Astro-E2 and Japanese future space programs for high energy astrophysic

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•Astro-E2•NeXT•XEUS•Small satellite programs

Tadayasu Dotani (ISAS)

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

Scientific Instruments on-board Astro-E2

XRT

HXD

Pre-collimator (Astro-E2)

Scientific Instruments on-board Astro-E2

XRS

XIS

Mechanical Cooler (Astro-E2)

Astro-E2: Effective AreasXRT+FPD Non-imaging Detector

Resolving power of the micro-calorimeter (XRS)

Effective Area of XRS

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.

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

Comparison of the 3 X-ray observatories

XMM-NewtonChandra

Astro-E2

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

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

Effective Area of the Supermirror

Focal length = 12m

8 m

6 m

60 cm

40 cm12 cm

Number of nest= 272

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

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

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.

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

Upgrading the mirror satellite: MSC1→MSC2

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.

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

Summary of the future programs

2005 2010 2015

Fabrication TestsLaunch

Astro-E2

Fabrication TestsLaunch

DesignNeXT

XEUS1 XEUS2Fabrication TestsDesignBasic research

Small satellite programs