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Space Plasma Particle InstrumentsDevelopment and Observation
Masafumi HIRAHARA (STEL, Nagoya Univ., Japan)
Example-1INDEX → Reimei (‘dawn’ ‘daybreak’ in Japanese)Micro-satellite by ISAS/JAXA both for
in-orbit demonstrations of innovative technology and scientific observations of small-scale auroral phenomena
Launched on August 23 in 2005 as a piggy-back by a Dnepr rocket from the Baikonur Cosmodrome in Kazakhstan
Example-2Medium-energy electron sensor with electrostatic energy analyzer and APD for ERG (Energy and Radiation in Geospace) satellite
The INDEX SatelliteFirst micro-satellite of ISAS/JAXA using in-house technology demonstration alsowith novel science payloads
Mission Subjects of the INDEX MissionINDEX (Innovative Technology Demonstration Experiment)1. Integrated satellite-controller system based on high-speed RISC
processors (Hitachi SH-3) with three voting system2. Three-axis attitude control system on micro-satellite3. Lithium-ion rechargeable batteries4. GPS receiver with all-sky coverage antennas for determining
satellite position5. Variable emittance radiator6. Solar-concentrated panel with multi-junction solar cell7. Compact S-band receiver and transmitter8. Compact ground tracking station based on PCs9. Science payloads for the exploration of small-scale auroral
properties
Reflector
Solar Array
Solar-concentrated panel with multi-junction solar cell
Sunlight
130℃
100℃
Solar PaddleReflectorReflector
ElectrodePositive LiMn2O4
Negative Graphite
Rated Capacity 3 Ah
Weight 75 g
Dimension 145 x 80 x 4 mm
Energy Density
Mass 158 Wh/kg
Volume 340 Wh/L
Charge Voltage 4.1 V (4.2 V)
Lower Limited Voltage 3.0 V
Specifications of Lithium-Ion Cell and Battery
Configuration 7 series of the cells2 parallels of the batteries
Potting Material Epoxy Resin
Case Material Al
Dimension 168×102×96 mm3
Weight 2.42 kg
Energy DensityWeight 70 Wh/kg
Volume 102.2 Wh/L
Manganese Oxide Li-Ion Pouch Cell
Lithium-Ion Battery
Mechanical InterferenceCheck
Acoustic Vibration Test with Mechanical Test Model (MTM) at NASDA
Vibration Test with Mechanical Test Model (MTM) at ISAS (Sagamihara)
3-m Antenna at ISAS (SSOC)
70 km70 km
500 k
m
Launch August 23 in 2005 as piggy-back on the Dnepr rocket forOICETS launched from the Baikonur Cosmodrome inKazakhstan
Orbit Sun-synchronous
Inclination: 98.6 deg.
Meridian: 12:50 - 0:50 LT
Altitude: 610-670 km
Orbital period:98.8 min.
Telemetry S-band for up- and down-link up to 133 kbps
Size/Weight 724×626×609 mm3 / 71.623 kg
Life More than three months (being extended to several years)
Introduction of Reimei
Satellite Attitude System
Attitude Three-axis stabilized
Sun-oriented basically
(within 15 deg. during the daytime)
Monitor Star tracker (STT)
(Sensor) Magnetic aspect sensor (GAS)
Sun sensors (SSAS and NSAS)
Three-axial optical fiber gyroscopes (FOGs)
Actuator Magnetic torquers (MTQs)
Reaction wheel (RW) spinning around z-axis
I. Multi-Spectral Auroral Imaging Camera (MAC)Three independent cameras consisting of CCDs and interference filters for N2
+ first negative band (427.8 nm), OI (557.7 nm), and N2 first positive band (670 nm) with time resolution of 120-1000 msec for observation and 4040 msec for calibration
II. Electron/Ion Energy Spectrum Analyzer (ESA/ISA)Top-hat type electrostatic energy analyzers for electrons and ions of 10 eV/q –12 keV/q devided by15 (30) logarithmic steps, each of which takes 1.25 msec.
III. Ambient Plasma Current Monitor (CRM)100 Hz-sampling from three sets of probes using the langmuir probe principle
i. Geomagnetic Aspect Sensor (GAS)200 Hz-sampling with three-axial fluxgate magnetometer inside satellite
ii. Data Recorders64-MB DRAM for raw data and 9-MB DRAM for compressed (telemetry) data
iii. SHU (Science Data Handling Unit)
Scientific Instruments/Units on Reimei
Multi-Spectral Auroral Imaging Camera (MAC)
Electron/Ion Energy Spectrum Analyzer (ESA/ISA)
Development and calibration of the auroral particle instruments
Electric interface test of auroral imaging camera
Final assembly of MAC
Principle and Techniquefor Space Plasma/Particle Measurement
・Thermal energy 0.01 ~ 30 eVI. Langmuir probe
・Low energy 10 eV ~ 30 keVI. Electrostatic energy analyzerII. Micro-channel plate (MCP) or channel electron multiplier
(CEM)・Medium energy 10 keV ~ 100 keV
I. Electrostatic energy analyzer II. MCP or avalanche photo diode (APD)
・High energy 30 keV ~ 2 MeVI. Solid state detector (SSD)
・Extremely high energy 300 keV ~ 20 MeVI. SSD, Scintillator + photomultiplier
Electron energy/flight directions analyses
Principle and Techniquefor Space Plasma/Particle Measurement
・Thermal energy 0.01 ~ 30 eVI. Langmuir probe
・Low energy 10 eV ~ 30 keVI. Electrostatic energy analyzerII. Micro-channel plate (MCP) or channel electron multiplier
(CEM)・Medium energy 10 keV ~ 100 keV
I. Electrostatic energy analyzer II. MCP or avalanche photo diode (APD)
・High energy 30 keV ~ 2 MeVI. Solid state detector (SSD)
・Extremely high energy 300 keV ~ 20 MeVI. SSD, Scintillator + photomultiplier
Electron energy/flight directions analyses
Collimator
Electrostatic EnergyAnalyzer(Top-hat type)
Detector (MCP)
Electron
Low-Energy Electron Instrument(Reimei Satellite, ISAS/JAXA)
GND
Cylindrically symmetric
+V
E
Electron energy (K)12 eV ~ 12 keV
Micro Channel Plates (MCP)
Examples of circular MCPsExample of pulse signal
Out
put (
50 m
V/d
iv)
Time response (0.5 ns/div)
RisingFalling
FWHM
Examples of gainApplied voltage (kV)
Sensitive to low-energy neutral/charged particles and photonsEffective areas are wide and various in shape.Generate fast sharp pulse signal with high gain up to 107-8
• Not capable of discriminating incident particles/photons• Pulse height varies one by one, independently, e.g., of energy.• High voltage must be applied.
Pictures of Low-Energy Electron Instrument(Reimei Satellite, ISAS/JAXA)
Electrostatic EnergyAnalyzer(Top-hat type)
Detector (MCP)
Pre-amplifier for MCP
High-voltage power supplies for electrostatic energy analyzer (lower) and MCP (upper)
150 mm
Weight: 1.4 kgPower: 2.4 W
Plasma Current Monitor(CRM)
Multi-spectral Auroral Camera(MAC)
Electron Spectrum Analyzer(ESA)
Ion Spectrum Analyzer(ISA)
Appearance of Reimei
MAC ISA
ESA
CRM
GAS
ICU
10
1
0.1
0.01
Elec
tron
(0 –
60 d
eg.)
Ener
gy (k
eV)
Elec
tron
(60
–12
0 de
g.)
Ener
gy (k
eV)
Elec
tron
(120
-18
0 de
g.)
Ener
gy (k
eV)
10
1
0.1
0.0110
1
0.1
0.01UT(09:MM:SS) 10:40 10:45 10:50 10:55 11:00 11:05
ILAT 74.2 73.9 73.7 73.4 73.1 72.8MLT 0.9 0.8 0.8 0.8 0.8 0.8
Electron Energy-Time SpectrogramsDecember 28, 2005
Electron Energy-Time Spectrograms and Aurora ImagesDecember 26, 2005
UT(09:MM:SS) 10:40 10:45 10:50 10:55 11:00 11:05ILAT 74.2 73.9 73.7 73.4 73.1 72.8MLT 0.9 0.8 0.8 0.8 0.8 0.8
Principle and Techniquefor Space Plasma/Particle Measurement
・Thermal energy 0.01 ~ 30 eVI. Langmuir probe
・Low energy 10 eV ~ 30 keVI. Electrostatic energy analyzerII. Micro-channel plate (MCP) or channel electron multiplier
(CEM)・Medium energy 10 keV ~ 100 keV
I. Electrostatic energy analyzer II. MCP or avalanche photo diode (APD)
・High energy 30 keV ~ 2 MeVI. Solid state detector (SSD)
・Extremely high energy 300 keV ~ 20 MeVI. SSD, Scintillator + photomultiplier
Electron energy/flight directions analyses
Avalanche Photo Diode (APD)Rough energy analysis for several - 100 keV electrons with high efficiencyEnough to apply about 100 V
Combination of cusp-type electrostatic energy analyzer and APD for medium-energy electron measurement
Array of APDsArray of APDs[c.f. Ogasawara et al., 2006][c.f. Ogasawara et al., 2006]
CuspCusp--type electrostatic analyzertype electrostatic analyzer[c.f. Kasahara et al., 2006][c.f. Kasahara et al., 2006]
Calibration Facility (Beam Line and Vacuum Chamber)
High-voltage powersupply (+50 kV)
High-voltage powersupply (+150 kV)
Ionization source withmass sepaator and beam expander
Isolation tube with linear accelerator
IsolationTransformer(200 kV)
Vacuum chamber
Turntablesand X-stage
End