Sea Launch User's Guide

More documents

Recommendations

Info

5.2 Structural Loads Overview The structural loading environments on all spacecraft primary and secondary structure are examined for • Ground transportation and handling. • Flight. • Spacecraft sinusoidal vibration testing. Compliance requirements of the spacecraft to these environments are in section 6. Quasi-static load factors for ground handling and transportation The Sea Launch system will not induce loads on the spacecraft that exceed the load factor envelope shown in figure 5-1 during spacecraft ground and ocean transportation, handling, and processing. The acceleration levels are shown for the spacecraft center of gravity. The accelerations can act simultaneously in the horizontal and vertical directions. The magnitude of the vector sum of the horizontal load factors for the two orthogonal horizontal directions is 0.5 g. The accelerations in figure 5-1 apply when the integrated launch vehicle is vertical or horizontal and while it is being erected or lowered. The orientation of the spacecraft when the Zenit-3SL is horizontal or vertical is shown in figures 5-2 and 5-3, respectively. Vertical, g 2.0 1.5 1.0 0.5 Horizontal, g –1.0 –0.5 0 0.5 1.0 265807J3-055R1 Figure 5-1. Transportation and Handling Limit Load Factors REV B D688-10009-1 5-3
Vertical Horizontal Horizontal 265807J3-056 Figure 5-2. Integrated Launch Vehicle Horizontal Vertical Horizontal Horizontal 265807J3-057 Figure 5-3. Integrated Launch Vehicle Vertical CLA required to determine quasistatic loads for flight Determining the ability of the spacecraft primary and secondary structure to withstand the dynamic loading events from flight requires a coupled loads analysis (CLA). Sea Launch performs a CLA for all critical flight events to determine the accelerations, loads, and deflections of all primary and secondary structure of the spacecraft caused by the coupled elastic behavior of the Zenit-3SL launch vehicle and the spacecraft. The results determine the interface loads of the spacecraft with the spacecraft adapter. The resulting equivalent spacecraft quasi-static load factors at the spacecraft center of gravity can then be determined for a specific spacecraft with given mass and stiffness properties. 5-4 D688-10009-1 REV B
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 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: 5.1 Transportation and Handling at
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)
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
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 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 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
show all

Sea Launch User's Guide

Create successful ePaper yourself

Delete template?

Save as template?