Space frame structure

Patent metadata

Field	Value
Publication number	US-9765512-B2
Application number	US-201313793117-A
Country	US
Kind code	B2
Filing date	Mar 11, 2013
Priority date	Mar 9, 2012
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

A structure comprising a space frame including a plurality of strut sections which cross at one or more locations within the space frame to define a node at each respective crossing location, wherein the strut sections are laminates comprising a plurality of ply layers, and wherein the ply layers of the crossing strut sections are interleaved at the node(s). Also a method of forming the structure. Also An aerofoil structure, comprising a space frame defining a cage adapted to receive upper and lower covers so as to form upper and lower aerodynamic surfaces of the aerofoil, and at least one spar extending generally spanwise across the structure, wherein the spar includes a spar web and upper and lower spar caps, and wherein the spar web is disposed on one of an interior or exterior side of the cage, and the spar caps are attached to the other of the interior or exterior side of the cage.

First claim

The invention claimed is:

1. A structure comprising a space frame including a plurality of strut sections which cross at one or more locations within the space frame to define a node at each respective crossing location, wherein the strut sections are laminates comprising a plurality of ply layers, and wherein the ply layers of the crossing strut sections are interleaved at the node(s),
wherein at least one of the strut sections has a generally non-planar profile, and
wherein a profile of the strut section flattens as the profile approaches one of the node(s).

2. The structure according to claim 1 , wherein at least one of the node(s) is substantially planar.

3. A structure comprising a space frame including a plurality of strut sections which cross at one or more locations within the space frame to define a node at each respective crossing location, wherein the strut sections are laminates comprising a plurality of ply layers, and wherein the ply layers of the crossing strut sections are interleaved at the node(s),
wherein at least one of the strut sections has a termination and a non-planar profile which flattens as the at least one of the strut sections approaches a termination of the at least one of the strut sections.

4. The structure according to claim 1 , wherein the space frame includes a composite material.

5. The structure according to claim 1 , wherein the space frame includes integrally formed sides.

6. The structure according to claim 1 , further comprising a corner element disposed between two adjacent sides of the space frame.

7. The structure according to claim 1 , wherein the space frame includes opposing nodes and a structural member extending between the opposing nodes.

8. The structure according to claim 1 , wherein the space frame is a cage.

9. A structure comprising a space frame including a plurality of strut sections which cross at one or more locations within the space frame to define a node at each respective crossing location, wherein the strut sections are laminates comprising a plurality of ply layers, and wherein the ply layers of the crossing strut sections are interleaved at the node(s),
wherein the space frame is a cage, and
wherein the cage has at least one open side.

10. The structure according to claim 1 , wherein the space frame includes at least one loop portion, which extends around the perimeter of the structure.

11. The structure according to claim 1 , further comprising a panel attached to the space frame.

12. A structure comprising:
a space frame including a plurality of strut sections which cross at one or more locations within the space frame to define a node at each respective crossing location, wherein the strut sections are laminates comprising a plurality of ply layers, and wherein the ply layers of the crossing strut sections are interleaved at the node(s), and
a panel attached to the space frame,
wherein at least one of the node(s) of the space frame is spaced from a surface of the panel in a direction normal to the panel surface.

13. The structure according to claim 11 , further comprising a plurality of panels attached to respective sides of the space frame.

14. An aerofoil comprising a structure according to claim 1 .

15. The aerofoil according to claim 14 , further comprising upper and lower covers attached to opposite sides of the space frame.

16. The aerofoil according to claim 14 , further comprising front and rear spars attached to opposite sides of the space frame.

17. The aerofoil according to claim 16 , wherein each spar includes a spar web and upper and lower spar caps, and wherein the spar web is disposed on one of an interior or exterior side of the space frame, and the spar caps are attached to or integrally formed with the other of the interior or exterior side of the space frame.

18. The aerofoil according to claim 14 , wherein the strut sections are substantially aligned with load carrying directions of the structure.

19. A method of forming a space frame structure, the method comprising the steps of:
a) providing a ply deposition device configured to deposit ply layers; and
b) depositing the ply layers to form a plurality of laminate strut sections that cross at one or more locations within the structure to define a node at each respective crossing location, such that the ply layers of the crossing strut sections are interleaved at the node(s), wherein at least one of the strut sections having a generally non-planar profile, and a profile of the strut section flattens as the profile approaches the node.

20. The method according to claim 19 , wherein the ply layers are deposited on a tool which is shaped to provide at least one of the strut sections with a non-planar cross-section.

21. The method according to claim 19 , wherein the structure rotates relative to the ply deposition device during the ply deposition process.

22. The method according to claim 19 , wherein the structure has a longitudinal axis, and wherein the ply deposition device moves relative to the structure in the direction of the longitudinal axis during the ply deposition process.

Assignees

• Airbus Operations Ltd

Inventors

• Williams Stephen

Classifications

• B29D99/0007

  having a variable cross-section · CPC title

• Y10T156/10

  Methods of surface bonding and/or assembly therefor · CPC title

• B29C70/38

  Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns {(application heads for tyres B29D30/28)} · CPC title

• E04B1/19 Primary

  Three-dimensional [3D] framework structures · CPC title

• Y02T50/433

  Cross-Sectional Technologies · mapped topic