Square symmetric double-double laminate structures and methods for manufacturing and using the same

Patent metadata

Field	Value
Publication number	US-11904589-B2
Application number	US-202217864505-A
Country	US
Kind code	B2
Filing date	Jul 14, 2022
Priority date	Jul 15, 2021
Publication date	Feb 20, 2024
Grant date	Feb 20, 2024

Abstract

Square symmetric composite laminate structures, and sub-modules thereof, are provided, along with methods of forming the same. The square symmetric laminate structures include two or more sub-laminate modules, each comprising: a first ply set consisting of a first ply layer oriented at a first angle and a second ply layer oriented at a second angle, a first sum of the first and second angles being ninety degrees; and a second ply set consisting of a third ply layer oriented at a third angle and a fourth ply layer oriented at a fourth angle, a second sum of the third and fourth angles being ninety degrees; wherein the second ply layer is positioned adjacent the third ply layer and the second and third ply layers are both positioned intermediate the first and fourth ply layers, thereby defining a double-double helix arrangement of the respective ply layers. Associated methods are also provided.

First claim

The invention claimed is:

1. A sub-laminate module comprising:
a first ply set consisting of a first ply layer oriented at a first angle and a second ply layer oriented at a second angle, a first sum of the first and second angles being ninety degrees; and
a second ply set consisting of a third ply layer oriented at a third angle and a fourth ply layer oriented at a fourth angle, a second sum of the third and fourth angles being ninety degrees;
wherein the second ply layer is positioned adjacent the third ply layer and the second and third ply layers are both positioned intermediate the first and fourth ply layers, thereby defining a double-double helix arrangement of the respective ply layers.

2. The sub-laminate module of claim 1 , wherein the first and second angles are different than the third and fourth angles, respectively.

3. The sub-laminate module of claim 1 , wherein in-plane shear coupling is zero.

4. The sub-laminate module of claim 1 , wherein the first ply set has a layup of [Φ/(π/2−Φ)] and the second ply set has a layup of [−Ψ/−(π/2−Ψ)].

5. The sub-laminate module of claim 4 , wherein [Φ+Ψ]=90° and Φ≠Ψ.

6. The sub-laminate module of claim 5 , wherein either Φ=0° and Ψ=90° or Φ=90° and Ψ=0°.

7. The sub-laminate module of claim 5 , wherein Φ lies in a range of 60°-75° and Ψ lies in a range of 15°-30°.

8. The sub-laminate module of claim 5 , wherein the layup is either [±30/±60] or [±60/±30].

9. The sub-laminate module of claim 5 , wherein the layup is either [±15/±75] or [±75/±15].

10. The sub-laminate module of claim 4 , wherein Φ=Ψ.

11. The sub-laminate module of claim 10 , wherein Φ and Ψ=45°.

12. The sub-laminate module of claim 11 , wherein in-plane shear coupling is zero.

13. The sub-laminate module of claim 1 , wherein the first ply set has a layup of [Φ/(π/2−Φ)]+π/4 and the second ply set has a layup of [−Ψ/−(π/2−Ψ)]+π/4.

14. The sub-laminate module of claim 13 , wherein either: [Φ+Ψ]=90° and Φ≠Ψ; or Φ=Ψ.

15. A composite laminate structure comprising:
two or more sub-laminate modules of claim 1 ,
wherein:
in each of the two or more sub-laminate modules the first and second angles are different than the third and fourth angles, respectively; and
the first, second, third, and fourth angles are each different across the two or more sub-laminate modules.

16. The composite structure of claim 15 , wherein:
a first of the two or more sub-laminate modules the first ply set has a layup of [Φ/(π/2−Φ)] and the second ply set has a layup of [−Ψ/−(π/2−Ψ)]; and
a second of the two or more sub-laminate modules the first ply set has a layup of [Φ/(π/2−Φ)]+π/4 and the second ply set has a layup of [−Ψ/−(π/2−Ψ)]+π/4.

17. The composite structure of claim 16 , wherein the first sub-laminate module layup is [±30/±60] and the second sub-laminate module layup is [±75/±105].

18. The composite structure of claim 15 , wherein thermal expansion coefficients of the two or more sub-laminate modules are equalized.

19. A wing skin comprising the composite structure of claim 15 .

20. A method of forming a square symmetric composite laminate structure, the method comprising the steps of:
forming a first ply layer by dispensing a first set of first elongate tapes oriented in a first direction and a second set of second elongate tapes oriented in a second direction, a first sum of the first and second directions being 90 degrees, and
forming a second ply layer by dispensing a third set of first elongate tapes oriented in a third direction and a fourth set of second elongate tapes oriented in a fourth direction, a second sum of the third and fourth directions being 90 degrees,
wherein:
the first and second directions are different than the third and fourth directions, respectively;
the first ply layer has a layup of [Φ/(π/2−Φ)] and the second ply layer has a layup of [−Ψ/−(π/2−Ψ)]; and
the second elongate tape is positioned adjacent the third elongate tape and the second and third elongate tapes are both positioned intermediate the first and fourth elongate tapes, thereby defining a double-double helix arrangement of the respective elongate tapes forming the first and second ply layers.

Assignees

• Univ Leland Stanford Junior

Inventors

• Tsai Stephen W
• Wang Dan
• Miravete Antonio

Classifications

• B32B38/1808 Primary

  characterised by the laying up of the layers · CPC title

• B32B7/022

  Mechanical properties · CPC title

• B32B7/027

  Thermal properties · CPC title

• B32B7/03

  with respect to the orientation of features (direction of fibres or filaments B32B5/12) · CPC title

• B32B38/1833

  Positioning, e.g. registration or centering · CPC title