Japan Geoscience Union Meeting 2025

Presentation information

[E] Poster

P (Space and Planetary Sciences ) » P-CG Complex & General

[P-CG20] Future missions and instrumentation for space and planetary science

Thu. May 29, 2025 5:15 PM - 7:15 PM Poster Hall (Exhibition Hall 7&8, Makuhari Messe)

convener:Takefumi Mitani(Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science), Masaki Kuwabara(Rikkyo University), Shoichiro Yokota(Graduate School of Science, Osaka University), Yuichiro Cho(Department of Earth and Planetary Science, University of Tokyo)


5:15 PM - 7:15 PM

[PCG20-P10] Development of Radiation Monitor for Space weather measuring Electrons (RMS-e) for Himawari-10

*Taku Namekawa1, Kaori Sakaguchi2, Kenichi Otsuji1, Park Inchun1, Shinji Saito1, Takefumi Mitani3 (1.National Institute of Information and Communications Technology, 2.Ministry of Internal Affairs and Communications, 3.Japan Aerospace Exploration Agency)

Keywords:Space weather, High-energy electrons, Geostationary meteorological satellite, Solid-state detectors

Radiation Monitor for Space weather measuring Electrons (RMS-e) is an electron detector that will be installed on the next geostationary meteorological satellite Himawari-10 to provide continuous observations of high-energy electrons in the geostationary satellite orbit over Japan. Current space weather forecasting in Japan is based on observations from the GOES satellites, which have different conditions from the space environment around the geostationary satellite orbits over Japan. RMS-e will provide continuous observations of energetic electrons in geostationary satellite orbits over Japan, which are critical for improving the accuracy of space weather forecasts in Japan.
RMS-e consists of two sets of stacked solid-state detectors (SSDs) made of silicon semiconductors called RMS-e lo and RMS-e hi. RMS-e lo and RMS-e hi are designed to measure electrons with energies in the range of 50 keV to 1300 keV and 0.8 to 5 MeV, respectively. The energy resolution of RMS-e lo is 26% for 50 keV electrons and that of RMS-e hi is 15.8% for 1 MeV electrons based on the results of electron irradiation tests performed on the engineering model (EM) of RMS-e. Qualitative confirmation of the effect of the collimator, which determines the field of view of RMS-e lo and RMS-e hi, has also been completed based on the results of electron irradiation tests.
We are currently developing a proto-flight model (PFM) of RMS-e with the aim of supplying observation data in 2029. In this presentation, we report on the development status of RMS-e and the results of the irradiation tests conducted on RMS-e EM.