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An aircraft wing tip device may include a unitized, monolithic leading edge torque box that may be formed of polymer matrix fiber-reinforced material. The leading edge torque box may include a skin that may define a continuous, uninterrupted outer mold line surface extending aftwardly from a winglet

An aircraft wing tip device may include a unitized, monolithic leading edge torque box that may be formed of polymer matrix fiber-reinforced material. The leading edge torque box may include a skin that may define a continuous, uninterrupted outer mold line surface extending aftwardly from a winglet leading edge by a distance of at least approximately 60 percent of a local chord length. The leading edge torque box may further include at least one internal component extending between opposing inner surfaces of the skin and being integrally formed therewith.

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1. A wing tip device for an aircraft, comprising: a unitized, monolithic leading edge torque box formed of polymer matrix fiber-reinforced material and including: a skin formed as a composite layup and defining a continuous, uninterrupted outer mold line (OML) surface extending aftwardly from a lead

1. A wing tip device for an aircraft, comprising: a unitized, monolithic leading edge torque box formed of polymer matrix fiber-reinforced material and including: a skin formed as a composite layup and defining a continuous, uninterrupted outer mold line (OML) surface extending aftwardly from a leading edge of the wing tip device by a distance of at least approximately 60 percent of a local chord length;at least one spar formed as a composite layup and oriented in a spanwise direction and having a web extending between opposing inner surfaces of the skin and being integrally formed therewith; andat least one pair of rigid soluble mandrels positioned within an interior of the leading edge torque box on opposite sides of the spar for compacting the composite layup of the skin against an outer mold line tool surface while simultaneously compacting the web of the spar between the pair of rigid soluble mandrels during co-curing of the composite layups to form the leading edge torque box, after which the rigid soluble mandrels are removed from the leading edge torque box by solubilization. 2. The wing tip device of claim 1, wherein: the composite layups comprise at least one of thermosetting composite material, thermoplastic composite material, pre-impregnated composite material, and resin-infused composite material. 3. The wing tip device of claim 1, wherein: the at least one spar comprises a front spar and a rear spar;the front spar being located aft of the leading edge of the wing tip device; andthe rear spar being located at a torque box aft end. 4. The wing tip device of claim 1, wherein: the wing tip device comprises one of a raked wing tip and a split winglet having upper and lower winglets. 5. The wing tip device of claim 1, wherein: the wing tip device comprises a winglet configured to extend outwardly from a wing of the aircraft. 6. The wing tip device of claim 5, wherein: the winglet includes a curved transition for transitioning the winglet from a wing tip of the wing to a canted section of the winglet. 7. The wing tip device of claim 1, further comprising: a trailing edge section joined to a torque box aft end. 8. The wing tip device of claim 7, wherein: the trailing edge section is attached to a rear spar located at the torque box aft end. 9. The wing tip device of claim 7, wherein: a forward end of the trailing edge section is mechanically fastened to the torque box aft end. 10. The wing tip device of claim 7, wherein: the trailing edge section comprises at least two separate panels including a trailing edge upper panel and a trailing edge lower panel; andthe trailing edge upper panel and the trailing edge lower panel each having a forward end being joined to the torque box aft end. 11. The wing tip device of claim 7, wherein: the trailing edge section comprises a unitary structure including a trailing edge upper panel and a trailing edge lower panel integrally formed with the trailing edge upper panel. 12. A winglet for an aircraft, comprising: a unitized, monolithic leading edge torque box formed of polymer matrix fiber-reinforced material and including: a skin formed as a composite layup and defining a continuous, uninterrupted outer mold line (OML) surface extending aftwardly from a winglet leading edge by a distance of at least approximately 60 percent of a local chord length;a front spar and a rear spar each formed as a composite layup and oriented in a spanwise direction and each having a web extending between opposing inner surfaces of the skin and being integrally formed therewith; anda plurality of rigid soluble mandrels positioned within an interior of the leading edge torque box on opposite sides of the front spar for compacting composite layups of the skin and the front spar and rear spar against an outer mold line tool surface while simultaneously compacting the web of the front spar between a pair of the rigid soluble mandrels during co-curing of the composite layups to form the leading edge torque box, after which the rigid soluble mandrels are removed from the leading edge torque box by solubilization. 13. The winglet of claim 12, wherein: the winglet includes a curved transition for transitioning the winglet from a wing tip of an aircraft wing to a canted section of the winglet when mounted to the wing tip. 14. The winglet of claim 12, further including: a trailing edge section integrally formed with the leading edge torque box into a unitized, monolithic, composite structure such that the winglet comprises a single, unitary structure from the winglet leading edge to the winglet trailing edge. 15. An aircraft, comprising: a wing having a wing tip;a winglet formed as a unitized, monolithic leading edge torque box formed of polymer matrix fiber-reinforced material, including: a skin formed as a composite layup and defining a continuous, uninterrupted outer mold line (OML) surface extending aftwardly from a winglet leading edge by a distance of at least approximately 60 percent of a local chord length;at least one spar formed as a composite layup and oriented along a spanwise direction of the winglet and having a web extending between and integrally formed with opposing inner surfaces of the ski;the winglet extending outwardly from the wing tip; andat least one pair of rigid soluble mandrels positioned within an interior of the leading edge torque box on opposite sides of the spar for compacting the composite layup of the skin and the at least one spar against an outer mold line tool surface while simultaneously compacting the web of the spar between the pair of rigid soluble mandrels during co-curing of the composite layups to form the leading edge torque box, after which the rigid soluble mandrels are removed from the leading edge torque box by solubilization. 16. The aircraft of claim 15, wherein: the winglet being oriented at an outward cant angle relative to vertical. 17. The aircraft of claim 16, wherein: the outward cant angle is between approximately 0-45 degrees relative to vertical. 18. The aircraft of claim 15, wherein: the at least one spar comprises a front spar and a rear spar. 19. The aircraft of claim 15, wherein: the winglet includes a curved transition for transitioning the winglet from the wing tip to a canted section of the winglet. 20. The aircraft of claim 15, further including: a trailing edge section joined to a torque box aft end of the torque box.