An actuating mechanism for variable camber edges of aerodynamic airfoils-viz., variable camber leading edges and/or variable camber trailing edges-characterized by its rigidity and structural stability and which permits varying the camber of a flexible continuous airfoil skin while maintaining a uni
An actuating mechanism for variable camber edges of aerodynamic airfoils-viz., variable camber leading edges and/or variable camber trailing edges-characterized by its rigidity and structural stability and which permits varying the camber of a flexible continuous airfoil skin while maintaining a uniform, essentially constant curvature throughout the chordal extent of deflection for any given degree of deflection; yet, wherein (a) the airfoil skin (i) is not required to function as a load carrying element, (ii) is not subjected to chord-wise stress from movement of the actuating linkage, and (iii) is not subjected to localized stress resulting from localized deflection; (b), the actuating linkage is contained entirely within the airfoil aerodynamic contour at all operating positions; (c), the actuating linkage is readily adaptable for use with, and is compatible with, virtually any conventional structural wing box without requiring modification of the wing box structure and without compromise to wing box location and/or extent; and (d), which permits of optimized negative (down) and positive (up) deflection of a desired airfoil edge so as to permit attainment of differing optimized airfoil performance characteristics for virtually any type of airfoil. More specifically, the present invention pertains to simplified actuating linkages for continuous skin variable camber airfoil edges comprising only two sets of 4-bar linkages-viz., one set to control horizontal and vertical displacement of the structural member defining the airfoil edge, and the other set controlling the angle of rotation of such structural member and the moment applied to the end of the flexible skin panel.
대표청구항▼
In a continuous skin variable camber airfoil of the type having (i) a rigid, centrally located, span-wise structural wing box including means defining both leading and trailing structural main frames, (ii) a leading structural edge member spaced forwardly from said wing box, (iii) a trailing structu
In a continuous skin variable camber airfoil of the type having (i) a rigid, centrally located, span-wise structural wing box including means defining both leading and trailing structural main frames, (ii) a leading structural edge member spaced forwardly from said wing box, (iii) a trailing structural edge member spaced rearwardly from said wing box, and (iv) a wing chord reference plane extending through the leading and trailing edges of said airfoil, an improved actuating mechanism for interconnecting at least one of said leading and trailing structural edge members to said main frame defining means so as to permit controlled deflection of said at least one structural edge member relative to said wing chord reference plane while providing structural load bearing support for said at least one structural edge member in all operating positions thereof, said actuating mechanism comprising, in combination: (a) a first 4-bar linkage assembly for controlling horizontal and vertical displacement of said structural edge member and including (i) said main frame defining means, (ii) a first generally horizontal control link pivotally connected adjacent one end thereof to the lower inboard edge of said structural edge member at a point P1 and projecting therefrom toward said structural wing box, (iii) a second generally upright control link pivotally connected adjacent its upper end to said main frame defining means at a point P2 and pivotally connected adjacent its lower end to the other end of said first control link at a point P1,2, and (iv) a third control link having a length greater than said second control link pivotally connected at one end to said first control link at a point P1,3 intermediate points P1 and P1,2 and at its other end to said main frame defining means at a point P3 spaced from and intermediate the points P1 and P2, said third control link projecting generally towards said structural edge member from point P3 when in the cruise camber position; (b) a second 4-bar linkage assembly for controlling angular rotation of said structural edge member and including (i) said first control link, (ii) a fourth generally horizontal control link pivotally connected at one end to said first control link at point P1,2 and extending towards and terminating short of point P1,3, (iii) a fifth generally upright control link pivotally connected at its lower end to the free end of said fourth link at a point P4,5 and pivotally connected at its upper end to said main frame defining means at point P3, and (iv) a sixth generally horizontal control link pivotally connected at one end to the upper inboard edge of said structural edge member at a point P6 and pivotally connected at its opposite end to said fifth control link at a point P5,6 intermediate points P3 and P4,5; and, (c) actuating means for causing the pivotal connection at point P1,2 between said first, second and fourth control links to pivot about point P2.
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