Anti-spin aircraft structure

Abstract

The invention discloses a structure and a system for making an aircraft anti-spin. Aircraft resistance to spin is accomplished by confining the stall cells to the wing region (220) adjacent to the fuselage and away from the wingtips (210). Wing features that facilitate this constraint include, but are not limited to, one or more folds (215), stall bars (320), vortex generators (630), wing twist (510-550), wing sweep, and horizontal stability device. The aircraft structural features presented by the invention, alone or in combination, render the aircraft anti-spin by constraining the stall cells, which allows the control surfaces of the aircraft to remain operable to control the aircraft.

Description

[0001] related application [0002] This application is related to and claims the benefit of U.S. Nonprovisional Patent Application 13 / 946,572, filed July 19, 2013, and U.S. Provisional Patent Application No. 61 / 674,267, filed July 20, 2002, both of which are incorporated by reference The entire text is hereby incorporated for all purposes as if fully set forth herein. technical field [0003] Embodiments of the present invention generally relate to aerodynamic techniques intended to prevent an aircraft from being able to enter a spin, and more particularly to the structure of said technique to render an aircraft spin-resistant. Background technique [0004] The leading cause of fatal accidents in small aircraft is loss of control. Because the aircraft will often, but not always, enter flight regimes outside its normal envelope at high rates, a loss of control usually occurs and thus causes some panic among the crew. Loss of control can be caused by a number of factors, in...

AI Technical Summary

Problems solved by technology

correspondingly, if the aircraft is not certified for spin recovery, it is assumed that the spin is irrecoverable and it is considered unsafe to perform a spin in that aircraft

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