Pre-Phase A Report - Lisa - Nasa

Recommendations

Info

160 3-3-1999 9:33 Corrected version 2.08
Chapter 8 Technology Demonstration in Space To minimize the cost and risk associated with the full LISA mission it is essential to have well-understood and proven technology available. A LISA technology demonstration mission is therefore highly desirable. Such a mission should not just provide a functional test but should instead aim at testing the key technologies required for LISA to within an order of magnitude of the final performance in the relevant mHz frequency range. 8.1 ELITE – The European LISA Technology Demonstration Satellite 8.1.1 Introduction The proposed European LIsa TEchnology demonstration satellite (ELITE) aimstotest the key technologies of inertial sensing, drag-free control, and low-frequency laser interferometry required for LISA. The single ELITE spacecraft will contain two isolated proof masses which will be used as references for the drag-free/attitude control system. The proof masses will also serve as reference mirrors for the laser interferometer package. The interferometer will provide an independent measurement of relative displacement between the masses, allowing a direct assessment of the relative acceleration between the masses. Field emission (ion) thrusters will be the primary actuators for the drag-free/attitude control. An autonomous startracker plus Sun sensor will be used for coarse attitude control/safe-mode. A cold-gas system will be used for coarse-attitude control. The target launch year is 2002 (pending the timely development of the key technologies), with a nominal mission duration of six months. Various candidate orbits and launch options are being considered. It is desirable to have an orbit altitude above 10 000 km in order to avoid the charging of the proof masses due to interaction with trapped protons in the Van Allen Belts. The baseline choice is a Geostationary orbit (GEO) which avoids the proton belts completely, but which necessitates an apogee kick motor for orbit injection. Another option would be to utilise a shared launch into a suitable orbit without the need for an apogee kick motor. One Corrected version 2.08 161 3-3-1999 9:33
Page 1 and 2:
LISA Laser Interferometer Space Ant
Page 3 and 4:
LISA Laser Interferometer Space Ant
Page 5 and 6:
Foreword The first mission concept
Page 7 and 8:
The result of the Team-X study was
Page 9 and 10:
Contents Foreword iii Executive Sum
Page 11 and 12:
Contents ix 4.2.3 Acceleration nois
Page 13 and 14:
Contents xi 9 Science and Mission O
Page 15 and 16:
Executive Summary 1 Executive Summa
Page 17 and 18:
Executive Summary 3 Complementarity
Page 19 and 20:
Mission Summary 5 LISA Mission Summ
Page 21 and 22:
Chapter 1 Scientific Objectives By
Page 23 and 24:
1.1 Theory of gravitational radiati
Page 25 and 26:
Page 27 and 28:
Page 29 and 30:
Page 31 and 32:
Page 33 and 34:
1.2 Low-frequency sources of gravit
Page 35 and 36:
Page 37 and 38:
Page 39 and 40:
Page 41 and 42:
Page 43 and 44:
Page 45 and 46:
Page 47 and 48:
Page 49 and 50:
Page 51 and 52:
Chapter 2 Different Ways of Detecti
Page 53 and 54:
2.2 Ground-based detectors 39 2.2 G
Page 55 and 56:
2.2 Ground-based detectors 41 Count
Page 57 and 58:
2.4 Spacecraft tracking 43 2.4 Spac
Page 59 and 60:
2.7 Heliocentric versus geocentric
Page 61 and 62:
2.8 The LISA concept 47 telescopes
Page 63 and 64:
2.8 The LISA concept 49 Figure 2.6
Page 65 and 66:
2.8 The LISA concept 51 seem rather
Page 67 and 68:
Chapter 3 Experiment Description 3.
Page 69 and 70:
3.1 The interferometer 55 Fiber to
Page 71 and 72:
3.1 The interferometer 57 3.1.4 Sys
Page 73 and 74:
3.1 The interferometer 59 Figure 3.
Page 75 and 76:
3.1 The interferometer 61 3.1.6 Las
Page 77 and 78:
3.1 The interferometer 63 signal sh
Page 79 and 80:
3.1 The interferometer 65 for a sin
Page 81 and 82:
3.2 The inertial sensor 67 design (
Page 83 and 84:
3.2 The inertial sensor 69 and the
Page 85 and 86:
3.2 The inertial sensor 71 Figure 3
Page 87 and 88:
3.2 The inertial sensor 73 sufficie
Page 89 and 90:
3.3 Drag-free/attitude control syst
Page 91 and 92:
3.3 Drag-free/attitude control syst
Page 93 and 94:
Chapter 4 Measurement Sensitivity 4
Page 95 and 96:
4.1 Sensitivity 81 averaged transfe
Page 97 and 98:
4.2 Noises and error sources 83 The
Page 99 and 100:
4.2 Noises and error sources 85 Tab
Page 101 and 102:
4.2 Noises and error sources 87 cod
Page 103 and 104:
4.2 Noises and error sources 89 cha
Page 105 and 106:
4.2 Noises and error sources 91 fre
Page 107 and 108:
4.2 Noises and error sources 93 ele
Page 109 and 110:
4.2 Noises and error sources 95 is
Page 111 and 112:
4.2 Noises and error sources 97 and
Page 113 and 114:
4.2 Noises and error sources 99 Eq.
Page 115 and 116:
4.3 Signal extraction 101 here that
Page 117 and 118:
4.3 Signal extraction 103 phase loc
Page 119 and 120:
4.4 Data analysis 105 • LISA obse
Page 121 and 122:
4.4 Data analysis 107 for ground-ba
Page 123 and 124: 4.4 Data analysis 109 that are defi
Page 125 and 126: 4.4 Data analysis 111 with the phas
Page 127 and 128: 4.4 Data analysis 113 density Sn(f)
Page 129 and 130: 4.4 Data analysis 115 box (in stera
Page 131 and 132: 4.4 Data analysis 117 LISA’s dist
Page 133 and 134: Chapter 5 Payload Design 5.1 Payloa
Page 135 and 136: 5.2 Payload structural components 1
Page 137 and 138: 5.2 Payload structural components 1
Page 139 and 140: 5.4 Mass estimates 125 5.4 Mass est
Page 141 and 142: 5.7 Thermal analysis 127 the Y-shap
Page 143 and 144: 5.8 Telescope assembly 129 surface
Page 145 and 146: 5.9 Payload processor and data inte
Page 147 and 148: 5.9 Payload processor and data inte
Page 149 and 150: Chapter 6 Mission Analysis 6.1 Orbi
Page 151 and 152: 6.3 Injection into final orbits 137
Page 153 and 154: 6.4 Orbit configuration stability 1
Page 155 and 156: 6.5 Orbit determination and trackin
Page 157 and 158: Chapter 7 Spacecraft Design 7.1 Sys
Page 159 and 160: 7.1 System configuration 145 2220 m
Page 161 and 162: 7.1 System configuration 147 7.1.4
Page 163 and 164: 7.2 Spacecraft subsystem design 149
Page 165 and 166: 7.3 Micronewton ion thrusters 151 b
Page 167 and 168: 7.3 Micronewton ion thrusters 153 F
Page 169 and 170: 7.3 Micronewton ion thrusters 155 (
Page 171 and 172: 7.3 Micronewton ion thrusters 157 F
Page 173: 7.4 Mass and power budgets 159 The
Page 177 and 178: 8.1 ELITE - European LISA Technolog
Page 179 and 180: 8.3 ELITE Technologies 165 8.2.2 Co
Page 181 and 182: 8.4 ELITE Satellite design 167 inco
Page 183 and 184: Chapter 9 Science and Mission Opera
Page 185 and 186: 9.2 Mission operations 171 9.2 Miss
Page 187 and 188: 9.3 Operating modes 173 Power savin
Page 189 and 190: Chapter 10 International Collaborat
Page 191 and 192: 10.3 Schedule 177 The ESA Project M
Page 193 and 194: References [1] C.W. Misner, K.S. Th
Page 195 and 196: References 181 [35] C. Cutler, T.A.
Page 197 and 198: References 183 [77] J.E. Faller and
Page 199 and 200: References 185 [104] E. Grun, H.A.
Page 201 and 202: List of Acronyms - and other abbrev
Page 203 and 204: List of Acronyms 189 LHC Large Hadr
Page 205: Rear cover figure : This Report has
show all

Pre-Phase A Report - Lisa - Nasa

Create successful ePaper yourself

Delete template?

Save as template?