Aircraft wing space frame

Patent metadata

Field	Value
Publication number	US-10850826-B2
Application number	US-201715468866-A
Country	US
Kind code	B2
Filing date	Mar 24, 2017
Priority date	Mar 24, 2017
Publication date	Dec 1, 2020
Grant date	Dec 1, 2020

Abstract

Aircraft wings have an interior volume that incorporates a space frame as a primary supporting structure of the wing, and enables securement of an aircraft fuselage to the wing. The space frame includes carbon fiber rods arranged to handle tensile and compression loads otherwise carried by conventional wing spars, ribs, and stringers normally connected to heavy structural metal wing box joints at the sides of a fuselage for attachment of left and right wings. The space frame also includes sleeve and shaft connectors secured to the carbon fiber rods, the connectors arranged in truss-like configurations for preventing buckling of the carbon fiber rods. The space frame is designed to extend at least midspan between wings, so that traditional wing box joints on a fuselage can be eliminated. Finally, wing skin panels secured to the space frame are designed to support only aerodynamic loads of flight.

First claim

What is claimed is:

1. An aircraft wing comprising:
an exterior skin defining an interior volume;
the interior volume having a space frame configured to support all tensile, compression, bending and torsional loads applied to the wing during flight, landing, and ground operations of the aircraft wing;
wherein the space frame is defined by a first array of carbon fiber rods extending spanwise within the interior volume, and a second array of carbon fiber rods extending chordwise within the interior volume; the first and second arrays secured together by a first plurality of connectors, and wherein the exterior skin is secured to the space frame by a second plurality of connectors;
wherein the first array of carbon fiber rods comprises upper and lower carbon fiber rods, and the space frame further comprises a third array of midspan carbon fiber rods that also secure the upper carbon fiber rods to the lower carbon fiber rods via the first plurality of connectors;
wherein the midspan carbon fiber rods comprise a distinct load path within the space frame, the midspan carbon fiber rods being configured to extend spanwise from an aircraft fuselage to a midspan portion of the interior volume of the wing;
wherein the fuselage and the midspan portion each include a plurality of vertical elements that space the upper carbon fiber rods from the lower carbon fiber rods; and
wherein each midspan carbon fiber rod is fixed to, and extends between, at least one pair of the vertical elements.

2. The aircraft wing of claim 1 , wherein the space frame comprises a primary supporting structure of the wing, and wherein the exterior skin is configured to support only aerodynamic loads.

3. The aircraft wing of claim 1 , wherein the first plurality of connectors comprises sleeve connectors secured to the carbon fiber rods, each sleeve connector securing one of the carbon fiber rods of the first array to one of the carbon fiber rods of the second array.

4. The aircraft wing of claim 3 , wherein elongated rigid shafts extend on an angle between the sleeve connectors to provide angled bracing between upper and lower chordwise carbon fiber rods of the second array of carbon fiber rods.

5. The aircraft wing of claim 1 , comprising an integrated system of left and right wings, wherein the space frame comprises at least a midspan portion of the interior volume of both left and right wings.

6. The aircraft wing of claim 5 , wherein the space frame extends spanwise at least midspan of the interior volume of each wing.

7. The aircraft wing of claim 5 , wherein the upper spanwise extending carbon fiber rods are in a state of compression when the wing is in flight, and in a state of tension when the wing is not in flight.

8. The aircraft wing of claim 5 , wherein the lower spanwise extending carbon fiber rods are in a state of tension when the wing is in flight, and in a state of compression when the wing is not in flight.

9. The aircraft wing of claim 8 , wherein the midspan carbon fiber rods are configured to transfer compressive loads between the left and right wings.

10. The aircraft wing of claim 9 , wherein each midspan carbon fiber rod structurally links an upper spanwise carbon fiber rod with a lower spanwise carbon fiber rod.

11. A space frame comprising a pair of integrated left and right aircraft wings having an exterior skin defining an interior volume of the wings; the space frame comprising:
a first array of carbon fiber rods configured to extend spanwise within the interior volume at least midspan of each wing, and a second array of carbon fiber rods configured to extend chordwise from a leading edge to a trailing edge within the interior volume; the first and second arrays secured together by a first plurality of connectors, and the exterior skin is secured to the space frame by a second plurality of connectors;
wherein the first array of carbon fiber rods comprises upper and lower spanwise extending carbon fiber rods, and the space frame further comprises a third array of midspan carbon fiber rods that also secure the upper carbon fiber rods and the lower carbon fiber rods together via the first plurality of connectors;
wherein the midspan carbon fiber rods comprise a distinct load path within the space frame, the midspan carbon fiber rods being configured to extend spanwise from an aircraft fuselage to a midspan portion of the interior volume of each wing;
wherein the fuselage, and the midspan portion of each wing, include a plurality of vertical elements that space the upper carbon fiber rods from the lower carbon fiber rods; and
wherein each midspan carbon fiber rod is fixed to, and extends between, at least one pair of the vertical elements.

12. The space frame of claim 11 , wherein the first plurality of connectors comprises sleeve connectors coupled to the carbon fiber rods of the first and second arrays.

13. The space frame of claim 12 , wherein elongated rigid shafts extend on an angle between the first plurality of connectors to provide angled bracing between upper and lower chordwise carbon fiber rods of the second array of carbon fiber rods.

14. The space frame of claim 11 , wherein each of the first and second arrays of carbon fiber rods include upper and lower carbon fiber rods secured together by the first plurality of connectors.

15. The space frame of claim 11 , wherein the first plurality of connectors include compound sleeve connectors, wherein each compound sleeve connector is configured to tie together an upper carbon fiber rod of the first array to an upper carbon fiber rod of the second array, and to tie together a lower carbon fiber rod of the first array to a lower carbon fiber rod of the second array.

16. The space frame of claim 11 , further comprising a second plurality of sleeve connectors, and wherein each of the second plurality of sleeve connectors comprises an elongated sleeve having an elongated skin panel sleeve connector configured to secure a skin panel to the space frame.

17. The space frame of claim 16 , wherein each of the second plurality of sleeve connectors is configured to extend spanwise over the first array of carbon fiber rods.

18. The space frame of claim 11 , wherein the space frame extends spanwise at leastmidspan of the interior volume of each wing.

19. The aircraft wing of claim 3 , further comprising a second plurality of sleeve connectors, and wherein each of the second plurality of sleeve connectors comprises an elongated sleeve having an elongated skin panel sleeve connector configured to secure a skin panel to the space frame.

20. The aircraft wing of claim 19 , wherein each of the second plurality of sleeve connectors is configured to extend spanwise over the first array of carbon fiber rods.

Assignees

• Boeing Co

Inventors

• Chengalva Mahesh Krishna

Classifications

• B64C3/187

  Ribs · CPC title

• B64C3/18 Primary

  Spars; Ribs; Stringers · CPC title

• B64C3/26

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64C3/00 Primary

  Wings (ornithopter wings B64C33/02) · CPC title

• B64F5/00

  Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for · CPC title