A manual wing-fold mechanism provides a means by which to reconfigure the wing of an aircraft between a flight configuration and one that can be easily stowed and transported. The folding mechanism includes an extension tube that enables the outboard portion of the wing to be extended away from the
A manual wing-fold mechanism provides a means by which to reconfigure the wing of an aircraft between a flight configuration and one that can be easily stowed and transported. The folding mechanism includes an extension tube that enables the outboard portion of the wing to be extended away from the inboard section of the wing, rotated about the lateral axis of the aircraft and then pivoted rearward so that the wing is aligned with the longitudinal axis of the aircraft along side the fuselage. The wing-fold mechanism is independent of the structural components of the wing used to convey aerodynamic loads during flight and provides a means for the user to bring the outboard wing section into a near alignment position while the wing-fold mechanism thereafter assists to refine the alignment into its final flight configuration.
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1. A wing-fold mechanism for use in an aircraft, comprising: a wing having a first wing section associated with a wing tip and a first wing section spar, and a second wing section associated with a wing root and a second wing section spar, and wherein the wing in flight configuration defines a later
1. A wing-fold mechanism for use in an aircraft, comprising: a wing having a first wing section associated with a wing tip and a first wing section spar, and a second wing section associated with a wing root and a second wing section spar, and wherein the wing in flight configuration defines a lateral axis of the aircraft spanning through the wingtip and the root;a plurality of shear pins configured to couple the first wing section spar to the second wing section spar wherein the plurality of shear pins are substantially parallel to the lateral axis;a folding apparatus, independent of the first wing section spar and the second wing section spar, coupling the first wing section to the second wing section wherein the folding apparatus is configured to translate the first wing section away from the second wing section along the lateral axis, rotates the first wing about the lateral axis and pivots the first wing section about a vertical axis perpendicular to the lateral axis placing the first wing section spar substantially perpendicular to the second wing section spar. 2. The wing-fold mechanism for use in an aircraft of claim 1, wherein when the wing is in flight configuration a portion of the first wing spar overlaps with a portion of the second wing section spar. 3. The wing-fold mechanism for use in an aircraft of claim 1, wherein the plurality of shear pins transfer in-flight aerodynamic loads from the first wing section to the second wing section. 4. The wing fold mechanism for use in an aircraft of claim 1, wherein each of the plurality of shear pins includes a first diameter and a second diameter and wherein a shear load is distributed among the first diameter and the second diameter. 5. The wing-fold mechanism for use in an aircraft of claim 1, wherein each of the plurality of shear pins includes a plurality of cross-sectional diameters. 6. The wing-fold mechanism for use in an aircraft of claim 1, wherein each of the plurality of shear pins are received by one of a corresponding plurality of shear pin sockets. 7. The wing-fold mechanism for use in an aircraft of claim 6, wherein each of the plurality of shear pins are associated with the first wing section. 8. The win fold mechanism for use in an aircraft of claim 6, wherein each of the plurality of shear pins are associated with the first wing section spar. 9. The wing-fold mechanism for use in an aircraft of claim 6, wherein each of the plurality of shear pin sockets is associated with the second wing section. 10. The wing-fold mechanism for use in an aircraft of claim 6, wherein each of the plurality of shear pin sockets is associated with the second wing section spar. 11. The wing-fold mechanism for use in an aircraft of claim 6, wherein one or more of the plurality of shear pins are secured in the corresponding plurality of shear pin sockets by a transverse lock pin. 12. A foldable aircraft wing, comprising: a first wing section having a first wing spar;a second wing section having a second wing spar wherein in a flight configuration the first wing spar is coupled to the second wing spar forming a wing spar juncture to transfer aerodynamic loads between the first wing section and the second wing section; andan extension device, independent of the first wing spar and the second wing spar, pivotally coupling the first wing section to the second wing section, wherein responsive to decoupling the first wing spar from the second wing spar the extension device is configured to extend the first wing section apart from the second wing section along a lateral axis substantially parallel with the first wing spar, rotates the first wing section about the lateral axis, and pivots the first wing section at a pivot point associated with the second wing section, to a transportable configuration. 13. The foldable aircraft wing of claim 12, wherein in the flight configuration a portion of the first wing spar overlaps a portion of the second wing section spar. 14. The foldable aircraft wing of claim 12, wherein the extension device is independent of the first wing spar and the second wing spar. 15. The foldable aircraft wing of claim 12, wherein the extension device is independent of aerodynamic loads transferred between the first wing spar and the second wing spar. 16. The foldable aircraft wing of claim 12, wherein the extension device includes a guiding channel to align the plurality of shear pins with the plurality of shear pin sockets as the first wing section transitions from the transportable configuration to the flight configuration. 17. The foldable aircraft wing of claim 12, wherein the first wing section includes a floating bearing circumscribing the extension device and wherein the floating bearing displaces the first wing section perpendicularly to the lateral axis and about the extension device as the plurality of shear pins engage the plurality of shear pin sockets. 18. The foldable aircraft wing of claim 12, wherein the wing spar juncture includes a plurality of shear pins and a plurality of shear pin sockets. 19. The foldable aircraft wing of claim 18, wherein the plurality of shear pins are substantially aligned with the lateral axis and fixed to the first wing section. 20. The foldable aircraft wing of claim 18, wherein in the flight configuration the plurality of shear pins are secured within the plurality of shear pin sockets by a transverse lock pin. 21. The foldable aircraft wing of claim 18, wherein each of the plurality of shear pins includes a first pin diameter and a second pin diameter and wherein a shear load is distributed among the first pin diameter and the second pin diameter. 22. The foldable aircraft wing of claim 21, wherein each of the plurality of shear pin sockets includes a first socket diameter and a second socket diameter corresponding to the first pin diameter and the second pin diameter respectively. 23. A system for modifying a wing from a transportable configuration to a night configuration, the system comprising: a first wing spar associated with a first wing section and wherein the first wing section in the transportable configuration is substantially orthogonal to a second wing section;a second wing spar associated with the second wing section wherein the first wing spar is attachable to the second wing spar at a wing spar juncture;a folding device, independent of the first wing spar and the second wing spar, coupling the first wing section to the second wing section and operable to position the first wing section front the transportable configuration to the flight configuration so as to align the first wing spar with the second wing spar at the wing spar juncture along a lateral axis; anda plurality of shear pins, aligned with the lateral axis and fixed to the first wing section, coupling the first wing spar to the second wing spar wherein each of the plurality of shear pins includes a first pin diameter and a second pin diameter and wherein a shear load is distributed among the first pin diameter and the second pin diameter. 24. The system for modifying a wing according to claim 23, wherein the folding device is independent of aerodynamic loads transferred between the first wing spar and the second wing spar. 25. The system for modifying a wine according to claim 23, wherein the first wing section includes a floating bearing operable to displace the first wing section perpendicularly to a lateral axis parallel to the first wing spar as the plurality of shear pins couple the first wing spar to the second wing spar. 26. The system for modifying a wing according to claim 23, wherein the plurality of shear pins are aligned with a lateral axis parallel to the first wing spar. 27. The system for modifying a wing according to claim 23, wherein in the flight configuration a portion of the first wing spar overlaps a portion of the second wing section spar.
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