Laminate sandwich panel

1. A laminated structure comprising:

a front facesheet;

a rear facesheet; and

a core arrangement disposed between the front facesheet and the rear facesheet; wherein

the core arrangement is bonded to the front facesheet by curing a first adhesive joint, the front facesheet forming a front facing surface, and bonded to the rear facesheet by curing a second adhesive joint, the rear facesheet forming a rear facing surface, the first adhesive joint and the second adhesive joint being concurrently cured (co-cured) under pressure;

the core arrangement includes a plurality of ribs, the ribs disposed so as to form walls defining a reticulated lattice of cells;

the ribs have a thickness in a first direction and a height in a second direction approximately orthogonal to the facesheets and to the first direction that extends between the first adhesive joint and the second adhesive joint, the height being at least 100× larger than the thickness;

each cell has three or more walls, each wall formed by a different one of the plurality of ribs, each rib forming a respective wall of at least two different ones of the cells;

the ribs are disposed approximately (a) at right angles, so as to form cells having an approximately rectangular cross section, or (b) in a triaxial arrangement, so as to form cells having a triangular cross section;

and

one or more of the ribs include a dimpled or corrugated surface for increased resistance to buckling loads.

2. The laminated structure of claim 1 , wherein:

each rib has a first edge surface facing the front facesheet and a second edge surface facing the rear facesheet; and

one or both of the first adhesive joint and the second adhesive joint are formed by:

reticulating a first film adhesive over the first edge surfaces;

reticulating a second film adhesive over the second edge surfaces; and

concurrently curing an assembly of the core arrangement coupled with the front facesheet by the first reticulated film adhesive and coupled with the rear facesheet by the second reticulated film adhesive.

3. The laminated structure of claim 2 , wherein reticulating one or both of the first film adhesive and the second film adhesive includes:

disposing an adhesive layer upon a facing surface of the core arrangement; and

heating one or both of the adhesive layer and the core arrangement.

4. The laminated structure of claim 2 , wherein curing the assembly includes encapsulating the assembly in a flexible enclosure impermeable to air and reducing a pressure interior to the flexible enclosure.

5. The laminated structure of claim 4 , wherein a pressure exterior to the flexible enclosure is one atmosphere or greater.

6. The laminated structure of claim 2 , wherein curing the assembly includes heating the assembly to an elevated temperature.

7. The laminated structure of claim 6 , wherein the elevated temperature is at least 300° F.

8. The laminated structure of claim 2 , wherein the first edge surface is not parallel to the second edge surface.

9. The laminated structure of claim 2 , wherein one or both of the first edge surface and the second edge surface are curved.

10. The laminated structure of claim 1 , wherein one or more of the ribs have a height that varies along a length in a third direction approximately orthogonal to the first direction and the second direction such that, when the ribs are assembled to form the core arrangement, the front facing surface and the rear facing surface are independently shaped to distinctly different contours.

11. A spacecraft comprising:

a laminated structure configured as an equipment panel, a solar array panel or an antenna reflector, the laminated structure including:

a front facesheet;

a rear facesheet; and

a core arrangement disposed between the front facesheet and the rear facesheet, the core arrangement adhered to the front facesheet by a first adhesive joint, the front facesheet forming a front facing surface, and adhered to the rear facesheet by a second adhesive joint, the rear facesheet forming a rear facing surface; wherein

the core arrangement includes a plurality of ribs, the ribs disposed so as to form walls defining a reticulated lattice of cells;

the ribs have a thickness in a first direction and a height in a second direction approximately orthogonal to the facesheets and to the first direction that extends between the first adhesive joint and the second adhesive joint, the height being at least 100× larger than the thickness;

each cell has three or more walls, each wall formed by a different one of the plurality of ribs, each rib forming a respective wall of at least two different ones of the cells;

the ribs are disposed approximately (a) at right angles, so as to form cells having an approximately rectangular cross section, or (b) in a triaxial arrangement, so as to form cells having a triangular cross section;

the first adhesive joint and the second adhesive joint are concurrently cured under pressure; and

one or more of the ribs include a dimpled or corrugated surface for increased resistance to buckling loads.

12. The spacecraft of claim 11 , wherein:

each rib has a first edge surface facing the front facesheet and a second edge surface facing the rear facesheet; and

one or both of the first adhesive joint and the second adhesive joint are formed by:

reticulating a first film adhesive over the first edge surfaces;

reticulating a second film adhesive over the second edge surfaces; and

concurrently curing an assembly of the core arrangement coupled with the front facesheet by the first reticulated film adhesive and coupled with the rear facesheet by the second reticulated film adhesive.

13. The spacecraft of claim 12 , wherein reticulating one or both of the first film adhesive and the second film adhesive includes:

disposing an adhesive layer upon a facing surface of the core arrangement; and

heating one or both of the adhesive layer and the core arrangement.

14. The spacecraft of claim 11 , wherein one or more of the ribs have a height that varies along a length in a third direction approximately orthogonal to the first direction and the second direction such that, when the ribs are assembled to form the core arrangement, the front facing surface and the rear facing surface are independently shaped to distinctly different contours.

15. A method of fabricating a laminated structure, the method comprising:

bonding a core arrangement to a front facesheet by curing a first adhesive joint; and

bonding the core arrangement to a rear facesheet by curing a second adhesive joint, wherein:

the first adhesive joint and the second adhesive joint are concurrently cured (co-cured) under pressure;

the core arrangement is disposed between the front facesheet and the rear facesheet, the core arrangement including a plurality of ribs, the ribs disposed so as to form walls defining a reticulated lattice of cells;

each cell has three or more walls, each wall formed by a different one of the plurality of ribs, each rib forming a respective wall of at least two different ones of the cells;

the ribs are disposed approximately (a) at right angles, so as to form cells having an approximately rectangular cross section, or (b) in a triaxial arrangement, so as to form cells having a triangular cross section;

the ribs have a thickness in a first direction and a height in a second direction approximately orthogonal to the facesheets and to the first direction that extends between the first adhesive joint and the second adhesive joint, the height being at least 100× larger than the thickness; and

one or more of the ribs include a dimpled or corrugated surface for increased resistance to buckling loads.

16. The method of claim 15 , wherein:

each rib has a first edge surface facing the front facesheet and a second edge surface facing the rear facesheet; and

the first adhesive joint and the second adhesive joint are formed by:

reticulating a first film adhesive over the first edge surfaces;

reticulating a second film adhesive over the second edge surfaces; and

concurrently curing an assembly of the core arrangement coupled with the front facesheet by the first reticulated film adhesive and coupled with the rear facesheet by the second reticulated film adhesive.

17. The method of claim 16 , wherein curing the assembly includes encapsulating the assembly in a flexible enclosure impermeable to air and reducing a pressure interior to the flexible enclosure.

18. The method of claim 16 , wherein curing the assembly includes heating the assembly to an elevated temperature.

19. The method of claim 16 , wherein one or both of the first edge surface and the second edge surface is curved.

20. The method of claim 15 , wherein one or more of the ribs have a height that varies along a length in a third direction approximately orthogonal to the first direction and the second direction such that, when the ribs are assembled to form the core arrangement, the front facing surface and the rear facing surface are independently shaped to distinctly different contours.