Shortening wingspan of an aircraft
According to one aspect of the present disclosure, an apparatus for shortening a wingspan of an aircraft is disclosed. The apparatus comprises a first link extending from a wingtip of the aircraft and moveably coupled to a fixed wing of the aircraft. A second link also extends from the wingtip and is moveably coupled to the fixed wing. An actuator is coupled to the fixed wing and to the second link. The actuator is configured to move the second link and cause the wingtip to move between an extended position and a stowed position.
1. An apparatus for shortening a wingspan of an aircraft, the apparatus comprising:
a first link extending from a wingtip of the aircraft and moveably coupled to a fixed wing of the aircraft;
a second link extending from the wingtip and moveably coupled to the fixed wing; and
an actuator coupled to the fixed wing and to the second link, the actuator comprising a piston;
wherein the actuator is configured to extend the piston to move the second link and cause the wingtip to move between an extended position in which the wingtip is substantially coplanar with the fixed wing and a stowed position in which the wingtip is substantially coplanar with the fixed wing.
2. The apparatus of claim 1 , further comprising a third link comprising an actuator end rotatably coupled to the actuator and a mounting end rotatably coupled to the fixed wing.
3. The apparatus of claim 2 , wherein the second link comprises a first connecting member and a second connecting member.
4. The apparatus of claim 3 , wherein the first connecting member comprises a latch extension that defines a latch aperture, and the apparatus further comprises a latch actuator affixed to a fixed wing front spar of the fixed wing, the latch actuator configured to extend a latch pin through the latch aperture of the latch extension to lock the wingtip in the extended position.
5. The apparatus of claim 3 , wherein the first connecting member and the second connecting member are rotatably coupled to the fixed wing at a second link joint.
6. The apparatus of claim 5 , wherein the second link joint is coupled to an actuator joint, and the actuator is rotatably coupled to the actuator joint.
7. The apparatus of claim 6 , wherein the actuator is rotatably coupled to the fixed wing at the actuator joint.
8. The apparatus of claim 1 , wherein a fixed wing end of the first link is rotatably coupled to a fixed wing rear spar of the fixed wing at a first link fixed wing joint.
9. The apparatus of claim 8 , wherein a wingtip end of the first link is rotatably coupled to a support rib of the wingtip at a first link wingtip joint.
10. The apparatus of claim 9 , wherein the first link wingtip joint is located at a center of gravity of the wingtip.
11. The apparatus of claim 1 , further comprising a track affixed to the fixed wing and defining an elongated channel, wherein the first link comprises a roller at a fixed wing end that extends into the elongated channel to guide movement of the wingtip between the extended position and the stowed position.
12. The apparatus of claim 11 , further comprising a latch assembly affixed to a trailing end of the track, the latch assembly configured to releasably capture a latch stay affixed to the second link to lock the wingtip in the extended position.
13. The apparatus of claim 11 , wherein a fixed wing end of the second link is rotatably coupled to a fixed wing spar of the fixed wing at a second link fixed wing joint.
14. The apparatus of claim 13 , wherein a wingtip end of the second link is rotatably coupled to a support rib of the wingtip at a second link wingtip joint.
15. The apparatus of claim 14 , wherein the second link wingtip joint is located at a center of gravity of the wingtip.
16. The apparatus of claim 11 , wherein the second link comprises a piston joint, and the actuator is rotatably coupled to the piston joint.
17. The apparatus of claim 11 , wherein the actuator is rotatably coupled to the fixed wing at an actuator joint.
18. An aircraft, comprising:
a fixed wing extending from a fuselage;
a wingtip moveably coupled to an outboard end of the fixed wing; and
an apparatus for moving the wingtip at least partially behind the fixed wing, the apparatus comprising:
a first link extending from the wingtip of the aircraft and moveably coupled to the fixed wing of the aircraft;
a second link extending from the wingtip and moveably coupled to the fixed wing; and
an actuator coupled to the fixed wing and to the second link, the actuator comprising a piston;
wherein the actuator is configured to extend the piston to move the second link and cause the wingtip to move between an extended position in which the wingtip is substantially coplanar with the fixed wing and a stowed position in which the wingtip is substantially coplanar with the fixed wing.
19. A method of shortening a wingspan of an aircraft, the method comprising:
providing an apparatus for moving a wingtip at least partially behind a fixed wing of the aircraft, the apparatus comprising:
a first link extending from a wingtip of the aircraft and moveably coupled to a fixed wing of the aircraft;
a second link extending from the wingtip and moveably coupled to the fixed wing; and
an actuator coupled to the fixed wing and to the second link;
positioning the wingtip at an outboard end of the fixed wing; and
extending the actuator to move the second link and cause the wingtip to move from an extended position corresponding to a first wingspan of the aircraft in which the wingtip is substantially coplanar with the fixed wing to a stowed position corresponding to a second wingspan of the aircraft shorter than the first wingspan and in which the wingtip is substantially coplanar with the fixed wing.
20. The aircraft of claim 18 , further comprising a track affixed to the fixed wing and defining an elongated channel, wherein the first link comprises a roller at a fixed wing end that extends into the elongated channel to guide movement of the wingtip between the extended position and the stowed position.