LATERAL PLY LAYUP OF COMPOSITE SPAR

• US 20160039514A1
• Filed: 08/08/2014
• Published: 02/11/2016
• Est. Priority Date: 08/08/2014
• Status: Abandoned Application

• Current Assignee: Brian T. Pitman
• Original Assignee: Brian T. Pitman
• Inventors: Pitman, Brian T.
• Application Number:
  US14/455,291
• Publication Number:
  US 20160039514A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B32B 2305/18 Fabrics, textiles
• CPC Class Codes: B32B 2309/06 Angles
• CPC Class Codes: B32B 2605/18 Aircraft
• CPC Class Codes: B32B 37/20 involving the assembly of continuous webs only
• CPC Class Codes: B64C 3/185 Spars

Abstract

A structural component, including a composite tapered wing spar including a first fiber layer and a main web, wherein respective longitudinal axes of fibers making up the first layer at least substantially lying on a plane corresponding to the main web of the wing spar are curved over at least most of the respective lengths of the fibers.

Claims

1. A structural component, comprising:

a composite tapered wing spar including a first fiber layer and a main web, wherein respective longitudinal axes of fibers making up the first layer at least substantially lying on a plane corresponding to the main web of the wing spar are curved over at least most of the respective lengths of the fibers.

2. The structural component of claim 1, wherein the spar includes a first flange having a first flange radius connecting the main web of the spar to the first flange, the first flange extending along at least a part of the spar in a longitudinal direction of the spar, wherein local direction of the longitudinal axis of the fibers at the first flange radius making up the first layer is effectively 90 degrees relative to the general direction of extension of the first flange.

3. The structural component of claim 1, wherein the spar includes a main web and a first flange having a first flange radius connecting the main web to the first flange, the first flange extending along at least a part of the spar in a longitudinal direction of the spar, wherein local direction of the longitudinal axis of the fibers at the first flange radius making up the first layer is about 45 degrees relative to the general direction of extension of the first flange.

4. The structural component of claim 1, wherein the spar includes a main web and a first flange having a first flange radius connecting the main web to the first flange, the first flange extending along at least a part of the spar in a longitudinal direction of the spar, wherein local direction of the longitudinal axis of the fibers at the first flange radius making up the first layer is effectively 0 degrees relative to the general direction of extension of the first flange.

5. The structural component of claim 1, wherein the spar includes a second flange having a second flange radius connecting the main web to the second flange, the second flange extending along at least a part of the spar in the longitudinal direction of the spar, wherein local direction of the longitudinal axis of the fibers at the second flange radius making up the first layer is about 90 degrees relative to the general direction of extension of the second flange, wherein the direction of extension of the first flange is at a non-zero angle relative to the direction of extension of the second flange.

6. The structural component of claim 1, wherein the spar includes a second flange having a second flange radius connecting the main web to the second flange, the second flange extending along at least a part of the spar in the longitudinal direction of the spar, wherein local direction of the longitudinal axis of the fibers at the second flange radius making up the first layer is about 45 degrees relative to the general direction of extension of the second flange, wherein the direction of extension of the first flange is at a non-zero angle relative to the direction of extension of the second flange.

7. The structural component of claim 1, wherein the spar includes a second flange having a second flange radius connecting the main web to the second flange, the second flange extending along at least a part of the spar in the longitudinal direction of the spar, wherein local direction of the longitudinal axis of the fibers at the second flange radius making up the first layer is effectively 0 degrees relative to the general direction of extension of the second flange, wherein the direction of extension of the first flange is at a non-zero angle relative to the direction of extension of the second flange.

8. The structural component of claim 1, further comprising a second layer, wherein a longitudinal axis of fibers making up a second layer of the spar are curved, wherein local direction of the longitudinal axis of the fibers making up the second layer is about 90 degrees relative to respective local direction of the longitudinal axis of the fibers making up the first layer.

9. The structural component of claim 1, further comprising a second layer, wherein a longitudinal axis of fibers making up a second layer of the spar are straight, wherein local direction of the longitudinal axis of the fibers making up the second layer is about 45 degrees relative to respective local direction of the longitudinal axis of the fibers making up the first layer.

23. An aircraft, comprising:

a wing, including a wing spar corresponding to the structural component of claim 1.

10. A method of fabricating a composite structure, comprising:

laying down a plurality of fibers in a first layer to form a composite spar, wherein the first layer has a first component that extends generally in a first plane and a second component that extends generally in a second plane and a third component that extends generally in a third plane such that a first transition zone between the first and second components extends in at least a first generally linear manner and such that a second transition zone between the second and third components extends in at least a second generally linear manner in a different direction than the first generally linear manner, wherein

the method further comprises steering plies of the fibers of the first layer to be, at the first transition zone, effectively normal to the direction of extension of the first transition zone and to be, at the second transition zone, effectively normal to the direction of extension of the second transition zone.

11. The method of claim 10, further comprising:

laying down a plurality of fibers in a second layer above the first layer to form the composite spar, wherein the second layer has a fourth component that extends generally in the first plane and a fifth component that extends generally in the second plane and a sixth component that extends generally in the third plane such that a third transition zone between the fourth and fifth components extends in at least the first generally linear manner and such that a fourth transition zone between the fifth and sixth components extends in at least the second generally linear manner, wherein

the method further comprises steering plies of the fibers of the second layer to be, at the third transition zone, effectively parallel to the direction of extension of the fourth transition zone and to be, at the fourth transition zone, effectively parallel to the direction of extension of the fourth transition zone.

12. The method of claim 10, further comprising:

laying down a plurality of fibers in a second layer above the first layer to form the composite spar, wherein the second layer has a fourth component that extends generally in the first plane and a fifth component that extends generally in the second plane and a sixth component that extends generally in the third plane such that a third transition zone between the fourth and fifth components extends in at least the first generally linear manner and such that a fourth transition zone between the fifth and sixth components extends in at least the second generally linear manner, wherein

the method further comprises steering ±

45 degree plies of the fibers of the second layer such that local directions of extensions of the fibers of the second layer are about 45 degrees relative to the local directions of extensions of the fibers of the first layer for substantially all locations of the spar.

13. The method of claim 12, further comprising:

laying down a plurality of fibers in a third layer above the first layer or the second layer to form the composite spar, wherein the third layer has a seventh component that extends generally in the first plane and an eighth component that extends generally in the second plane and a ninth component that extends generally in the third plane such that a fifth transition zone between the seventh and eighth components extends in at least the first generally linear manner and such that a sixth transition zone between the eighth and ninth components extends in at least the second generally linear manner, wherein

the method further comprises steering ±

45 degree plies of the fibers of the second layer such that local directions of extensions of the fibers of the second layer are about 45 degrees relative to the local directions of extensions of the fibers of the second layer for substantially all locations of the spar.

14. The method of claim 10, wherein:

the second component corresponds to a body of the spar and the first and third components correspond to flanges of the spar.

25. A method, comprising:

constructing an aircraft by;

fabricating a wing by fabricating a wing spar by executing the method of claim 10.

15. A structural component, comprising:

a composite tapered wing spar having a web and two flanges on opposite sides of the web, the composite tapered wing spar having a first fiber layer made up of a plurality of plies that are effectively normal to directions of extensions of the respective flanges at respective transition zones of the flanges and web, wherein the directions of extensions of the respective flanges are obliquely angled relative to one another.

16. The structural component of claim 15, comprising:

the composite tapered wing spar having a second fiber layer made up of a plurality of plies, wherein the plies of the second layer have respective longitudinal axes that are straight, wherein a first ply of the plurality of plies of the second layer is effectively parallel to a respective direction of extension of one of the flanges at a first transition zone of the one flange and web, wherein a second ply of the plurality of plies of the second layer is effectively parallel to a respective direction of extension of the other of the flanges at a second transition zone of the other flange and web, and wherein most plies of the plurality of plies of the second layer located between the first ply and the second ply extend at respective oblique angles relative to one another and to the direction of extension of the first ply and the second ply.

17. The structural component of claim 15, comprising:

the composite tapered wing spar having a second fiber layer made up of a plurality of plies, wherein the plies of the second layer have respective longitudinal axes that are straight, wherein a first ply of the plurality of plies of the second layer is effectively parallel to a respective direction of extension of one of the flanges at a first transition zone of the one flange and web, wherein a second ply of the plurality of plies of the second layer is effectively parallel to a respective direction of extension of the other of the flanges at a second transition zone of the other flange and web, and wherein at least most plies of the plurality of plies of the second layer located between the first ply and the second ply extend at effectively the same oblique angle relative to one another and to the direction of extension of the first ply and the second ply.

18. The structural component of claim 15, comprising:

the composite tapered wing spar having a second fiber layer made up of a plurality of plies, wherein the plies have respective longitudinal axes that are straight, wherein a first ply of the plurality of plies of the second layer is effectively parallel to a respective direction of extension of one of the flanges at a first transition zone of the one flange and web, wherein a second ply of the plurality of plies of the second layer is effectively parallel to a respective direction of extension of the other of the flanges at a second transition zone of the other flange and web, and wherein almost all plies of the plurality of plies of the second layer located between the first ply and the second ply extend at respective oblique angles to one another and to the direction of extension of the first ply and the second ply.

19. The structural component of claim 15, wherein the wing spar has a second fiber layer made up of a plurality of plies, wherein the plies of the second fiber layer have first plies that extend a full length of the spar and second plies that extend a partial length of the spar, wherein the first and second plies are generally uniformly dispersed relative to location in the chord wise direction of the spar.

20. The structural component of claim 15, wherein the plies of the first layer extend in a curve across the web from a first flange to the second flange.

21. The structural component of claim 15, wherein the composite tapered wing spar has a second fiber layer made up of oblique angle plies having local directional components that are oblique to respective local directional components of the plies of the first layer.

22. The structural component of claim 16, wherein the composite tapered wing spar has a third fiber layer made up of oblique degree plies having local directional components that are oblique to respective local directional components of the plies of the second layer.

24. An aircraft, comprising:

a wing, including a wing spar corresponding to the structural component of claim 15.