Patent ID: 6929216
Filing Date: 2005-08-16
Classification: B64C,F16C,Y02T,Y10T

Abstract:
1. A canard for an aircraft, comprising: an airfoil portion having a first airfoil surface and a second airfoil surface facing opposite from the first airfoil surface, the airfoil portion being configured to be positioned external to an aircraft fuselage, the airfoil portion having a first portion configured to be exposed to a flow external to the fuselage, the airfoil portion further having a second portion movably coupled to the first portion, the second portion including a flight control surface; and a connecting portion depending from the airfoil portion and having an attachment portion configured to attach to an aircraft internal to the aircraft fuselage, the connecting portion having a first load path positioned to carry a first load portion between the airfoil portion and the attachment portion, the connecting portion further having a second load path spaced apart from the first load path and positioned to carry a second load portion between the airfoil portion and the attachment portion, the connecting portion being rotatable about a rotation axis positioned between the first and second load paths with at least part of the connecting portion eccentric relative to the rotation axis.