ML18117A369
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TMI-1 UFSAR APPENDIX 5A 5A-i REV. 18, APRIL 2006 APPENDIX 5A GILBERT ASSOCIATES, INC., REPORT TO METROPOLITAN EDISON COMPANY ON
SUMMARY
OF AIRCRAFT IMPACT DESIGN FOR THREE MILE ISLAND NUCLEAR STATION UNIT 1 This Report Contains:
5 pages of text 7 tables 42 figures
TMI-1 UFSAR APPENDIX 5A 5A-ii REV. 18, APRIL 2006 TABLE OF CONTENTS SECTION TITLE 1
INTRODUCTION 2
DYNAMIC LOAD FACTORS 3
ANALYSIS 3.1 SHELL ANALYSIS 3.1.1 APEX OF THE DOME 3.1.1.1 ANALYSIS FOR CASE A & B IMPACT LOADINGS 3.1.1.1.1 STRUCTURAL RESPONSE 3.1.1.1.2 LOCAL MATERIAL FAILURE 3.1.1.2 ANALYSIS FOR CASE C IMPACT LOADING 3.1.1.3 ANALYSIS FOR CASE D IMPACT LOADING 3.1.2 DOME TO GIRDER TRANSITION 3.1.3 GIRDER TO CYLINDER TRANSITION (SPRING LINE) 3.1.4 IMPACT AT GRADE 3.2 PLATE ANALYSIS 3.2.1 FUNDAMENTAL FREQUENCY 3.2.2 FINITE-ELEMENT ANALYSIS FOR SLABS 3.2.3 DESIGN CRITERIA FOR REINFORCING 3.2.4 DESIGN CHECK 4
ADDITIONAL DETAIL STUDIES 4.1 BEARING FAILURE OF CONCRETE UNDER DIRECT IMPACT 4.2 SHEAR-OFF THE ANCHORS 4.2.1 CASE A: SHEAR-OFF THE ANCHORS OF VERTICAL TENDONS 4.2.2 CASE B: SHEAR-OFF THE ANCHORS OF DOME TENDONS 4.2.3 CASE C: SHEARING-OFF THE HOOP TENDONS 4.3 SPALLING DUE TO AIRCRAFT IMPACT ON THE OUTSIDE WALLS 4.4 IMPACT EFFECTS ON EQUIPMENT AND COMPONENTS
4.5 REFERENCES
TMI-1 UFSAR APPENDIX 5A 5A-iii REV. 18, APRIL 2006 LIST OF TABLES TABLE TITLE 5A-1 Time Variable tn 5A-2 Dynamic Load Factors (DLF) 5A-3 Kinetic Energy of The Dome 5A-4 Upper Bound Displacements 5A-5 Comparison of The Stress Resultants for Prestress Loadings 5A-6 Reactor Load (R) Calculations Case 1: With Wings and Engines Detached 5A-7 Reactor Load (R) Calculations Case 2: With Wings and Engines Attached
TMI-1 UFSAR APPENDIX 5A 5A-iv REV. 18, APRIL 2006 LIST OF FIGURES FIGURE TITLE 5A-1 Total Reaction Vs Time Curve 5A-2 Load Time Curve For 720 Aircraft At 200 Knots 5A-3 Maximum Dynamic Load Factor Vs Period or Frequency Of A One-Degree-Freedom System Under the Impact of Boeing 720 5A-4 Spherical Cap Under A Ring Load 5A-5 Spacial And Time Distribution of Load On Shell 5A-6 Grid For Dynamic Finite-Element Analysis of Aircraft Impingement on Dome 5A-7 Effect of Aircraft Impingement On Dome of Containment Structure - Constant Deceleration 5A-8 Deflections and Stresses For Aircraft Impingement for Time = 0.16 Seconds -
Constant Deceleration 5A-9 Velocity Diagram For 720 Aircraft at 200 Knots Impact Speed with Wings and Engines Detached 5A-10 Velocity Diagram For 720 Aircraft at 200 Knots Impact Speed with Wings and Engines Attached 5A-11 720 Aircraft Mass Distribution 5A-12 Boeing - 720 Fuselage Buckling (Crushing) Load 5A-13 Time Variation of Shell Vertical Displacements with Wings and Engines Detached 5A-14 Time Variation of Shell Vertical Displacement with Wings and Engines Attached 5A-15 Time Variation of Shell Surface Stresses Aircraft with Wings and Engines Detached 5A-16 Time Variation of Shell Surface Stresses Aircraft with Wings and Engines Attached 5A-17 Pressure Distribution For Aircraft Impact 5A-18 Aircraft Impact At Girder to Dome Transition 5A-19 Aircraft Impact At Spring Line 5A-20 Radial Deflection Impact At Spring Line
TMI-1 UFSAR LIST OF FIGURES (cont'd)
FIGURE TITLE APPENDIX 5A 5A-v REV. 18, APRIL 2006 5A-21 Aircraft Impact At Grade 5A-22 Rectangular Finite-Element 5A-23 For The Roof Slab Heat Exchanger Vault Moment Diagram 5A-24 DELETED 5A-25 DELETED 5A-26 Critical Aircraft Impact-Direction 1 5A-27 Concrete Cover to Protect Against Aircraft Impact 5A-28 Detail of Anchor Block 5A-29 Prestress Stresses After Nine Tendons Fail 5A-30 Critical Aircraft Impact-Directions 2 and 3 5A-31 Equal Spacing of Roof Tendons 5A-32 Dome Tendons 5A-33 Minimum Spacing of Hoop Tendons 5A-34 Comparison of Prestress Loading 5A-35 Reaction Load and Fuselage Decel. (with Wings and Engines Detached) 5A-36 Reaction Load and Fuselage Decel. (with Wings and Engines Attached) 5A-37 Hoop and Meridional Stresses at 36 Inches from the Edge of the Loaded Area 5A-38 Average Shear Stress in the Dome at time + = 0.20 seconds.Wing and Engines Remain Attached to Fuselage 5A-39 Average Shear Stress in the Dome at time + = 0.20 seconds. Wing and Engines Remain Detached to Fuselage 5A-40 FEM Model - Radial Stresses Due to Prestress and Aircraft Impact 5A-41 Radial Stresses Due to Prestress and Aircraft Impact 5A-42 Zones in Compression or Tension Due to Prestress or Aircraft Impact