MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Monitor of All-Sky X-ray Image on KIBO K. Kawasaki M. Matsuoka, S. Ueno, H. Tomida, N.Kuramata, T. Yokota, M. Morii Japan Arerospace Exploration Agency (JAXA) Oct. 17, 2005

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Contents - MAXI overview - MAXI Payload - Attached payload vs. Satellite mission - Summary MAXI Thermal Mechanical Model

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka 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 Kibo ISS motion MAXI

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka 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

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka FOV of MAXI slit

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka FOV of GSC & SSC

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Total weight: 535 kg MAXI Payload 180cm 107cm 80cm

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka MAXI Payload ATCSElectronics Grapple Fixture PIU (KIBO-EF Interface) Carrier Interface Optical Star Sensor Ring Laser Gyro Gas Slit Cameras (GSC) Solid-state Slit Cameras (SSC) Radiator for X-ray CCDs

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Outline of the MAXI instrument GSCSSC Detector Energy Range Effective Area Number of camera Field of View Energy Resolution Spatial Resolution Proportional Counter Xe+CO 2 (1%) gas 2-30keV 5350 cm x 160 degree 18% 1 mm X-ray CCD keV 200 cm x 90 degree mm (pixel size)

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka GSC ( Counter,Slit & Collimators ) Slit Counter 358 mm

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka ΔE ~ 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 ～ 100cm 2 x 2 Solid-State Slit Camera (SSC) 30cm CCDs Collimator Slit 200mm

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Loop Heat Pipe Radiator System LHP+CCD(EM) Thermal Vacuum Test Evaporator Condensers

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Alertdelay MAXI Performance 160 deg 1.5 deg (FWHM) 1 orbit = 90 min GSC (Gas cam) SSC (CCD cam.) Sky Coverage Instant 2 %1.3 % 1 orbit90-98% Max 70% ImagingPSF1.5 deg (FWHM) PositionAccuracy < 6 arcmin Spectroscopy 2-30 keV ( 18 % ) keV ( <150 eV) Timing Accuracy 120  sec 3-16 sec Sensitiv- ity (5  ) 1 orbit 10 mCrab20 mCrab 1 week 1 mCrab 2 mCrab Real data (> 50 % ) From Detection to Alert < 30 sec (Goal) Stored (< 50 %) From Detection to Alert 20 min – 3 hours User Interf- ace AlertInternet (mail, socket) DataImage, Spectum, Light curve via Web browser

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Weight Envelope 535kg L1850xW800xH1065mm KIBO- EF Power Survival Power Data Coolant (ATCS) P/L Support data 120Vdc 350.8W(typ) 120Vdc 96.0W(peak) MIL-STD-1553B 48kbps(max) IEEE802.3/10BASE-T 600kbps(max) FC ℃ ~24 ℃ 155kg/hr ISS GN&C data 、 Solar panel joint rotation angle, etc ELM-ESSurvival Power 120Vdc ＠ JEM-EF 116.6W(peak) 28Vdc ＠ STS 104W(peak) HTV-EPSurvival Power 120Vdc ＠ JEM-EF 177.2W(peak) 50Vdc ＠ HTV 66.3W(peak) Resources

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Interface with Kibo (Mechanical) Grapple Fixture (I/F with Robotics arm) PIU: Payload Interface Unit (I/F with KIBO-EF) PAM-PU: Payload Attach Mechanism – Passive Unit (Carrier Interface) (Carrier Interface)

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Interface with Kibo (Electrical Power, Data communication) Power Distributor Data Processor Mission Data Processor

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Interface with Kibo (ATCS: Active Thermal Control System) Cold Plates Accumulators

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka MAXI Data Communication System

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Attached payload vs. Satellite Strong points: 1)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.

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka 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.)

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Attached payload vs. Satellite Weak points 1)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.

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka 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.

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka H-IIB Transfer Vehicle (HTV) Launch Schedule August, 2008 ? Space Shuttle H-IIB Rocket ELM-ES

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Summary MAXI : all-sky X-ray monitor on Kibo/ISS Two-types of Detectors GSCs & SSCs covering 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.

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka - END -

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka GSC (Gas cam) SSC (CCD cam.) Sky Coverage Instant 2 %1.3 % 1 orbit90-98% Max 70% ImagingPSF1.5 deg (FWHM) PositionAccuracy < 6 arcmin Spectroscopy 2-30 keV ( 18 % ) keV ( <150 eV) Timing Accuracy 120  sec 3-16 sec Sensitiv- ity (5  ) 1 orbit 10 mCrab20 mCrab 1 week 1 mCrab 2 mCrab Real data (> 50 % ) From Detection to Alert < 30 sec (Goal) Stored (< 50 %) From Detection to Alert 20 min – 3 hours User Interf- ace AlertInternet (mail, socket) DataImage, Spectum, Light curve via Web browser Alertdelay NASA MAXI Performance Systematic error level orbit dayweek

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Sensitivity of MAXI 1 orbit (30 sources) 1 day (100 sources) 1 week (1000 sources) RXTE ASM

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka MAXI achieves the same sensitivity as this image by one month observation.

MAXI - Monitor of All-sky X-ray Image 56 th INTERNATIONAL ASTRONAUTICAL COGRESS Oct.17, 2005, Fukuoka Horizontal View Zenithal View MAXI FOV Sky View from MAXI