201
Scientific targets • P h y s ic a l p ro c e s s i n p la s m a u n iv e rs e ( m ic ro s c a le ) –Particle acceleration in space plasma –Energy transfer in magnetosphere around planets –Release of magnetic energy and energy transfer to space plasma • M e a s u re m e n t o f ra d ia ti o n e n v ir o n m e n t (m a c ro s c a le )
–Distribution of energetic particles in solar system –Dynamics of Heliosphere with fluxes of particles (spectrum and time variation)
We can not see what is happening in interplanetary space unless we go there. Ex. Magnetic Field, particles, solar wind (plasma). In-situ measurements by space plasma mission are important to study,
Activity of Development fo r P a rt ic le D e te c to rs • T w o m a in g ro u p s i n J A X A – IS A S f o r s c ie n ti fi c m is s io n s • Development for scientific missions • E x p lo ra ti o n o f p la n e t m is s io n s • N e w d e te c to rs o p ti m iz e d f o r s c ie n ti fi c t a rg e ts in e a c h m is s io n – IA T f o r m e a s u re m e n t o f ra d ia ti o n e n v ir o n m e n t • M e a s u re m e n t o f ra d ia ti o n e n v ir o n m e n t fo r satellite in order to investigate the e ff e c t o f ra d ia ti o n d a m a g e i n n e w t e s t in s tr u m e n ts a n d n e w e le c tr ic p a rt s
In tr o o n h e a v y io n instruments in JAXA and requirements fo r th e s p a c e p la s m a a p p li c a ti o n s T a k e s h i T a k a s h im a ISAS/JAXA
This document is provided by JAXA.
202
C o n fi g u ra ti o n • C u s p t y p e e le c tr o s ta ti c a n a ly s e r
–curvature radius ~ sensor diameter –minimises sensor size with full azimuthal angle coverage• T o F u n it o p ti m is e d f o r c o m b in a ti o n w it h c u s p t y p e ESA
Cusp type electrostatic analyser Time-of-Flight unit including SSDs SSDs (20[mm]x20[mm] strip type x~25) MCP
start electrons
ions carbon foils stop electrons
Energy : 10 - 200 keV G=2.2x10-2[cm2 sr keV/ keV] ΔE/E=15% Size 250mmΦ x 200mm
M e d iu m E n e rg y P a rt ic le a n a ly z e r (M E P )
Energy range [keV/q]~10-190 FOV(in 1 spin) [sr]4π g-factor [cm2sr keV/keV/ 22.5o]1.4x10-3 ΔE/E18% Energy steps16 Angle Res.[deg]~25 3D Spectrum [sec]~3 (spin period)
(m / q )/ Δ (m / q ) ~ 6 MCP
SSSDs
Carbon thin foil
220 mm
P la s m a i n s tr u m e n t L o w E n e rg y P a rt ic le ( L E P )
Incident ion Detector (MCP)With larger energy With smaller energy Target energy particles
Spherical deflector Electric field (Sweep to energy ) Energy Range : eV --- a few 10 keV/q Size : about 150mm x 100mm
O b s e rv a ti o n o f e n e rg y r a n g e f o r s p a c e p la s m a m is s io n s E X . E R G 5 keV 30 keV 100 keV 3000 keV LEP MEP H E P X E P
With New technology
10 eV
Plasma wave Ring Current Radiation Particles
Electric field analyzer : E/q Electric field analyzer TOF + SSD : m, E, q TOF + SSD : m, E Multi-layer SSD : z, E 10 eV – 40 keV (ion/electron) 10 keV – 120 keV (ion) 10 keV – 100keV (electron) 30 keV – 1000 keV (proton/electron) 60keV – 1200 keV (oxygen) 1 MeV -10 MeV (electron)? Plasma wave ??
This document is provided by JAXA.
203
Δ E x E p a rt ic le i d e n ti fi c a ti o n m e th o d
Incident Particle (Z, A, E) ΔE part E part ΔE: thickness X1(ΔX) deposited E ΔE1 E: thickness particle stop deposited E ErR1 : total range Rr : range in E part ΔE x E scatter plots accelerated Fe beam test at LBL
ΔX = X1/cosθ To measure the incident angle of particle by two PSDs is important
θPSD1 PSD2 Fe
High Energy Particle instrument (HEP2)
CPS CharacteristicsPhotographs and the diagram of the CPS HID ( High-energy Isotope Detector ) 4 detectors and 32 ch preamplifiers and shaping amplifiers70 mm
70m m PSD-1 PSD-2 B+ Si (Li) x 6 ΔΕxE method
High Energy Particle instrument (HEP1) TOF+SSD type
Energy range : 100 – 2300 keV for ion 100 – 1700 keV for electron G-factor : 0.015 cm2 str for TOF 0.027 cm2 str for ΔE-E Si detector : ΔE Si : 3 mmφ 9µm E Si : 14 mmφ 460µm Ion sensorElectron sensorm/q(T OF)
counts O
8+O
7+m/q(T OF)
E(SSD) O
8+O
7+2E
07E
08E
0H e
2+H e
2+Only T OF T OF+SSD
H
+H
+E
0Not identify He
2+and O
7+without SSD-ener gy Separate He
2+and O
7+ions with SSD-ener gy
TOFSSDThis document is provided by JAXA.
204
ERG mission: scientific small satellite program Science : relativistic electron acceleration in the radiation belt Launch : after 2012 Strong radiation environment SCOPE/CrossScale mission : formation flight Science : cross scale coupling and plasma universe Launch : after 2017 Jupiter exploration mission: Science : particle acceleration and binary star Launch : after 2025 Strongest radiation environment
T a rg e t m is s io n s
W h a t w e n e e d a n d r e q u ir e m e n ts to G e a n t4 i n o u r s p a c e m is s io n s ? • D e s ig n t o o ls f o r a d e v e lo p m e n t o f n e w d e te c to r – R e d u c e c o n ta m in a ti o n o f h ig h e n e rg y p a rt ic le s
•Especially for exploration missions, mass resource is very severe and then the instrument need to be designed with balance between mass resource and performance– N o t fo r s c ie n ti s t b u t fo r e n g in e e r to d e s ig n in s tr u m e n ts
•It is too difficult to use Geant4 in order to design new instruments for engineer. Ex if can use CAD data, it is comfortable •typical environment template –Low earth orbit, Radiation belt –Interplanetary, planetary orbiter (Moon, Mars, Jupiter etc)W h a t w e n e e d a n d r e q u ir e m e n ts t o G e a n t4 i n o u r s p a c e m is s io n s ? • D a ta a n a ly s is : a lr e a d y o b s e rv e d d a ta – B a c k g ro u n d r e je c ti o n f ro m o b s e rv a ti o n d a ta • C o n ta m in a ti o n o f h ig h e n e rg y p a rt ic le s b a c k g ro u n d t h a t p a s s t h ro u g h t h e i n s tr u m e n t b o d y • T ra c e o f p a rt ic le t ra c k s i n s e n s o r w it h e n e rg y ra n g e b e tw e e n e V t o G e V ( d e p o s it e d e n e rg y c a lc u la ti o n ) a n d f ra g m e n ta ti o n o f in c id e n t p a rt ic le • S e c o n d a ry e le c tr o n e m it te d f ro m m a te ri a ls b y h ig h e n e rg y p a rt ic le s
This document is provided by JAXA.
