Sea Launch User's Guide

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3.4 Coast Phase Attitude Three-axis pointing The Block DM-SL can accommodate preferred three-axis attitude pointing (including sun pointing) while coasting between Block DM-SL main engine burns. Attitude and attitude rate accuracy depend heavily on spacecraft mass properties. Preliminary attitude and attitude rate are assumed to be ±3 deg and ±0.25 deg/sec in all three axes (2.3σ). Roll maneuvers Continuous rolls for spacecraft thermal control and battery charging are supported. For a roll rate of 5 deg/sec, the roll-axis pointing accuracy is ±4 deg and the attitude rate accuracy is ±0.2 deg/sec in all three axes (2.3σ). 3-14 D688-10009-1 REV B
3.5 Spacecraft Separation Separation event Spacecraft separation typically occurs 500 sec after the final Block DM- SL main engine shutdown. This allows for engine cooling and reorientation to the required spacecraft separation attitude. Several hours after separation, the Block DM-SL performs a contamination and collision avoidance maneuver (CCAM), which prevents future contact with the spacecraft. The Block DM-SL then vents all residual propellant and gasses and depletes any remaining charge in its batteries. Separation capabilities The separation system provides a relative velocity between the Block DM-SL and the spacecraft of at least 0.3 m/sec. The Block DM-SL attitude control system can provide a longitudinal spin rate if desired. The separation springs can provide a straight pushoff or a small transverse angular rate. Attitude and attitude rate accuracy depend heavily on spacecraft mass properties and spin rate, but for preliminary purposes may be assumed to be ±2.5 deg and ±0.6 deg/sec in all three axes for a nonspinning separation (2.3σ). Injection accuracy The injection accuracy at spacecraft separation is a function of the injection orbit and the mission flight duration. Table 3-3 indicates the injection accuracy for a standard GTO mission (2.3σ). Table 3-3. Standard GTO Injection Accuracy (2.3σ) Orbital Parameter Perigee height Apogee height Inclination RAAN Argument of perigee Injection Accuracy ± 10 km ± 80 km ± 0.25 deg ± 0.25 deg (nonzero inclinations) ±0.25 deg (nonzero inclinations) REV B D688-10009-1 3-15
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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 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: High-energy and escape orbits Figur
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
Page 105 and 106: 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
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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
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Tracking and data relay satellite s
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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
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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
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In-flight discrete commands Number
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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
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Mission integration Analyses The fo
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HP facilities • Processing and fu
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ACS shared areas • Launch control
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LP security • Card readers will c
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Facilities • Use of additional of
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