trailing edges of the wings, and are each movable between a retracted position and a number of deployed positions, depending on the particular flight conditions of the aircraft. [0003] Figure 1A is a partial s...

AI Technical Summary

Problems solved by technology

However, a potential disadvantage of this arrangement is that a complex mechanism is generally required to deploy the flaperon 60b to the rearward configuration, especially when the mechanism is configured to fit within the narrow wing section to reduce the outer fairing. size

On the other hand, simple mechanisms such as simple hinges tend to extend away from the profile of the wing section, requiring relatively large, heavy hinge supports and associated fairings that create drag

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