Sea Launch User's Guide

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Customer work areas The spacecraft contractor and customer work areas are located on the first bridge deck directly above the launch control center (fig. 9-12). The area has ground support equipment (GSE) rooms, office areas, conference rooms, individual offices, and storage rooms. The GSE rooms provide space for the equipment necessary to control and monitor the spacecraft during mission operations. The GSE is loaded to the deck area just behind each room, using the ship’s overhead cranes. The GSE rooms contain • Patch panels for hard-line links to the launch control center. • Countdown and countup clocks. • Public address, intercom, and telephone services. • Overhead monitors displays connected to CCTV networks. • 120/208 V, 60-Hz, and 220/380 V, 50-Hz power. • Uninterruptible power supplies for 60 and 50 Hz power. Customer storage Office Office Office Office P P P P Office P, PC Customer ground support equipment room CCTV, P, F, I, M CCTV, P, F, I, M Customer ground support equipment room Customer storage Customer office area VCR, Customer VTC, I, P conference room VCR, Customer VTC, I, P conference room Customer office area F, I, P, VCR PC, P, F, I, VCR F, I, P,VCR P P P P Office Office Office Sea Launch office area Sea Launch weather offices Sea Launch EGSE room P, PC 265807J3-130R1 Figure 9-12. Spacecraft Contractor Work Area on First Bridge Deck REV B D688-10009-1 9-15
Customer office areas The two office areas for spacecraft customers consist of an open bay and three individual offices. A conference room and a storage room dedicated to customer use is also provided adjacent to the office area. Additional conference space is provided directly behind the launch control center. Each conference room has seating, overhead projectors, and teleconferencing equipment. COMSAT services Telephones, fax machines, teleconferencing, and data links are provided from the ACS to customer home locations through commercial COMSAT services (see fig. 9-13). Radio frequency links between the ACS and the launch platform allow communications with the spacecraft in the hangar and on the launch pad, and between spacecraft GSE rooms on the ACS and launch platform. 265807J3-122R1 Figure 9-13. Assembly and Command Ship INMARSAT B 9-16 D688-10009-1 REV B
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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
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Circular and elliptical orbits Figu
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High-energy and escape orbits Figur
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3.5 Spacecraft Separation Separatio
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Mid 2002 6700 Planned future growth
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Planning Phase (Through SC Delivery
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4.2 Mission Analysis and Operations
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SC/SLS ICD SC ICD verification plan
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Mission-specific documentation The
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Operations plan The operations plan
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5.1 Transportation and Handling at
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Vertical Horizontal Horizontal 2658
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Base acceleration, g 1.2 1.0 0.8 0.
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135 130 Sound pressure levels, dB 1
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SCA1666 The shock spectrum shown in
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5.6 Electromagnetic Environment The
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Radiated environment There are six
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200 180 160 140 Electric field, dB
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Ground processing and transportatio
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Ground processing and transportatio
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1200 PLF separation 1000 Block DM M
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120 100 Legend: Predicted internal
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Contamination control during ground
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Spacecraft isolation The spacecraft
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6. SPACECRAFT DESIGN CONSIDERATIONS
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6.1 Mass and Center of Gravity (CG)
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Table 6-2. Expected Spacecraft Mass
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7000 6000 5000 Spacecraft mass, kg
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■ Sea Launch RF Susceptibility 16
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6.4 Spacecraft Design Verification
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Static loads test A spacecraft stat
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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
Page 155 and 156: Postlaunch reports Sea Launch provi
Page 157 and 158: ■ Integrated LV Transfer to LP Pi
Page 159 and 160: 265807J3-015R2 Figure 9-3. Home Por
Page 161 and 162: Encapsulation cell 15 m x 38 m (50
Page 163 and 164: Encapsulation cell The encapsulatio
Page 165 and 166: 9.2 Assembly and Command Ship Funct
Page 167 and 168: Spacecraft checkout accommodations
Page 169: Capabilities Launch control center
Page 173 and 174: 265807J3-128 Figure 9-15. Assembly
Page 175 and 176: ■ Mess Hall ■ Coffee Bar ■ Ma
Page 177 and 178: Launch vehicle in launch position L
Page 179 and 180: Communications and access Telephone
Page 181 and 182: Communications Internal communicati
Page 183 and 184: Helicopter operations Sea Launch op
Page 185 and 186: 10.2 Telemetry Assets Overview Sea
Page 187 and 188: Tracking and data relay satellite s
Page 189 and 190: Customer responsibilities The custo
Page 191 and 192: Phase II⎯ development The custome
Page 193 and 194: FAA/AST compliance All launch licen
Page 195 and 196: 12. SYSTEM RELIABILITY Overview Sea
Page 197 and 198: APPENDIX A User Questionnaire When
Page 199 and 200: Spacecraft Orbit Parameters SI Unit
Page 201 and 202: Effective isotropic radiated power
Page 203 and 204: In-flight discrete commands Number
Page 205 and 206: Dynamic Environment Allowable accel
Page 207 and 208: Ground Processing (continued) Stand
Page 209 and 210: Ground Processing (continued) LP (t
Page 211 and 212: APPENDIX B. SEA LAUNCH STANDARD OFF
Page 213 and 214: Meetings and reviews • Customer k
Page 215 and 216: Mission integration Analyses The fo
Page 217 and 218: HP facilities • Processing and fu
Page 219 and 220: 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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