Sea Launch User's Guide

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LIST OF TABLES Page 2-1 Flight History.................................................................................................... 2-3 2-2 Zenit Specifications .......................................................................................... 2-6 2-3 Block DM-SL Specifications.......................................................................... 2-11 3-1 Typical Flight Timeline⎯GTO Mission .......................................................... 3-5 3-2 Single Block DM-SL Burn Standard GTO Parameters .................................... 3-9 3-3 Standard GTO Injection Accuracy (2.3σ)....................................................... 3-15 3-4 Estimate of Additional Future Performance Capability as a Function of Launch Date ................................................................................ 3-16 4-1 Mission Team Roles and Responsibilities ........................................................ 4-3 5-1 Spacecraft Fatigue Environment for Transportation and Handling.................. 5-2 5-2 Motions During Transit to Launch Site ............................................................ 5-2 5-3 Acoustics During Flight⎯1/3-Octave Band Sound Pressure Levels ............... 5-7 5-4 Sea Launch RF Environment.......................................................................... 5-15 5-5 PPF Thermal Environments............................................................................ 5-17 5-6 Payload Unit Environmental Control⎯Air Conditioning Inlet Conditions ... 5-19 6-1 Expected Spacecraft Mass and CG Limits Using Standard-Offering SCA...... 6-4 6-2 Expected Spacecraft Mass and CG Limits Using Upgraded SCA ................... 6-5 6-3 Factors of Safety and Test Options................................................................. 6-11 6-4 Sine Vibration Test Levels and Duration........................................................ 6-13 6-5 Spacecraft Acoustic Margins and Test Duration ............................................ 6-14 7-1 Umbilical Configurations.................................................................................. 7-8 7-2 In-Flight Telemetry, Command, and Separation Breakwire Interfaces.......... 7-10 REV B D688-10009-1 xix
ABBREVIATIONS AND ACRONYMS ACS ARS AST BR9DM CARF CCAM C 3 CCTV CDR CIS CLA CPSP EGSE EMC EMI EPTME EPTV FAA/AST FMH FONSI GEO GORR GPS GSE GTO h a h p HP ICD I/F ILV IPT IS ISPS LAN LCC assembly and command ship anomaly resolution system U.S. Department of Transportation Office of the Associate Administrator for Commercial Space Transportation Zenit-3SL telemetry system central altitude reservation function contamination and collision avoidance maneuver velocity squared at infinity closed-circuit television critical design review Commonwealth of Independent States coupled loads analysis customer prelaunch safety package electrical ground support equipment electromagnetic compatibility electromagnetic interference encapsulated payload transportation mechanical equipment encapsulated payload transport vehicle U.S. Department of Transportation Office of the Associate Administrator for Commercial Space Transportation free molecular heating finding of no significant impact geosynchronous Earth orbit ground operations readiness review global positioning system ground support equipment geosynchronous transfer orbit height of apogee height of perigee Home Port interface control document interface integrated launch vehicle integrated product team interface skirt interface skirt and payload structure local area network launch control center REV B D688-10009-1 xxi
Page 1 and 2: SM® User’s Guide _______________
Page 3 and 4: TABLE OF CONTENTS 1. INTRODUCTION .
Page 5 and 6: Mission manager and team ..........
Page 7 and 8: 6.2 Modal Frequencies..............
Page 9 and 10: Weather conditions ................
Page 11 and 12: 11.2 Safety Assessment Phases......
Page 13 and 14: LIST OF FIGURES Page 1-1 Generic In
Page 15: 8-16 Payload Unit Mating to the Zen
Page 19 and 20: 1. INTRODUCTION Purpose The purpose
Page 21 and 22: Milestones • Customer kickoff •
Page 23 and 24: Sea Launch Company Sea Launch Compa
Page 25 and 26: KB Yuzhnoye/PO Yuzhmash KB Yuzhnoye
Page 27 and 28: 2. VEHICLE DESCRIPTION Overview The
Page 29 and 30: Table 2-1. Flight History Component
Page 31 and 32: RD-171 engine The RD-171 engine, wh
Page 33 and 34: Block DM-SL interface plane Liquid
Page 35 and 36: 2.3 Block DM-SL—Upper Stage Confi
Page 37 and 38: Attitude control Three-axis stabili
Page 39 and 40: Spacecraft adapter Payload structur
Page 41 and 42: Cooling air From encapsulation to l
Page 43 and 44: 3. PERFORMANCE Overview The Zenit-3
Page 45 and 46: 20 N HAWAIIAN ISLANDS North Pacific
Page 47 and 48: Flight timeline Table 3-1 lists the
Page 49 and 50: Groundtrack Figure 3-3 shows the as
Page 51 and 52: 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
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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
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Ground processing and transportatio
Page 93 and 94:
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
Page 101 and 102:
Spacecraft isolation The spacecraft
Page 103 and 104:
6. SPACECRAFT DESIGN CONSIDERATIONS
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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
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6.5 Horizontal Handling Processing
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7. INTERFACES 7.1 Mechanical Interf
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360 deg 180 deg 331 deg 180 deg 360
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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
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Days 1 2 3 4 5 6 7 8 9 101112131415
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Figure 8-5. Fit Check on Adapter Su
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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
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Figure 8-17. Integrated Launch Vehi
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8.3 Phase III⎯Transit and Launch
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Launch rehearsals Two rehearsals ar
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Figure 8-23. Assembly and Command S
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Figure 8-24. Liftoff From the Launc
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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
Page 167 and 168:
Spacecraft checkout accommodations
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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
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
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APPENDIX B. SEA LAUNCH STANDARD OFF
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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
Page 221 and 222:
LP security • Card readers will c
Page 223:
Facilities • Use of additional of
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