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Monitor of All-Sky X-ray Image on KIBO

Monitor of All-Sky X-ray Image on KIBO. Oct. 17, 2005 IAC@Fukuoka. K. Kawasaki M. Matsuoka, S. Ueno, H. Tomida, N.Kuramata, T. Yokota, M. Morii Japan Arerospace Exploration Agency (JAXA) http://www-maxi.tksc.jaxa.jp. Contents MAXI overview MAXI Payload

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Monitor of All-Sky X-ray Image on KIBO

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  1. Monitor of All-Sky X-ray Image on KIBO Oct. 17, 2005 IAC@Fukuoka K. Kawasaki M. Matsuoka, S. Ueno, H. Tomida, N.Kuramata, T. Yokota, M. Morii Japan Arerospace Exploration Agency (JAXA) http://www-maxi.tksc.jaxa.jp

  2. Contents • MAXI overview • MAXI Payload • Attached payload vs. Satellite mission • Summary MAXI Thermal Mechanical Model

  3. MAXI Kibo ISS motion Overview of MAXI • Attached payload on Kibo-EF (Exposed Facility) • All Sky X-ray Monitor on ISS • Scanning all sky every 90 min • launched by H2B Rocket or Space Shuttle in 2008 • Mission life ~ 2years

  4. Overview of MAXI • Two Types of X-ray Detectors (Slit Camera) • Gas Slit Camera (GSC) • Solid-state Slit Camera (SSC) • Scientific Goals • Long-term AGN Variability • Diffuse X-ray Sources • GRB afterglow • X-ray Novae and Alert

  5. Zenith FOV Scanning direction FOV (Vertical) Slit cameras ISS moving direction Position sensitive detector (One-dimension) FOV (Horizontal) Earth FOV of MAXI slit

  6. FOV of GSC & SSC

  7. MAXI Payload 180cm 107cm 80cm Total weight: 535 kg

  8. Radiator for X-ray CCDs PIU (KIBO-EF Interface) Grapple Fixture Electronics Optical Star Sensor ATCS Solid-state Slit Cameras (SSC) Ring Laser Gyro Gas Slit Cameras (GSC) Carrier Interface MAXI Payload

  9. Outline of the MAXI instrument

  10. Slit GSC (Counter,Slit & Collimators) 358 mm Counter

  11. Slit Collimator 200mm CCDs 30cm Solid-State Slit Camera(SSC) ΔE ~ 145 eV @ 6 keV • 1024x1024 pixel CCD Osaka Univ./Hamamatsu Photonics • MAXI employs 2 SSCs • Each SSC has 16 CCD chips with one-stage Peltier cooler • Operated at –60℃ • Effective area ～100cm2 x 2

  12. Evaporator Condensers Loop Heat Pipe Radiator System LHP+CCD(EM) Thermal Vacuum Test

  13. 1.5 deg (FWHM) 160 deg MAXI Performance 1 orbit = 90 min Alert delay

  14. Resources

  15. Interface with Kibo (Mechanical) PIU: Payload Interface Unit (I/F with KIBO-EF) Grapple Fixture (I/F with Robotics arm) PAM-PU: Payload Attach Mechanism – Passive Unit (Carrier Interface)

  16. Interface with Kibo(Electrical Power, Data communication) Power Distributor Data Processor Mission Data Processor

  17. Interface with Kibo(ATCS: Active Thermal Control System) Cold Plates Accumulators

  18. MAXI Data Communication System

  19. Attached payload vs. Satellite • Strong points: • MAXI utilizes ISS/Kibo’s resources so that MAXI payload design is rather simple. • - Electrical power, Coolant (ATCS) • > Neither solar panels nor radiator panels are needed. • GN&C (Attitude and altitude control) of ISS • > Neither attitude control system nor thruster system is needed. • Command/Telemetry system of ISS. • > MAXI ground system is rather simple.

  20. Attached payload vs. Satellite Strong points 2) More resources (mass and volume, and man power) can be provided to the instruments. 3) ISS attitude and orbit is suitable for all-sky monitor missions. 4) On-orbit inspection by crew or TV camera. (Repair by EVA is possible, but MAXI is not designed for it.) 5) Potential capability for retrieval and upgrade on the ground. (However, MAXI will be disposed of in orbit.)

  21. Attached payload vs. Satellite • Weak points • Continuous communication is not feasible (50~70%). The situation will be worse until the Assembly Complete (AC). • 2) We have to interface with several other systems (Kibo, ISS, carrier, and robotics), making its I/F design complicated. • 3) Safety design requirements from manned space system may lead to rather a conservative design. • 4) Launch schedule ambiguity. • 5) Interference of FOV by the ISS structure, solar panels, and radiator panels is rather significant.

  22. Improvement after CDR (Risk Mitigation) • 1) Attitude Determination System onboard. • To compensate data downlink missing/delay, and to alert as soon as possible. • 2) LHPRS shutdown / start-up Heater are added. • To survive at any contingency modes at assembly phase. • 3) Robust launch capability • Corresponding to the earliest launch opportunity, both HTV and Shuttle.

  23. Launch Schedule August, 2008 ? ELM-ES H-IIB Transfer Vehicle (HTV) Space Shuttle H-IIB Rocket

  24. Summary • MAXI : all-sky X-ray monitor on Kibo/ISS • Two-types of Detectors • GSCs & SSCs covering 0.5-30 keV band • 2008 August ~ 2 years • Flight Hardware is being fabricated. Some improvement has done for risk mitigation. • Attached payload design is simple. • Our experience was presented. Those will be beneficial to subsequent Kibo-EF missions.

  25. - END - http://www-maxi.tksc.jaxa.jp

  26. Systematic error level MAXI Performance orbit day week 1977-79 Alert delay NASA

  27. RXTE ASM 1 orbit (30 sources) 1 day (100 sources) 1 week (1000 sources) Sensitivity of MAXI

  28. MAXI achieves the same sensitivity as this image by one month observation.

  29. MAXI FOV Zenithal View Horizontal View Sky View from MAXI

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