Language：Japanese  

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Elsevier BV  

DOI： 10.1016/j.actaastro.2025.05.048

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.23.18

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.23.9

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Publishing type：Research paper (international conference proceedings)   Publisher：International Astronautical Federation (IAF)  

DOI： 10.52202/083084-0088

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Language：Japanese  

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Elsevier BV  

DOI： 10.1016/j.actaastro.2024.06.042

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/astj.22.51

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Language：Japanese   Publishing type：Research paper (conference, symposium, etc.)  

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Elsevier BV  

DOI： 10.1016/j.actaastro.2023.08.044

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Elsevier BV  

DOI： 10.1016/j.actaastro.2023.03.040

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.21.29

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.20.49

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Springer Science and Business Media LLC  

Abstract

Volatile and organic-rich C-type asteroids may have been one of the main sources of Earth’s water. Our best insight into their chemistry is currently provided by carbonaceous chondritic meteorites, but the meteorite record is biased: only the strongest types survive atmospheric entry and are then modified by interaction with the terrestrial environment. Here we present the results of a detailed bulk and microanalytical study of pristine Ryugu particles, brought to Earth by the Hayabusa2 spacecraft. Ryugu particles display a close compositional match with the chemically unfractionated, but aqueously altered, CI (Ivuna-type) chondrites, which are widely used as a proxy for the bulk Solar System composition. The sample shows an intricate spatial relationship between aliphatic-rich organics and phyllosilicates and indicates maximum temperatures of ~30 °C during aqueous alteration. We find that heavy hydrogen and nitrogen abundances are consistent with an outer Solar System origin. Ryugu particles are the most uncontaminated and unfractionated extraterrestrial materials studied so far, and provide the best available match to the bulk Solar System composition.

DOI： 10.1038/s41550-022-01745-5

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Other Link： https://www.nature.com/articles/s41550-022-01745-5

Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Frontiers Media SA  

In this article, a self-reconfiguring OrigamiSat concept is presented. The reconfiguration of the proposed OrigamiSat is triggered by combining the effect of 4D material (i.e. origami’s edges) and changes in the local surface optical properties (i.e., origami’s facets) to harness the solar radiation pressure acceleration. The proposed OrigamiSat uses the principle of solar sailing to enhance the effect of the Sun radiation to generate momentum on the Aluminised Kapton (Al-Kapton) origami surface by transitioning from mirror-like to diffusely reflecting optical properties of each individual facet. Numerical simulations have demonstrated that local changes in the optical properties can trigger reconfiguration. A minimum of 1-m edge size facet is required for a thick-origami to generate enough forces from the Sun radiation. The thick-origami pattern is 3D-printed directly on a thin Al-Kapton film (the solar sail substrate which is highly reflective). An elastic filament (thermoplastic polyurethane TPU) showed best performance when printing directly on the Al-Kapton and the Acrylonitrile Butadiene Styrene with carbon fiber reinforcement (ABS/cc) is added to augment the origami mechanical properties. The 4D material (shape memory polymer) is integrated only at specific edges to achieve self-deployment by applying heat. Two different folding mechanisms were studied: 1) the cartilage-like, where the hinge is made combining the TPU and the 4D material which make the mounts or valleys fully stretchable, and 2) the mechanical hinge, where simple hinges are made solely of ABS/cc. Numerical simulations have demonstrated that the cartilage-like hinge is the most suitable design for light-weight reconfigurable OrigamiSat when using the solar radiation pressure acceleration. We have used build-in electric board to heat up the 4D material and trigger the folding. We envisage embedding the heat wire within the 4D hinge in the future.

DOI： 10.3389/frspt.2022.876585

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Authorship：Corresponding author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/astj.21.21

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：American Association for the Advancement of Science (AAAS)  

DOI： 10.1126/science.abj8624

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.2514/1.a35043

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1038/s41550-021-01550-6

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Other Link： https://www.nature.com/articles/s41550-021-01550-6

Language：English   Publishing type：Research paper (scientific journal)   Publisher：American Institute of Aeronautics and Astronautics (AIAA)  

DOI： 10.2514/1.a35084

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Part of collection (book)   Publisher：Elsevier  

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Language：English   Publishing type：Part of collection (book)   Publisher：Elsevier  

DOI： 10.1016/b978-0-323-99731-7.00017-9

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/astj.20.134

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Springer Science and Business Media LLC  

DOI： 10.1038/s41550-021-01371-7

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Other Link： https://www.nature.com/articles/s41550-021-01371-7

Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.19.477

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.19.604

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.19.584

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Authorship：Corresponding author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

Spin-type solar sails have the advantage of being lighter compared to other deployment methods, but can exhibit complex deployment dynamics. Severe asymmetric dynamics was observed in the deployment experiment in a vacuum chamber. In this study, this deployment behavior is reproduced by numerical simulations using multi-particle techniques that take into account membrane collisions. We propose a simple method to predict whether a significant asymmetry will occur by calculating the energy change of the membrane. The conditions for realizing symmetric deployment are presented.

DOI： 10.2322/astj.20.73

CiNii Research

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Elsevier BV  

DOI： 10.1016/j.asr.2020.06.005

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Elsevier BV  

DOI： 10.1016/j.asr.2020.10.007

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Elsevier {BV}  

DOI： 10.1016/j.actaastro.2021.01.020

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Elsevier BV  

DOI： 10.1016/j.icarus.2020.114220

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：American Institute of Aeronautics and Astronautics (AIAA)  

DOI： 10.2514/1.j059717

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Springer Science and Business Media LLC  

DOI： 10.1038/s41550-020-01271-2

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Other Link： http://www.nature.com/articles/s41550-020-01271-2

Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1016/j.actaastro.2020.10.031

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1038/s41550-020-1179-z

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1007/s42064-020-0083-8

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (international conference proceedings)  

DOI： 10.1007/s42064-019-0063-z

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Springer Science and Business Media LLC  

DOI： 10.1007/s42064-019-0062-0

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Other Link： http://link.springer.com/article/10.1007/s42064-019-0062-0/fulltext.html

Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Springer Science and Business Media LLC  

DOI： 10.1007/s42064-019-0067-8

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Other Link： http://link.springer.com/article/10.1007/s42064-019-0067-8/fulltext.html

Authorship：Corresponding author   Language：Japanese   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

<p>Solar sail technique was demonstrated in the IKAROS mission. However, the membrane of IKAROS has deformed to a shape that was not flat. The whole membrane changes greatly like an umbrella shape or a saddle shape depending on the warping direction of the thin-film devices on the membrane, such as thin-film solar cells, reflectivity control devices and dust counters. Objection of this study is to clarify mechanism of influence on solar radiation pressure (SRP) torque due to warp of thin-film device and its solution method. Therefore, the shape of the overall membrane is clarified by using a simple finite element model and the SRP torque with respect to the shape is calculated, and the mechanism of the overall shape change in warpage and its influence is clarified. As a result, the influence on SRP is related to membrane stiffness and warped direction and it is found that the suitable conditions to minimize SRP torque are as follows: a) the sail is warped in the radial direction, b) the base film of the sail has low stiffness, c) the outermost part of the sail has high stiffness, and d) the length of bridges between petals is short.</p>

DOI： 10.2322/astj.JSASS-D-19-00044

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1126/science.aaz6306

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：American Association for the Advancement of Science (AAAS)  

DOI： 10.1126/science.aaz1701

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1038/s41586-020-2102-6

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Language：Japanese   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

<p>At bipropellant chemical propulsion systems, iron in oxidizer is one of the topics to be noted and controlled. Actually, to avoid the influence of the iron ingredient, several long term mission spacecraft such as interplanetary probes flush the oxidizer piping periodically. The major influence of steel contaminated oxidizer is known to be flow decay. Still, operation data of the HAYABUSA2 spacecraft indicates possibility of other drawbacks. This paper discusses its impact to the reactivity of the hypergolic propellant, especially for the propellant combination of N₂H₄/MON3, which is the case of HAYABUSA2. A series of open cup firing tests show that the reactivity deteriorates when the oxidizer is contaminated with iron.</p>

DOI： 10.2322/astj.JSASS-D-19-00032

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Language：Japanese   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

<p>A thin-film device mounted on development type membrane structure is limited to arrangement and deployment on the plane. In this paper, we propose a three-dimensional film structure (3D film) that can stereoscopically place and deploy thin-film devices. This method can be widely applied to non-spin type or spin type developable structures having a mast structure. In this paper, in order to apply to non-spin / spin type developed structures, we evaluate extension shapes of 3D film by crease and condition of existence / nonexistence of centrifugal force, and placement and arrangement of thin-film devices.</p>

DOI： 10.2322/astj.JSASS-D-19-00008

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.2514/1.G003776

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.17.603

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1007/s42064-019-0056-y

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1007/s42064-018-0047-4

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：American Association for the Advancement of Science (AAAS)  

DOI： 10.1126/science.aav8032

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：American Association for the Advancement of Science (AAAS)  

DOI： 10.1126/science.aaw0422

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1016/j.icarus.2018.12.011

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Language：Japanese   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

<p>The membrane of a spinning solar sail IKAROS is considered to be deformed toward the Sun. The deformation was kept even under low spin rate. Previous studies suggest that curvature of thin-film solar cells on the membrane increases the out-of-plane stiffness. For a solar power sail OKEANOS, the shape, out-of-plane stiffness, and natural frequency have to be predicted. In this paper, the effect of a curved thin-film device on the natural frequency of a rectangle membrane under uniaxial tension is investigated. Three types of membranes are evaluated: a membrane with a curved thin-film device, a membrane with a flat thin-film device, a plane membrane. Geometric nonlinear finite element analysis and eigenvalue analysis are conducted to investigate the natural frequencies under varying tension. The simulations are verified by vibration experiments. It is found that under low tension, the natural frequency of the membrane with the curved thin-film device is significantly higher than that of the others and that under high tension, the natural frequency of the membrane with the thin-film device is slightly lower than that of the plane membrane. The results show that curved thin-film devices have a significant impact on the out-of-plane stiffness of a membrane under low tension.</p>

DOI： 10.2322/astj.JSASS-D-17-00088

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Authorship：Lead author,　Corresponding author   Language：Japanese   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

<p>The chemical propulsion system of Hayabusa-2 consists of 12 bipropellant thrusters whose thrust is 20N. The communication with Hayabusa was lost due to the fuel leakage just after touchdown in 2005. Akatsuki failed to enter orbit around Venus in 2010. The chemical propulsion system of Hayabusa-2 took measure to prevent these accidents. It satisfied the requirements of continuous injection for SCI (Small Carry-on Impactor) operation. The short injection impulse was estimated using flight data. It was changed by the thruster temperature and the frequency of use. The approximation of the long injection impulse was improved using TCM (Trajectory Correction Maneuver) data and VIC (Velocity Increment Cut) test data. This paper presents development and outward operation of the chemical propulsion system of Hayabusa-2.</p>

DOI： 10.2322/astj.JSASS-D-18-00008

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.2514/1.A34201

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Language：English   Publishing type：Research paper (international conference proceedings)  

DOI： 10.2514/1.A34165

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1016/j.pss.2018.06.020

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.16.500

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.16.353

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.16.306

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.2322/tjsass.61.119

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.16.328

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1093/mnras/stx3092

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Language：Japanese   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

<p>IKAROS is a solar power sail demonstrator launched by JAXA in 2010. IKAROS successfully deployed its large sail by a centrifugal force due to the spin motion of the spacecraft body and obtained a solar power sail navigation. In the evaluation of IKAROS membrane shape, some unexpected phenomena were observed; (1) tether connecting IKAROS membrane and main body got loose in spite of normal spin rate, and (2) the membrane was not warped by photon pressure in spite of low spin rate. The purpose of this paper is to understand generation mechanisms about these unexpected phenomena. Because thin-film devices of thin-film solar cell and reflectivity control device are multilayer film structures, curves occur. The bending stiffness of IKAROS membrane is increased due to the curve. This paper presents the multi-particle model of the membrane considering curve and bending moment of thin-film device. The membrane shape is estimated by numerical simulations and the influence of the thin-film device is made clear.</p>

DOI： 10.2322/astj.JSASS-D-17-00050

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1016/j.actaastro.2017.07.050

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Authorship：Last author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/astj.jsass-d-17-00004

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Authorship：Lead author,　Corresponding author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

DOI： 10.14822/kjsass.65.7_208

CiNii Books

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.14.pt_25

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.14.pq_7

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

<p>The latest re-acquisition of IKAROS, which rebooted after hibernation mode, was achieved on April 23, 2015. In this re-acquisition, post-processing of open-loop tracking data was performed to search for IKAROS. The open-loop method enables signal processing, even under difficult communication conditions. The algorithm for processing open-loop tracking data is proposed and is applied for actual signal from IKAROS. It is demonstrated that the signal can be well analyzed by removing the Doppler shift effect because of the orbital and spinning motion of IKAROS, even when the signal is too weak to be acquired by real-time operation. Using the method proposed in this study, estimating the spinning motion of a spacecraft and acquiring various data are possible as well as detecting signal. This research can be applied not only to a spinning-type spacecraft, such as IKAROS, but also to those with uncertain attitudes. </p>

DOI： 10.2322/tastj.14.pj_13

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

<p>JAXA has developed a Jovian Trojan asteroid sample return mission using a solar power sail. Jovian Trojan asteroids are among the few remaining frontiers in our solar system and may hold clues to its formation and evolution. However, visiting Jovian Trojans is much more difficult than reaching near-Earth objects because of the large amount of fuel required to reach them. Moreover, large distance from the sun makes power generation difficult. Solar power sails offer an effective way of realizing such challenging exploration. This paper outlines a solar power sail spacecraft and discusses the design of a trajectory for a sample return mission to a Jovian Trojan asteroid. The time of flight is long, but a large payload can be delivered to the asteroid by using a solar power sail. Reducing the duration of a sample return mission is difficult, but it is possible for a one-way mission. This paper presents a trajectory design for such a one-way mission.</p>

DOI： 10.2322/tastj.14.pd_127

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.14.pk_1

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.14.9

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

DOI： 10.14822/kjsass.63.11_355

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Language：English   Publishing type：Research paper (international conference proceedings)  

DOI： 10.2514/1.A33158

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Authorship：Last author   Language：Japanese   Publishing type：Research paper (scientific journal)  

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Authorship：Lead author,　Corresponding author   Language：Japanese   Publisher：日本航空協会  

CiNii Books

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Authorship：Lead author,　Corresponding author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：日本航空宇宙学会  

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

This study estimates the effect of creases, or plastic wrinkle lines, on the out-of-plane stiffness of solar sails. A method to simulate the crease effects using reduced-order finite-element (FE) models is proposed, and is applied to a practical solar sail architecture. A detailed crease shape is determined by a geometrically nonlinear FE analysis using a simple model first; the effect of creases is then replaced by beam elements. This method substantially reduces the computational effort required for the FE analysis of a solar sail model. The result suggests the significant impact of creases on membranes out-of-plane stiffness when the tension level in the membrane is small.

DOI： 10.2322/tastj.12.pc_107

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

The solar power sail is a deep space probe that will be powered by a hybrid propulsion system with solar photon acceleration and ion engines to explore the outer planetary regions of the Solar System without having to rely on nuclear power. The Japan Aerospace Exploration Agency (JAXA) launched the worlds first solar sail demonstration spacecraft, "IKAROS" (Interplanetary Kite-craft Accelerated by Radiation Of the Sun), in 2010. This spacecraft successfully demonstrated several key technologies related to the use of a solar power sail in a deep space flight environment. JAXA is currently planning an outer Solar System exploration mission using the demonstrated solar power sail technology, where the spacecraft will fly to Jupiter and perform a swing-by for a Jovian Trojan asteroid. This study undertook a trajectory design and system feasibility analysis for this mission. Candidate target asteroids were selected based on ballistic trajectory analysis, and then, electric-propulsion, continuous-thrust trajectory design was conducted to verify the conditions assumed for the ballistic analysis (e.g., estimate of steering loss due to the low-thrust trajectory). It was found that out of over 4000 Trojan asteroids, only 7 are feasible candidates considering the preliminary system design results. To broaden the choice of target asteroids, it will be necessary to reduce the weight of the solar power sail itself, its deployment mechanism, and the bus electronics.

DOI： 10.2322/tastj.12.pd_85

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

This paper proposes a method to store a large solar-sail membrane while ensuring repeatability of its stored configuration. Large membranes used as a solar sail should be stored compactly to save the launch volume; in addition, their stored configuration should be sufficiently predictable in order to guarantee reliable deployment in orbit. However, it is difficult to store a large membrane compactly because of the finite thickness of the membrane. This paper demonstrates the feasibility of the proposed "bulging roll-up" method experimentally using 10m-size membranes, and evaluates the repeatability of its stored configuration quantitatively.

DOI： 10.2322/tastj.12.pc_75

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

Japan Aerospace Exploration Agency (JAXA) are planning an outer solar system exploration and sample return mission from a Jovian Trojan asteroid using a 3000 m² solar power sail. The difficulty of this mission is a severe restriction on the weight; only 300 kg is allocated for sampling and returning to Earth. In this weight, fuel for trajectory and attitude control, sampling mechanism, re-entry capsule, and other systems required to return to the Earth are included. In this paper, a preliminary analysis of this sample return mission is conducted. Three scenarios for sampling are proposed; sampling with a 3000 m² solar power sail, with a detachable small solar power sail using electric propulsion systems and with a small probe using chemical propulsion systems. The mission analysis shows that the most feasible configuration is to conduct the sampling with the 3000 m² solar power sail using an extension mast.

DOI： 10.2322/tastj.12.pk_43

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

A solar power sail demonstrator &ldquo;IKAROS&rdquo; deployed its square large membrane successfully by centrifugal force. The deployment consisted of two stages. The flight data suggest that the membrane deployment in the second stage was remarkably non-synchronous. This paper reproduces the non-synchronous deployment behavior using a small experimental model deployed in a vacuum chamber. Then, two kinds of finite-element analyses are conducted to show that the effect of membrane creases may have caused the non-synchronous deployment.

DOI： 10.2322/astj.13.71

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

Piecewise Straight Fold is proposed for large solar sail membranes to simultaneously realize the high packaging efficiency and the simple folding. The fold pattern is based on Spiral Fold to reduce the deviation of the fold line, which improve the packaging efficiency. In addition, the fold pattern consists of piecewise straight fold lines, which approximate the Spiral Fold line, in order to simplify the folding. A simple manufacturing process of Piecewise Straight Fold is developed based on the Z-fold membrane. The preliminary experimental results show the feasibility of the Piecewise Straight Fold and its simple manufacturing process, where the high packaging efficiency is also verified. The wrapping fold experiments for the solar power sail membrane is demonstrated by using the Piecewise Straight Fold. In the wrapping fold experiments, the applicability of the Piecewise Straight Fold to the solar power sail membrane is verified.

DOI： 10.2322/tastj.12.pc_49

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.12.tk_19

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

DOI： 10.2322/tastj.12.pc_63

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

The small solar power sail demonstrator IKAROS was developed and launched in 2010 by JAXA and deployed its large membrane successfully. Through IKAROS's on-orbit operation, one of the most critical problems was a sail's shape imbalance during the sail deployment sequence. This paper focuses on the evaluation and consideration of the sail's imbalance through high vacuum experiments using a scale-down sail model. The experimental results obtained using the specially designed rotating mechanism and a small scale model lead to a hypothesis of the reason for the IKAROS's imbalanced deployment. The experimental results are extrapolated up to IKAROS's scale, using dimensionless analyses.

DOI： 10.2322/tastj.12.pc_55

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Language：English   Publishing type：Research paper (scientific journal)  

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Language：English   Publishing type：Research paper (scientific journal)  

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)  

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DOI： 10.2322/tastj.12.pb_33

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

In a heater control system including a number of elements, the power consumption may exceed the capacity of the power supply when a lot of elements require the power source simultaneously. In such case, the system has some risk of power shortages, while the time-averaged power consumption is enough low for the power supply. If an equipment gathers the information about the temperature of each elements and controls each switches not to turned on simultaneously, the over consumption would be prevented. However, this system needs many cables between center equipment and each elements, and becomes complex and lacks versatility. To solve these problems, authors has proposed a novel multi-agent heater controller that maintains the temperature at each element, while the whole power consumed is kept constant, without any specific server in the system. In this paper, a new developed multi-agent heater controller for spacecraft is introduced and results of experiments to verify the control system are shown. The results are compared with the results of simulations.

DOI： 10.2322/jjsass.62.69

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

IKAROS (Interplanetary Kite-craft Accelerated by Radiation of the Sun) was injected into the Venus transfer orbit by H-IIA rocket together with AKATSUKI on 21st May 2010. IKAROS has newly developed Reaction Control System called Gas-Liquid Equilibrium thruster. Gas-Liquid Equilibrium thruster loads propellant as liquid state and eject as gas state. Gas-Liquid equilibrium thruster is the thruster system suited for small spacecraft because of its easy handling depending on the non-toxic and non-inflammable propellant, which has relatively low pressure. This paper shows the development and operation result that this new thruster system work on good conditions at interplanetary trajectory compared to the prospect of performance.

DOI： 10.2322/tastj.12.tf_13

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

Solar Power Sail is a novel spacecraft with hybrid propulsion of large-area solar sail and electric propulsion driven by thin-film solar panel. The Solar Power Sail spacecraft is currently developed to probe into the outer-solar system bodies out to the Jupiter orbit, which was not well precedently explored. This mission aims to explore Trojan asteroids and interplanetary dusts by remote sensing and in-situ sampling using orbital rendezvous or fly-by technique. Scientific objective of this mission is not only planetary science but also novel astronomy; measurement of the infrared extragalactic background light without foreground contamination of the zodiacal light thanks to low-density environment at deep space, polarization measurement of the gamma-ray burst and accurate determination of its direction based on the interplanetary network technique. The Solar Power Sail mission will thus develop a new direction of space astronomy and planetary science providing us an interplanetary telescope site and will play an important roll to form a new interdisciplinary science field.

DOI： 10.2322/tastj.12.tr_1

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Authorship：Lead author   Language：English   Publishing type：Part of collection (book)   Publisher：Springer Berlin Heidelberg  

DOI： 10.1007/978-3-642-34907-2_3

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Language：English   Publishing type：Part of collection (book)   Publisher：Springer Berlin Heidelberg  

DOI： 10.1007/978-3-642-34907-2_5

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Language：English   Publishing type：Part of collection (book)   Publisher：Springer Berlin Heidelberg  

DOI： 10.1007/978-3-642-34907-2_6

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Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1016/j.actaastro.2013.07.036

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Authorship：Lead author,　Corresponding author   Language：English  

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japan Society for Aeronautical and Space Sciences  

CiNii Books

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

Two separation cameras and four fixed monitor cameras are mounted on solar sail demonstrator &ldquo;IKAROS&rdquo; in order to get panoramic view of the sail. Both cameras were designed to be wide field of view, and this cause huge lens distortion. In this paper, we describe the method to correct lens distortion and estimate the dynamics of separated cameras based on bundle adjustment, and also measure the displacement of sail tips using images taken by the two different kinds of cameras on orbit. For 3-dimensional shape estimation of the membrane, we use renormalization technique for removing statistical error bias, and find that the membrane is slightly bent to the direction of the sun.

DOI： 10.2322/astj.12.47

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

DOI： 10.14822/kjsass.61.7_247

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

EJSM (Europa Jupiter System Mission) is an international Jovian system mission with three spacecraft. Coordinated observation of Jovian magnetosphere is one of the important targets of the mission in addition to icy satellites, atmosphere, and the interior of Jupiter. JAXA will take a role on the magnetosphere spinner JMO (Jupiter Magnetospheric Orbiter), whereas ESA will launch JGO (Jupiter Ganymede Orbiter) and NASA will be responsible for JEO (Jupiter Europa Orbiter). One possibility is to combine JMO with a proposed solar sail mission of JAXA for Jupiter and one of Trojan asteroids. Since Trojan asteroids could be representing raw solid materials of Jupiter or at least outer solar system bodies,involvement of Trojan observation should enlarge the scope and enhance the quality of EJSM.

DOI： 10.2322/tastj.10.tk_37

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japan Society for Aeronautical and Space Sciences  

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

In this paper, the behavior of flexible membranes is investigated via numerical simulations using the multi-particle method (MPM) in which the membrane is replaced by a spring, damper and mass. To verify the model, some experiments on membrane vibration using a vacuum chamber are carried out. These results are compared with the results of numerical simulations using the MPM, and then the membrane structural model based on the MPM is refined to accurately simulate the behavior of membranes in experiments.

DOI： 10.2322/tastj.11.27

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

Interplanetary Kite-craft Accelerated by Radiation Of the Sun (IKAROS) was launched in May, 2010. IKAROS deployed its membrane in space and generated electricity using its thin-film solar cells on the sail membrane. This paper focused on the fabrication process of the flight model of the thin-film solar cell array. IKAROS had 144 modules of thin-film solar cells with 360 W in total output power. One module was fabricated by stacking 4 layers; protective film, thin-film solar cell, anti-warpage layer and sail membrane. The size of one module is 220 mm x 300 mm x 152.5 μm. They were bonded each other with silicon glue. The connection between module and module or between module and sail membrane were also bonded with silicon glue. The fabricated thin-film solar cell array was examined from the point of possible damages during the fabrication process, resulting in no critical damage to the thin-film solar cell array. Moreover, it successfully generated in the orbit, in comparison to the assumed power generation from the results of the generation test before the launch.

DOI： 10.2322/tastj.10.po_4_27

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Language：English   Publishing type：Research paper (international conference proceedings)  

DOI： 10.1016/j.actaastro.2012.03.032

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japan Society for Aeronautical and Space Sciences  

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

The performance of tank devices, such as porous metals and a metal fiber, on liquid propellant retention was evaluated under microgravity environment. IKAROS carries the gas-liquid equilibrium propulsion system which stores propellant as liquid phase in a storage tank and expels only gaseous propellant from the tank. Surface tension in pores of tank devices holds liquid propellant in them. As a result of microgravity experiments, it was found that the performance on liquid retention is higher than that estimated from results of bubble point experiment, and it strongly depends on the existence of bubbles in liquid propellant. From the results of the experiment, this paper proposes the location of porous metals in the storage tank to prevent bubbles from remaining with propellant consumption.

DOI： 10.2322/astj.11.123

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

The Japan Aerospace Exploration Agency (JAXA) makes the world's first solar power sail demonstration of photon propulsion and thin film solar power generation during its interplanetary cruise by IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun). It deployed and spans a membrane of 20 meters in diameter taking the advantage of the spin centrifugal force. It accelerates and controls the orbit using solar radiation pressure successfully. This is the first actual solar sail flying an interplanetary voyage. This paper presents the summary of development and operation of IKAROS and introduces the outline of the extended solar power sail mission toward Jupiter and Trojan asteroids.

DOI： 10.2322/tastj.10.po_4_13

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

Japan Exploration Agency (JAXA) launched a powered solar sail "Interplanetary Kite-craft Accelerated by Radiation Of the Sun (IKAROS)" on May 21, 2010. One of the primal technologies demonstrated at IKAROS is the spin-deployment of the sail whose diameter is 20 m class. After the launch, two-step deployment operation was performed and successful expansion of the sail was confirmed. This paper shows the flight data and observed dynamic motion during the deployment. At the quasi-static first stage deployment, the spin rate of main body shows little oscillation after each step and then damped quickly. The damping ratio of the spin rate after a later step of deployment is estimated by curve-fitting to be 0.0127. At the dynamic second stage deployment, the nutation motion is maintained within ±1.5 deg/s and the spin rate of main body is converged quickly about 60s after the deployment start. These flight result and observed dynamic motion during the deployment are compared with the results of numerical simulations using multi-particle model. These results show that the multi-particle model can simulate the global behavior of membrane sufficiently except the dumping motion of in-plane oscillation between the main body and the expanded membrane.

DOI： 10.2322/tastj.10.po_4_21

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japan Society for Aeronautical and Space Sciences  

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japan Society for Aeronautical and Space Sciences  

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun) is the world's first solar sail demonstration spacecraft. It was launched in May 2010 and has 14-m-square solar sail. Solar sail is a propulsion system which accelerates the spacecraft with the solar radiation pressure, and its performance is largely affected by its unevenness. In order to recover a shape of the sail in the space, pictures of IKAROS taken in the space with cameras separated from the main body are used because of its structural complexity. There are two types of image analysis method and in this paper shape from shading method, in which the brightness of pixels is focused on, is adopted. Since there are some causes of image degradation and they are difficult to model, some cases are verified to know the detail characteristics. This paper presents the approach for analyzing the pictures to obtain the shape of IKAROS sail, and compares the result with the one of another image analysis method and flight data of the attitude motion.

DOI： 10.2322/jjsass.60.167

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japan Society for Aeronautical and Space Sciences  

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.7446/jaesa.0404.07

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

This paper analyzes the behavior of an interplanetary dust particle on a horseshoe orbit by solving equations of the circular restricted three-body problem (CR3BP) analytically to predict the distribution of dust particles around the Earth's orbit, because in previous research numerical simulation showed that dust particles trapped on a horseshoe orbit contributes a number density of dust particles around the Earth's orbit. An analytical solution is obtained by coordinate transformation and linearization of external forces on the assumption that a horseshoe orbit is an oscillation centered at Lagrange point L3. This paper describes properties of the horseshoe solution and also shows that the analytical solution of the CR3BP is consistent with that of numerical integration.

DOI： 10.2322/tastj.10.pr_17

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

In this paper, the attitude dynamics of IKAROS, which is spinning solar sail, are presented. The first mode model of out-of-plane sail deformation (FMM) and multi-particle model (MPM) are introduced to analyze the oscillatory motion of the spinning solar sail. Three oscillation modes are derived from the FMM. They are caused by the nutation motion of the main body, as well as the nutation motion and the out-of-plane oscillation of the sail. The precise attitude motion after sail deployment and reorientation using thrusters is calculated using the MPM considering thruster plume. The IKAROS flight data of the nutation angular velocities of the main body after sail deployment or reorientation using thrusters are nearly equal to the analytical data found using the FMM and MPM.

DOI： 10.2322/tastj.10.27

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Authorship：Lead author,　Corresponding author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japan Society for Aeronautical and Space Sciences  

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

Microgravity experiments were performed to evaluate liquid propellant retention force of a porous metal. In our gas-liquid equilibrium propulsion system, porous metals are equipped in a storage tank and surface tension in pores of the porous metals holds liquid propellant in them, which ensures expelling of only gaseous propellant from a storage tank. The performance of a porous metal for liquid retention was evaluated by two different microgravity experiments. In the first one, the acrylic tank filled with semilunar porous metals and liquid propellant was rotated by a motor. The performance was evaluated by considering a force balance between liquid retention force and centrifugal force acting on the liquid propellant absorbed in porous metals. In the other one, the internal pressure in the tank was reduced by propellant ejection from a nozzle. The performance was evaluated by exhaustion time. As a result, it was found that liquid retention force was equal to, or higher than analytical value (bubble point pressure), and extractable gas volume of each ejection strongly depends on the existence of bubbles in liquid propellant.

DOI： 10.2322/tastj.10.pb_19

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Authorship：Lead author,　Corresponding author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Physical Society of Japan (JPS)  

Japan Aerospace Exploration Agency (JAXA) successfully achieved the world's first solar power sail technology by IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun) mission in 2010. It demonstrated a photon propulsion and thin film solar power generation during its interplanetary cruise. The sail of 200m^2 was deployed and kept extended by centrifugal force of the spacecraft rotaion. IKAROS also succeeded in accelerating and controlling the orbit by actively exploiting solar radiation pressure, and thus became the world's first actual solar sailer flying an interplanetary voyage. This paper presents the design of IKAROS solar sail system, operation results and introduces a perspective of this new technology to apply to the next generation mission toward Jupiter and Trojan asteroids.

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

While analyzing membrane dynamic characteristics, Multi Particle Method (MPM) has several advantages than Finite Element Method (FEM). This paper presents the influence of spring allocation on the analytical value of flexural vibration using MPM. Two MPM models, one is using parallelogram element and the other is using rectangular element, and FEM model as a reference are used for comparison of the accuracy evaluations. Flexural vibration phenomenon is selected for the comparison of the eigenvalue analysis under applying a shear force upon rectangular membrane. Analytical accuracies of the eigenvalue of the membrane flexural vibration are found to be very much dependent on the shear force value and the spring allocation of the analytical model of MPM.

DOI： 10.2322/astj.11.29

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Authorship：Last author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japan Society of Microgravity Application  

IKAROS is a small solar power sail demonstration spacecraft developed by JAXA. The spacecraft launched on May 2010 succeeded in deploying a thin solar power sail membrane with 14 meters in width and 7.5 micrometers in thickness. The membrane was folded and wrapped around the spacecraft and unfurled by centrifugal force in two stages. Since the deployment test of the large thin membrane is impossible on the ground, a huge amount of numerical simulations were performed before launch by employing the multi-particle system model (MPM) and the nonlinear elasto-dynamic finite element analysis (NEDA). MPM approximates a thin membrane with a spring-mass-damper system and enables fast numerical simulations. NEDA is based on the energy momentum method which preserves the total energy, the linear momentum and the angular momentum and enables reliable simulations of flexible multi-body systems. In this paper, their numerical results are compared with flight data and the deployment behaviors of the membrane are discussed.

DOI： 10.15011/jasma.29.1.48

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

EJSM (Europa Jupiter System Mission) is a planned Jovian system mission with three spacecraft aiming at coordinated observations of the Jovian satellites especially Europa and the magnetosphere, atmosphere and interior of Jupiter. It was formerly called "Laplace" mission. In October 2007, it was selected as one of future ESA scientific missions Cosmic Vision (2015-2025). From the beginning, Japanese group is participating in the discussion process of the mission. JAXA will take a role on the magnetosphere spinner JMO (Jupiter Magnetosphere Orbiter). On the other hand, ESA will take charge of JGO (Jupiter Ganymede Orbiter) and NASA will be responsible for JEO (Jupiter Europa Orbiter). In February 2009, EJSM is prioritized as the first candidate of outer planet flagship mission and mission study continues in the course of Cosmic Vision. The expected launch time of EJSM will be expected in 2020. Currently we are seeking a possibility to combine JMO with a proposed solar sail mission of JAXA for Jupiter and one of Trojan asteroids.

DOI： 10.2322/tastj.8.tk_35

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japanese Society for Planetary Sciences  

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Elsevier BV  

DOI： 10.1016/j.asr.2011.02.022

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

This study investigates the trajectory analysis of small solar sail demonstration spacecraft IKAROS considering the uncertainty of solar radiation pressure. Estimation of solar sail force model in space is the key factor for successful solar sail navigation because the solar sail have large uncertainty due to the flexible membrane. Since the sail wrinkles after the deployment and its surface will suffer from degradation, the solar sail force model is difficult to develop on the ground. In this paper, a practical analysis of estimating the solar sail force model from Doppler and range observable is investigated. This is demonstrated by orbit determination including parameter estimation of solar sail model. Some examples are described to investigate better parameters to estimate the solar sail force model.

DOI： 10.2322/tastj.8.pd_37

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.2514/1.52552

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

The Japan Aerospace Exploration Agency (JAXA) will make the world's first solar power sail craft demonstration of photon propulsion and thin film solar power generation during its interplanetary cruise by IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun). The spacecraft deploys and spans a membrane of 20 meters in diameter taking the advantage of the spin centrifugal force. The spacecraft weighs approximately 310kg, launched together with the agency's Venus Climate Orbiter, AKATSUKI in May 2010. This will be the first actual solar sail flying an interplanetary voyage.

DOI： 10.2322/tastj.8.to_4_25

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Language：Japanese  

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Other Link： http://id.nii.ac.jp/1004/00007743/

Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1016/j.actaastro.2011.06.005

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Authorship：Last author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

The tether sampling method is a new minor-body sampling method proposed by the authors. It consists of three phases; 1) shooting a corer to penetrate the surface of a minor-body, 2) pulling up the corer with tether using a reel mechanism, 3) recovering the corer into a storage box. In this paper, the recovery phase is focused on, and its feasibility under micro-gravity is examined using parabolic flights. The experimental setup and parameters are described in this paper, and the experimental results indicate that the retrieval phase in tethered sampling method is feasible to work under micro-gravity.

DOI： 10.2322/tstj.7.pk_23

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

The solar sailing spacecraft is one of the promising propulsion systems for the future deep space exploration mission. Japan Aerospace Exploration Agency (JAXA) has been studying the spin solar sail spacecraft which has a squared-shape type solar sail. One of the most significant objective to control the satellite orbit of the spacecraft is to estimate the thrust force induced by the photon, namely to establish the acceleration model before the launch. In a view point to use this model in orbit, the calibration of the acceleration model and evaluation of the dynamics on orbit are also important issue. This paper presents the way to construct the acceleration model of the Solar Radiation Pressure (SRP) on ground, and the calibration and evaluation strategy for this model by using the on-orbit data.

DOI： 10.2322/tastj.8.pk_1

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

The Japan Aerospace Exploration Agency (JAXA) is studying the feasibility of using the solar power sail as a new propulsion engine for deep space exploration missions. In this paper, the sail shape and equipment layout for missions utilizing small-sized solar power sails are proposed. The two-stage deployment method of the sail is also proposed. The sail need to be deployed statically at the first stage, and two types of deployment mechanisms are introduced. On the other hand the second stage of the deployment can be performed dynamically, and the oscillating motion of the membrane is converged by tethers connecting the membrane to the main body. The deployment motions are analyzed by numerical simulations using multi-particle models in order to verify the deployment. They are compared with the results calculated by finite element method models. The numerical simulation results are discussed from the technological viewpoint of the sail deployment dynamics and mechanisms.

DOI： 10.2322/tstj.7.pd_87

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

Solar sail is one of the promising propulsion systems for future deep space exploration missions as it does not require any fuel to acquire propulsive force. Although folding method and deployment mechanism of the sail have been intensively developed, attitude control of the solar sail, which is necessary for the orbital control by the solar sail, has not been much studied. This paper discusses the attitude dynamics and the control method of a spinning type solar sail spacecraft. The spinning type solar sail, where the sail equipped around the spacecraft hub is to be deployed and extended by centrifugal force, has no rigid structure supporting its membrane. This type of mechanism has the advantage in its simple and lightweight structure, however, the attitude control is difficult due to the flexibility of the membrane. In this paper, we introduced a mathematical dynamics model including first oscillation mode of the membrane which can handle coupled motion of a rigid spacecraft and a flexible membrane, and analytically developed a controller that can avoid unnecessary oscillatory motion. The performance of the controller was verified by numerical simulations using more precise multi-particle numerical model.

DOI： 10.2322/tstj.7.pd_49

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

Miniaturization and high performance are always required for space equipments. But, it can be said that miniaturization and high performance are generally contradictory requirements. In this research, a fluid loop insulation and cooling system was built as a means of realizing both miniaturization and high voltage. For the working fluid of the system, fluorinated inactive liquids were used which can provide high electrical insulation and thermal conductivity. In this paper, to begin with, the electrical insulation property of the fluorinated inactive liquids was verified by an experiment. Then the dynamics model of the constructed insulation and cooling system was derived by a system identification experiment. Finally, a control law for temperature control was constructed using the estimated model and cooling performance of the system was examined by both numerical simulations and experiments.

DOI： 10.2322/tstj.7.pf_23

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

The instruments and actuators in the attitude control system of small spacecraft are restricted in weight and space, and need to be reduced in weight and size. The rhumb line control strategy is one of the most popular schemes in reorientation of spin-stabilized spacecraft, since it requires only a spin sun sensor and a single axis reaction control system. By being combined with active nutation control, rhumb line control can reorient the spin axis of the spacecraft to any direction. To verify the control strategy, we manufactured an attitude controller and demonstration experiments were conducted using a motion table at ISAS/JAXA. This paper reviews the configuration of the controller and the outlines of the experiments, and evaluates the control performance. The same type of controller was installed in the Solar Sail Subpayload Satellite (SSSAT) launched in September 2006. An attitude control experiment in orbit was not conducted because of trouble with the satellite, but new control logic for the SSSAT was implemented for the attitude controller. This paper also reviews the control logic of the SSSAT.

DOI： 10.2322/tstj.7.25

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Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japan Society for Aeronautical and Space Sciences  

In the proposed gas-liquid equilibrium thruster, fuel is mainly stored in the liquid phase in the tank and is ejected in the gas phase, powered by the vapor pressure of the fuel. As compared to conventional thrusters, the thrust level of this thruster is low. However, the system configuration of this thruster is simple because components such as combustors or high-pressure reservoirs are not required. Further, this thruster is lighter than other thrusters. Fuels with low toxicity and that are easily available can be selected in this thruster from many kinds of fuel candidates. As a result, this thruster can be easily handled. This thruster can be used as an actuator for controlling the attitude and maneuvering the orbit of small satellites.

DOI： 10.2322/tstj.7.tb_29

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

This paper describes the navigation and the guidance strategy of the small spacecraft for flyby using the images of the target small body. We derived navigation and guidance accuracies of this mission analytically, and confirmed them by numerical simulations. For high accurate flyby, the center of the target needs to be measured accurately. However the shade area on the target surface makes it difficult to know the target center position from the information of the center of brightness on image. This uncertainty caused the guidance error. To resolve this problem, this paper proposes a method to calculate the target center from the tangent points of the sun light. The validity of the method is examined in the experiment.

DOI： 10.2322/jjsass.56.558

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1016/j.actaastro.2006.12.054

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Authorship：Lead author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.2514/1.14910

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Language：English   Publishing type：Research paper (scientific journal)  

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Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Robotics Society of Japan  

The purpose of this study is to develop a simple but useful robot with passive joints. As an example of such a robot, this paper presents dynamic rolling of a 5R closed kinematic chain, only two of whose joints are actuated.When it rolls, it has one DOF for its absolute orientation besides two DOFs for its shape. The absolute orientation is independent of the constraint for forming the closed kinematic chain. If its unactuated joints were actuated, the closed form would be over-actuated but the absolute orientation could not be driven directly. We show that the absolute orientation is subject to an acceleration constraint, not a velocity constraint. Therefore, the formulation of the dynamics of the rolling motion makes it possible to control the absolute orientation. The shape and orientation of the robot cannot be controlled simultaneously. This paper proposes a control strategy switching the shape and orientation controllers. The orientation controller reduces a negative acceleration caused by gravity which acts on the robot. We verify the control strategy by computer simulations and experiments.

DOI： 10.7210/jrsj.22.112

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Other Link： https://jlc.jst.go.jp/DN/JALC/00235657093?from=CiNii

Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1163/156855304322753290

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Other Link： https://dblp.uni-trier.de/db/journals/ar/ar18.html#ChoiMTO04

Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1163/1568553041257440

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Other Link： https://dblp.uni-trier.de/db/journals/ar/ar18.html#ChoiMO04

Authorship：Lead author,　Corresponding author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

We propose the concept of Tethered Satellite Cluster Systems. The system consists of the satellites connected by tethers, and keeps and changes the formation with active tension/length control of the tether. The purpose of the system is the saving of the thruster fuel required for the coordinated mission and the improvement of the control precision, using tether tension. The system is applied to tethered service satellites, which perform the missions, for example an autonomic inspection, casting, capture, moorage and deorbit of an uncontrolled satellite. In this paper, we treat the rotating motion; satellites rotate on the center of the mass of the system with the formation in same plane. We establish the coordinated control method using tension and thrust. This control method can decrease the fuel consumption of the thruster, for utilizing the tether tension/torque equilibriums. It can also improve the control precision. Moreover, we establish the formation control method without thrust for the transition to the objective formation.

DOI： 10.2322/jjsass.50.109

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Other Link： https://jlc.jst.go.jp/DN/JALC/00155754506?from=CiNii

Authorship：Lead author,　Corresponding author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

In this paper, the dynamics of tether winding target is analyzed. This problem is not peculiar to capture of an uncontrolled satellite with tether. It contains the common technology to casting the tether in order to moor the floating object in space, or to operating tether in the ground. This paper presents three-dimensional model of a tether and a target. The tether is divided into concentrated masses in order to consider the tether motion. The target is regarded as a prism. In formulation of the system, the friction and the normal reaction between the target and the concentrated mass is defined as contact force. And the impulse equations applied to the case that more than two concentrated masses collide with the target in the same time, is derived. In numerical simulations, the verification of this model is presented by the comparison with fundamental two-dimensional model of a tether and a target, and three-dimensional winding motions, the sideslip and the gyro effect, are shown.

DOI： 10.2322/jjsass.50.64

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Other Link： https://jlc.jst.go.jp/DN/JALC/00155860726?from=CiNii

Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Robotics Society of Japan  

This paper discusses coupling of two 2R open kinematic chains with their second joints unactuated in the horizontal plane. When they are not coupled, they can operate as independent underactutaed manipulators and when they are coupled, they can operate as a single 5R parallel manipulator which has the same number of actuators as its degrees of freedom. In the horizontal plane, they cannot make use of gravity for motion generation. In parallel mechanisms, uncertainty and stationary-uncertainty singularities exist in general. If the two open kinematic chains form such a singular configuration when they touch with each other, they can exert force with each other and therefore can be coupled easily. In addition, at a stationary-uncertainty singular configuration, they can escape from it after they are coupled simply by controlling their joint velocities. We propose a coupling mechanism without actuation, which can be a smooth free joint when coupling is achieved. The two open kinematic chains can reach an uncertainty singular configuration if they touch with each other at certain initial configurations. This paper analyzes this motion and show such initial configurations. We experimentally verify the proposed coupling.

DOI： 10.7210/jrsj.21.444

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Other Link： https://jlc.jst.go.jp/DN/JALC/00208624336?from=CiNii

Authorship：Last author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Robotics Society of Japan  

This paper proposes a novel manipulation method with a quadruped robot using its whole body. The quadruped robot we have developed can take various postures. Two of its legs can support its body by standing on the knees and the other two can serve as arms. The robot can hold a relatively big and heavy object with its two arms and can manipulate the object by moving its body. The two legs standing on the knees form a closed link system. Its desired configurations during the manipulation are at an increased mobility singularity if all knees and tips of the two legs are in contact with the floor. The problem with the singularity is that the mobility of the robot changes significantly around it. This paper shows a contact condition for the legs free from such a singularity. We conduct experiments to verify that our quadruped robot can perform the manipulation. A possible application of the manipulation is loading/unloading an object onto/from the body of a quadruped robot.

DOI： 10.7210/jrsj.20.734

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Other Link： https://jlc.jst.go.jp/DN/JALC/00160201781?from=CiNii

Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Robotics Society of Japan  

Serial link robots with unactuated (passive) joints are attracting research interest. If two of such robots can couple with each other, they can reconfigure to a parallel robot, which can make the number of actuators equal to the number of degrees of freedom. If they can couple with each other at different portions of them, they can constitute a reconfigurable parallel robot. This paper proposes this concept of a robot, presenting that two two-link robots, the first joints of which are unactuated, can reconfigure to a 5-link planar parallel configuration and a 4-link planar parallel configuration plus one actuated link. This reconfigurable parallel robot has only two actuators but can have multiple functions by reconfigurations. Due to the unactuated joints, whether or not the two-link robots can couple with each other is a non-trivial problem. We propose coupling sequences for forming the 4-link and 5-link configurations and verify those experimentally.

DOI： 10.7210/jrsj.20.640

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Other Link： https://jlc.jst.go.jp/DN/JALC/00363910091?from=CiNii

Language：English   Publishing type：Research paper (scientific journal)   Publisher：Japanese Rocket Society  

We have participated in the ARLISS (A Rocket Launch International Student Satellite) project since 1999 to design, manufacture and operate small satellites. These satellites called CanSat are the size of soft drink can (350ml). We launched five CanSats on the Black Rock desert in Nevada, U.S, to 12,000ft using amateur rocket, and dropped them with parachutes in July 2000. During their dropping, we operated these CanSats and tested their functions. Furthermore, we conducted additional experiments in Taiki town, Hokkaido, Japan using a balloon to check functions that didn't work well in ARLISS experiment. In this paper, we describe the mission, subsystem design and results of. the experiments on each CanSat, and report the results of the additional balloon experiments.

DOI： 10.11230/jsts.16.1_9

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Authorship：Corresponding author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japan Society of Mechanical Engineers  

DOI： 10.1299/kikaic.66.809

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DOI： 10.1299/kikaic.66.447

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Authorship：Corresponding author   Language：Japanese   Publishing type：Research paper (scientific journal)   Publisher：The Japan Society of Mechanical Engineers  

DOI： 10.1299/kikaic.66.1731

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Publisher：SPIE  

DOI： 10.1117/12.3018734

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DOI： 10.1117/12.3018410

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DOI： 10.26077/049g-4058

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DOI： 10.1115/SSDM2024-121330

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Publisher：International Astronautical Federation (IAF)  

DOI： 10.52202/078357-0090

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Language：Japanese   Publisher：[東京] : 日本航空宇宙学会  

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Other Link： https://ndlsearch.ndl.go.jp/books/R000000004-I032968836

Language：Japanese   Publisher：[東京] : 日本航空宇宙学会  

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Publisher：American Institute of Aeronautics and Astronautics  

DOI： 10.2514/6.2023-1785

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Language：English  

DOI： 10.1109/WPTCE56855.2023.10216227

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Language：English   Publisher：宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)  

第31回アストロダイナミクスシンポジウム (2021年7月26-27日. オンライン開催)資料番号: SA6000167060レポート番号: ASTRO-2021-C008
The 31th Workshop on JAXA Astrodynamics and Flight Mechanics 2021 (July 26-27, 2021. Online Meeting)

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Language：English   Publisher：宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)  

第31回アストロダイナミクスシンポジウム (2021年7月26-27日. オンライン開催)資料番号: SA6000167049レポート番号: ASTRO-2021-B023
The 31th Workshop on JAXA Astrodynamics and Flight Mechanics 2021 (July 26-27, 2021. Online Meeting)

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Language：English   Publisher：宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)  

第31回アストロダイナミクスシンポジウム (2021年7月26-27日. オンライン開催)資料番号: SA6000167074レポート番号: ASTRO-2021-C022
The 31th Workshop on JAXA Astrodynamics and Flight Mechanics 2021 (July 26-27, 2021. Online Meeting)

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Language：English   Publishing type：Research paper, summary (international conference)  

DOI： 10.2514/6.2021-1606

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Language：English   Publishing type：Research paper, summary (international conference)  

DOI： 10.2514/6.2019-1017

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DOI： 10.2514/6.2018-0964

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Language：English   Publisher：IEEE  

DOI： 10.1109/rws.2018.8304954

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Language：English   Publishing type：Research paper, summary (international conference)  

DOI： 10.2514/6.2018-0212

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Language：English   Publishing type：Research paper, summary (international conference)  

DOI： 10.2514/6.2017-1113

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Authorship：Lead author,　Last author,　Corresponding author   Language：Japanese  

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Language：Japanese  

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Publisher：American Institute of Aeronautics and Astronautics  

DOI： 10.2514/6.2016-1218

DOI： 10.2322/astj.jsass-d-19-00044_references_DOI_4NKsvbLMpsE6VIMZN3bztXfriBz

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Language：Japanese   Publisher：宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)  

第48回月・惑星シンポジウム (2015年7月29-31日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県
48th ISAS Lunar and Planetary Symposium (July 29-31, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
著者人数: 14名ほか
資料番号: SA6000045020

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Language：English   Publishing type：Research paper, summary (international conference)  

DOI： 10.2514/6.2015-0436

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Language：Japanese   Publisher：GEOCHEMICAL SOCIETY OF JAPAN  

DOI： 10.14862/geochemproc.62.0_227

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Language：English   Publishing type：Research paper, summary (international conference)  

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Language：Japanese   Publisher：The Institute of Electronics, Information and Communication Engineers  

Solar power sail that is being developed by JAXA as a planetary exploration spacecraft utilizes a combination of electric and photon propulsion system. The solar power sail requires a super lightweight flexible power generation system that uses thin film solar cells. We are developing a mounting method of the thin film solar cells on the membrane of the sail. Major issues of our study are shape control and connection between thin film solar array and thin film electrical wiring harnesses. We describe experimental results of shape control by oxide sputtering on the polyimide film and thin film solar cells and evaluation results of trial production of the thin film solar array connected with the thin film flexible wiring harnesses by heat sealing.

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Authorship：Last author,　Corresponding author   Language：Japanese  

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DOI： 10.2514/6.2014-0832

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Language：Japanese   Publisher：The Institute of Electronics, Information and Communication Engineers  

A solar power sail is a Japanese original concept that gets electricity from thin film solar cells on the solar sail in addition to acceleration by solar radiation. Japan Aerospace Exploration Agency (JAXA) successfully achieved the world's first solar power sail technology by IKAROS mission. A solar power sail craft can save the fuel using a solar sail and it can also gain the necessary electric power using a vast area of thin film solar cells on the membrane even when it is away from the sun. It can be a hybrid propulsion system by activating the ultra-high specific impulse ion engines with the power generated by thin film solar cells. Thus it is suitable for outer planetary exploration. This paper introduces IKAROS mission and proposes Trojan asteroids exploration using solar power sail.

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Language：Japanese   Publisher：The Institute of Electronics, Information and Communication Engineers  

A solar power sail is a Japanese original concept that gets electricity from thin film solar cells on the solar sail in addition to acceleration by solar radiation. Japan Aerospace Exploration Agency (JAXA) successfully achieved the world's first solar power sail technology by IKAROS mission. A solar power sail craft can save the fuel using a solar sail and it can also gain the necessary electric power using a vast area of thin film solar cells on the membrane even when it is away from the sun. It can be a hybrid propulsion system by activating the ultra-high specific impulse ion engines with the power generated by thin film solar cells. Thus it is suitable for outer planetary exploration. This paper introduces IKAROS mission and proposes Trojan asteroids exploration using solar power sail.

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Language：Japanese   Publisher：The Institute of Electronics, Information and Communication Engineers  

A solar power sail is a Japanese original concept that gets electricity from thin film solar cells on the solar sail in addition to acceleration by solar radiation. Japan Aerospace Exploration Agency (JAXA) successfully achieved the world's first solar power sail technology by IKAROS mission. A solar power sail craft can save the fuel using a solar sail and it can also gain the necessary electric power using a vast area of thin film solar cells on the membrane even when it is away from the sun. It can be a hybrid propulsion system by activating the ultra-high specific impulse ion engines with the power generated by thin film solar cells. Thus it is suitable for outer planetary exploration. This paper introduces IKAROS mission and proposes Trojan asteroids exploration using solar power sail.

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Language：Japanese   Publisher：The Institute of Electronics, Information and Communication Engineers  

A solar power sail is a Japanese original concept that gets electricity from thin film solar cells on the solar sail in addition to acceleration by solar radiation. Japan Aerospace Exploration Agency (JAXA) successfully achieved the world's first solar power sail technology by IKAROS mission. A solar power sail craft can save the fuel using a solar sail and it can also gain the necessary electric power using a vast area of thin film solar cells on the membrane even when it is away from the sun. It can be a hybrid propulsion system by activating the ultra-high specific impulse ion engines with the power generated by thin film solar cells. Thus it is suitable for outer planetary exploration. This paper introduces IKAROS mission and proposes Trojan asteroids exploration using solar power sail.

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Authorship：Lead author,　Last author,　Corresponding author   Language：Japanese  

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DOI： 10.2514/6.2013-1804

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Authorship：Lead author,　Last author,　Corresponding author   Language：Japanese  

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Language：Japanese   Publisher：The Japan Society of Mechanical Engineers  

An inspection of nano-probe, or deployable camera(DCAM) for a solar sail demonstrator IKAROS is developed in order to monitor the IKAROS deployable large membrane on orbit to Venus in space, and it is world first success to take picture of the satellite In this paper, we show the result of the 3 dimensional reconstruction of the membrane shape using renormalization technique for removing statistical bias We also describe the verification test at the ground using proto-type model of DCAM We make sure of the method of the analysis of membrane shape in this test

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Language：English   Publishing type：Research paper, summary (international conference)  

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DOI： 10.2514/6.2012-1748

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DOI： 10.2514/6.2011-1888

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DOI： 10.2514/6.2011-1967

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