Sea Launch User's Guide

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Anomaly resolution system (ARS) The Sea Launch ARS, based on the existing Boeing failure review, analysis, and corrective action system used on several integrated air vehicles and avionics platforms, has been established along with a system database. The ARS is in place to acquire and assess failure history, criticality, and effectiveness of changes, and as a database from which recommendations can be validated. The ARS is also used to gather data on test and flight failures, design changes, test results, and repair decisions. Ensuring reliability growth Sea Launch has processes and plans in place to ensure continued reliability growth as the system matures (see fig. 12-1). Revisions if required Advertised reliability requirement Input from existing systems Predictions and comparisons Reliability analysis Operating requirements Partner/ industry alerts Test program Failure reporting and analysis Mission-critical hardware list Trend analysis Corrective action Safety Availability Maintainability Others Pedigree review Failure database 265807J3-066R2 Figure 12-1. Anomaly Resolution System 12-2 D688-10009-1 REV B
APPENDIX A User Questionnaire When completed, this questionnaire provides the Boeing Commercial Space Company, acting on behalf of the Sea Launch Limited Partnership, with the preliminary data necessary to begin evaluation of the compatibility of the Sea Launch system with a new spacecraft type and to start the integration process. Companies considering the Sea Launch system should complete this questionnaire and return it to: Boeing Commercial Space Company SEA LAUNCH PROGRAM PO Box 3999, MS 6E-60 Seattle, WASHINGTON 98124-2499 USA (Attention: Ms. Amy Buhrig) Boeing Commercial Space Company will treat this data as customer proprietary information and will not disclose any part of the information contained herein to any entity outside the Sea Launch Limited Partnership without your expressed written permission. For further information contact: Ms. Amy Buhrig Phone: 425-393-1884 Fax: 425-393-1050 REV B D688-10009-1 A-1
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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
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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
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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
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
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: 12. SYSTEM RELIABILITY Overview Sea
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
Page 211 and 212: APPENDIX B. SEA LAUNCH STANDARD OFF
Page 213 and 214: 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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