An Overview of MAXI onboard JEM-EF of the International Space
Station
M.Matsuoka*a, K.Kawasakia, S.Ueno a, H.Tomidaa, M.Kohamaa, M.Ishikawaa, H.Katayamaa,
M.Suzukia, T.Miyakawaa, T.Miharab, N.Isobeb, H.Tsunemic, E.Miyatac, H.Negoro d, M.Nakajima d,
N.Kawaie, J.Kataokae, A.Yoshidaf, K.Yamaokaf and M.Moriig
a
JAXA, Tsukuba, Ibaraki 305-8505, Japan; bRIKEN, Wako, Saitama 351-0198, Japan; cOsaka
Univ. Toyonaka, Osaka 560-0043, Japan ; dNihon Uni., Chiyoda-ku, Tokyo 101-0062, Japan ;eTokyo Institute of Technology, Meguro-ku, Tokyo 152-8551, Japan; fAoyama-gakuin Univ.,
Sagamihara, Kanagawa 229-8558, Japan; gRikkyo Univ. , Toshima-ku, Tokyo 171-8501, Japan
ABSTRACTMAXI is the first payload to be attached on JEM-EF (Kibo exposed facility) of ISS. It provides an all sky X-ray image
every ISS orbit. If MAXI scans the sky during one week, it could make a milli-Crab X-ray all sky map excluding brightregion around the sun. Thus, MAXI does not only inform X-ray novae and transients rapidly to world astronomers if
once they occur, but also observes long-term variability of Galactic and extra-Galactic X-ray sources. MAXI also
provides an X-ray source catalogue at that time with diffuse cosmic X-ray background.
MAXI consists of two kinds of detectors, position sensitive gas-proportional counters for 2-30 keV X-rays and CCD
cameras for 0.5-10 keV X-rays. All instruments of MAXI are now in final phase of pre-launching tests of their flight
modules. We are also carrying out performance tests for X-ray detectors and collimators. Data processing and analysis
software including alert system on ground are being developed by mission team.
In this paper we report an overview of final instruments of MAXI and capability of MAXI.
Keywords: MAXI, JEM-EF, ISS, ASM, X-ray nova, X-ray transient, Monitor of All sky X-ray Image, All Sky Monitor

1. INTRODUCTIONMAXI is an acronym of “Monitor of All-sky X-ray Image”. MAXI is the first payload of astronomical observations
from JEM-EF (“Kibo” exposed facility) on ISS.
All sky X-ray monitors (ASMs) have been occasionally performed as a payload on some satellites since 1960 era. So far
performed ASMs make progress every decade at the point of X-ray detectability. Most ASMs have detected X-ray novae
and X-ray transients in our Galaxy and informed these results to general astronomers to promote to observe the objects indetail with multi-wavelength observational instruments. The data of long-term variability of Galactic X-ray sources havebeen accumulated in many cases and thus produced a great progress of physics of compact X-ray sources.
The ASM of RXTE1,2. has worked to monitor Galactic X-ray sources systematically since 1995, while variabilities oflimited bright extra-Galactic X-ray sources such as AGNs have been provided. A recent gamma-ray burst monitor
satellite, Swift3., has observed X-ray intensity of considerable number of AGNs in the energy band of 15-200 keV. Thus
Swift has contributed to variability physics of AGNs. Some of BL Lac objects produce ultra high energy gamma-ray
around Tev energy in their active phase4.. Cherenkov telescopes on ground for Tev gamma-ray observations cooperatewith useful information of AGN activity provided by ASM.
In this situation MAXI project has been prepared since 1998. MAXI was approved as the first astronomical payload
attached on JEM-EF of ISS in 19985.. Since the construction of ISS has been delayed so long time, time schedule of
MAXI completion has been also delayed. Now it is decided that MAXI will be carried to ISS together with structure of*matsuoka.masaru@jaxa.jp , phone 81-29-868-3780; fax 81-29-868-3956

JEM-EF by Space Shuttle in 2009. The design of MAXI is conservative, but the detectability every satellite orbit is in
the best level among almost all sky monitors. This means that MAXI can monitor many AGNs in all sky. Detectabilityof MAXI is one milli-Crab or less than one milli Crab for one week observation.
MAXI is now in final phase of pre-launching preparation. All the flight unit components of MAXI have been fabricatedand then they are in final test phase and MAXI integration test is going on. Software development for data processing
and data analysis is also in progress.
In this paper we report properties of instrument as well as an overview of a final hardware of MAXI.

2. OBJECTIVES OF MAXIMAXI observes a certain object for limited time every ISS orbit with slit
cameras. The X-ray detector is sensitive to one dimensional image through aslit, where the wide field of view through the slit spans the sky perpendicular
to ISS moving. The scanning image for a certain object is obtained withtriangular response of a slat collimator according to ISS moving. A cross pointof the slit image and the triangular response image corresponds to a source
location on the sky (see in Fig.1).
Objects located along a great circle stays for 30-40 sec in a field of view of
MAXI, where this time of stay is the shortest in MAXI field. For other objects
in slanted field from the great circle we achieve longer observations. Anytarget comes repeatedly in a field of MAXI every ISS orbital period, 90 min.
In this situation MAXI can monitor a short time scale variability intermittently
for bright X-ray sources such as X-ray pulsars and low mass X-ray binaries.
For weak X-ray sources MAXI can monitor their variability in a time scale of
90 min or longer if we integrate their data6,7. .

Fig. 1. A point spread function of MAXI
camera for a point X-ray source. ISS
scanning direction shows triangularresponse, while a slit width image showsa trapezoid basically.

MAXI consists of two kinds of X-ray detectors, that is, gas proportional counters with 2-30 keV band and CCDs with
0.5-10 keV band. We call a former set as GSC, while a latter set as SSC. A main role of MAXI is to monitor many Xray sources in a long term scale longer than 90 minutes. Thus astrophysical objectives of MAXI are as follows;(1) Once MAXI discovers an X-ray nova or a transient X-ray source, or a flare-up of AGNs, MAXI alerts the discovery
to multi-wavelength astronomers. MAXI will provide rapid alert system in nearly real time using automatic analysis
system. Then it enables us to make follow-up observations with optical telescopes, radio telescopes, and ultra-highenergy gamma-ray observatories as well as other X-ray or infrared space observatories. This scenario is mosttypical for ASM performance.
(2) For a long term variability of Galactic and extra-Galactic objects, MAXI provides X-ray light curves of many AGNs,
where time scale of data point depends on the intensity; e.g., MAXI will provide a light curve in data point every
week for about 100 AGNs or more. Mission life time of MAXI is two years or more. Therefore, we expect
periodic or aperiodic variability of the AGNs in reasonable time scale.
(3) MAXI provides a reasonable X-ray source catalogue using all data. Since most X-ray sources are variable, the yearby-year catalogue plays a historical importance. A global distribution and variability of AGNs will be observed.
(4) MAXI provides X-ray spectra for bright X-ray sources in the energy band of 0.5-30 keV. In low energy band CCD
camera obtains emission lines such as OVII, OVIII and so on from hot region of supernova remnants with better
energy resolution.
(5) Recent SUZAKU observations of X-ray emission lines in geocorona have discovered the recombination lines ofionized carbon and oxygen which are variable8.. It is believed that distant hot component from supernova remnants
is overlaid by this geocorona. It is expected that repeated global observations by MAXI SSC’s CCD camera could
discriminate two components as well as research of geocorona.
(6) Recently remarkable progress of gamma-ray burst has been achieved with specific gamma-ray burst satellites,
HETE-29. and Swift3.. Rapid follow-up optical observations are desired for cosmological distant gamma-ray bursts.

It is believed that gamma-ray bursts play as a probe to investigate cosmological distant region and thus the first stepof star formation era10.. MAXI is possible to catch a gamma-ray burst and inform its location rapidly. A large
optical telescope enables us to make detailed spectroscopic observations.
(7) MAXI will make observation cooperated with GLAST11. as well as SUZAKU, XMM-Newton and Chandra. If
MAXI fortunately obtains somewhat interesting episode of X-ray sources, large pointing X-ray telescopes could
make follow-up observations for more detailed investigation. Gamma-ray large telescope, GLAST, will be launchedsoon. GLAST is one of gamma-ray all sky monitors. Therefore, MAXI and GLAST are possible to obtain thevariability from the same target with X-ray band and gamma-ray band simultaneously. Such observation might carry
the first interesting result.
(8) MAXI has a GPS receiver to keep time accuracy of 100 µsec, it is possible to make phase analysis and folding formilli-sec pulsars.

3. SPECIFICATION OF MAXIMAXI is the first astronomical observation payload on a big space structure, the ISS. It is considered that a small
payload should not be selfish to compromise with much constraint of ISS. In order to realize MAXI in early phase as thefirst payload on JEM-EF, we have designed MAXI in the following concept.
(1) The payload makes fit a standard one on JEM-EF; i.e. the weight and size as well as interface are limited.
(2) The payload makes fit the environment on ISS/JEM-EF. The orbit and attitude of ISS are also acceptable for the
payload. It performs scanning observations for sky, but does not require a celestial pointing observation.
(3) Scientific meaning is not lost seriously even if time schedule were extremely delayed. So far the construction of theISS has been delayed so long time with various reason. It is not suitable for the payload whose scientific goal will
be achieved by other satellites or on ground based observatories.
(4) The payload team is as flexible as they accept any situation even if the ISS project were inevitably changed.
(5) The payload is not only fabricated with moderate cost, but also achieves cost performance. The payload is
accommodated to many interfaces in big structure.
(6) The payload makes promote better or the best science with conservative instrumentation.
Considering these items, we have decided the specification of MAXI. In spite of more restrictions in comparison to freeflyers, MAXI is an ASM of old generation with the best detectability. Once new X-ray source is detected, MAXI is able
to determine the location with precision of 0.1 degree. The location accuracy depends on the intensity and integration
time, but alignment acuracy is better than 0.1 degree.
Table 1. Specification of MAXI

X-ray detector
X-ray energy range
Total detection area
Energy resolution
Field of view
Position resolution
Angular resolution
Time resolution
Weight

GSC : Gas Slit Camera
12 units of one dimensional position sensitive
proportional counters. Xe+CO2(1%) 1.4 atm.
2-30 keV
5350 cm2
18% @5.9 keV
1.5x160 deg.
1 mm
0.1 deg.
0.1 msec
160 kg

SSC : Solid-state Slit Camera
32 chips of X-ray CCD
1 square inch,1024x1024 pixels
0.5-10 keV
200 cm2< 150 eV @5.9 keV
1.5x90 deg.
0.025 mm (pixel size)
0.1 deg.
0.1 sec
11 kg

４．

AN OVERVIEW OF MAXI CONFIGURATIONMAXI will be attached to No.1 payload interface unit (PIU) of JEM-EF (Figure 2), and then it goes around the earth.
Since X-ray cameras of MAXI are pointed toward two directions of zenith and horizon, we can scan a certain target
twice every ISS orbit with two directional cameras. Even if the ISS goes through high background regions such as South
Atlantic Anomaly (SAA), either camera could scan any source once every orbit.

Fig. 2. JEM (Kibo) of Pressurized Module and Exposed Facility (EF). MAXI will be attached to No.1 port of EF.

MAXI has two kinds of slit cameras, gas slit cameras (GSCs) and solid state slit cameras (SSC). An overview of MAXI
is shown in Figure 3. Since attitude of the ISS is not stable by a few degrees every orbit, a visual star camera (VSC) anda ring laser gyro (RLG) are usable for determination of source location. Milli-second absolute time is taken from GPS
data. An active thermal control system (ATCS) keeps instruments in moderate temperature with liquid coolant.

Fig. 3. An overview of MAXI.

The GSC consists of 6 units. One unit of GSC is shown with position sensitive gas proportional counter in Figure 4. A
field of view of the one unit covers 80x3.5 degrees (bottom-to-bottom). The 80 degrees correspond to the crossing fieldfor ISS moving. Both of the zenith and horizon GSC have respective three units and cover sky of 160 degrees in total.
In principal the GSC can scan almost all sky every ISS orbit, but it avoids some region around the sun, where highvoltage will be reduced to zero volt.
The SSC also consists of two directional cameras, zenithal and horizontal directions, where we call them as SSC-H/Z.
Each camera covers 90 degrees crossing over ISS moving with 16 CCD chips as shown in Figure 5.

5．

PERFORMANCE OF GSC

The GSC is a conventional slit hole camera. Twelve sets of one dimensional proportional counter have 5640 cm2
detection area in total. Each counter has the six cells of carbon resistive wires which are guarded by veto-detector region
in bottom and both sides12. . The unit of GSC which consists of 2 proportional counters and slat collimators is shown in
Figure 4. Response of slat collimator has 3.5 degrees in bottom-to-bottom for narrow slat width, while a slit image
corresponds to one degree covering a wide field between - 40 degrees and + 40 degrees.
The proportional counters detect incident X-ray photons from vertical to 40 degree direction. Considering thisdirectional performance we made laboratory test and simulation for proportional counter. Here we explain some resultsof these tests.

Fig. 4. The GSC unit which consists of two gas proportional counters.

The test of position resolution was performed every 10 mm along each carbon wire for all proportional counters. The
data have been taken using 0.1 mm pensile X-ray beams of X-ray energies, 4.6, 8.0 and 17.4 keV . Total length ofcarbon anode wire is 32cm, and thus the value of total resistance is 31-37 kΩ. A little difference of resistivity depends
on slight difference of wire diameters. Energy response is also different from different anode wire. We have taken
comprehensive data useful for energy response and position response12,13.. We also have taken slat collimator response
data using X-ray pencil beams14.. The data base including these data is referred to response function at the time of data
analysis.
In actual data analysis we will use each response function for two dimension surface of all carbon wires. Pulse height
response depends on X-ray energy, where hard X-rays suffer the effect of anomalous gas amplification 12. .

6．

PERFORMACE OF SSC

SSC-H/Z consist of 16 CCDs, respectively, where the CCD plays as one dimensional position sensitive detector for slat
collimator and slit hole similar to GSC system. A response of slat collimator scanning direction is 3 degrees for bottomto-bottom, while a slit image corresponds to one degree covering a wide field of view of 90 degrees (Figure 5). One
orbit scan of SSC corresponds to 90 degrees times 360 degrees. Thus it takes about two months to scan all sky by SSC
according to precession of ISS orbital plane.

Fig. 5. A set of SSC consisting of a horizontal SSC and a zenithal SSC.

The X-ray CCD chip of SSC is produced by Hamamatsu Photonics K.K.. The CCD is sensitive to radiation, but theirradiation test of simulated radiation belt fluence suggests that the CCD can survibe as normal status for expected threeyear mission15. . Nevertheless, it is possible to inject charges in the CCD before it becomes damage due to radiation16. .
In order to take better energy resolution with CCD, all CCDs are cooled down to -60 degree C using Peltier device andloop heat pipe radiation system (LHPRS). Maximum power of Peltier device is 1 W/CCD. The LHPRS can transfer
heat from Peltier and emit heat from radiation panel. Performance tests in laboratory have been done withsatisfaction17,18.. A typical data of X-ray spectra shows 150 eV for Mn K X-rays (5.9 keV).

7．

DATA PROCESSING AND ANALYSIS SYSTEM OF MAXI

The data of MAXI is downloaded through ISS communication system. The data flow from MAXI to JAXA is shown in
Figure 6. All of MAXI observation data are collected to the operation control center at Tsukuba Space Center of JAXA.
MAXI has two kinds of data communication system, system telemetry of S-band with 25 kbps (nominal) and a medium
rate data system with 200 kbps (nominal). The MAXI data sent through the system telemetry include minimum
important information on X-ray light curves, energy spectra and directions of X-ray events, while the data throughmedium rate data system include detailed information corresponding to respective data outputs from detectors. Once thesystem telemetry data are obtained, automatic alert software system will work for finding X-ray novae, transient X-ray
sources, and variable X-ray sources. Important alert on such X-ray sources will be rapidly sent via internet to world
astronomers. Further detailed information analyzed by duty scientists will follow on. The data through medium rate
system will be used for further detailed analysis. Data processing and analysis software are being developed by mission
team19.. Public data system will be open in time by MAXI team.
The key results of X-ray source data are open to the public after routine analysis for further cooperated research.

Fig.6. Data communication system of MAXI.

8．

SIMULATION OF MAXI DATA AND DETECTABILITY

The GSC of MAXI usually observes a certain object twice every ISS orbit with GSC-H and Z. The data for weak source
are not only accumulated from both observations, but also integrated from observations by repeated orbits. We havesimulated this accumulation of GSC data for various sources. Now we show some results of simulations; e.g., Fig.7
shows simulated data for 10 and 100 mCrab sources with respective observation times, while Fig.8 shows one mCrab
source simulation for one week observation. We took account for reasonable intrinsic background as well as cosmic Xray background in these simulations. It is concluded from the present simulation that it is possible to detect the sources
stronger than several 10 mCrab for one orbit observation, while possible to detect the sources stronger than 10 mCrab for
one day obseravation. For one mCrab source it will take one week. It may be also possible to detect weaker sources than
one mCrab, but unexpected systematic error becomes serious for weaker sources.

Fig. 7. Simulation for detectability. Each detected point spreadfunction is shown on 3 x 3 degrees map. Cosmic Xray background and intrinsic background areconsidered in this simulation.

Fig.8.

One milli Crab source simulation for one
week. Simulation method is as same as Fig.7.

9．

PRESENT STATUS AND INTERNATIONAL ROLE OF MAXI

Now MAXI is in final phase of payload fabrication and testing. The integration test is going on from August, 2007 to
May 2008. MAXI will be launched by Space Shuttle together with JEM-EF January, 2009; the mission life is 3 years.
Development of data process and analysis software is in progress. Hot data of NAXI alert system will not only be sent
directly to dedicated users, but also open to public news such as GCN, ATEL, IAUC, etc.
MAXI is only the conventional X-ray all sky monitor of which design is conservative. Nevertheless, detectability of Xray sources is milli-Crab for one week observation. At present the ASM on Rossi-XTE is still working, but it is not sure
if Rossi-XTE will survive further three years. Anyway MAXI will play an ASM with better detectability of one milliCrab from 2009.

10. Acknowledgement
We and all the MAXI team members, thank the following companies and institutions for developing respective subsystems of MAXI; that is, NEC Corporation for MAXI bus system, Meisei Electric Co., Ltd for mission instruments,
Oxford Instrum. for gas proportional counters, Hamamatsu Photonics K.K. for CCD, ATK Space (Swales Aerospace) for
LHPRS, DTU (Technical University of Denmark) for Optical Star Sensor, Institute of Aerospace Technology in JAXA
for GPS, and other cooperated companies and institutions.

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