Strain Isolation Layer Assemblies and Methods

• US 20130104966A1
• Filed: 10/31/2011
• Published: 05/02/2013
• Est. Priority Date: 10/31/2011
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Grip, Robert Erik, Rawdon, Blaine Knight, Crooks, Tab Hunter, Stola, Michael F.
• Granted Patent: US 8,957,303 B2
• Time in Patent Office: Days
• US Class Current: 136/251
• CPC Class Codes: B64D 27/353 using solar cells
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/34 In-flight charging photovoltaics B64U50/31
• CPC Class Codes: H01L 31/042 PV modules or arrays of single PV cells supporting structures for PV modules H02S20/00
• CPC Class Codes: H02S 10/40 Mobile PV generator systems
• CPC Class Codes: H02S 20/00 Supporting structures for PV modules
• CPC Class Codes: Y02B 10/20 Solar thermal
• CPC Class Codes: Y02E 10/50 Photovoltaic [PV] energy
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

In an embodiment of the disclosure, there is provided a strain isolation layer assembly. The assembly has a rigid solar layer; a strain isolation layer having a discontinuous configuration, a vertical rigidity, and a horizontal shear flexibility; and an underlying substrate layer. The strain isolation layer is coupled between the rigid solar layer and the underlying substrate layer to form a strain isolation layer assembly, such that the strain isolation layer isolates the rigid solar layer to reduce one or more strains induced on the rigid solar layer.

Claims

1. A strain isolation layer assembly comprising:

a rigid solar layer;

a strain isolation layer having a discontinuous configuration, a vertical rigidity, and a horizontal shear flexibility; and

,

an underlying substrate layer;

wherein the strain isolation layer is coupled between the rigid solar layer and the underlying substrate layer to form a strain isolation layer assembly, such that the strain isolation layer isolates the rigid solar layer to reduce one or more strains induced on the rigid solar layer.

2. The assembly of claim 1 further comprising an added layer coupled between the rigid solar layer and the strain isolation layer.

3. The assembly of claim 2 wherein the added layer comprises a core layer and one or more facesheet layers.

4. The assembly of claim 1 wherein the rigid solar layer is first coupled to an added layer to form a sandwich structure, and the sandwich structure is coupled to the strain isolation layer.

5. The assembly of claim 1 wherein the rigid solar layer is selected from a group comprising one or more solar panels, one or more solar cells, a solar panel array comprising one or more solar modules of solar cells, and a solar panel laminated assembly.

6. The assembly of claim 1 wherein the rigid solar layer has a thickness in a range of from about 0.006 inch to about 0.030 inch.

7. The assembly of claim 1 wherein the strain isolation layer is selected from a group comprising a perforated foam strain isolation layer, a column support strain isolation layer, a hinged support strain isolation layer, a foam blade support strain isolation layer, a looped fiber strain isolation layer, and a sliced foam strain isolation layer.

8. The assembly of claim 1 wherein the vertical rigidity of the strain isolation layer stabilizes the rigid solar layer to resist compressive buckling and wrinkling.

9. The assembly of claim 1 wherein the strain isolation layer has a shear modulus of about 0.03 psi (pounds per square inch) to about 1 psi (pounds per square inch).

10. The assembly of claim 1 wherein the horizontal shear flexibility reduces a structural strain and a thermal strain between the underlying substrate layer and the rigid solar layer.

11. The assembly of claim 1 wherein the underlying substrate layer is a structure selected from a group comprising an aircraft, a spacecraft, a satellite, a space station, a rotorcraft, a watercraft, an automobile, a truck, a bus, and an architectural structure.

12. The assembly of claim 1 wherein the one or more strains is selected from a group comprising a mechanical strain selected from a group comprising a compressive strain, a tensile strain and a torsional strain;

and a thermal strain comprising a differential thermal expansion strain relating to coefficients of thermal expansion.

13. An aircraft comprising:

a strain isolation layer having a discontinuous configuration, a vertical rigidity, and a horizontal shear flexibility;

the strain isolation layer joining a rigid solar layer to a surface of a flexible aircraft wing, such that the strain isolation layer isolates the rigid solar layer to reduce one or more strains induced on the rigid solar layer.

14. The aircraft of claim 13 further comprising an added layer coupled between the rigid solar layer and the strain isolation layer.

15. The aircraft of claim 13 wherein the rigid solar layer is selected from a group comprising one or more solar panels, one or more solar cells, a solar panel array comprising one or more solar modules of solar cells, and a solar panel laminated array.

16. The aircraft of claim 13 wherein the strain isolation layer is selected from a group comprising a perforated foam strain isolation layer, a column support strain isolation layer, a hinged support strain isolation layer, a foam blade support strain isolation layer, a looped fiber strain isolation layer, and a sliced foam strain isolation layer.

17. The aircraft of claim 13 wherein the strain isolation layer has a shear modulus of about 0.03 psi (pounds per square inch) to about 1 psi (pounds per square inch).

18. The aircraft of claim 13 wherein the one or more strains is selected from a group comprising a mechanical strain selected from a group comprising a compressive strain, a tensile strain and a torsional strain;

and a thermal strain comprising a differential thermal expansion strain relating to coefficients of thermal expansion.

19. A method of reducing one or more strains on a rigid solar layer, the method comprising:

providing a strain isolation layer having a discontinuous configuration, a vertical rigidity, and horizontal shear flexibility; and

,

attaching the strain isolation layer between a rigid solar layer and an underlying substrate layer, such that the strain isolation layer isolates the rigid solar layer to reduce one or more strains induced on the rigid solar layer.

20. The method of claim 19 further comprising attaching an added layer between the strain isolation layer and the rigid solar layer.

21. The method of claim 19 wherein the rigid solar layer is selected from a group comprising one or more solar panels, one or more solar cells, a solar panel array comprising one or more solar modules of solar cells, and a solar panel laminated array.

22. The method of claim 19 wherein the strain isolation layer is selected from a group comprising a perforated foam strain isolation layer, a column support strain isolation layer, a hinged support strain isolation layer, a foam blade support strain isolation layer, a looped fiber strain isolation layer, and a sliced foam strain isolation layer.

23. The method of claim 19 wherein the strain isolation layer has a shear modulus of about 0.03 psi (pounds per square inch) to about 1 psi (pounds per square inch).

24. The method of claim 19 wherein the one or more strains is selected from a group comprising a mechanical strain selected from a group comprising a compressive strain, a tensile strain and a torsional strain;

and a thermal strain comprising a differential thermal expansion strain relating to coefficients of thermal expansion.