1. Astro-E2 and Japanese future space programs for high energy astrophysics Astro-E2 NeXT XEUS Small satellite programs Tadayasu Dotani (ISAS)

2. Astro-E2 A 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

3. Scientific Instruments on-board Astro-E2 XRT HXD Pre-collimator (Astro-E2)

4. Scientific Instruments on-board Astro-E2 XRS XIS Mechanical Cooler (Astro-E2)

5. Astro-E2: Effective Areas XRT+FPD Non-imaging Detector

6. Resolving power of the micro-calorimeter (XRS)

7. Effective Area of XRS

8. 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.

9. 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

10. Comparison of the 3 X-ray observatories XMM-Newton Chandra Astro-E2

11. 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

12. Key Technology: supermirror Soft X-rays Hard X-rays Pt C Incident angle = 0.169 deg 15 blocks 95 layers Model calculation Periodic length = 3–12 nm Bragg reflection

13. Effective Area of the Supermirror Focal length = 12m 8 m 6 m 60 cm 40 cm 12 cm Number of nest = 272

14. Balloon Experiment of the Supermirror InFOC  S 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

15. Development of Detectors for NeXT (1) TES micro-calorimeter Superconducting magnet Heat switch Salt pill (2) Hybrid detector Upper 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

16. XEUS X-ray Evolving Universe Spectroscopy mission Effective area 30 m 2 (@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 m 2 ) to XEUS2 (30 m 2 ) using ISS. Concept design are being made under ESA/Japan collaboration. Launch: 2013 or later.

17. Formation Flight Mirror 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

18. Upgrading the mirror satellite: MSC1→MSC2

19. 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.

20. 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 possibilities: 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

21. Summary of the future programs 2005 2010 2015 Fabrication Tests Launch Astro-E2 Fabrication Tests Launch Design NeXT XEUS1 XEUS2 Fabrication Tests Design Basic research Small satellite programs