Deployable wing for an aircraft

• US 10,106,243 B2
• Filed: 04/12/2016
• Issued: 10/23/2018
• Est. Priority Date: 04/12/2016
• Status: Active Grant

• Current Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Original Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Inventors: Keavney, Thomas E., Rufino, John C.
• Primary Examiner(s): Ellis, Christopher P
• Application Number:
  US15/096,998
• Publication Number:
  US 20170291683A1
• Time in Patent Office: 924 Days
• CPC Class Codes: B64C 3/30 comprising inflatable structural components
• CPC Class Codes: B64D 17/80 in association with aircraft, e.g. for braking thereof

Abstract

An apparatus for selectively increasing a wing area of an aircraft having a fuselage with an interior space includes an inflatable wing moveable between a stowed condition located in the interior space and a deployed condition located outside the interior space. A plurality of reels is secured to the aircraft. A plurality of suspension lines connects the wing to the reels. At least one reel is operable to unwind a corresponding suspension line to allow the wing to inflate to the deployed condition exclusively by ram air generated by movement of the aircraft. A method of use for a deployable wing is also provided.

Claims

1. An apparatus for selectively increasing a wing area of an aircraft having a fuselage with an interior space, the apparatus comprising:

an inflatable wing moveable between a stowed condition located in the interior space and a deployed condition located outside the interior space;

a canopy tube located in the interior space, the inflatable wing being configured, in the stowed condition, to be at least partially contained within the canopy tube;

a plurality of reels secured to the aircraft; and

a plurality of suspension lines connecting the wing to the reels, at least one reel of the plurality of reels being operable to unwind a corresponding suspension line to allow the wing to inflate to the deployed condition exclusively by ram air generated by movement of the aircraft, and at least one reel of the plurality of reels being selectively operable to retract a corresponding suspension line to control deflation of the wing and return of the wing into the stowed condition.

2. The apparatus of claim 1, wherein the wing includes flexible upper and lower wing panels, each of the upper and lower wing panels being significantly longer in a starboard-port direction than in a fore-aft direction, the upper and lower wing panels being attached together at the aft portions thereof with the fore portions of the upper and lower wing panels being spaced apart, when the wing is in a fully deployed condition, to admit ram air into a wing interior space defined by the upper and lower wing panels.

3. The apparatus of claim 2, including at least one flexible interior baffle extending vertically between the upper and lower wing panels and substantially perpendicular thereto, each interior baffle being substantially oriented in a fore-aft direction to partition the wing interior into a plurality of interior compartments spaced apart in the starboard-port direction.

4. The apparatus of claim 1, wherein, when in the deployed condition, the wing is curved at least one of convexly-upward in the fore-aft direction and convexly-upward in the starboard-port direction.

5. The apparatus of claim 1, wherein the wing is made substantially from a flexible sheet material.

6. The apparatus of claim 1, wherein at least one suspension line includes selectively vertically spaced proximal and distal line portions with a line junction located vertically therebetween, the proximal line portion having a single line strand and being connected to a selected reel, and the distal line portion including a plurality of line strands, each line strand being connected to the wing at a location spaced from the other line strands of that suspension line, the plurality of line strands being aggregated at the line junction into the single line strand connected to the selected reel.

7. The apparatus of claim 1, wherein the plurality of reels is configured for selective operation to selectively change a surface area of a forward edge of the wing during transition of the wing between the stowed and deployed conditions.

8. An aircraft comprising:

an outer mold line on a fuselage of the aircraft;

an interior space within the fuselage;

an inflatable wing moveable between a stowed condition, wherein the wing is substantially contained within the interior space and a deployed condition, wherein the inflatable wing is located wholly outside the outer mold line, in the ambient space, the inflatable wing including substantially planar flexible upper and lower wing panels being attached together at an aft edge thereof and including space vertically therebetween, when the wing is in the deployed condition, to form a wing interior configured to accept, and thus become inflated by, ram air flow;

a canopy tube within the interior space, the canopy tube configured to at least partially contain the inflatable wing in the stowed condition;

a plurality of reels secured to the aircraft within the interior space; and

a plurality of selectively vertically extending suspension lines connecting the wing to the reels, at least one reel of the plurality of reels being selectively operable to extend a corresponding suspension line to allow the wing to inflate to the deployed condition exclusively by ram air flow generated by movement of the aircraft, and at least one reel of the plurality of reels being selectively operable to retract a corresponding suspension line to control deflation of the wing and return of the wing into the stowed condition.

9. The aircraft of claim 8, including at least one flexible interior baffle extending vertically between the upper and lower wing panels and substantially perpendicular thereto, each interior baffle being substantially oriented in a fore-aft direction to partition the wing interior into a plurality of interior compartments spaced apart in the starboard-port direction.

10. The aircraft of claim 8, wherein, when in the deployed condition, the wing is curved convexly-upward in the fore-aft direction and convexly-upward in the starboard-port direction.

11. The aircraft of claim 8, wherein at least one suspension line includes vertically spaced proximal and distal line portions with a line junction located vertically therebetween, the proximal line portion having a single line strand and being connected to a selected reel, and the distal line portion including a plurality of line strands, each line strand being connected to the wing at a location spaced from the other line strands of that suspension line, the plurality of line strands being aggregated at the line junction into the single line strand connected to the selected reel.

12. A method of use for a deployable wing for an aircraft having a fuselage with an interior space, the method comprising:

providing an inflatable wing selectively movable between stowed and deployed conditions, the wing having an open fore edge and a substantially closed aft edge and a wing interior located laterally therebetween, the wing being secured to the aircraft at least by a plurality of suspension lines connecting the wing to a plurality of reels in the interior space;

substantially containing the wing within the interior space when the wing is in the stowed condition, including at least partially containing the wing within a canopy tube located in the interior space;

exposing the open fore edge of the wing to ram air generated by movement of the aircraft to allow the wing interior to inflate with the ram air;

deflating the wing interior of the wing in the deployed condition by selectively operating at least one reel to retract a corresponding suspension line; and

returning the wing from the deployed condition to the stowed condition in the interior space of the aircraft.

13. The method of claim 12, including opening the interior space to ambient space.

14. The method of claim 12, wherein exposing the open fore edge of the wing to ram air generated by movement of the aircraft to allow the wing interior to inflate with the ram air includes operating at least a chosen one of the reels to extend the suspension line attached to the chosen reel.

15. The method of claim 14, wherein exposing the open fore edge of the wing to ram air generated by movement of the aircraft to allow the wing interior to inflate with the ram air includes operating at least a chosen other one of the reels to retract the suspension line attached to the chosen other reel.

16. The method of claim 12, wherein exposing the open fore edge of the wing to ram air generated by movement of the aircraft to allow the wing interior to inflate with the ram air includes operating at least one reel to pull the aft edge of the wing in an aft direction from the canopy tube.

17. The method of claim 12, wherein at least one suspension line includes vertically spaced proximal and distal line portions with a line junction located vertically therebetween, the proximal line portion having a single line strand and being connected to a selected reel, and the distal line portion including a plurality of line strands, each line strand being connected to the wing at a location spaced from the other line strands of that suspension line, the plurality of line strands being aggregated at the line junction into the single line strand connected to the selected reel, the method including operating the selected reel to concurrently extend or retract the plurality of line strands of that suspension line.

18. The method of claim 12, including selectively changing a surface area of a forward edge of the wing during transition of the wing between the stowed and deployed conditions by selective operation of at least one reel.