Sea Launch User's Guide

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Flight history The Zenit was first launched in 1985 from Baikonur Cosmodrome in Kazakhstan. As of June 2000, the Zenit two-stage vehicle has completed 30 missions in 34 launch attempts. The Zenit first-stage booster also served as a strap-on for the Energia launch vehicle and logged an additional eight successes in two flights in this capacity. The Block DM-SL is a modification of an existing design developed by RSC Energia. It has a long and successful history as the fourth stage of the Proton LV. With the addition of an upgraded avionics and guidance suite, the Block DM superseded the Block D upper stage in 1974 and has since flown 184 successful missions as of July 2000. Primary missions have been geosynchronous transfer orbit (GTO); geosynchronous orbit (GEO); and interplanetary, including missions to Halley’s Comet, Venus, and Mars. Significant configuration differences between the Zenit-3SL and its predecessor are • New navigation system. • Next-generation flight computer. • Stiffened first stage. • Fueling lines modified for third stage. Flight success ratios Table 2-1 lists flight success ratios for each of the three Zenit-3SL stages as of May 2000. The engineering reliability estimate shown in table 2-1 accounts for • Extensive testing performed when changes are made to the rocket or the ground support equipment. • Expected reliability growth, using statistics of more mature boosters using similar processes and procedures also built and launched in the former USSR. • An exhaustive failure analysis team that investigates the flight anomalies and produces measures to ensure that the anomalies never occur again. • The <strong>Sea</strong> <strong>Launch</strong> mission assurance and audit process that is in place and operating. 2-2 D688-10009-1 REV B
Table 2-1. Flight History Component Introduction Flight Success Ratio Reliability Estimate Zenit Stage 1 1985 42 of 44 (95.4%) 98.4% Zenit Stage 2 1985 30 of 34 (88.2%) 94.3% Block DM 1974 184 of 190 (96.8%) 98.2% Payload accommodation (PLA) The PLA is a new development hardware item, but the design is based on launch experience that extends back over three decades. The PLA design protects the spacecraft from transportation, handling, launch, and flight environments. The design features • Streamlined operational flows. • Flexibility to accommodate varied spacecraft models. REV B D688-10009-1 2-3
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 and 16: 8-16 Payload Unit Mating to the Zen
Page 17 and 18: ABBREVIATIONS AND ACRONYMS ACS ARS
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: 2. VEHICLE DESCRIPTION Overview The
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
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
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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
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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
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7.2 Electrical Interfaces Overview
Page 127 and 128:
Radio frequency link (rerad) A dire
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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
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34 inches 688-95510-002 Scaffold as
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265807J3-105 Figure 8-13. Payload U
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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
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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
Page 187 and 188:
Tracking and data relay satellite s
Page 189 and 190:
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
Page 197 and 198:
APPENDIX A User Questionnaire When
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Spacecraft Orbit Parameters SI Unit
Page 201 and 202:
Effective isotropic radiated power
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In-flight discrete commands Number
Page 205 and 206:
Dynamic Environment Allowable accel
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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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Sea Launch User's Guide

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