Thermoplastic skin panels, torque box and method

1. A stiffened skin panel assembly, comprising:

a panel including inner and outer facesheets, and a panel core sandwiched between the inner and outer facesheets, the panel core including alternating sections of truss core portions and solid laminate portions arranged side-by-side and contact with each other edge-to-edge, wherein the truss core portions are tapered in thickness along the edge-to-edge contact; and

spars respectively attached to the solid laminate portions.

2. The stiffened skin panel assembly of claim 1 , wherein:

the spars include flanges;

the solid laminate portions form spar caps aligned with the flanges; and

the stiffened skin panel assembly further includes fasteners extending through the flanges and the spar caps.

3. The stiffened skin panel assembly of claim 1 , wherein each of the solid laminate portions is a fiber reinforced thermoplastic.

4. The stiffened skin panel assembly of claim 1 , wherein each of the truss core portions is a fiber reinforced thermoplastic.

5. The stiffened skin panel assembly of claim 1 , wherein each of the truss core portions includes a top chord, a bottom chord and a plurality of webs connecting the top chord with the bottom chord.

6. The stiffened skin panel assembly of claim 5 , wherein the webs extend parallel to the spars.

7. The stiffened skin panel assembly of claim 1 , wherein the outer facesheet is a fiber reinforced thermoplastic forming an outer skin of the panel.

8. The stiffened skin panel assembly of claim 1 , wherein the inner and outer facesheets and the panel core are a consolidated thermoplastic.

9. The stiffened skin panel assembly of claim 1 , wherein each of the inner facesheet and the outer facesheet extends continuously across the alternating sections of the truss core portions and solid laminate portions.

10. A wing torque box, comprising:

first and second skin panel assemblies; and

at least two spaced apart spars extending between the first and second skin panel assemblies,

each of the first and second skin panel assemblies including respective inner and outer facesheets and a respective core sandwiched between the respective inner and outer facesheets,

each respective core including truss core portions and solid laminate portions, wherein each of the solid laminate portions forms a spar cap configured to be fastened to one of the spars.

11. The wing torque box of claim 10 , wherein each of the inner facesheet, the outer facesheet, and the core is a fiber reinforced thermoplastic.

12. The wing torque box of claim 10 , wherein each inner facesheet extends continuously over respective solid laminate portions and respective truss core portions.

13. The wing torque box of claim 12 , wherein each inner facesheet is disposed between the spars and respective solid laminate portions.

14. The wing torque box of claim 10 , wherein each of the truss core portions is a fiber reinforced thermoplastic and includes a top chord, a bottom chord and a plurality of webs connected between the top chord and the bottom chord.

15. The wing torque box of claim 14 , wherein:

each outer facesheet is a laminate forming an outer skin and overlies the top chord of respective truss core portions, and

the respective inner facesheet extends over the bottom chord of the respective truss core portions.

16. A method of making a stiffened skin panel assembly, comprising:

assembling a panel core by arranging alternating sections of thermoplastic truss core portions and thermoplastic laminate portions arranged side-by-side and contact with each other edge-to-edge, wherein the truss core portions are tapered in thickness along the edge-to-edge contact;

placing the panel core between a thermoplastic inner facesheet and a thermoplastic outer facesheet; and

co-consolidating the panel core, the thermoplastic inner facesheet and the thermoplastic outer facesheet.

17. The method of claim 16 , further comprising:

laying up each of the thermoplastic truss core portions; and

pre-consolidating the thermoplastic truss core portions before assembling the panel core.

18. The method of claim 16 , wherein arranging the alternating sections includes placing the thermoplastic truss core portions in face-to-face contact with the thermoplastic outer facesheet across an entire area of the thermoplastic truss core portions.

19. The method of claim 16 , wherein the co-consolidating includes:

placing the panel core, the thermoplastic inner facesheet, and the thermoplastic outer facesheet in a set of dies, and

heating the dies to a consolidation temperature using smart susceptors.

20. The method of claim 16 , further comprising:

fastening a spar to each of the thermoplastic laminate portions.