초록 ▼

An aircraft wing assembly includes a first wing portion and a structural spar that is disposed within the first wing portion. The structural spar is rotatable between an engaged position, wherein the structural spar engages a first internal structure of the first wing portion to stiffen the first wi

An aircraft wing assembly includes a first wing portion and a structural spar that is disposed within the first wing portion. The structural spar is rotatable between an engaged position, wherein the structural spar engages a first internal structure of the first wing portion to stiffen the first wing portion, and a disengaged position, wherein the structural spar does not engage the first internal structure of the first wing portion.

대표청구항 ▼

1. An aircraft wing assembly, comprising: a first wing portion;a tip panel that is fixed to the first wing portion; anda structural spar that is disposed within the first wing portion and is connected to the tip panel by a rotational joint, wherein the structural spar is rotatable with respect to th

1. An aircraft wing assembly, comprising: a first wing portion;a tip panel that is fixed to the first wing portion; anda structural spar that is disposed within the first wing portion and is connected to the tip panel by a rotational joint, wherein the structural spar is rotatable with respect to the first wing portion and the tip panel between an engaged position, wherein the structural spar engages a first internal structure of the first wing portion to stiffen the first wing portion, and a disengaged position, wherein the structural spar does not engage the first internal structure of the first wing portion. 2. The aircraft wing assembly of claim 1, further comprising: a second wing portion, wherein the first wing portion and the second wing portion are telescopically related. 3. The aircraft wing assembly of claim 2, wherein the first wing portion and the second wing portion cooperate to define a telescopic wing having an extended position and a retracted position. 4. The aircraft wing assembly of claim 3, wherein the structural spar is restrained from moving from the disengaged position to the engaged position when the telescopic wing is in the retracted position. 5. The aircraft wing assembly of claim 3, wherein the structural spar includes a first spar portion and a second spar portion that are telescopically related. 6. The aircraft wing assembly of claim 1, wherein the structural spar has a first surface and a second surface that are spaced apart by a first distance, and the structural spar has a third surface and a fourth surface that are spaced apart by a second distance that is less than the first distance, wherein the first surface of the structural spar engages the first internal structure of the first wing portion when the structural spar is in the engaged position. 7. The aircraft wing assembly of claim 6, wherein the second surface of the structural spar engages a second internal structure of the first wing portion when the structural spar is in the engaged position. 8. The aircraft wing assembly of claim 1, wherein the first internal structure is a skin of the first wing portion. 9. The aircraft wing assembly of claim 1, wherein the first internal structure is connected to a skin of the first wing portion. 10. The aircraft wing assembly of claim 1, wherein the first internal structure is an internal rib that is connected to a skin of the first wing portion. 11. The aircraft wing assembly of claim 1, wherein the first internal structure is a spacer that is connected to a skin of the first wing portion. 12. The aircraft wing assembly of claim 1, wherein the structural spar includes a first contoured surface and the first internal structure includes a second contoured surface that is in engagement with the first contoured surface when the structural spar is in the engaged position. 13. The aircraft wing assembly of claim 1, wherein the structural spar is in engagement with a stop surface on an interior of the first wing portion when the structural spar is in the engaged position, and the stop surface restrains rotation of the structural spar in at least a first rotational direction. 14. The aircraft wing assembly of claim 1, further comprising: a locking member that is engageable with the first wing portion and the structural spar when the structural spar is in the engaged position to restrain the structural spar against moving to the disengaged position. 15. The aircraft wing assembly of claim 14, wherein the locking member is a pin that is receivable within an aperture in the structural spar. 16. An aircraft wing assembly, comprising: a telescopic wing having a first wing portion and a second wing portion, wherein the first wing portion and the second wing portion are telescopically related; anda structural spar having a first spar portion and a second spar portion that are telescopically related, wherein the structural spar is connected to the telescopic wing such that the telescopic wing and the structural spar move in unison, wherein the structural spar is rotatable between a disengaged position, in which the telescopic wing and the structural spar are free to move between an extended position and a retracted position, and an engaged position, in which the telescopic wing and the structural spar are disposed in the extended position and are restrained from moving to the retracted position. 17. The aircraft wing assembly of claim 16, wherein the structural spar stiffens a skin of the telescopic wing when the structural spar is in the engaged position. 18. The aircraft wing assembly of claim 16, wherein the structural spar engages a first internal structure of the telescopic wing to stiffen the telescopic wing when the structural spar is in the engaged position. 19. The aircraft wing assembly of claim 18, wherein the first internal structure includes at least one of a skin of the first wing portion, an internal rib that is connected to the skin of the first wing portion, or a spacer that is connected to the skin of the first wing portion. 20. The aircraft wing assembly of claim 16, further comprising: a locking member that is engageable with the telescopic wing and the structural spar when the structural spar is in the engaged position to restrain the structural spar against moving to the disengaged position.