Sea Launch User's Guide

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Other • A helicopter is provided to support mission operations. Both the ACS and the launch platform are equipped with landing pads. • A comprehensive photo-optical recording system is used to document launches. • External communications are handled through INTELSAT satellites and Sea Launch ground stations in Brewster, WA, and Eik, Norway. Zenit-3SL flight operations Zenit first- and second-stage flight operations are completely automatic. A mission event timeline is included in section 3, table 3-1 of this user’s guide. All Stage 1 and 2 events occur within the view of the ACS. The spent stages fall in the Pacific Ocean, far short of the coast of South America and the major coastal shipping lanes. Any deviation of flight trajectory from preprogrammed limits causes onboard systems to automatically terminate propulsion and end the mission. This approach to flight safety has been used successfully for decades by the CIS and obviates the need for the traditional range safety officer. At second-stage separation from the Block DM-SL, four solid propellant rocket motors at the base of Stage 2 fire to back the stage away from the Block DM-SL. The Block DM-SL lower and middle adapters are jettisoned during this period, the lower adapter is jettisoned with Stage 2, and the middle adapter is jettisoned just before Block DM-SL ignition. Block-DM flight operations Before launch, the Block DM-SL onboard systems are turned on and initialized, its oxidizer tank level is adjusted, and power is transferred from the LP umbilical to the Block DM-SL internal power supply. During the Stage 1 and 2 flight, the Block DM-SL remains inactive, except for preparations for autonomous flight. Following Stage 2 separation, the Block DM-SL is inserted into the target orbit with a single main engine burn. For two-burn missions, the Block DM-SL performs a settling burn using the attitude control/ullage propulsion system prior to the second burn of the main engine. Burn program options include, but are not limited to, one- or two-impulse insertion GTO and multiple burns (up to a maximum of five) to medium Earth orbit (MEO) or planetary escape. Following spacecraft insertion into the target orbit, the Block DM-SL separates from the spacecraft and performs a CCAM. Disposal options include transfer of the Block DM-SL to a higher or lower disposal orbit that mitigates orbital debris generation risk and reduces the spent stage orbital lifetime. 8-26 D688-10009-1 REV B
Postlaunch reports Sea Launch provides near real-time confirmation of key ascent events (PLF jettison, engine burns, spacecraft separation, etc.). An injection report is delivered within 50 min of spacecraft separation. The injection report documents the state vector of the Block DM-SL just prior to spacecraft separation, and is provided to customer personnel in the launch control center. A postflight report is delivered 60 days after launch. The postflight report documents performance of the Sea Launch systems and interfaces as related to documented requirements. Data includes operations and launch environments (ground and flight), launch time, separation state vector, injection orbit and accuracy, separation attitude and rates, contamination and collision avoidance maneuver performance, and flight event sequences. REV B D688-10009-1 8-27
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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
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 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: 8.4 Flight Operations Range trackin
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
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
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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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