1. Figure 1 – NSTX Upper Umbrella Assembly Upgrade Design: Version 3

2. Figure 2 – Single Segment Strap Assembly Version 3 with G10/ 304 SS Supports G10 Support 304 SS Support

3. Figure 3 – Single Segment Strap Assembly: Center Strap Only

4. B tor = 1 T I = 130 kA B pol =.3 T U rad thermal =.018 in U vert thermal =.3 in 38 Laminations: -.060” thk;.005” gap Mat’l: Copper Wt full = 37.4 lb (Wt arch = 20.4 lb) 2” 2.523” 7.5” R in = 3.160” R out = 5.688” 5” Figure 4 – Single Laminated Strap Assembly with Applied Fields and Current

5. x x x x x x x x x x x x x x x x x x Out-of-Plane Load (z-direction) F op = 2*I*B pol *R F op = 2 x 130,000 A/ 38 x.3 T x 5.688/39.37 m F op = 296.4 N = 66.6 lbf [per lamination] In-Plane Load (y-direction) F ip / L = I*B tor F ip / L = 130,000 A/ 38 x 1 T [per lamination] F ip / L = 3,421 N/ m x.2248 lbf/ N x 1 m/ 39.37 in F ip / L = 19.53 lbf/ in press ip = (F ip / L)/ w press ip = 19.53 lbf/in / 2 in press ip = 9.77 lbf/ in 2 (applied to inside cylindrical faces) Calculated EMAG Loads B pol B tor I+I+ I+I+ R w F op press ip

6. Figure 5A – Single Lamination FEA Model: Mesh and Boundary Conditions 3 Elements thru Thickness Ux =.018 in Uy =.3 in Uz = 0 Press = 9.7 psi Force = 66.6 lbf Fixed

7. Figure 5B – Single Lamination Linear Results: von Mises Stress Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

8. Figure 5C – Single Lamination Linear Results: von Mises Stress Loads: Thermal Displacements Only

9. Figure 5D – Single Lamination Linear Results: von Mises Stress Loads: In-Plane (Pressure) Load Only

10. Figure 5E – Single Lamination Linear Results: von Mises Stress Loads: Out-of-Plane (Force) Load Only

11. Large deflection = On Figure 5F – Single Lamination Nonlinear Results: von Mises Stress Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

13. Baseline-Design MathCAD Flex Strap Lamination Analysis: Conclusions/ Recommendations ~3/4 overall stiffness due to Inner Strap Assy OOP torsional stress dominates in Outer Strap Assy; thermal displacement bending dominates in Inner Strap Assy OOP force proportional to radius Thermal displacement bending stress inversely proportional to radius Deflection force inversely proportional to radius Proposed Design: –Outer Assy: 12X.090” thick, 2.0” wide laminations –Inner Assy: 19X.060” thick, 2.0” wide laminations –Mat’l: Fully-hardened Cu-Zr

14. Baseline Design Proposed Design ASM International, “Atlas of Stress-Strain Curves”, Electrolytic Tough-Pitch Copper (C11000) Figure 5G – Copper Stress-Strain Curves versus % Cold Work Baseline Design and Proposed Design Combined-Load Stresses Shown

15. Baseline Design Proposed Design NIST Monograph 177, “Properties of Copper and Copper Alloys at Cryogenic Temperatures” Figure 5H – Copper Fatigue S-N Curves versus % Cold Work Baseline Design and Proposed Design Combined-Load Stresses Shown

16. Figure 5J – Single Lamination Nonlinear Results: Z-Deformations Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP) Large deflection = On

17. Figure 5K – Single Lamination Nonlinear Results: Z-Deformations_Front Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP) Large deflection = On

18. Figure 5L – Single Lamination Nonlinear Results: von Mises Stress Loads: Emag Pressure (In Plane) Only Large deflection = On σ hoop = P*R/ t = 9.77 psi x 5.688 in/.060 in = 924 psi

19. Figure 5M – Single Lamination Pre-Stressed Linear Buckling Results Load multiplier LMF applies to all Emag loads and thermal displacements 1 st Mode Load Multiplier = 58.4 2 nd Mode Load Multiplier = 73.0 3 rd Mode Load Multiplier = 117.6 Large deflection = Off 1 st Mode Load Multiplier = 58.4 (Nonlinear 1 st Mode Load Multiplier = 50)

20. Figure 5N – Single Lamination Nonlinear Buckling: Y-Deformation at Onset (1) Load multiplier factor LMF applies only Out-of-Plane Emag load Large deflection = On Y 080 LMF = 14

21. Figure 5P – Single Lamination Nonlinear Buckling: Y-Deformation at Onset (2) Load multiplier factor LMF applies only to Out-of-Plane Emag load Large deflection = On LMF = 26 Y 080

22. Conclusions Buckling due mostly to out-of-plane load. In- plane load (pressure outward) reduces buckling; thermal displacements slightly increase buckling. Good agreement between linear and nonlinear buckling results with load multiplier factor applied to both Emag loads and to thermal displacements. Load multiplier factor over 14 for nonlinear analysis with constant in-plane load and increasing out-of-plane load (conservative).

23. Figure 6A – 3 Lamination FEA Model: Mesh 3 Elements / Lamination

24. Large deflection = On Frictional contact (COF =.4) Figure 6B – 3 Lamination Nonlinear Results: von Mises Stress Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

25. Figure 6C – 3 Lamination Nonlinear Results: Z-Deformations Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP) Large deflection = On Frictional contact (COF =.4)

26. Figure 6D – 3 Lamination Nonlinear Results: Z-Deformations_Front Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP) Large deflection = On Frictional contact (COF =.4)

27. Figure 6E – 3 Lamination Nonlinear Results: Contact Status Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP) Large deflection = On Frictional contact (COF =.4)

28. Figure 6F – 3 Lamination Results: Linear Buckling Mode Multiplier Load Multiplier factor LMF applies to all Emag loads and thermal displacements Large deflection = Off Frictional contact (COF =.4) 1 st Mode Load Multiplier = 58.2 2 nd Mode Load Multiplier = 60.7 3 rd Mode Load Multiplier = 61.8

29. Figure 7A – Single Laminated Strap Assembly FEA Model: Bonded and Frictionless Contact Areas

30. 3 elements/ lamination Figure 7B – Single Laminated Strap Assembly FEA Model: Mesh # Nodes = 850423 # Elements = 152895

31. Fig. 7C –Laminated Strap Assembly FEA Results - Thermal Displacements Only: von Mises Stress Large deflection = Off Frictional contact (COF = 0)

32. Fig. 7D –Laminated Strap Assembly FEA Results – Thermal Displacements Only: Total Deformation Large deflection = Off Frictional contact (COF = 0)

33. T nodes Heat Gen JS F Lorentz B y =.3T B z = 1 T I = 130 kA Non-Linear Large Deflection Non-Linear Large Deflection Fig. 8A – Upper Flex Strap ANSYS Multiphysics Analysis Work Flow Diagram u x =.018” u y =.30”

34. Figure 8B – Single Segment_Center Strap Assembly: Mesh

35. Fig. 8C – Single Segment_Center Strap Assembly: von Mises Stress_Iso-View

36. Fig. 8D – Single Segment_Center Strap Assembly: von Mises Stress_Side View

37. Figure 8E – Single Segment_Center Strap Assembly: Joint Contact Pressure

38. Figure 8F – Single Segment_Center Strap Assembly: Thread Stress

39. Figure 9A – Strap-to-E Beam Joint Analysis: Solid Model

40. Figure 9B – Strap-to-E Beam Joint Analysis: Full-Load von Mises Stress

41. Figure 9C– Strap-to-E Beam Joint Analysis: Maximum Shear Stress Full-LoadPretension

42. Figure 9D – Strap-to-E Beam Joint Analysis: Contact Pressure Full Load PressureBolt Pretension-Only Pressure

43. Figure 9E – Strap-to-E Beam Joint Analysis: Contact Status Bolt Pretension-Only StatusFull Load Status

44. Figure 10A – Strap-to-TF Coil Outer Leg Joint: Solid Model

45. Figure 10B – Strap-to-TF Coil Outer Leg Joint Analysis: Full-Load Stress

46. Figure 10C – Strap-to-TF Coil Outer Leg Joint Analysis: Contact Pressure Full Load PressureBolt Pretension-Only Pressure

47. Fig. 10D – Strap-to-TF Coil Outer Leg Joint: TF Leg-Only Contact Pressure Full Load PressureBolt Pretension-Only Pressure

48. Figure 10E – Strap-to-TF Coil Outer Leg Joint Analysis: Contact Status Bolt Pretension-Only StatusFull Load Status

49. Fig. 11A – Single Segment_Center Strap Electric Model: Boundary Conditions 130,000 A 0 V

50. Figure 11B – Single Segment_Center Strap Electric Model Results: Voltage

51. Fig. 11C – Single Segment_Center Strap Electric Model Results: Current Density

52. Fig. 11D – Single Segment_Center Strap Electric Model Results: Joule Heat

66. Shear Key Copper Threads, Static Results (cont.) A-1 12,500lbs peak, 8 Threads A-2 12,620lbs peak, 8.5 Threads A-3 13,120lbs peak, 9 Threads A-4 12,500lbs peak, 8 Threads A-5 10,880lbs peak, 7 Threads A-6 12,380lbs peak, 8 Threads Correlation between pull out force and the number of threads pulled explains scatter By design shear key bolt will catch 8-9 threads