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