Patent
Apparatus and method for twisting a wing to increase lift on aircraft and other vehicles
TLDR
In this paper, a method and apparatus for varying the twist of a wing such that induced drag is minimized or reduced during cruise and lift is maximized or increased at least during takeoff and landings is presented.Abstract:
A method and apparatus for varying the twist of a wing such that induced drag is minimized or reduced during cruise and lift is maximized or increased at least during takeoff and landings. In addition, variations in the twist may produce yawing and rolling moments. The twist amount is varied pursuant to the operating conditions, including those parameters used to determine the lift coefficient. The twist for reducing induced drag and/or improving lift may be employed by geometric or aerodynamic twist, including full span control surfaces used to provide roll control, high-lift and reduced induced drag. The twist may also be employed by twisting just a portion of the wing or the entire wing, either geometrically or aerodynamically.read more
Citations
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TL;DR: In this article, the structural stiffness of a wing is modulated to modulate the twist of the wing in the presence of aerodynamic forces, and a system and method for enabling controlled twisting of a tip of an aircraft's wing in response to the aerodynamic force experienced by the wing is presented.
References
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Journal ArticleDOI
Lifting-Line Analysis for Twisted Wings and Washout-Optimized Wings
TL;DR: In this article, a more practical form of the analytical solution for the effects of geometric and aerodynamic twist (washout) on the low-Mach-number performance of a finite wing of arbitrary planform is presented.
Theoretical symmetric span loading at subsonic speeds for wings having arbitrary plan form
John Deyoung,Charles W Harper +1 more
TL;DR: In this paper, a method for finding the symmetric span loading for a certain class of wings can be found, where the geometry of these wings is limited only to the extent that they must have symmetry about the root chord, must have a straight quarter-chord line over the semispan, and must have no discontinuities in twist.
Patent
Active flexible wing aircraft control system
TL;DR: In this paper, a system for controlling an aircraft by aeroelastic deflections of the wings which is effective beyond control surface reversal is disclosed, including flexible wings, leading and trailing edge control surfaces attached to the wings, sensors to measure selected aircraft flight parameters, an information processing system to receive and process pilot command signals and signals from the sensors, and control mechanisms in the wing that respond to processed signals from information processing systems.
Patent
Elastomeric transition for aircraft control surface
TL;DR: Flexible rods are secured to either the wing or the control surface and extend through the holes (128, 124) in the elastomeric material (126), providing a smooth aerodynamic transition as mentioned in this paper.
The Calculation of Aerodynamic Loading on Surfaces of Any Shape
TL;DR: In this article, the authors present a method for calculating aerodynamic loads on wings of arbitrary shape based on potential theory and use a general mathematical formula for continuous loading on a wing which is equivalent to a double Fourier series with unknown coefficients.