Sea Launch User's Guide

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5.4 Acoustics Space average sound pressure levels The launch vehicle internal acoustic levels shown in table 5-3 and figure 5-7 are average sound pressure levels internal to the payload unit. These values apply to a spacecraft having an equivalent radius that results in a spacecraft to payload fairing gap of 0.43 m (1.5 ft). Fill effects to be considered The equivalent radius of the spacecraft is defined as the radius of a circle with a cross-sectional area equal to the spacecraft cross-sectional area. The envelope of the internal maximum expected sound pressure levels can also be provided after clocking and fill effects for a specific spacecraft are determined. The compliance requirements of the spacecraft to the internal acoustic environment are given in section 6. Table 5-3. Acoustics During Flight⎯ 1/3-Octave Band Sound Pressure Levels 1/3 octave band center frequency, Hz Sound pressure levels, dB 31.5 119 40 121 50 123 63 125 80 127 100 129 125 130 160 131 200 133 250 134 315 133 400 131 500 129 630 127 800 125 1,000 122 1,250 121 1,600 120 2,000 119 2,500 118 3,150 117 4,000 115 5,000 114 6,300 113 8,000 111 10,000 110 • OASPL = 142 dB • Reference: 2 x 10 -5 Pa (2.9 x 10 -9 psi) 265807J3-048 REV B D688-10009-1 5-7
135 130 Sound pressure levels, dB 125 120 115 110 105 100 10 100 1,000 10,000 Note: 1/3 octave band center frequency, Hz • Overall sound pressure level = 142 dB • Reference: 2 x 10 -5 Pa (2.9 x 10 -9 psi) Figure 5-7. Acoustic Environment During Flight 265807J3-061 5.5 Shock Maximum shock at spacecraft separation Shock levels for the three adapters currently offered The maximum shock at the spacecraft interface occurs at the moment of spacecraft separation. Other shock inputs are well within this envelope and do not require additional consideration. Shock environments are provided for the three spacecraft adapters currently available. • SCA1194 has a diameter of 1194 mm and a Marmon clamp separation system. • SCA1666 has a diameter of 1666 mm and a Marmon clamp separation system. • SCA702 and SCA702GEM have diameters of 1664 mm and fourbolt separation systems. The maximum shock environments for these systems are consistent with industry standards. Check with <strong>Sea</strong> <strong>Launch</strong> for availability of other spacecraft adapters. Additional or increased-strength adapters will be evaluated depending on customer requirements. 5-8 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
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
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: Base acceleration, g 1.2 1.0 0.8 0.
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)
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
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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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Sea Launch User's Guide

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