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Astro-E2 and Japanese future space programs for high energy astrophysic
s
•Astro-E2•NeXT•XEUS•Small satellite programs
Tadayasu Dotani (ISAS)
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Astro-E2A powerful X-ray observatory developed under Japan-US collaboration. It is a recovery mission of Astro-E, which was failed in February, 2000.
•High spectral resolution (E~10 eV) with a micro-calorimeter.•Very large, simultaneous bandwidth (0.5–600 keV).•Large collecting area with high sensitivity.•Launch: 2005/1-2
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Scientific Instruments on-board Astro-E2
XRT
HXD
Pre-collimator (Astro-E2)
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Scientific Instruments on-board Astro-E2
XRS
XIS
Mechanical Cooler (Astro-E2)
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Astro-E2: Effective AreasXRT+FPD Non-imaging Detector
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Resolving power of the micro-calorimeter (XRS)
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Effective Area of XRS
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Simulated Spectra: A2199 (higher energy part)
Astro-E2: 100 ks
BeppoSAX observations indicated the presence of a hard tail.
ASCA GIS
Hard tail can be clearly detected.
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Simulated Spectra: A2199 (lower energy part)
Astro-E2: 100 ks
XIS
XRS
Triplet lines from He-like iron are easily resolved.
Good statistics of XIS and high resolution of XRS work complementary.
Z=0.03
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Comparison of the 3 X-ray observatories
XMM-NewtonChandra
Astro-E2
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NeXT(Next X-ray telescope)
• X-ray supermirror capable of focusing up to ~80 keV.
• Hybrid detector covering 0.1–80 keV.
• Large format TES calorimeter for high-resolution imaging spectroscopy.
• Soft -ray detector with high sensitivity.
• Launch: ~2010?
A next generation X-ray observatory following Astro-E2
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Key Technology: supermirrorSoft X-rays
Hard X-raysPtC
• Incident angle = 0.169 deg
• 15 blocks
• 95 layers
Model calculation
• Periodic length = 3–12 nm
Bragg reflection
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Effective Area of the Supermirror
Focal length = 12m
8 m
6 m
60 cm
40 cm12 cm
Number of nest= 272
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Balloon Experiment of the Supermirror InFOCS
•Collaboration between Nagoya Univ. & NASA/GSFC•First imaging observation in 20-40 keV with the supermirror.•Launched on July 5, 2001, from Texas, USA.•Succeeded to observe Cyg X-1
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Development of Detectors for NeXT
(1) TES micro-calorimeter
Superconducting magnet
Heat switch Salt pill
(2) Hybrid detectorUpper stage: Thinned CCD (<10 keV)
Lower stage: Pixel detector (>10 keV) CdTe, etc.
3-side buttable CCD developed by HPK
VA2TA(IDE)
CdTe CdTe pixel detector with analog VLSI
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XEUSX-ray Evolving Universe Spectroscopy mission
• Effective area 30 m2 (@1keV) with a focal length of 50 m.
• Formation flight between the mirror satellite (MSC) and the detector satellite (DSC).
• Mirror satellite evolves from XEUS1 (6 m2) to XEUS2 (30 m2) using ISS.
• Concept design are being made under ESA/Japan collaboration.
• Launch: 2013 or later.
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Formation FlightMirror satellite(MSC1)
Detector satellite
50 m
Mirror
Optical bench
Thermal baffles, launch support structure
Optical baffle
•Mirror satellite takes a Kepler orbit.•Detector satellite takes a non-Kepler orbit to follow the mirror satellite.•Alignment accuracy of the two satellites should be better than 1mm.
Docking port
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Upgrading the mirror satellite: MSC1→MSC2
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XEUS - Sensitivity Comparison
• A limiting sensitivity of 4×10-18 erg cm-2 s-1 – about 250 times deeper than XMM-Newton.
The sensitivity of XEUS is well matched to that of the new generation of observatories working in other wavebands.
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Small Satellite Programs
• Small satellites: 10 kg – a few hundreds kg.• Appropriate launch system (including vehicles) needs
to be established.• Small satellite programs include following possibilitie
s: XMAS - X-ray milli-Arcsecond Satellite DELUXS - Diffuse Emission from Large-scale Universe X-ray Spectrometer Solid-state Compton telescope to detect polarization in GRB Large area CCD satellite Wide-field, hard X-ray survey satellite Wide-field, imaging survey satellite with soft X-ray telescope X-ray polarization detector
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Summary of the future programs
2005 2010 2015
Fabrication TestsLaunch
Astro-E2
Fabrication TestsLaunch
DesignNeXT
XEUS1 XEUS2Fabrication TestsDesignBasic research
Small satellite programs