Minimize Solar-B

Solar-B / Hinode Mission

Solar-B is a Japanese solar physics mission of JAXA/ISAS, a successor to the highly successful Solar-A/Yohkoh mission of Japan/USA/UK. After launch, the in-orbit Solar-B spacecraft was given the name “Hinode,” meaning “sunrise.” Solar-B will, for the first time, provide quantitative measurements of the full vector magnetic field on small enough scales to resolve elemental flux tubes. The field of view and sensitivity allow changes in the magnetic energy to be related to both steady state (coronal heating) and transient changes (flares, coronal mass ejections) in the solar atmosphere.

The Solar-B mission is again being conducted as a multi-institutional and international collaboration between Japan (JAXA, NAOJ), the United States (NASA/GSFC and MSFC, SAO (Smithsonian Astrophysical Observatory), Lockheed Martin Solar and Astrophysics Laboratory, NRL (Naval Research Laboratory), and the United Kingdom with PPARC (Particle Physics and Astronomy Research Council); the MSSL (Mullard Space Science Laboratory) of the University College London and RAL (Rutherford Appleton Laboratory) are the prime partners of PPARC. As the lead agency, JAXA is responsible for the spacecraft, spacecraft integration, the optical telescope and the launch of the spacecraft. ESA (European Space Agency) and the Norwegian Space Center joined the Solar-B team in 2005; they are providing ground station coverage for the Solar-B mission. 1) 2) 3) 4) 5) 6)

The overall goal is to study and to understand the dynamic sun and its effect on terrestrial climate (global change) and space weather. Further major science objectives are:

• Comprehensive study of the sun's magnetic fields and a new view into the magnetic dynamics of the plasma universe (first spaceborne quantitative observations of the sun's full vector magnetic fields). Understanding basic plasma astrophysics such as the dynamo and magnetic reconnection processes.

• Study of the physics of the sun's luminosity and its variation

• Study of the processes which produce the UV and X-ray emission in the chromosphere and corona

• Study of solar wind energetics. Eruption and expansion of the sun's atmosphere.


Background: The conceptual design for a follow-up mission to Solar-A/Yohkoh (launched in Aug. 1991) started in 1994. After government approval of the mission in 1998, the SOLAR-B mission started in 1999 with the US (NASA) and the UK (PPARC) in the program as international partners. The first test of a prototype model of the electronics was conducted in 2001; the initial checks of the mechanical and thermal test models were conducted in 2002. Through these tests the validity of the initial design and the test method were confirmed.
All the flight models were initially assembled in Sept. 2004, and the electrical and mechanical interface checks were executed. The flight models were integrated again in July 2005 for the final performance test after fixing problems. The performance tests were completed in July 2006, and the spacecraft was transported to the launch site in August 2006. 7)


Figure 1: Image of the Solar-B spacecraft and instrument positions (image credit: JAXA)


The Solar-B spacecraft is three-axis stabilized and pointed toward the sun. It is being developed/integrated by Mitsubishi Electric Corporation (MELCO) of Tokyo as prime contractor to JAXA. The spacecraft bus has a size of 2.0 m x 1.6 m x 3.8 m (L x W x H). Attitude is being sensed by IRU (Inertial Reference Unit) and by gyros with a combination of two types sun sensors and a star tracker providing absolute calibration. The two type CCD sun sensors provide highly accurate and stable sun angle to the attitude control system. One is the CCD sun sensor called NSAS (Non-Spin type Solar Aspect Sensor) and the others are two sets of UFSS (Ultra Fine Sun Sensor). NSAS is providing a pointing accuracy of 0.05º, random noise of 0.005º and FOV of ±50º. UFSS has very high accuracy of a few arcseconds and the resolution of 0.1 arcsec. The arithmetic average of pointing signals measured with UFSS-A and UFSS-B is used in controlling the spacecraft attitude in a normal operation mode. 8) 9)


Figure 2: Functional block diagram of UFSS (image credit: NEC Toshiba, JAXA)

Attitude actuation is provided by four reaction wheels, referred to as RCS (Reaction Control Subsystem). Solar-B is a sun-pointing spacecraft. The pointing stability is in the order of 0.1 arcsec over 10 seconds while finer image stabilization of 0.02 arcsec is achieved over 10 s for the optical telescope using its own correlation tracker/tip-tilt mirror system. Total electric power of 1 kW (EOL) is provided by two solar arrays (total length of 10 m).

An onboard solid-state recorder has a capacity of 8 Gbit. The onboard data compression technique (a special purpose, 12-bit JPEG/DPCM chip) provides either lossy or lossless image compression, dependent on the type of imagery processed. The spacecraft launch mass is about 900 kg (about 700 kg of dry mass with about 175 kg of thruster gas for orbit maintenance). The nominal mission life is three years (design life of 2 years min.). 10) 11) 12)

Spacecraft bus size

2.0 m (L) x 1.6 m (W) x 3.8 m (H)

Spacecraft pointing

Sun-pointing,stability of 0.1 arcsec, finer image stabilization of 0.02 arcsec is achieved over 10 s

RF communications

X-band for science data with 4 Mbit/s downlink
S-band for TT&C data
Solid state onboard recorder with a capacity of 3 Gbit (lossless image compression and onboard processing)


1 kW (EOL),2 solar arrays with a total length of 10 m

Spacecraft mass

893 kg (~700 kg of dry mass with ~175 kg of thruster gas for orbit maintenance)

Mission design life

2 years, with a goal of 3 years

Table 1: Overview of spacecraft parameters

Launch: The launch of the Solar-B spacecraft took place on Sept. 23, 2006 on a JAXA M-V-7 launch vehicle from USC (Uchinoura Space Center) at Uchinoura Kagoshima, Japan. Secondary payloads on this flight are: SSSat (Solar-sail Sub-payload Satellite), a microsatellite of JAXA/ISAS to demonstrate some technologies required for the future solar power sail spacecraft, and HIT-Sat (Hokkaido Institute of Technology Satellite), a CubeSat of 3 kg.

Orbit: Sun-synchronous circular orbit, altitude = 680 km, inclination = 98.1º, period = 98 minutes, a dawn/dusk orbit with a LTDN (Local Time of Descending Node) at about 18:00 hours. This orbit keeps the instruments in nearly continuous sunlight, with no day/night cycling for nine months each year.

RF communications are provided in X-band and in S-band (TT&C function). The downlink playback data rate is 4 Mbit/s (X-band). ESA and the Norwegian Space Center are providing ground station coverage for the Solar-B mission through the Svalbard Satellite Station (SvalSat), located on the Norwegian Svalbard islands (78.216º N, 20º E). - The SBSC (Solar-B Science Center) is located at NAOJ (National Astronomy Observatory Japan), Tokyo, while DARTS (Data Archive and Transfer System) is a web-based comprehensive data archive hosted at JAXA/ISAS.


Figure 3: Artist's view of the Earth-orbiting Hinode spacecraft observing the sun (image credit: ESA)



Mission status:

• 2014: The Hinode spacecraft and its payload are operating nominally. On Feb. 7, Hinode observed a major sunspot activity in the AR (Active Region) 11967 that released numerous solar flares (Figure 4). 13)

By studying the sun's magnetic field, scientists hope to shed new light on explosive solar activity that can interfere with satellite communications and electric power transmission grids on Earth and threaten astronauts on the way to or working on the surface of the moon. In particular, they want to learn if they can identify the magnetic field configurations that lead to these explosive energy releases and use this information to predict when these events may occur.


Figure 4: The top image of AR 11967 was acquired by SOT (Solar Optical Telescope) aboard Hinode in the Calcium II H line on Feb. 7, 2014 at 16:09 UT. The lower image is a wider view of AR 11967 as seen by SDO on Feb.12, 2014, at 01:35 UT (image credit: NASA, JAXA,Lockheed Martin)

• 2013: The Hinode spacecraft and its payload are operating nominally. The current mission extension is up to the end of 2014 (proposal for extension up to 2016 in June 2013).

• In November 2012, Hinode captured the scene of the total solar eclipse while flying over northern Australia. Its onboard XRT (X-Ray Telescope) took images of the sun gradually being covered by the moon on Nov. 14, 2012. 14)


Figure 5: Image of the total eclipse over Australia (image credit: JAXA)

• April 2012: For the first time, an international research team, consisting mainly of researchers from the NAOJ (National Astronomical Observatory of Japan) and RIKEN, recently discovered the phenomenon of the polarity of the polar magnetic field in the solar polar region reversing faster than expected by using SOT (Solar Optical Telescope) mounted on the Solar Observation Satellite "Hinode." 15)

The research team found that between 2008 and 2012, the reversal from minus to plus polarity of the magnetic field was taking place only in the north polar region of the sun, while the magnetic field did not change much in the south polar region. The magnetic field of the solar polar region is known to reverse every 11 years. However, as the reversal occurred only on the north pole, and also with the development of a sunspot that was related to the polar magnetic field reversal, the condition is very similar to the “Mounder Minimum,” which brought a cold period to Earth in the mid 17th century. This phenomenon and its further movement need more attention. 16)

• The Solar-B/Hinode spacecraft and its payloads are operating nominally in 2012.


Figure 6: SOT image of a solar flare observed on August 4, 2011 (image credit: MSFC) 17)

Legend to Figure 6: The SOT (Solar Optical Telescope) zoomed in on AR 11263 on August 4, 2011, five days before the active region produced the largest flare of this cycle, an X6.9.

• On February 1, 2011, the Hinode satellite captured this breathtaking image of a coronal hole (Figure 7), seen in the top center of the image (a polar coronal hole can also be seen at the bottom of the image). A coronal hole is an opening in the sun's magnetic field through which gas can easily escape into space. 18)


Figure 7: Photo of a coronal hole taken by the XRT instrument on Feb. 1, 2011 (image credit: NASA)

• On January 4, 2011, the Hinode spacecraft observed an annular solar eclipse using its XRT (X-Ray Telescope). 19)

• The Hinode spacecraft and its instruments are operating nominally in 2010 (Ref. 10).

• Hinode clarifies the origin of low-speed solar winds: The origin of low-speed solar winds was found to be at the parting plane of the magnetic field that exists at the end of the active area of the winds. This finding was achieved by combining the observations of the Solar Physics Satellite "Hinode" and those of photosphere magnetic fields.

Such a parting plane of a magnetic field is found to be a boundary between the magnetic field of the active area and other magnetic fields, and the magnetic reconnection is easily triggered in the environment of the parting plane. This observation result suggests the possibility that magnetic reconnection may drive low-speed solar winds.

• Hinode has been providing ample new findings on magnetic activities in the solar atmosphere which are revolutionalizing our understanding on the Sun. These findings include frequent X-ray jets and magnetic field concentration in the polar regions, unexpectedly-high jet activities in the chromosphere, and transient horizontal magnetic field ubiquitously covering the photosphere. 20)


Figure 8: Sunspot on the sun’s surface captured by the optical telescope onboard Hinode (image credit: NAOJ, JAXA, NASA) 21)

Legend to Figure 8: The observations were made at a wavelength of 460 nm (the colors in the image have been artificially enhanced and differ from the actual colors). Convection called granules can be seen in the photosphere (right). Small spots between the convection cells are magnetic elements (the minimum unit of a magnetic field) that have an exceptionally strong magnetic field.


Figure 9: Large solar flare captured by SOT on Dec. 13, 2006. A two-ribbon structure and some of post-flare loops between the two ribbons are clearly seen (image credit: NAOJ, JAXA, NASA, Ref. 21)

• Since its first-light observation on 25 Oct. 2006, the image-stabilization system has been working with a performance of better than 0.01 arcsec rms and the SOT has been continuously providing unprecedented solar data of high spatial resolution (Ref. 31).

• So far, the data from Hinode have brought a new perspective of solar physics and a wealth of discoveries. For instance, data analysis shows that magnetic waves play a critical role in driving the solar wind into space. An international team at MSSL has found a source of the stream of particles that make up the slow solar wind using data from Hinode and SOHO. The solar wind can have low or high speeds. The low-speed or slow solar wind moves at only 1.5 million km/h. The high-speed wind is moving at speeds as high as 3 million km/h. 22)

• Starting in December 2007, Hinode's X-band transmitter signal began to experience irregularities in the latter half of each contact with the ground. The cause of the X-band anomaly is currently under investigation, and the status of the X-band will continue to be regularly monitored.

• Since May 27, 2007, European scientists have free access to the data of the Hinode mission through the Hinode Science Data Centre in Norway, developed and run by the Institute of Theoretical Astrophysics at the University of Oslo on behalf of ESA and the NSC (Norwegian Space Centre). It is part of ESA's and Norway's joint contribution to this solar mission. Norway provides also ground station coverage through the SvalSat downlink station at Svalbard (Spitzbergen), which nearly quadruples the data rate and thus significantly increases Hinode's science return. 23)

• As of Dec. 22, 2006, the Hinode instruments completed in-orbit testing and the mission became operational.

• First-light observation on Oct. 25, 2006 (top door deployed). Initial checkouts of the instrument were conducted and superior performance of SOT was confirmed. 24)

• After the deployment of the side door of OTA on 14th October 2006, electrical components of SOT were turned on and basic functional tests of moving mechanisms and cameras were carried out successfully. The period after opening the side door and before opening the top door was designated as the initial bakeout phase of the OTA prior to introducing the sun light into the telescope, and decontamination heaters of the primary and secondary mirrors of OTA were turned on to maintain the temperature of critical surfaces higher than other parts of the telescope.


Figure 10: Synoptic view of the sun with the XRT instrument (image credit: NAOJ)



Sensor complement: (SOT, XRT, EIS)

Multidimensional observation of the sun with three telescopes: The sensor complement consists of a coordinated set of optical, EUV and X-ray instruments (high-resolution solar telescopes and spectrometers) to investigate the interaction between the sun's magnetic field and its corona [interaction between the sun's photospheric velocity and magnetic fields (SOT/FPP) and its extended atmosphere: chromosphere and corona (XRT/EIS)]. Co-alignment of SOT and EIS is realized through the XRT visible light telescope and the temperature overlap of EIS. - The MDP (Mission Data Processor) of Solar-B coordinates the observations of the sensor complement and handles the data from the various instruments. 25) 26)

The temperature of the solar atmosphere ranges from about 5500 K (corresponding to visible light) to millions of degrees (corresponding to x-ray radiation). For this reason it is necessary to study the sun using instruments sensitive to radiation over a broad range of wavelengths. Spectroscopic observations are particularly important because they allow detailed determinations of plasma parameters such as temperature, density, and element abundance from measurements of the absolute intensities and intensity ratios of spectral lines. Furthermore, using the Doppler effect, determination of line-of-sight bulk flows and nonthermal turbulent motions are also possible from measurements of the wavelength positions of spectral lines and the shapes of the line profiles, respectively. 27)

From the technology perspective, the sensor complement of Hinode is characterized by:

• Ultra-high spatial resolution optics and detectors

• Multi-layer gratings and coatings from SERTS; Ultra-high resolution X-ray imaging - heritage of TRACE

• Space-qualified linear polarimeters

• Enhanced large format detectors: 4 k x 2 k CCDs for SOT; 2 k x 2 k pixels for XRT; 2 k x 1 k pixels for EIS. The cadence of exposures is on the order of a few seconds to 10 seconds for the fastest case, so that large volumes of image data are produced by each telescope. A readout of a CCD partial area is possible to reduce the size of data to be downlinked, but the data volume is still fairly large.

• Solar pointing and tracking capability in the order of 0.1 arcseconds.


Figure 11: Model of the solar atmosphere and regions where Hinode instruments can observe (image credit: NAOJ)


Figure 12: Payload locations of the Solar-B (Hinode) spacecraft (NAOJ, JAXA)


SOT (Solar Optical Telescope):

SOT represents a joint development between Japan and the USA, in which Japan provides the telescope optics and the USA the FPP (Focal Plane Package). The international collaboration consists of: NAOJ (National Astronomical Observatory of Japan), Lockheed Martin Advanced Technology Center (LMATC), Mitsubishi Electric Corporation (MELCO), NCAR High Altitude Observatory (HAO), NASA/MSFC, and JAXA. The objective is to obtain continuous high-resolution magnetic field imagery of the sun's surface. The telescope feeds a complex FPP designed for photospheric and chromospheric imaging and spectropolarimetry. SOT is designed to achieve a consistent 0.2 arcsec spatial resolution. 28) 29)


Figure 13: Illustration of the SOT instrument (image credit: NAOJ)


Figure 14: Schematic view of SOT instrument components (image credit: NASA/MSFC, LMATC)

SOT is a diffraction-limited and aplanatic Gregorian telescope with an aperture of 0.5 m. It provides an angular resolution of 0.25 arcsec (175 km on the sun) over the field of view (FOV) of about 328 x 164 arcsec. The spectral range of SOT is 480-650 nm. The focal plane package of the optical telescope consists of broad- and narrow-band filtergraphs (filter vector magnetographs) and a spectro-polarimeter. This combination allows to obtain, for the first time, a continuous series of high-precision vector magnetograms, Dopplergrams, and filtergrams with sub-arcsec resolution. 30) 31) 32)


Figure 15: Optical and control interfaces of SOT (image credit: NAOJ)


Figure 16: Block diagram of the SOT instrument (image credit: NASA/MSFC, LMATC)

The SOT instrument is designed and developed by the international collaboration between NAOJ (National Astronomical Observatory of Japan), LMATC (Lockheed Martin Advanced Technology Center), Palo Alto, CA, MELCO (Mitsubishi Electric Corporation), HAO (High Altitude Observatory), Boulder, CO, NASA/MSFC, Huntsville, ALA, and JAXA, Tokyo. The PIs are: S. Tsuneta (NAOJ) and A. Title (LMATC).

SOT is so far the largest telescope with highest performance ever to observe the sun from space. The SOT telescope itself consists of two major components:

OTA (Optical Telescope Assembly), consisting of a 50 cm aperture Gregorian telescope with a collimating lens unit and an active tip-tilt mirror for an image-stabilization

FPP (Focal Plane Package), housing two filtergraphs and a spectro-polarimeter.

OTA and FPP are optimized for the measurement of the vector magnetic field and associated dynamics in the solar photosphere. SOT will obtain a continuous series of diffraction-limited images, achieved by 50 cm diameter aperture telescope.

The images are being acquired under very stable pointing conditions. The BFI (Broadband Filter Imager) produces photometric images with broad spectral resolution in 6 bands (CN band, Ca II H line, G band, 3 continuum bands) at the highest possible spatial resolution (0.0541 arcsec/pixel) and cadence (< 10 s typical) over the full field of view (218 × 109 arcsec). This will allow accurate measurements of the horizontal flows and temperature of the solar surface, and to identify sites of strong magnetic fields.

The NFI (Narrowband Filter Imager) measures very narrow spectral bands in the photosphere and chromosphere to derive line-of-sight velocities of solar plasma.


Figure 17: Major components of the OTA (image credit: NASA/MSFC)

Optical Telescope Assembly (OTA)

Telescope type

Aplanatic Gregorian telescope with heat dump mirror

Primary mirror

50 cm aperture diameter, light weight glass composite

Primary-secondary mirror length

1.5 m

Spectral range

480 - 650 nm


328 arcsec x 164 arcsec

Effective f ratio

9.055 at secondary focus

Polarization modulator (PMU)

Rotation speed: continuous, 1.6 s/rotation

Angular resolution

Diffraction limited at 0.25 arcsec (175km on the sun)

Polarimetric accuracy


FPP (Focal Plane Package) Vector Magnetograph

Magnetic lines

Fe I 525.0 nm, Fe I 630.2 nm, continuum:524.6 nm, velocity: Fe I 532.4 nm


164 arcsec x 164 arcsec

Magnetic sensitivity

B (longitudinal): 1 - 5 G (gauss)
B (transverse): 30 - 50 G

Temporal resolution

5 minutes


Time series of photospheric vector magnetograms, Doppler velocity and photospheric intensity

FPP Spectro-Polarimeter (SP)


- Spectra of two Fe lines at 630.15 and 630.25 nm and nearby continuum
- Raw spectra are added and subtracted onboard to demodulate, forming Stokes parameters I, Q, U, and V.

Instrument type

Littrow echelle


164 arcsec x 164 arcsec

Spatial sampling (slit)

0.16 arcsec

Spectral coverage

630.08 - 630.32 nm

Spectral resolution/sampling

30 mÅ / 21.5 mÅ

Measurement of polarization

Stokes I, Q, U, V simultaneously with dual beam (orthogonal linear components)

Polarization SNR

103 (normal map)


Detailed Stokes line profiles of intensity and polarization

FPP Correlation Tracker (CT)

CCD detector

50 x 50 pixels, 0.22 arcsec/pixel

Frame rate

580 Hz

Spectral range

629-634 nm

Displacement range

± 5 pixels

Error signal accuracy

~ 0.01 arcsec



SOT data rate (after compression)

~300 kbit/s, assuming 15 downlink stations/day

Allocated telemetry rate

~1.3 Mbit/s (nominal for SOT)

Table 2: Overview of SOT instrument parameters


218 arcsec × 109 arcsec (full FOV)


4k x 2k pixel (full FOV), shared with the NFI

Spatial sampling

0.0541 arcsec/pixel (full resolution)

Spectral coverage

Center (nm)

Width (nm)

Line of interest





Magnetic network imaging




Chromospheric heating




Magnetic elements



Blue continuum




Green continuum




Red continuum


Exposure time

0.03 - 0.8 s (typical)

Table 3: Specification of BFI (Broadband Filter Imager)


328 arcsec x 164 arcsec (unvignetted 264 arcsec x 164 arcsec)


4k x 2k pixel (full FOV), shared with BFI

Spatial sampling

0.08 arcsec/pixel (full resolution)

Spectral windows (nm) and lines of interest

Center (nm)







Mg I b 517.27


Chromospheric Dopplergrams and magnetgrams



Fe 524.71
Fe I 525.02
Fe I 525.06


Photospheric magnetograms



Fe I 557.61


Photospheric Dopplergrams



Na I D 589.6


Very weak fields (scattering polarization) Chromospheric fields



Fe I 630.15
Fe I 630.25
Ti I 630.38


Photospheric magnetograms
Umbral magnetograms



H I 656.28


Chromospheric structure

Exposure time

0.1 - 1.6 s (typical)

Table 4: Specification of NFI (Narrow Filter Imager)


Figure 18: The FPP optics package (image credit: NASA/MSFC, LMATC)


Figure 19: Optical layout of the SOT instrument (image credit: NAOJ)


Figure 20: Front-end schematic of the SOT telescope assembly (image credit: MSSL)

OTA (Optical Telescope Assembly): The OTA (Figure 21) consists of an aplanatic Gregorian; the primary mirror (M1) and the secondary mirror (M2) of effective aperture of 500 mm, a CLU (Collimating Lens Unit) near the center of the primary mirror, a PMU (Polarization Modulator Unit), an active Tip-Tilt Mirror (CTM-TM), and an ACL (Astigmatism Corrector Lens). In addition, the OTA has two field stops between the primary and secondary mirrors; one is a HDM (Heat Dump Mirror) at the focus of the primary mirror and the other is a secondary field stop (2FS) at the Gregorian focus (Ref. 31).

The OTA was designed to fulfill the following scientific and engineering requirements:

1) To resolve at least 0.2 arcsec solar features over a field view of 320 x 160 arcsec

2) To offer a negligible chromatic aberration with a wide coverage of observation wavelengths from 388 to 668 nm without focus adjustment and to give a well-defined optical interface with FPP

3) To provide negligible instrumental polarization before a polarization modulator for precise polarization measurements

4) To accommodate thermal design to reject unwanted solar light from the telescope components as early as possible.


Figure 21: Optical configuration of OTA (image credit: NAOJ, JAXA)

A layout of overall the OTA structural assembly is shown in Figure 22. The center panel ring (called center section) provides the mechanical interface to the spacecraft. OTA is mounted on the CFRP-made cylindrical optical bench unit (OBU) to the spacecraft with three quasi-kinematic titanium alloy mounting legs with stress-relief spring structures. The center section is equipped with alignment cubes at the top surface which represent the mechanical and optical axes of the OTA; they are used for co-alignment among other telescopes and spacecraft attitude control system sun sensors.

The primary mirror, made of light-weighted (70% removed and thus only 14 kg mass) ULE, is supported by three stress-free mounting mechanisms seated on the CFRP bottom panel (called mirror cell), interfaced with three superinvar pads bonded on the side of the mirror. The pad interface of the mounting mechanism is torque-free about three axes and also free in the radial direction, thus providing a kinematic mount for the primary mirror (Ref. 31).

Note: ULETM (Ultra-Low Expansion) is a glass material of Corning Glass that exhibits no dimensional changes over extreme temperature variations; it is generally considered to be one of best in the world for astronomical optics.


Figure 22: Configuration of the OTA structural assembly (image credit: NAOJ, JAXA)

FPP (Focal Plane Package): The FPP structure consists of an aluminum honeycomb optical bench with side panels and a cover plate. Note that because of the large depth of focus, using aluminum with large CTE (Coefficient of Thermal Expansion) does not pose a problem. The FPP box is mounted on the OBU by a spacecraft-provided kinematic mount. The FPP is thermally isolated from the OBU. Each CCD detector is cooled by its own dedicated radiator. The FPP includes the NFI (Narrowband Filter Imager) and BFI (Broadband Filter Imager), plus the Stokes spectro-polarimeter (SP).

The FPP (Figure 18) has a re-imaging lens followed by the beam splitter. The effective combined focal length is 1550 cm (f/31), and the depth of focus in the FPP focal plane is about 400 µm. The focus is adjusted by moving the re-imaging lens through commands from the ground. The re-imaging lens has a stroke of ±25 mm to have a sufficient margin based on the focus budget breakdown table, which has numerous deterministic and statistical factors (Ref. 6).

On the downstream side of the beam splitter are the broadband and narrow-band filter channels sharing a common CCD camera, the spectro-polarimeter, and the correlation tracker. A non-polarizing beam splitter divides the light between SP and the filtergraph (Filter Imager), and then the polarizing beam splitter in the filter channel transmits the p-polarized light to the NFI and the s-polarized light to the BFI.

The FPP electrical box (FPP-E) has the computer for controlling the FPP and performs onboard data-processing such as Stokes demodulation. The other electrical box (FPP-PWR) contains the power supply for the entire FPP subsystem. The MDP (Mission Data Processor) controls the FPP observations.


Figure 23: The SOT subsystem electrical instrument configuration (image credit: NAOJ, NASA)

Legend to Figure 23: OTA (Optical telescope Assembly), FPP (Focal Plane Package), PMU (Polarization Modulation Unit), CTM-TM (Tip-Tilt fold Mirror), MDP (Mission Data Processor), FPP-E (main electronics box for FPP), FPP-PWR (power supply for FPP subsystem), CTM-E (main electronics box for OTA and TTM), CTM-TE(analog driver for the TTM), DHU (spacecraft Data handling Unit), DR (spacecraft central Data Recorder), CT (Correlation Tracker) a high speed CCD camera.

SOT observing modes: With the CLU (Collimator Lens Unit) and the tip-tilt fold mirror, the OTA delivers a pointing-stabilized parallel beam to the FPP. The FPP is configured with the re-imaging lens followed by the beam-splitter for the filtergraph, the spectro-polarimeter, and the correlation tracker channels. FPP performs both filter (FG) and spectral (SP) observations at high polarimetric precision, and both types of observation may be performed simultaneously yet independently in response to the macro-commands from MDP (Ref. 6).

In filter observation, a 4 k x 2 k CCD camera is shared by the broadband (BFI) and narrowband (NFI) filter imagers, and the NFI and BFI are selected by a common mechanical shutter. The SP and CT have their own CCD detectors. The NFI uses a tunable birefringent filter (Lyot filter) to record filtergrams, Dopplergrams, and longitudinal and vector magnetograms across the spectral range from 517.0 - 657.0 nm, including several spectral lines: Mg ib (517.3 nm; chromospheric Dopplergram and Magnetogram), Fe i (525.0, 524.7, 525.0 nm), Fe i (557.6 nm), Na i (589.6 nm; chromospheric Dopplergram and Magnetogram), Fe i (630.3, 630.2nm), and H i (656.32 nm; chromospheric structure). The BFI has interference filters to image the photosphere (CN i 388.3 nm, CH i 430.5 nm) and low chromosphere (Ca ii H 396.9 nm), and to make blue (450.5 nm), green (555.1 nm), and red (668.4 nm) continuum measurements for irradiance studies.

The SP is an off-axis Littrow-Echelle spectrograph that records dual-line (Fe i 630.25 nm and Fe i 630.15 nm) dual beam (with the polarization beam splitter, which is a polarization analyzer, in front of SP CCD) Stokes spectra for high precision Stokes polarimetry.

The time sequencing of the science data acquisition by SOT is controlled according to observation tables (one for FG and the other for SP) on the MDP.


XRT (X-Ray Telescope):

XRT is of SXT (Soft X-ray Telescope) heritage flown on Yohkoh. XRT is a cooperative instrument between NASA and JAXA. NASA provides the grazing-incidence mirror optics, built by Goodrich Corporation and the SAO (Smithsonian Astrophysics Observatory) team, while JAXA/NAOJ provide the CCD camera. XRT images the high temperature plasma of the corona (0.5 to 20 MK) with an improved angular resolution - a few times better than Yohkoh's SXT. 33) 34)

The XRT has two optical systems. One is for X-ray and the other is for visible light (G-band). The optics layout is similar to Yohkoh/SXT and these optical systems make X-ray and G-band images on one CCD. - XRT has two filter wheels for X-ray analysis filters and a G-band filter. These filter wheels have in total 12 positions (6 position in each filter wheel), 9 positions are used for X-ray analysis filters and one for the visible-light filter. The X-ray analysis filters provide the capability of temperature analysis over the range 6.1 < log T < 7.5. 35) 36) 37)

To provide a high-resolution soft X-ray image with low noise and large dynamic range, the data acquisition system for XRT uses a single 2 k x 2 k pixel CCD array. The CCD is being operated at a temperature of -43º C on orbit. XRT can take partial frame images. The sizes of partial frame images are: 64, 128, 192, 256, 384, 512, 768, 1024, 1536, or 2048 pixels. XRT is equipped with a modified Wolter I grazing-incidence (GI) X-ray telescope to image the full sun disk at ~ 1.5 arcsec angular resolution onto a 2048 x 2048 back-illuminated CCD focal plane detector.

X-ray Optics (Optimized Wolter-I Grazing Incidence Optics)

Focal length

2708 mm

Aperture diameter

> 340 mm

Spectral band width

2 - 200 Å

Effective area

5.0 cm2 @ 0.56 keV & 1 keV

FOV (Field of View)

Full disk or partial disk (> 30 arcmin)



Temperature range

6.1 < log T < 7.5

Temperature discrimination

log T = 0.2

Temporal resolution

Cadence = 2 s (reduced FOV), exposure time: min = 4 ms, max = 10 s

Visible Optics

Focal length

2708 mm


4305 Å (G-band)


> 30 arcsec

Camera CCD

CCD type

2 k x 2 k back-illuminated CCD (E2C/CCD 42-40 of E2V Technologies Ltd.)

Pixel size

13.5 x 13.5 µm (corresponding to 1 arcsec x 1 arcsec resolution)


Coronal images at different temperatures

Table 5: Parameters of the XRT instrument


Figure 24: Major components of the XRT instrument (image credit: NASA/MSFC)


Figure 25: Optical path of the XRT instrument (image credit: NASA/MSFC)

The onboard instrument MDP (Mission Data Processor) controls the XRT observations providing the following functions:

• Observation controlled by observation tables (FOV, time cadence)

• Automatic Exposure Control (AEC). MDP achieves the proper exposure time by analyzing the intensity distribution of the observed X-ray images.

• Automatic Region Selector (ARS)

• Flare Detection (FLD). MDP can detect the occurrence of a flare using flare patrol images taken by XRT.

• Pre-Flare Buffer

• Image compression. MDP can compress the image data using either JPEG (lossy) or DPCM (lossless) method.


EIS (EUV Imaging Spectrometer):

PPARC provides the EIS instrument with NASA and JAXA/NAOJ participating with some hardware and software. EIS is primarily aimed at observing the dynamics of the solar corona. The objective of EIS is to determine velocity fields and other plasma parameters in the corona and the transition region, thus helping to relate coronal dynamic behavior, observed with the XRT, to the underlying photospheric magnetic field, observed with the optical telescope. The EIS instrument is also expected to unveil inflow and outflow of magnetic reconnection, and hence together with the two other telescopes, to finally solve long-standing controversies on coronal heating and dynamics. 38) 39) 40) 41) 42) 43)

EIS represents the next stage in the development of scanning imaging EUV spectrometers. The instrument consists of a multi-layer coated single mirror telescope, and a stigmatic imaging spectrometer incorporating a multilayer coated diffraction grating. The image produced by the primary mirror is imaged onto and entrance slit/slot and the light which passes through this spectrometer aperture is dispersed and re-imaged in the focal plane of the CCD detector. - The EIS instrument uses a panel construction to form the instrument box with all the optical subsystems mounted on a single 3.5 m long optical bench. The panels are made from thin CFRP (Carbon Fiber Reinforced Plastic) laminates with a sandwich core of aluminium honeycomb.

The telescope is an off-axis paraboloid design with a focal length of 1.9 m and a mirror diameter of 150 mm. EIS has a total length of 3 m. Multilayer toroidal gratings disperse the spectrum onto 2 detectors, each covering 40 Å.


Aperture diameter

150 mm (off-axis parabola)

Focal length

1934 mm

Off-axis distance

70 mm

Plate scale at slit

9.4 µm/arcsec

Slit and slot

1 arcsec, 2 arcsec, 40 arcsec, and 266 arcsec width at primary focus

Fine mirror scan range

±3 arcmin solar image motion
Max. FOV of raster (EW x NS): 576 arcsec x 512 arcsec

Large FOV translation

±800 arcsec shift of FOV center in East-West direction



Toroid; holographic laminar, uniform line spacing

Wavelength ranges

170-210 Å and 250-290 Å (the reflectivity of the mulitlayers restrict the performance below 180 Å and above 204 Å)


1.65 Å/mm or 0.0223 Å/CCD pixel

Angular resolution

2 arcsec; four slit/slot positions are available: 1 arcsec slit, 2 arcsec slit, 40 arcsec slot, and 266 arcsec

Spectral/velocity resolution

3 km/s for Doppler velocities, 20 km/s for line widths

Temporal resolution
- In spectroscopy mode
- In imaging mode

< 1 s in dynamic events, ~ 10 s in active regions
monochromatic imaging of an active region (~4 x 4 arcmin) in 3 s for dynamic events, 10 s otherwise


Doppler line widths and shifts and monochromatic images

CCD Camera


Marconi 42-20, MPP

Format (spatial x spectral)

1024 x 2048 pixels

Pixel size

13.5 µm

Readout electronics
- Window size
- No of spectral windows

512 x 2048 max.
25 max.

Table 6: Overview of of the EIS instrument parameters

EIS provides monochromatic images of the transition region and the corona at high cadence using a slot. High spectral resolution images can be obtained by rastering with a slit. EIS is able to response to XRT's trigger. In addition it uses internal triggers - a flare trigger and a brightpoint trigger. Furthermore, there is an ability for automatic exposure control of the slots. 44)

Some science goals of EIS are:

• Active region loops: spatial determination of physical conditions as functions of position and time in active region loops

• Coronal hole boundaries: measurements of physical parameters inside and outside of coronal holes

• Quiet sun brightenings: determination of the relationship between different categories of quiet sun events

• Solar flares: spatial determination of evaporation, location of turbulence, and detection and measurement of reconnection flows in flares

• CME (Coronal Mass Ejection) onset: spatial velocity and dimming measurements at high temporal resolution.


Figure 26: Concept of the EIS instrument configuration (image credit: MSSL)


Figure 27: Schematic view of the EIS optics (image credit: MSSL, NAOJ)

Effective area

0.5 cm2 peak @ ~195 Å for 170-210 Å band
0.2 cm2 peak @ ~270 Å for 250-290 Å band

Expected line intensity from 1 arcsec x 1 arcsec area

Quiet sun

~30 photon/s for Fe XII 195
~6 photon/s for He II 256

Active region

~9 x 102 photon/s for Fe XII 195
~4 x 101 photon/s for He II 256
~4 x 102 photon/s for Fe XV 284

M2 class flare

~1 x 105 photon/s for Fe XXIV 192
~3 x 103 photon/s for He II 256
~2 x 104 photon/s for Fe XXIV 255
~1 x 103 photon/s for Fe XV 284

Accuracy of measurement

Doppler velocity: delta v=1.0 km/s for ~1x103 photons (Fe XV 284)
delta v=1.0 km/s for ~2 x104 photons (Fe XXIV 255)

Data compression in MDP (Mission Data Processor)

Bit compression: 16 to 12 bit or 14 to 12 bit compression

Data rate

~1/8 of total telemetry; ~40 kbit/s after compression

Control of EIS observation

Observing sequence in EIS ICU (Instrument Control Unit)

Table 7: EIS instrument performance


Figure 28: Schematic diagram of EIS showing the identity and location of the key subsystems (image credit: MSSL)


Figure 29: Photo of the EIS instrument (image credit: NAOJ)



3) T. Kosugi, K. Matsuzaki, T. Sakao, T. Shimizu, Y. Sone, S. Tachikawa, T. Hashimoto, K. Minesugi, A. Ohnishi, T. Yamada, S. Tsuneta, H. Hara, K. Ichimoto, Y. Suematsu, M. Shimojo, T. Watanabe, S. Shimada, J. M. Davis, L. D. Hill, J. K. Owens, A. M. Title, J. L. Culhane, L. K. Harra, G. A. Doschek, L. Golub, “The Hinode (Solar-B) Mission: An Overview,” Solar Physics, Vol. 243, No 1, June 2007, pp. 3-17


5) Takeo Kosugi, “International Collaboration to Study the Nature of Solar Activity,” URL:

6) S. Tsuneta, K. Ichimoto, Y. Katsukawa, S. Nagata, M. Otsubo, T. Shimizu, Y. Suematsu, M. Nakagiri, M. Noguchi, T. Tarbell, A. Title, R. Shine, W. Rosenberg, C. Hoffmann, B. Jurcevich, G. Kushner, M. Levay, B. Lites, D. Elmore, T. Matsushita, N. Kawaguchi, H. Saito, I. Mikami, L. D. Hill, J. K. Owens, “The Solar Optical Telescope for the Hinode Mission: An Overview,” Feb. 18, 2008, arXiv:0711.1715v3 [astro-ph], URL:

7) Hirohisa Hara, “Hinode: A New Solar Observatory in Space,” The Japan Society of Plasma and Nuclear Fusion Research, Vol. 2, 2007, p. 1008

8) Katsuhiko Tsuno, Takahisa Yamamoto, Masahito Kubo, Yoshifumi Shimizu, Eiji Hirokawa, Tatsuaki Hashimoto, “CCD sun sensors on board “Hinode” Solar Observatory,” Proceedings of the 7th ICSO (International Conference on Space Optics) 2008, Toulouse, France, Oct. 14-17, 2008

9) Y. Katsukawa, Y. Masada, T. Shimizu, S. Sakai, K. Ichimoto, “Pointing Stability of Hinode and Requirements for the next Solar Mission Solar-C,” ICSO 2010 (International Conference on Space Optics), Rhodes Island, Greece, Oct. 4-8, 2010, URL:


11) S. Tsuneta, K. Ichimoto, Y. Suematsu, T. Shimizu, H. Hara, R. Kano, S. Nagata, T. Tamura, M. Nakagiri, M. Noguchi, Y. Kato, T. Watanabe, Y. Hanaoka, M. Sawa, M. Otsubo, T. Kosugi, T. Yamada, T. Sakao, K. Matsuzaki, K. Minesugi, A. Onishi, Y. Katsukawa, K. Kobayashi, M. Kubo, “Development of the Solar-B Spacecraft,” 2001


13) “Hinode Views Sunspot Activity,” NASA, March 5, 2014, URL:

14) “HINODE captured total solar eclipse over Australia,” JAXA, Nov. 19, 2012, URL:

15) “Polar Field Reversal as observed with Hinode,” NAOJ, April 19, 2012, URL:

16) “Hinode observations revealed polar field reversal only at North Pole of the Sun!,” April 20, 2012, URL:

17) “Activity of Sunspot Cycle 24,” August 9, 2001, URL:

18) “Hinode Looks Into a Hole on the Sun,” NASA, URL:

19) “Annular solar eclipse observed by HINODE,” January 7, 2011, JAXA, URL:

20) Saku Tsuneta, “Hinode: A New Solar Observatory in Space,” AAPPS (Association of Asia Pacific Physical Sciences) Bulletin June 2009, Vol. 19, No. 3, URL:

21) Saku Tsuneta, Hinode - A New Solar Observatory in Space," AAPPS Bulletin, June 2009, Vol. 19, No. 3, pp. 11-18, URL:

22) “Hinode: source of the slow solar wind and superhot flares,”, April 2, 2008, ESA, URL:


24) Kiyoshi Ichimoto and the Hinode/SOT team, “Solar Optical Telescope onboard Hinode for Diagnosing the Solar Magnetic Fields,” The Japan Society of Plasma Science and Nuclear Fusion Research, Volume 2, 2007, S1009 -1 to S1009-6

25) T. Watanabe and the Solar-B Team, “Solar-B Scientific Operation and its Observation Modes,” 35th COSPAR Scientific Assembly, Paris, France, July 18-25, 2004

26) T. Kosugi and the Solar-B Team, “Solar-B: A New Challenge to the Magnetic Sun,” 35th COSPAR Scientific Assembly, Paris, France, July 18-25, 2004

27) C. Korendyke, C. Brown, J. Seely, S. Myers, “International collaboration yields a high-performance EUV spectrometer for Solar-B spacecraft,” SPIE's oe magazine (Optical Engineering), Aug. 2002, pp. 23-26

28) S. Tsuneta, A. Title, “Science with Solar-B Solar Optical Telescope,” 5th COSPAR Scientific Assembly, Paris, France, July 18-25, 2004

29) S. Tsuneta, “Solar-B Mission and Optical Telescope Assembly,”URL:

30) Solar Optical Telescope (SOT), URL:

31) Yoshinori Suematsu, Kiyoshi Ichimoto, Yukio Katsukawa, Saku Tsuneta, Toshifumi Shimizu, “Instrument design and on-orbit performance of the Solar Optical Telescope aboard Hinode (SOLAR-B),” Proceedings of the 7th ICSO (International Conference on Space Optics) 2008, Toulouse, France, Oct. 14-17, 2008

32) Kiyoshi Ichimoto, Saku Tsuneta, Yoshinori Suematsu, Toshifumi Shimizu, Masashi Otsubo, Yoshihiro Kato, Motokazu Noguchi, Masao Nakagiri, Tomonori Tamura, Yukio Katsukawa, Masahito Kubo, Yasushi Sakamoto, Hirohisa Hara, Kenji Minesugi, Akira Ohnishi, Hideo Saito, Noboru Kawaguchi, Tadashi Matsushita, Toshitaka Nakaoji, Kazuhiro Nagae, Joji Sakamoto, Yoshihiro Hasuyama, Izumi Mikami, Keizo Miyawaki, Yasushi Sakurai, Nobuaki Kaido, Toshihide Horiuchi, Sadanori Shimada, Toshio Inoue, Masaaki Mitsutake, Norimasa Yoshida, Osamu Takahara, Hidenori Takeyama, Masaharu Suzuki, Shun-ichi Abe, “The Solar Optical Telescope onboard the Solar-B,” Sept. 8, 2004

33) L. Golub, “New Dimensions in Coronal Studies from the XRT on Solar-B,” 35th COSPAR Scientific Assembly, Paris, France, July 18-25, 2004

34) R. Kano, T. Sakao, H. Hara, S. Tsuneta, K. Matsuzaki, K. Kumagai, M. Shimojo, K. Minesugi, K. Shibasaki, E. E. DeLuca, L. Golub, J. Bookbinder, D. Caldwell, P. Cheimets, J. Cirtain, E. Dennis, T. Kent, M. Weber, “The Hinode X-Ray Telescope (XRT): Camera Design, Performance and Operations,” Solar Physics, ISSN: 0038-0938 (Print) 1573-093X (Online), DOI: 10.1007/s11207-007-9058-7, SpringerLink Date: Dec. 25, 2007, URL:

35) E. DeLuca, “The X-Ray Telescope for Solar-B,” 37th AAS/SPD (Solar Physics Division) Meeting, UNH, Durham, NH, USA, June 25-30, 2006

36) X-ray Telescope (XRT), URL:

37) T. Sakao, R. Kano, H. Hara, K. Matsuzaki, M. Shimojo, S. Tsuneta, T. Kosugi, K. Shibasaki, K. Kumagai, M. Sawa, T. Tamura, S. Iwamura, M. Nakano, Z. Du, K. Hiyoshi, M. Horii, L. Golub, J. A. Bookbinder, P. C. Cheimets, L. D. Hill, J. K. Owens, “Focal Plane CCD Camera for the X-Ray Telescope (XRT) aboard SOLAR-B,” Sept. 8, 2004

38) J. L. Culhane, G. A. Doschek, T. Watanabe, “Solar-B EIS and its Scientific Goals,” 35th COSPAR Scientific Assembly, Paris, France, July 18-25, 2004

39) J. Len. Culhane, George A. Doschek, Tetsuya Watanabe, James Lang,, “The EUV Imaging Spectrometer and its Role in the Solar-B Mission,” URL:

40) G. A. Doschek, C. M. Brown, C. M. Korendyke, J. T. Mariska, S. H. Myers, J. F. Seely, K. P. Dere, J. Lang, J. L. Culhane, T. Watanabe, “The Extreme Ultraviolet Imaging Spectrometer (EIS) on Solar-B,” Summer 2006 Solar Physics Division/AAS meeting, University of New Hampshire, Durham, New Hampshire, USA, June 25-26, 2006

41) J. L. Culhane, L. K. Harra, G. A. Doschek, J. T. Mariska, T. Watanabe, H. Hara, “The Solar-B EUV imaging spectrometer and its science goals,” Advances in Space Research, Vol. 36, Issue 8, 2005, pp. 1494-1502

42) J. L. Culhane, L. K. Harra, A. M. James, K. Al-Janabi, L. J. Bradley, R. A. Chaudry, K. Rees, J. A. Tandy, P. Thomas, M. C. R. Whillock, B. Winter, G. A. Doschek, C. M. Korendyke, C. M. Brown, S. Myers, J. Mariska, J. Seely, J. Lang, B. J. Kent, B. M. Shaughnessy, P. R. Young, G. M. Simnett, C. M. Castelli, S. Mahmoud, H. Mapson-Menard, B. J. Probyn, R. J. Thomas, J. Davila, K. Dere, D. Windt, J. Shea, R. Hagood, R. Moye, H. Hara, T. Watanabe, K. Matsuzaki, T. Kosugi, V. Hansteen, and O. Wikstol, “The EUV Imaging Spectrometer for Hinode,” Solar Physics, Vol. 243, No 1, June 2007, pp. 19-61

43) H. Hara, “EUV Imaging Spectrometer,” 2005, URL:


The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: ”Observation of the Earth and Its Environment: Survey of Missions and Sensors” (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates.