Pre-Phase A Report - Lisa - Nasa

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132 Chapter 5 Payload Design Units Number Total Mass Power per Notes of Units (kg) Unit (W) Processor 2 2.3 10.5 X-strap board 2 1.8 0.75 between A & B strings 1553 board 2 1.8 1 1553 bus controller RS 422 board 4 1.8 2 Serial I/O for accels., etc VME chassis 2 1.8 – composite material Shielding – 1 – Totals 10.5 kg 14.25 W Dimensions of complete payload computer: 233×199×321 mm 3 =14.9 litres Table 5.6 Payload computer mass, power, volume budgets. 5.9.2 Payload data interfaces The data interfaces between the payload subsystems and the spacecraft are shown in Figure 5.7 . The baseline approach is to use a MIL-STD-1553 data bus to link all of the DFACS hardware elements to the payload processor, with the exception of the accelerometers (including UV discharge system) and interferometer electronics which are directly linked to the payload processor via an RS 422 interface. The payload processor is linked to the spacecraft processor via the 1553 bus. If it turns out to be feasible in terms of bus management and reliability, the 1553 interfaces may be replaced throughout by RS 422 interfaces, with considerable cost benefit. For the time being, however, the 1553 protocol is the baseline choice. Bus control. The MIL-STD-1553 protocol requires no more than one bus controller. Initially, the spacecraft processor is the bus controller for coarse attitude control. During a transition phase, after the payload processor (nominally String A) is brought on line, bus control is transferred from the spacecraft processor to the payload processor. This is accomplished by a “dynamic bus control” command which is available within the framework of the 1553 standard. (Alternatively, the spacecraft processor could retain control of the bus and use remote-terminal-to-remote-terminal transfers.) Payload command and data handling software. The payload command and data handling (C&DH) software layer resides on the payload processor and includes the 1553 interface and data structures for normal payload operations, plus the RS 422 interface with the accelerometers and interferometer electronics. The command handler accepts and routes commands either directly from the 1553 interface, or as stored program commands loaded into the payload processor memory. These program commands may be timetagged with absolute or relative time, or may be conditional commands. The spacecraft computer which controls the telemetry must be configured such as to accept/send data packets from/to the payload processor as commanded by the payload C&DH layer. All payload flight software will be developed using commercial compilers (C, C++, orAda). 3-3-1999 9:33 Corrected version 2.08
5.9 Payload processor and data interfaces 133 THRUSTER DRIVE ELECTRONICS STAR TRACKERS PAYLOAD PCU THRUSTERS CCSDS protocol SUN SENSORS (COARSE & FINE) NON−VOLATILE MEMORY ACCELEROMETERS (sensors, UV system) 1553 BUS RS422 BUS SPACECRAFT PROCESSOR RAD6000−SC 128 Mbyte DRAM 3 MByte PROM INTERFEROMETER ELECTRONICS (photodiodes etc) Figure 5.7 Payload data interfaces. switchable bus control coarse attitude safe mode SPACECRAFT PAYLOAD standby mode intermediate mode acquisition mode drag−free/fine attitude Corrected version 2.08 3-3-1999 9:33
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LISA Laser Interferometer Space Ant
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LISA Laser Interferometer Space Ant
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Foreword The first mission concept
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The result of the Team-X study was
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Contents Foreword iii Executive Sum
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Contents ix 4.2.3 Acceleration nois
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Contents xi 9 Science and Mission O
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Executive Summary 1 Executive Summa
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Executive Summary 3 Complementarity
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Mission Summary 5 LISA Mission Summ
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Chapter 1 Scientific Objectives By
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1.1 Theory of gravitational radiati
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1.2 Low-frequency sources of gravit
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Chapter 2 Different Ways of Detecti
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2.2 Ground-based detectors 39 2.2 G
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2.2 Ground-based detectors 41 Count
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2.4 Spacecraft tracking 43 2.4 Spac
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2.7 Heliocentric versus geocentric
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2.8 The LISA concept 47 telescopes
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2.8 The LISA concept 49 Figure 2.6
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2.8 The LISA concept 51 seem rather
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Chapter 3 Experiment Description 3.
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3.1 The interferometer 55 Fiber to
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3.1 The interferometer 57 3.1.4 Sys
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3.1 The interferometer 59 Figure 3.
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3.1 The interferometer 61 3.1.6 Las
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3.1 The interferometer 63 signal sh
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3.1 The interferometer 65 for a sin
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3.2 The inertial sensor 67 design (
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3.2 The inertial sensor 69 and the
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3.2 The inertial sensor 71 Figure 3
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3.2 The inertial sensor 73 sufficie
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3.3 Drag-free/attitude control syst
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3.3 Drag-free/attitude control syst
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Chapter 4 Measurement Sensitivity 4
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References 183 [77] J.E. Faller and
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References 185 [104] E. Grun, H.A.
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List of Acronyms - and other abbrev
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List of Acronyms 189 LHC Large Hadr
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Rear cover figure : This Report has
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