Sea Launch User's Guide

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LEO low Earth orbit LOX liquid oxygen LP launch platform LRR launch readiness review LV launch vehicle MD mission director MDR mission dress rehearsal MECO1 main engine cutoff number 1 MEO medium Earth orbit MES1 main engine start number 1 MMDS mission management display system MRR mission readiness review NIMA National Imagery and Mapping Agency OASPL overall sound pressure level PDR preliminary design review PLF payload fairing PLU payload unit PPF payload processing facility RF radio frequency RH relative humidity S&MA safety and mission assurance SBA strongback assembly S/C; SC spacecraft SCA spacecraft adapter SL Sea Launch SLS Sea Launch system TDRSS Tracking and Data Relay Satellite System TIM technical interchange meeting TM technical manual WX weather XFR transfer xxii D688-10009-1 REV B
1. INTRODUCTION Purpose The purpose of The Sea Launch User’s Guide is to familiarize current and potential customers with the Sea Launch system and associated launch services. This document is the starting point for understanding the Sea Launch spacecraft integration process and the overall capabilities of the system. Further information may be obtained by contacting Sea Launch directly. 1.1 Overview of the Sea Launch System What the system includes The Sea Launch system includes • The Zenit-3SL launch vehicle. • The launch platform. • The assembly and command ship. • Spacecraft and launch vehicle processing facilities. • Tracking and communications assets. Sea Launch Standard Offerings and Options (appendix B) describes the hardware, launch services, facilities, support services, and optional services provided by the Sea Launch Limited Partnership. The Home Port for the launch platform and assembly and command ship is located in the Port of Long Beach in Southern California. The payload processing facility, which accommodates a full range of spacecraft electrical and mechanical processing, testing, and fueling capabilities, is also in Home Port. REV B D688-10009-1 1-1
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: ABBREVIATIONS AND ACRONYMS ACS ARS
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
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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
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5.6 Electromagnetic Environment The
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Radiated environment There are six
Page 89 and 90:
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
Page 111 and 112:
■ Sea Launch RF Susceptibility 16
Page 113 and 114:
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
Page 125 and 126:
7.2 Electrical Interfaces Overview
Page 127 and 128:
Radio frequency link (rerad) A dire
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8. SPACECRAFT INTEGRATION AND LAUNC
Page 131 and 132:
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
Page 167 and 168:
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
Page 195 and 196:
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
Page 203 and 204:
In-flight discrete commands Number
Page 205 and 206:
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
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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