090423_EXCEED_Web版
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1
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4 A 3 B X 3 LEO (Flexible Standard Bus) C 2
5 3
6 kg SPICA ASTRO-H GEOTAIL GINGA YOHKOH AKEBONO NOZOMI ASCA HITEN ASTRO-G PLANET-C HAYABUSA SPRINT 5 JAXA NOTE 2009
7 3»»»»»» kg400kg 300W 1kW 3 1 4
8 DE 5
9 - - (SADA) - - GPS - IRUSTT EMC I/F A B C = 2 = 3 = 1 9
10 ±Y±X 20W mm 200kg 50Hz30Hz [OPTION] I/F3 [OPTION] fix 2GBDR SpaceWire [OPTION] 1 [DELTA] 11
11 S 2Mbps(QPSK)128 or [OPTION] [DELTA] ORBCOMM 150W [OPTION] 300W [OPTION] 60W 50V BAT50Ah8 [OPTION] BAT35Ah (SSR)MMO [OPTION] 1 [DELTA] 12
12 31 [OPTION] [OPTION] 60rpm Z( / ±30[deg ]) 4 5rpm-Z(± 30[deg]) [OPTION] rpm [DELTA] [OPTION] 3N kg [OPTION] 1 [DELTA] 13
13 LEO3GTO krad [DELTA]EMC [OPTION] 1 [DELTA] 14
14 1SDR RFP (11/18, 12/1)(12/25) MTM, TTM
15 1 GSTOS, SIB2 MTM(1001-)/TTM(1002-) (EUVEUV) (MCP background) MCP20095 MTM(0912-)/TTM(0911-) ()
16 EUV 320kg() 1m 1m 4m 900km 1200km (i=31deg) arc-sec 3
17 EXCEED Mission EUV Spectrometer Aperture baffle Slit viewing camera EUV spectrometer Slit viewing camera Shell structure EUV grating EUV spectrometer electronics component 5-stage MCP detector EUV reflector Small satellite bus module TOPS/EUV Optics 概 要 TOPS mission structure Launching 2012 Mission life more than １year Orbit and control LEO 900 X 1200 Km 3-axis control Pointing accuracy ±1.5arcsec course, STT) 5arcsec (with slit camera) stability ± 5arcsec/120sec ミ ッ シ ョ ン 部 wavelength EUV ((55) nm) instrument EUV spectrometer weight 80 kg Power 200 W telemetry < 0.1 GB/day FOV X 4 (Slit)
18 Comets Astronomical monitor observations
19 Comets Astronomical monitor observations
20 SWCX Io Plasma Torus Comets SWCX Astronomical monitor observations Stellar (exo-solar) cycle, nova
21 Spectrum 11
22 EXCEED EUV
23 EUV EUV EUV 40% 10100eV 10% 60% 30% 10eV EUV EUV 90% Delamere & Bagenal (2003)
24 EUV EUV EUV 40% 10100eV 10% 60% 30% 10eV EUV EUV 90% Delamere & Bagenal (2003)
25 EUV EUV EUV 40% 10100eV 10% 60% 30% 10eV EUV EUV 90% Delamere & Bagenal (2003)
26 ? EUV 1? or MHD 3 8 6RJ RJ 100RJ
27 (1) outward transport 10R J Radial profiles of thermal plasma pressure in the Jovian magnetosphere observed by the Galileo spacecraft (Mauk et al. 2004) 50R J jrco-rotation enforcement current (Hill current) Auroral current system driven by radial transport of plasma from the source at Io. (Cowley et al. 2002).
28 (2) inward transport Whistler Production of synchrotron radiation from Jupiter. (Horne et al. 2008) Interchange() Inwardoutward
29 EUV(Cassini/UVIS) (HST/WFPC2) H 2 Lyman & Werner bands EUVFUV60nm-160nm) S +,S 2+,S 3+, O +,O 2+ (60nm-130nm)
30 EXCEED 2 EUV O + C +, N +
31
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34 Young sun Standard model 70-80% X/EUV
35 Young sun Standard model 70-80% X/EUV
36 Young sun Standard model 70-80% X/EUV
37 Solar wind of a young sun 100 Wood et.al. 2005
38 Solar wind of a young sun 100 Wood et.al. 2005
39 Young sun X (velocity of the present sun) X (flux of the present sun) X X (flux of the present sun) 100 X (flux of the present sun)
40 EXCEED O + 83nm CO 2 H 2 O H 121nm O 130nm O + 83nm
41 Simultaneous observations of a flux of the solar wind, induced exosphere and ionosphere, and the escaping tail their reactions upon the solar wind O+ 83nm Ionosphere Charge exchange (Solar wind) H 121nm O 130nm exosphere EXCEED Mission Slit cell of EUV spectrometer O+ 83nm C+ 133nm N+ 108nm Movie: from ESA Picture: from NASA
42 photons /sec Counts/hour 1σ O +4 /C nm x10-3 ~4x x10-1 ~2x10 1 ~ 1 day H 121 nm O 130 nm ~2x x10 1 ~6x ~1x10 1 8x10 2 ~2x10 3 ~ 10 sec O + 83 nm 7x10-2 ~2x x10 0 ~2x10 1 C nm x10-1 ~2x x10 1 ~7x10 1 ~ 100 sec N nm 7x10-2 ~2x x10 0 ~2x10 1 ~11 O + 83 nm C nm N nm x10-3 ~3x10-1 3x10-3 ~3x10 1 4x10-4 ~4x x10-1 ~3x10 1 1x10-1 ~1x10 3 3x10-2 ~3x10 2 ~ 1 day 34
43 CO 2 CO 2, N 2 N, C, Ar90% 1CO 2 MEX / OMEGA [Chassefiere et al., 2006] EXCEEDC +, N + 35
44 EUV EXCEED 36
45 EUV EXCEED Pioneer Venus Orbiter!"# PVOXY PVODPQ RS$%&!".TU VW2 H I J5D>K&LMNO 36
46 EXCEED Observation opportunity
47 EXCEED Mission EUV Spectrometer Aperture baffle Slit viewing camera EUV spectrometer Slit viewing camera Shell structure EUV grating EUV spectrometer electronics component 5-stage MCP detector EUV reflector Small satellite bus module TOPS/EUV Optics 概 要 TOPS mission structure Launching 2012 Mission life more than １year Orbit and control LEO 900 X 1200 Km 3-axis control Pointing accuracy ±1.5arcsec course, STT) 5arcsec (with slit camera) stability ± 5arcsec/120sec ミ ッ シ ョ ン 部 wavelength EUV ((55) nm) instrument EUV spectrometer weight 80 kg Power 200 W telemetry < 0.1 GB/day FOV X 4 (Slit)
48 Mission EUV EUV EUV MCP CCD MDP
49 Mission EUV EUV 20 cm SiC + SiC-CVD() EUV Heritage MCP
50 Mission CCD (Planet-C IR1 ) MDP
51 Mission Bus: SpW x 2ch µhcu ) SpW CMD HK, TLM SpW Hardware I/F -Bus SpW x 2 -Mission SpW x 12 RS422 x 2 Software I/F (in MDP) -Min H/W -Med OS/Driver/ Middleware -Max Software SpWR SpW SpW SpW SpW SpW SpW CMD CMD HK, TLM HK TLM SMU (Bus) CCD cam. sensor CCD cam. mechanics EUV sensor NIC08 SpW Cntrl Data, status, HK Cntrl status, HK CMD HK, TLM RS422 (or SpW) SpW MDP SpW x 3ch RS422 x 2ch 42 V4.1 (080401)
52 0.05mm 1.00mm 43 V4.1 (080401)
53 光学系 試作を実施中
54 SiC-CVD Sample
55 (1) MCP
56
57 EXCEED
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