Sea Launch User's Guide

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X PLU Roll II = 90 deg I = 0 deg O PLU la plane Yaw X US Pitch III = 180 deg Z PLU IV = 270 deg Y PLU Z US Y US O US Down during flight, up during launch preparations Z LV , Z US , Z PLU O LV , O US , O PLU X PLU = X US – 4000 mm X PLU = X LV – 44652 mm Y PLU = Y LV = Y US Z PLU = Z LV = Z US X LV Y LV , Y US , Y PLU VIEW A O LV Z LV A Y LV Figure 6-1. Zenit-3SL Coordinate System 265807J3-041R3 6-2 D688-10009-1 REV B
6.1 Mass and Center of Gravity (CG) Limits Definitive compatibility requiring multiple verification activities Several verification activities must be done to demonstrate Zenit-3SL compatibility with a specific spacecraft having a given mass and CG. These include • Coupled loads analysis. • Strength and controllability analyses. • Critical clearance analyses to assess volumetric constraints. • Performance calculations for the specific mission. • Peaking load calculations for spacecraft having a nonuniform interface stiffness. More information on spacecraft mass is presented in section 3.3. Current Zenit-3SL structural capability The Zenit-3SL launch vehicle can structurally accommodate spacecraft with a wide range of mass and CG for each of the three spacecraft adapters currently offered by <strong>Sea</strong> <strong>Launch</strong>. Table 6-1 provides the expected spacecraft mass and CG limits for the Zenit-3SL using a standard spacecraft adapter when the lateral load factor on the spacecraft is 2.0 g or less and the load distribution at the spacecraft interface is ideal. Definitive compatibility of a spacecraft with the Zenit-3SL requires all verification activities outlined above. In particular, peaking load calculations must be performed when the load distribution at the spacecraft interface is not ideal. REV B D688-10009-1 6-3
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SM® User’s Guide _______________
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TABLE OF CONTENTS 1. INTRODUCTION .
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Mission manager and team ..........
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6.2 Modal Frequencies..............
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Weather conditions ................
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11.2 Safety Assessment Phases......
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LIST OF FIGURES Page 1-1 Generic In
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8-16 Payload Unit Mating to the Zen
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ABBREVIATIONS AND ACRONYMS ACS ARS
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1. INTRODUCTION Purpose The purpose
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Milestones • Customer kickoff •
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Sea Launch Company Sea Launch Compa
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KB Yuzhnoye/PO Yuzhmash KB Yuzhnoye
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2. VEHICLE DESCRIPTION Overview The
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Table 2-1. Flight History Component
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RD-171 engine The RD-171 engine, wh
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Block DM-SL interface plane Liquid
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2.3 Block DM-SL—Upper Stage Confi
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Attitude control Three-axis stabili
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Spacecraft adapter Payload structur
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Cooling air From encapsulation to l
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3. PERFORMANCE Overview The Zenit-3
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20 N HAWAIIAN ISLANDS North Pacific
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Flight timeline Table 3-1 lists the
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Groundtrack Figure 3-3 shows the as
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Geosynchronous transfer orbit The Z
Page 53 and 54: Circular and elliptical orbits Figu
Page 55 and 56: High-energy and escape orbits Figur
Page 57 and 58: 3.5 Spacecraft Separation Separatio
Page 59 and 60: Mid 2002 6700 Planned future growth
Page 65 and 66: Planning Phase (Through SC Delivery
Page 67 and 68: 4.2 Mission Analysis and Operations
Page 69 and 70: SC/SLS ICD SC ICD verification plan
Page 71 and 72: Mission-specific documentation The
Page 73 and 74: Operations plan The operations plan
Page 75 and 76: 5.1 Transportation and Handling at
Page 77 and 78: Vertical Horizontal Horizontal 2658
Page 79 and 80: Base acceleration, g 1.2 1.0 0.8 0.
Page 81 and 82: 135 130 Sound pressure levels, dB 1
Page 83 and 84: SCA1666 The shock spectrum shown in
Page 85 and 86: 5.6 Electromagnetic Environment The
Page 87 and 88: Radiated environment There are six
Page 89 and 90: 200 180 160 140 Electric field, dB
Page 91 and 92: Ground processing and transportatio
Page 93 and 94: Ground processing and transportatio
Page 95 and 96: 1200 PLF separation 1000 Block DM M
Page 97 and 98: 120 100 Legend: Predicted internal
Page 99 and 100: Contamination control during ground
Page 101 and 102: Spacecraft isolation The spacecraft
Page 103: 6. SPACECRAFT DESIGN CONSIDERATIONS
Page 107 and 108: Table 6-2. Expected Spacecraft Mass
Page 109 and 110: 7000 6000 5000 Spacecraft mass, kg
Page 111 and 112: ■ Sea Launch RF Susceptibility 16
Page 113 and 114: 6.4 Spacecraft Design Verification
Page 115 and 116: Static loads test A spacecraft stat
Page 117 and 118: 6.5 Horizontal Handling Processing
Page 119 and 120: 7. INTERFACES 7.1 Mechanical Interf
Page 121 and 122: 360 deg 180 deg 331 deg 180 deg 360
Page 123 and 124: SCA702 and SCA702GEM The SCA702 has
Page 125 and 126: 7.2 Electrical Interfaces Overview
Page 127 and 128: Radio frequency link (rerad) A dire
Page 129 and 130: 8. SPACECRAFT INTEGRATION AND LAUNC
Page 131 and 132: Days 1 2 3 4 5 6 7 8 9 101112131415
Page 133 and 134: Figure 8-5. Fit Check on Adapter Su
Page 135 and 136: Payload mount assembly Flexure Inte
Page 137 and 138: 34 inches 688-95510-002 Scaffold as
Page 139 and 140: 265807J3-105 Figure 8-13. Payload U
Page 141 and 142: 8.2 Phase II⎯Mating to the LV and
Page 143 and 144: Figure 8-17. Integrated Launch Vehi
Page 145 and 146: 8.3 Phase III⎯Transit and Launch
Page 147 and 148: Launch rehearsals Two rehearsals ar
Page 149 and 150: Figure 8-23. Assembly and Command S
Page 151 and 152: Figure 8-24. Liftoff From the Launc
Page 153 and 154: 8.4 Flight Operations Range trackin
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Postlaunch reports Sea Launch provi
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■ Integrated LV Transfer to LP Pi
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265807J3-015R2 Figure 9-3. Home Por
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Encapsulation cell 15 m x 38 m (50
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Encapsulation cell The encapsulatio
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9.2 Assembly and Command Ship Funct
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Spacecraft checkout accommodations
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Capabilities Launch control center
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Customer office areas The two offic
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265807J3-128 Figure 9-15. Assembly
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■ Mess Hall ■ Coffee Bar ■ Ma
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Launch vehicle in launch position L
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Communications and access Telephone
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Communications Internal communicati
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Helicopter operations Sea Launch op
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10.2 Telemetry Assets Overview Sea
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Tracking and data relay satellite s
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Customer responsibilities The custo
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Phase II⎯ development The custome
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FAA/AST compliance All launch licen
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12. SYSTEM RELIABILITY Overview Sea
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APPENDIX A User Questionnaire When
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Spacecraft Orbit Parameters SI Unit
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Effective isotropic radiated power
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In-flight discrete commands Number
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Dynamic Environment Allowable accel
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Ground Processing (continued) Stand
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Ground Processing (continued) LP (t
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APPENDIX B. SEA LAUNCH STANDARD OFF
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Meetings and reviews • Customer k
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Mission integration Analyses The fo
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HP facilities • Processing and fu
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ACS shared areas • Launch control
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LP security • Card readers will c
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Facilities • Use of additional of
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Sea Launch User's Guide

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