We present the design and performance of the XRISM Soft X-Ray Spectrometer Resolve, successfully launched on a JAXA H-IIA rocket September 7, 2023. The instrument uses a 36-pixel array of microcalorimeters at the focus of a grazing-incidence x-ray mirror. The instrument has achieved an energy resolution of 4.5 eV (FWHM) at 6. The overall cooling chain was designed to provide a lifetime of at least 3 years in orbit and operate without liquid helium to provide redundancy and the longest operational lifetime for the instrument. Early indications that the cryogen lifetime will exceed 4 years. X-rays are focused onto the array with a high-throughput grazing incidence X-ray Mirror Assembly with over 200 nested two-stage X-ray reflectors. A series of onboard X-ray calibrations sources allow simultaneous energy scale calibration lines simultaneously while observing celestial sources. The inflight performance of Resolve will be described along with a summary of the scientific capabilities.
The initial on-orbit checkout of the soft X-ray spectroscopic system on board the XRISM satellite is summarized. The satellite was launched on September 6, 2023 (UT) and has been undergoing initial checkout since then. Immediately after the launch, the cryocoolers were turned on and their operation was established. The first cycle of the adiabatic demagnetization refrigerator was performed on Oct. 9th, 2023, to transition the sensor to steady-state operational temperature conditions. Subsequently, the filter wheel, which supports energy calibration, was started up. The energy scale is highly sensitive to the temperature environment around the sensor and its analog electronics. The gain correction was established by referring to the calibration X-ray line. For an optimization of the cooler frequencies, we took data including the noise spectra by scanning the cooler frequencies, and selected a good frequency pair in the on-orbit environment. At the last stage of the checkout, the gate valve, which protects the inside of the Dewar from outside air pressure at launch, was attempted to be opened to bring the system to a state where it is ready for regular operations but was failed.
Lobster eye optics are expected as to be a wide-field telescope and are suitable for future X-ray sky surveys and monitoring missions. The ultra-lightweight X-ray optics have been developed using MEMS technologies and the same way can be applied to the fabrication of lobster eye optics. A large number of slits with 20 micro-meters width were formed by an etching process in a 4-inch Si wafer with 300 micro-meters thickness. To collect X-rays on a focal plane, the wafer was plastic-deformed into a spherical shape with a radius of curvature of 1000 mm. Two deformed wafers were assembled in such a way as to arrange the slits of each wafer orthogonally. Then, samples of lobster eye optics were completed and the fabrication process flow with MEMS technologies can be confirmed.
We have been developing ultra-lightweight Wolter type-I X-ray telescopes fabricated with MEMS technologies for GEO-X (GEOspace X-ray imager) which is a small satellite mission to perform soft X-ray imaging spectroscopy of the entire Earth’s magnetosphere. The telescope is our original type of micropore optics and possesses lightness (∼5 g), a short focal length (∼250 mm), and a wide field of view (∼5° × ∼5°). The MEMS X-ray telescope is made of 4-inch Si (111) wafers. The Si wafer is first processed by deep reactive ion etching, which has numerous curvilinear micropores (a 20-μm width) whose sidewalls are utilized as X-ray reflective mirrors. High-temperature hydrogen annealing and chemical mechanical polishing processes are applied to make those sidewalls smooth and flat enough to reflect X-rays. After that, the wafer is plastic-deformed into a spherical shape and Pt-coated by a plasma atomic layer deposition process to focus X-rays with high reflectivity. Finally, we assemble two optics bent with different curvatures (1000- and 333-mm radii) and complete the Wolter type-I telescope. We optimized each process and conducted an X-ray irradiation test to assemble the full-processed optics into an EM telescope for the GEO-X mission, which enabled to complete the telescope to achieve an angular resolution of ∼4.8 arcmin in FWHM in the assembled telescope. We report on our latest development status and the X-ray imaging performance of the GEO-X EM telescope.
GEO-X (GEOspace X-ray imager) is a small satellite mission to visualize the Earth’s magnetosphere through Solar Wind Charge eXchange (SWCX). SWCX is known as soft X-ray emissions generated by the charge exchange between highly charged-state heavy ions and neutral atoms in the Earth’s exosphere. The GEO-X satellite is aimed to be launched during the upcoming solar maximum around 2025-2027 and is planned to be injected to a low-latitude orbit which allows visualization of the magnetosphere from outside the magnetosphere. The satellite will carry a light-weight X-ray imaging spectrometer, dramatically improving the size and weight of those onboard past X-ray astronomy satellites.
The X-Ray Imaging and Spectroscopy Mission (XRISM) project at JAXA officially started in 2018. Following the development of onboard components, the proto-flight test was conducted from 2021 to 2023 at JAXA Tsukuba Space Center. The spacecraft was launched from JAXA Tanegashima Space Center on September 7, 2023 (JST), and onboard components, including the science instruments, were activated during the in-orbit commissioning phase. Following the previous report in 2020, we report the spacecraft ground tests, the launch operation, in-orbit operations, and the status and plan of initial and subsequent guest observations.
Resolve is the instrument that utilizes an X-ray micro-calorimeter array onboard the XRISM (X-Ray Imaging and Spectroscopy Mission), which was launched on September 6 (UT), 2023. It fully met the spectral performance requirement (7 eV at 6 keV) both on the ground and in orbit and was confirmed to have the same performance as the SXS onboard the ASTRO-H (Hitomi) satellite. The detectors are operated at a low temperature of 50 mK to achieve the required energy resolution with the cooling system to satisfy the lifetime requirement of over 3 years. The cooling system is equipped with a 3-stage ADR and superfluid liquid He (LHe) as the heat sink for the ADR. The Joule-Thomson cooler unit and 2-stage Stirling cooler units are adopted to reduce heat load to the LHe. In the pre-launch operations, we carried out the low-temperature LHe top-off operation. The resultant amount of liquid He was over 35 L at the launch, which is sufficient to meet the lifetime requirement. During the post-launch operation, the LHe vent valve was opened five minutes after launch during the rocket acceleration, and the cryocoolers started in several revolutions as planned which established stable cooling of the dewar.
We are developing a complementary metal oxide semiconductor (CMOS) camera to be onboard GEO-X (GEOspace X-ray imager) microsatellite. The GEO-X mission observes soft X-rays produced by Solar Wind Charge eXchange (SWCX), in which ions in the solar wind collide with atoms in the Earth’s exosphere and steal electrons, to visualize the day-side magnetospheric boundary. The payload of the satellite is approximately 3U (∼ L 10 cm ×W 10 cm × H 30 cm) in size and approximately 10 kg in mass and consists of the X-ray telescope and a focal plane detector. A back-side illuminated CMOS sensor is placed on the focal plane of the X-ray telescope, and the optical blocking filter is used for high-sensitivity imaging spectroscopy of X-rays from 0.3−2.0 keV. The design and fabrication of the printed circuit boards for housekeeping data collection and the housing assembly are also ongoing. We implement our own on-board event extraction logic to achieve data acquisition at 48 fps without any data loss. In addition, we performed functional testing of a digital processing board using SoC (Zynq) and its radiation tolerance investigation and found that the pedestal level is stable even when irradiated Zynq with 100 MeV/u protons. Furthermore, we irradiated the sensor cooled to −35 °C with polychromatic X-rays of 0.5 − 7.0 keV to evaluate the spectral performance of the sensor. The energy resolution is found to be 120 eV (FWHM) at 0.6 keV and the lower edge of the effective energy range is below 300 eV.
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