Sea Launch User's Guide

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Weather systems The ACS has a self-contained weather station with the central office located on the first bridge deck (see fig. 10-2). Components of the weather system include a motion-stabilized C-band Doppler radar, upperatmospheric balloon release station, surface wind instruments, wave radar, and ambient condition sensors. The onboard meteorologist has access to satellite imagery and information from an onsite buoy (see fig. 10-3). Forecasts are provided periodically throughout the processing flow to verify operational weather constraints. Weather data is continuously updated for display on the MMDS. 265807J3-087 Figure 10-2. ACS Weather Office 265807J3-120 Figure 10-3. On-Site Meteorological Buoy REV B D688-10009-1 10-3
Helicopter operations Sea Launch operates a Bell 230 helicopter (fig. 10-4) to support mission operations such as pre- and postlaunch platform inspections, down-range clearing of the launch corridor, perimeter security patrol, and additional functions. The aircraft can carry as many as eight passengers. The ACS and launch platform are equipped with helicopter landing pads rated at 12,000 lb. The ACS is also equipped with a helicopter hangar and a 4,000 gal fuel storage tank. The helicopter has a operational range of 300 nmi and can be used for medical emergencies, if required. 265807J3-085 Figure 10-4. Sea Launch Bell 230 Helicopter 10-4 D688-10009-1 REV B
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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
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 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: Communications Internal communicati
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
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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Sea Launch User's Guide

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