We have planned the Lunar observatory project, TSUKUYOMI aiming to meter-wavelength observations on the Moon. One of the scientific objectives is to observe the 21 cm global signal from the Dark Ages using the 1–50 MHz observing frequency range. The receiving system must have a noise temperature sufficiently lower than the foreground noise and also requires the flat bandpass response. To cover the ultra-wide bandwidth, an electrically-short dipole antenna and a preamplifier with high input impedance will be employed. This paper focuses on a feasibility study of the system performance. The environment of and around the observation site, such as the lunar surface dielectric constant and the antenna height from the ground plane, affects the sensitivity because it alters important parameters such as the antenna beam pattern and impedance. The investigation results of relationship between the surrounding environment and the sensitivity will be also reported.
Understanding the origin of the Martian moons is the main objective of the JAXA MMX (Martian Moons eXploration) mission, that will be launched in October 2026. Among the 13 instruments composing the payload, MIRS is an infrared imaging spectrometer that will map the mineralogy and search for organic compounds on the moons’ surfaces. MIRS will also study the Martian atmosphere, focusing on the spatial and temporal variations of water, dust and clouds. MIRS is operating in the 0.9-3.6 μm spectral range with a spectral resolution varying from 22 nm to 32 nm. The field of view covers 3.3° whereas the instantaneous field of view is 0.35 mrad. This presentation will detail the design and present the end-to-end performance obtained during the final instrument test in a representative thermal environment.
Low-frequency radio observations below 50 MHz on the Moon are not subject to some radio interference, allowing for the study before the formation of the first star, which is impossible from the Earth. Our lunar observatory project, TSUKUYOMI, aims to observe the 21cm global signal from the Dark Ages, requiring wideband observations covering 1-50MHz to spot absorption features of ∼ 40 mK relative to the CMB. Considering the radiation from the Milky Way, which is the main foreground noise source and the reception characteristics of the short dipole antenna, a pre–amplifier with a noise lower than 2nV/√ Hz and an input capacitance of 25pF will result in a system noise well below foreground noise over the entire bandwidth and a roughly flat wideband response. Managing the input/floating capacitance and using a lumped constant circuit is crucial for wideband performance. This paper outlines the wideband system and delves into the system performance requirements.
Aim to Japan's participation in the Artemis program in the 2030s in mind, we pursue the feasibility studies of lunar telescope, including astronomical observations. Focusing on the meter-wavelength observations (observing frequency of lower than 50MHz), which cannot be observed in the harsh environments on the ground from the Earth, including the ionosphere and radio frequency interference, we have reported on conceptual design based on the results of our feasibility studies in Japan. The main scientific objectives we have studied so far are broadly covering the following three areas: astronomy and astrophysics, planetary science, and lunar science. In astrophysics, the observing frequency range of 1- 50MHz gives us an opportunity to observe the 21 cm global signal (spatial average temperature) from the Dark Ages, which is determined purely by cosmology and is not affected by first-generation star formation and cosmic reionization. In astronomy, it provides the images of the Milky Way galaxy at meter wavelengths. In planetary science, it will be possible to study the environments of exoplanets through 1) radio waves from auroras on gas giant exoplanets like Jupiter and 2) stellar radio-wave bursts. In lunar science, it has the potential to observationally study the lunar ionosphere, subsurface structure, and dust environment. At present, we plan the meter-wavelength interferometric array as lunar telescope, including the single-dish observations. In this paper, focused on the scientific requirements from cosmology, we will report the design concepts of Japanese lunar telescope project, including the advanced feasibility studies of antenna, receiver, signal chain and spectrometer that are compared as other studies in US, China and Europe. We named this project TSUKUYOMI.
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.
GEOspace X-ray imager (GEO-X) is a small satellite mission aiming at visualization of the Earth’s magnetosphere by X-rays and revealing dynamic couplings between solar wind and the magnetosphere. In-situ spacecraft have revealed various phenomena in the magnetosphere. X-ray astronomy satellite observations recently discovered soft X-ray emissions originating from the magnetosphere. We are developing GEO-X by integrating innovative technologies of a wide field of view (FOV) X-ray instrument and a small satellite for deep space exploration. The satellite combines a Cubesat and a hybrid kick motor, which can produce a large delta v to increase the altitude of the orbit to about 30 to 60 RE from a relatively low-altitude (e.g., geo transfer orbit) piggyback launch. GEO-X carries a wide FOV (5 × 5 deg) and a good spatial resolution (10 arcmin) X-ray (0.3 to 2 keV) imaging spectrometer using a micro-machined X-ray telescope and a CMOS detector system combined with an optical blocking filter. We aim to launch the satellite around the solar maximum of solar cycle 25.
GEO-X (GEOspace X-ray imager) is a small satellite mission aiming at visualization of the Earth’s magnetosphere by X-rays and revealing dynamical couplings between solar wind and magnetosphere. In-situ spacecraft have revealed various phenomena in the magnetosphere. In recent years, X-ray astronomy satellite observations discovered soft X-ray emission originated from the magnetosphere. We therefore develop GEO-X by integrating innovative technologies of the wide FOV X-ray instrument and the microsatellite technology for deep space exploration. GEO-X is a 50 kg class microsatellite carrying a novel compact X-ray imaging spectrometer payload. The microsatellite having a large delta v (<700 m/s) to increase an altitude at 40-60 RE from relatively lowaltitude (e.g., Geo Transfer Orbit) piggyback launch is necessary. We thus combine a 18U Cubesat with the hybrid kick motor composed of liquid N2O and polyethylene. We also develop a wide FOV (5×5 deg) and a good spatial resolution (10 arcmin) X-ray (0.3-2 keV) imager. We utilize a micromachined X-ray telescope, and a CMOS detector system with an optical blocking filter. We aim to launch the satellite around the 25th solar maximum.
MIRS (MMX InfraRed Spectrometer) is an imaging spectrometer onboard of MMX (Martian Moon eXploration) mission. MMX is a JAXA sample return mission that will be launched in September 2024 to Martian system, to bring back to Earth sample from Phobos, to observe in detail Phobos and Deimos and to monitor Mars’s atmosphere with observations of dust storm, clouds, and distributions of total amount of water vapor. The main objectives of the mission are to understand the origin of Martian moons, to constrain the processes for planetary formation and to understand the evolutionary processes of the Martian system. MIRS is a push-broom imaging spectrometer working in the range from 0.9 to 3.6 micron.
GEO-X (GEOspace X-ray imager) is a 50 kg-class small satellite to image the global Earth’s magnetosphere in X-rays via solar wind charge exchange emission. A 12U CubeSat will be injected into an elliptical orbit with an apogee distance of ∼40 Earth radii. In order to observe the diffuse soft X-ray emission in 0.3-2 keV and to verify X-ray imaging of the dayside structures of the magnetosphere such as cusps, magnetosheaths and magnetopauses which are identified statistically by in-situ satellite observations, an original light-weight X-ray imaging spectrometer (∼10 kg, ∼10 W, ∼10×10×30 cm) will be carried. The payload is composed of a ultra light-weight MEMS Wolter type-I telescope (∼4×4 deg2 FOV, <10 arcmin resolution) and a high speed CMOS sensor with a thin optical blocking filter (∼2×2 cm2 , frame rate ∼20 ms, energy resolution <80 eV FWHM at 0.6 keV). An aimed launch year is 2023-25 corresponding to the 25th solar maximum.
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