Sea Launch User's Guide

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2.2 Zenit Stage 2 Stage 2 primary structure The Zenit second stage also uses integral stiffened aluminum construction (see fig. 2-5). Stage 2 propellants are LOX and kerosene. The lower kerosene tank is toroid shaped and the LOX tank is a domed cylinder. The stage is powered by a single-nozzle RD-120 engine. 265807J3-037R1 Figure 2-5. Stage 2, Zenit-3SL Three-axis control The RD-8 vernier engine mounted in the aft end of Stage 2 provides three-axis attitude control. The RD-8 uses the same propellants as the single fixed-nozzle RD-120, with one turbo-pump feeding four gimbaling thrusters. The RD-8 produces 8100 kg (17,900 lb) of thrust. 2-8 D688-10009-1 REV B
2.3 Block DM-SL—Upper Stage Configuration The Block DM-SL is a restartable upper stage capable of restarting up to four times during a mission. Avionics are housed in a sealed toroidal equipment bay at the front end of the upper stage. An interstage cylinder of aluminum skin and stringer construction encloses the Block DM-SL. The configuration of the Block DM-SL is shown in figure 2-6. Propulsion Propulsive capability for the upper stage is provided by the 11D58M engine, which operates on liquid oxygen and kerosene. The kerosene is contained in a toroidal tank that encircles the main engine turbo pump. The spherical liquid oxygen tank is located above the fuel tank. The 11D58M has a single gimbaling nozzle that provides directional control during propulsive phases. REV B D688-10009-1 2-9
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 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: Block DM-SL interface plane Liquid
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
Page 87 and 88:
Radiated environment There are six
Page 89 and 90:
200 180 160 140 Electric field, dB
Page 91 and 92:
Ground processing and transportatio
Page 93 and 94:
Ground processing and transportatio
Page 95 and 96:
1200 PLF separation 1000 Block DM M
Page 97 and 98:
120 100 Legend: Predicted internal
Page 99 and 100:
Contamination control during ground
Page 101 and 102:
Spacecraft isolation The spacecraft
Page 103 and 104:
6. SPACECRAFT DESIGN CONSIDERATIONS
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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
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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
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
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Figure 8-23. Assembly and Command S
Page 151 and 152:
Figure 8-24. Liftoff From the Launc
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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
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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
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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
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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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