Sea Launch User's Guide

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Facilities Astrotech provides facility support services while the spacecraft is in the PPF. Section 10 describes the payload processing facility and services. • Access lifts are available to support personnel working on the spacecraft. • An adjacent control room is provided for spacecraft ground support equipment and personnel. • Garment change rooms, office facilities, remote control facilities, and warehouse or storage facilities are also available. Payload fairing delivery Before or in conjunction with spacecraft processing, the payload fairing and the interface skirt and payload structure (ISPS) also arrive at the PPF and are unloaded in the common airlock cell. Strongback assembly (SBA) An SBA is used for rotation of the spacecraft from horizontal to vertical for encapsulation (see fig. 8-6 and 8-7). • Boeing personnel move the ISPS into the encapsulation cell and place it on the SBA. • Once spacecraft standalone processing and fueling are complete, the spacecraft is mated to the spacecraft adapter and separation ordnance is installed. The spacecraft is then transported into the encapsulation cell and mated to the ISPS on the SBA (see fig. 8-8). • All systems are fully tested before mating and all mechanical and electrical interfaces are verified by established procedures. 3.5 m Top of payload structure Payload structure Interface skirt 1.84 m 0.65 m Skirt base Free vertical height* 0 m Floor level 5.54 m (218.4 in) 7.72 m (304 in) * “Crawlspace” height between SBA and PPF floor 265807J3-098 Figure 8-6. SBA Vertical Mating Position 8-6 D688-10009-1 REV B
Payload mount assembly Flexure Interface/spacer ring assembly Drive system and control assembly Multicomponent load cell Base assembly 265807J3-099 Figure 8-7. SBA Horizontal Raised Position 265807J3-100 Figure 8-8. SBA Rotating to Horizontal With Pathfinder Structure REV B D688-10009-1 8-7
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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
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 and 104: 6. SPACECRAFT DESIGN CONSIDERATIONS
Page 105 and 106: 6.1 Mass and Center of Gravity (CG)
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: Figure 8-5. Fit Check on Adapter Su
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 and 170: Capabilities Launch control center
Page 171 and 172: Customer office areas The two offic
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
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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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