著者
Takanao SAIKI Osamu MORI Jun'ichiro KAWAGUCHI
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.14, no.ists30, pp.Pd_127-Pd_132, 2016 (Released:2016-11-26)

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.
著者
Jun KIMURA Hauke HUSSMANN Shunichi KAMATA Koji MATSUMOTO Jürgen OBERST Gregor STEINBRÜGGE Alexander STARK Klaus GWINNER Shoko OSHIGAMI Noriyuki NAMIKI Kay LINGENAUBER Keigo ENYA Kiyoshi KURAMOTO Sho SASAKI
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.17, no.2, pp.234-243, 2019 (Released:2019-03-04)
参考文献数
50
被引用文献数
3

Laser altimetry is a powerful tool for addressing the major objectives of planetary physics and geodesy. Through measurements of distances between a spacecraft and the surface of the planetary bodies, it can be used to determine the global shape and radius: global, regional, and local topography: tidal deformation: and rotational states including physical librations. Laser altimeters have been applied in planetary explorations of the Moon, Mars, Mercury, and the asteroids Eros, and Itokawa. The JUpiter Icy Moons Explorer (JUICE), led by European Space Agency (ESA), has started development to explore the emergence of habitable worlds around gas giants. The Ganymede Laser Altimeter (GALA) will be the first laser altimeter for icy bodies, and will measure the shape and topography of the large icy moons of Jupiter, (globally for Ganymede, and using flyby ground-tracks for Europa and Callisto). Such information is crucial for understanding the formation of surface features and can tremendously improve our understanding of the icy tectonics. In addition, the GALA will infer the presence or absence of a subsurface ocean by measuring the tidal and rotational responses. Furthermore, it also improves the accuracy of gravity field measurements reflecting the interior structure, collaborating with the radio science experiment. In addition to range measurements, the signal strength and the waveform of the laser pulses reflected from the moon's surface contain information about surface reflectance at the laser wavelength and small scale roughness. Therefore we can infer the degrees of chemical and physical alterations, e.g., erosion, space weathering, compaction and deposition of exogenous materials, through GALA measurements without being affected by illumination conditions. JUICE spacecraft carries ten science payloads including GALA. They work closely together in a synergistic way with GALA being one of the key instruments for understanding the evolution of the icy satellites Ganymede, Europa, and Callisto.
著者
Jun KIMURA Hauke HUSSMANN Shunichi KAMATA Koji MATSUMOTO Jürgen OBERST Gregor STEINBRÜGGE Alexander STARK Klaus GWINNER Shoko OSHIGAMI Noriyuki NAMIKI Kay LINGENAUBER Keigo ENYA Kiyoshi KURAMOTO Sho SASAKI
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
pp.17.234, (Released:2019-01-31)
参考文献数
50
被引用文献数
3

Laser altimetry is a powerful tool for addressing the major objectives of planetary physics and geodesy. Through measurements of distances between a spacecraft and the surface of the planetary bodies, it can be used to determine the global shape and radius: global, regional, and local topography: tidal deformation: and rotational states including physical librations. Laser altimeters have been applied in planetary explorations of the Moon, Mars, Mercury, and the asteroids Eros, and Itokawa. The JUpiter Icy Moons Explorer (JUICE), led by European Space Agency (ESA), has started development to explore the emergence of habitable worlds around gas giants. The Ganymede Laser Altimeter (GALA) will be the first laser altimeter for icy bodies, and will measure the shape and topography of the large icy moons of Jupiter, (globally for Ganymede, and using flyby ground-tracks for Europa and Callisto). Such information is crucial for understanding the formation of surface features and can tremendously improve our understanding of the icy tectonics. In addition, the GALA will infer the presence or absence of a subsurface ocean by measuring the tidal and rotational responses. Furthermore, it also improves the accuracy of gravity field measurements reflecting the interior structure, collaborating with the radio science experiment. In addition to range measurements, the signal strength and the waveform of the laser pulses reflected from the moon's surface contain information about surface reflectance at the laser wavelength and small scale roughness. Therefore we can infer the degrees of chemical and physical alterations, e.g., erosion, space weathering, compaction and deposition of exogenous materials, through GALA measurements without being affected by illumination conditions. JUICE spacecraft carries ten science payloads including GALA. They work closely together in a synergistic way with GALA being one of the key instruments for understanding the evolution of the icy satellites Ganymede, Europa, and Callisto.
著者
Yuri MATSUSHITA Yasuhiro YOSHIMURA Toshiya HANADA Yuki ITAYA Tadanori FUKUSHIMA
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.20, pp.10-15, 2022 (Released:2022-02-05)
参考文献数
11
被引用文献数
1

This paper aims to assess the risk of mission termination for a large constellation of satellites in a low-Earth orbit. Many large constellations will be deployed to provide broadband network services using thousands of satellites. There is concern that such large constellations will have a serious impact on the long-term sustainability of outer space activities due to the rapid increase in population. First, therefore, the authors conducted an assessment under nominal activities (referred to as “business-as-usual”) on the basis of a prediction by ESA’s MASTER-2009 and NASA standard breakup model 2001 revision. The assessment found that nearly one catastrophic collision may happen in a large constellation, generating more than two million fragments as small as 1 mm in size. Second, the authors conducted a further assessment assuming a hypothetical collision of a satellite in a large constellation using the NASA standard breakup model and a spherical finite element model adopted in ESA’s MASTER-2009. In consequence, another catastrophic collision may happen to a large constellation, generating approximately a half-million fragments as small as 1 mm in size. Therefore, such catastrophic collisions and resulting secondary collisions should be prevented for large constellations.
著者
Hideki UCHIYAMA Takeshi MACHI Michitaro NAKAMURA Yoshiyuki GUNJI Satoshi NOZAWA Masahiro NOHMI Mami SAITO
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.19, no.4, pp.616-620, 2021 (Released:2021-07-04)
参考文献数
4

We propose a new educational use of a nanosatellite for high school and junior high school students, and not making a nanosatellite but using it. We held a workshop in which high school and junior high school students made observation plans using Stars-AO, which is a CubeSat equipped with a high-sensitivity visible-light camera. We evaluated the educational effects of the workshop by analyzing the response writings of the students and their replies to questionnaires. The participants' abilities and interest in science and space engineering increased because of the workshop. In this study, we report the workshop details and evaluation of its educational effects.
著者
Hiroshi ARAKI Ko ISHIBASHI Noriyuki NAMIKI Hirotomo NODA Masanori KOBAYASHI Keigo ENYA Masanobu OZAKI Takahide MIZUNO Yoshifumi SAITO Kazuyuki TOUHARA Shoko OSHIGAMI Shingo KASHIMA Jun KIMURA Shingo KOBAYASHI Gregor STEINBRUEGGE Alexander STARK Christian ALTHAUS Simone Del TOGNO Kay LINGENAUBER Hauke HUSSMANN
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.17, no.2, pp.150-154, 2019 (Released:2019-03-04)
参考文献数
10
被引用文献数
1

GALA (GAnymede Laser Altimeter) is one of the payload instruments of the JUICE (JUpiter ICy moons Explorer) project to be launched in 2022 to the Jovian icy moons Ganymede, Europa, and Callisto. GALA is developed through an international collaboration between Germany, Japan, Switzerland, and Spain. With the performance model of GALA, we have sought to create the interface conditions that satisfy the science requirements on the probability of false detection (PFD) and the range accuracy. The science requirements on GALA performance can be summarized as involving the following four criteria: [1] for Europa fly-by, PFD is less than 0.2 from an altitude of 1300 km or lower, [2] under the worst observation condition for albedo and surface slope of GCO500 (Ganymede Circular Orbit whose height is 500 km), the accuracy of ranging is less than 10 m and PFD is less than 0.2, [3] under the nominal observation condition of GCO500, the accuracy of ranging is less than 2 m and PFD is less than 0.1, and [4] under the best observation condition of GCO500, the accuracy of ranging is less than 1 m and PFD is less than 0.1. For the assessment, however, we had used literature data as the characteristics of the laser detector of GALA, avalanche photodiode (APD), which should be degraded due to the severe radiation environment around Jupiter. Then we carried out a more realistic model simulation of GALA by incorporating these degradation effects of APD. Characteristics of APD, such as gain, quantum efficiency, excess noise index, surface dark current, and bulk dark current, were re-evaluated through radiation tests using the data of dark and photo current of the APD irradiated with 2-MeV-electron and 50-MeV-proton beams, which are the radiation conditions assumed for JUICEGALA around Jupiter. These degraded characteristics of APD by radiation were introduced to our performance model of GALA. As a result, our performance simulation of GALA showed again that the science requirements are satisfied even after taking into account the degraded characteristics of APD. The remaining matter is the effect of noise or digitization in the Analog Electronics Module (AEM), which must be taken into account for the final specifications of GALA.
著者
Shota TAKAHASHI Naoko OGAWA Yasuhiro KAWAKATSU
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.17, no.3, pp.404-411, 2019 (Released:2019-05-04)
参考文献数
9
被引用文献数
1 1

Failure of the orbit insertion maneuver has a significant impact on the entire mission, for the trajectory of a spacecraft is largely deflected by swing-by. The risk can be reduced by targeting a point on the B-plane where the spacecraft reaches the free-return (FR) trajectory with the target body in the case of insertion failure. The backup orbit must also satisfy conditions suitable for the mission. We investigated the type of orbit insertion that is both robust to failure and reasonable for the mission requirements. We call this method FR ensured orbit insertion. Among various failure modes of the orbit insertion maneuver, we focus on the complete maneuver failure. The impact parameters on the B-plane to achieve the orbit insertion are formulated based on the geometry of velocity vectors at swing-by. The necessary deflection angle αFR at swing-by must be smaller than the possible maximum deflection angle αmax for the target body. When we introduce proper scaling factors, the relation of αmax and αFR is characterized by a single parameter λ. Using polar orbit insertion as an example, maps which show the reachability of FR trajectory after the insertion failure for each approaching condition are presented. The derived maps can be used as a tool to assess the applicability of the method in the mission design. Finally, as an application to practical mission design, we demonstrate the use of FR ensured orbit insertion in JAXA's MMX mission.
著者
Keiyu HANDA Masato FUNATSU Kenji SHIBUSAWA
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.18, no.5, pp.209-215, 2020 (Released:2020-09-04)
参考文献数
14
被引用文献数
1

Recently, various unmanned and manned Mars exploration programs have been proposed. To send a space vehicle safely to the ground of Mars, the vehicle needs to be protected from the aerodynamic heating. The accurate prediction of the aerodynamic heating is important for the design of safe and light-weight thermal protection system. For the accurate prediction, it is necessary to simulate the plasma generated behind the shock wave and to clarify its internal state. To investigate the state of the plasma, spectroscopic measurement is useful. We performed the spectroscopic measurements of carbon dioxide (CO2) plasma generated using microwave discharge under the pressure condition during Mars entry. To investigate the basic characteristics of microwave-discharged CO2 plasma, the spectra of the radiation were obtained in the wavelength region of 200 to 800 nm. As a result, carbon monoxide (CO) fourth positive bands, CO third positive bands, CO Ångström bands, and atomic oxygen lines were observed. Electronic excitation temperature was also estimated by the Boltzmann plot method for the atomic oxygen lines.
著者
Yoshiki YAMAGIWA Koki TAO Shoji SATO Kiyotoshi OTSUKA Yoji ISHIKAWA
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.16, no.2, pp.165-171, 2018 (Released:2018-03-04)
参考文献数
12

The understanding of cable dynamics is one of the most important issues for the design and construction of a space elevator. We propose a new method for constructing the space elevator by simultaneously deploying cables upward and downward from the main space station maintained in GEO and balancing both cables. The analysis is performed using our originally developed cable dynamics model. The model is a two-dimensional lamped mass model. In the model, the tether is modelled by mass points, which are connected to each other by a spring and a damper, and are pulled out per assumed length. In this study, we first analyze the cable dynamics and stress for assumed deployment conditions of the cables. We then obtain the total impulse necessary to keep the main station in GEO and control the cable speed during deployment so that it does not exceed the maximum stress of the cable. The results are also compared with the preceding method for the same conditions. The initial result shows that with the proposed cable-deployment method, the total propellant mass necessary to control cable dynamics while maintaining the station in GEO can be decreased by about one-third compared with that necessary to raise the main station to higher orbit and to control cable dynamics as in the preceding cable-deployment method.
著者
Takumi OYAMA Keiji HAGIWARA Hideyuki HORISAWA Kota FUKUDA
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.12, no.ists29, pp.Pb_85-Pb_90, 2014 (Released:2014-12-26)

This paper proposes direct focusing of repetitive high-power laser pulses on an arbitrary surface of a vehicle in the atmosphere to generate a blast wave at each pulse and push the vehicle along an impulse or thrust vector. Fundamental research was conducted on the interaction between a focused high-power laser pulse or blast wave and a surface with arbitrary curvatures. The characteristics of the impulse or thrust vector generation on the surface were numerically simulated. For simplicity, some fundamental shapes of the surface or vehicle were assumed for the simulation (i.e., planar and semicircular bodies) to examine shock–surface interactions. The impulse vector characteristics were also investigated experimentally. The results showed that the composition of the impulse vector (or each component) reached about 90% of the total impulse in the initial 10 μs. In this duration, a significant high-pressure region induced by the shockwave was localized near the laser irradiation spot; it acted on the surface vectors to induce a primary thrust. Based on these results, the directions of impulse vectors are primarily determined by the local surface vectors of the laser irradiation spots.
著者
Kent L. GEE Eric B. WHITING Tracianne B. NEILSEN Michael M. JAMES Alexandria R. SALTON
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.14, no.ists30, pp.Po_2_9-Po_2_15, 2016 (Released:2016-07-27)
被引用文献数
5 5

Near-field characterization of the acoustical environment near rockets has often involved extrapolating far-field measurements. However, because far-field amplitude data reveals only limited information about source characteristics, a vector intensity measurement system and analysis package has been developed to examine source features more directly. This paper describes the development of the measurement and analysis capability and its application to a horizontal firing of a GEM-60 solid propellant rocket motor firing conducted at ATK Space Systems near Promontory, Utah. An analysis of near-field intensity data provides insight both into the spatial extent and principal radiation lobe as a function of frequency. For 50 Hz, the far-field spectral peak frequency in the maximum radiation direction, the dominant source region derived from tracing the near-field intensity vectors spans 17-32 nozzle diameters, with peak radiation at ~68°. At high frequencies, the radiation results from a more contracted region that occurs farther upstream and is directed at about ~85°. These results point to the potential utility of near-field vector intensity measurements, in part because the near-field environments represented do not agree with historical far-field data-based models.
著者
Takashi ZAITSU Toshiko OHTA Hiroshi OHSHIMA Chiaki MUKAI
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.12, no.ists29, pp.Tp_7-Tp_9, 2014 (Released:2014-11-27)
被引用文献数
1 1

Occurrences of dental/oral diseases have been reported in the space environment and pre- or post-spaceflight and the deteriorations of oral defensive functions are evident in the space environment simulated experiments. NASA has identified 6 dental problems (Abscess, Avulsion/Tooth Loss, Caries, Crown Replacement, Exposed Pulp/Pulpitis and Filling Replacement) as the most important dental incidents to be dealt with in the long-term mission. To focus on the dental/oral health management for astronauts, dental examination and dental orthopantomogram are conducted as dental diagnosis. In addition, dental nerve block, dental prosthesis replacement and dental pain control are described in the treatment manual on the International Space Station (ISS). However, the systematic program to evaluate the risk of dental/oral problems in spacecraft and the manual to prevent the dental/oral problems in the space environment are still far from sufficient. To promote the dental/oral health of astronauts, the authors are going to launch “Space Oral Health Promotion (SOHP) project” which will tackle the research tasks and the operational countermeasures in space dentistry.
著者
Sho SASAKI Masaki FUJIMOTO Hajime YANO Takeshi TAKASHIMA Yasumasa KASABA Yukihiro TAKAHASHI Jun KIMURA Yuichi TSUDA Ryu FUNASE Osamu MORI Stefano CAMPAGNOLA Yasuhiro KAWAKATSU
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.10, no.ists28, pp.Tk_37-Tk_40, 2012 (Released:2013-06-07)

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.
著者
Naoko OGAWA Yuichi TSUDA Yuto TAKEI Hiroka INOUE Shota TAKAHASHI Yasuhiro KAWAKATSU
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.17, no.3, pp.398-403, 2019 (Released:2019-05-04)
参考文献数
3
被引用文献数
3 4

The Martian Moons eXploration (MMX) mission is now under study by the Japan Aerospace Exploration Agency (JAXA). Its scope includes the world's first landing on one of the Martian moons, collecting samples from the surface, and returning to Earth. This paper describes the orbit design for MMX. Nominal and backup trajectories for launch in 2024 and 2026 are discussed. The Mars orbit insertion (MOI) sequence using 3-impulse maneuvers is introduced. A new scheme, the robust MOI, is also proposed as a contingency to enhance the robustness of the mission sequence. A method to design a robust MOI trajectory and examples are presented.
著者
Kazuya IWATA Shinji NAKAYA Mitsuhiro TSUE
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.14, no.ists30, pp.Pa_31-Pa_38, 2016 (Released:2016-11-26)
被引用文献数
1 1

Oblique detonation under incompletely premixed conditions has not been well understood and is of great concern when difficulty of high-speed premixing in Oblique Detonation Wave Engine (ODWE), which is one of the most potential hypersonic aerospace propulsion systems, is taken into account. This study numerically investigated effects of fuel concentration gradients on oblique detonation and shock-induced combustion formed on a 28.20° wedge by solving two-dimensional Navier-Stokes equations with a detailed chemical kinetic mechanism of hydrogen-air combustion. Oblique detonation with smooth-transition formed at a Mach number of 8.00, a static temperature of 300 K, and a static pressure of 8.50 kPa was referred as the completely premixed case. Fuel concentration gradients were described by the Gaussian function. At the maximum equivalence ratio of 2.00, Smooth-transition was replaced by abrupt-transition. When maximum equivalence ratio exceeded 3.00, a V-shaped flame front appeared with its leading edge located away from the wedge, which caused two separate triple-points to be observed. Second triple point appeared at the intersection of the incident shock or the detonation front and a reflected shock generated by compression waves on the lower side of the deflagration front. Increase of the front angle enabled intensive combustion to be maintained downstream of it.
著者
Masahiko YAMAZAKI Yasuyuki MIYAZAKI
出版者
(一社)日本航空宇宙学会
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.8, no.ists27, pp.Pc_35-Pc_40, 2010 (Released:2010-12-29)
参考文献数
1
被引用文献数
1

The Spinning solar sail is expected to be a future space exploration system. Considering the dynamic deformation of the sail membrane is an indispensable factor in designing the spacecraft. But the mathematical model of the sail membrane is complex. Computational analysis is difficult and time consuming. Therefore this has a negative impact on simulation, design and control problems. The model reduction technique is required to shorten the design period. It is a necessary step in order to put the gossamer structure to practical use. In this presentation, the dynamic property of the square type spinning solar sail is revealed, and the requirements for constructing a reduction model are revealed. Then, empirical model reduction techniques are applied to gossamer structures, and the issue of constructing a low-order model is summarized.
著者
Muneo TAKAOKI Sachiko YANO Naomi MATHERS Fenny DWIVANY Rizkita ESYANTI Thomas DJAMALUDDIN Mhd Fairos ASILLAM Farahana KAMARUDIN Mohammed Selamat MADOM Sawat TANTIPHANWADI Nguyen Vu GIANG Kibo-ABC
出版者
(一社)日本航空宇宙学会
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.12, no.ists29, pp.Tp_1-Tp_5, 2014 (Released:2014-10-01)
被引用文献数
1

The “Space Seeds for Asian Future (SSAF)” program is one of the activities of the “Kibo-ABC” initiative under the Asia-Pacific Regional Space Agency Forum (APRSAF). The program intends to promote understanding, and to give regional space agencies experience in the utilization of the Japanese Experiment Module, “Kibo”, of the International Space Station (ISS). It also aims to provide young people in the Asia-Pacific region with opportunities to learn about leading edge sciences through their participations in experiments under peculiar space conditions, including microgravity. Students from Indonesia, Malaysia, Thailand and Vietnam participated in the SSAF2010-2011 program. As part of this program seeds from each of these nations were flown to the ISS and kept in the Kibo Module. These seeds were then returned to Earth where they were germinated and compared to control seed not flown in space. This experiment involved researchers, students and the general public. In the SSAF2013 program, there are plans to cultivate seeds indigenous to Asia in the Kibo/ISS facilities. The plan is to send Azuki bean (Vigna angularis) to Kibo, and observe the growth of their seedlings under dark conditions. Members of the Kibo-ABC initiative are collaborating in the preparation of the seed germination testing procedures, following which many people, including children, students and researchers, are expected to participate in the program.
著者
Tomomasa SHIBUYA Toshinori KUWAHARA Pasith TANGDHANAKANOND Shinya FUJITA Yuji SATO Kosuke HANYU Yu MURATA Adrien POTIER Morokot SAKAL Yuji SAKAMOTO
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.19, no.6, pp.855-864, 2021 (Released:2021-11-04)
参考文献数
20

The Space Robotics Laboratory (SRL) of Tohoku University has developed a 50-kg-class microsatellite called RISESAT, which was launched in January 2019. The main missions of this satellite are to conduct earth observation using a high-resolution telescope and perform a demonstration of optical communication. To achieve these missions, it is necessary to maintain the on-board components in a specified safe temperature range. In this satellite, on-board components such as the battery and power control unit are mounted to the central pillars of the satellite structure, which are insulated from the outer panels, and are thus not easily affected by the external environment. Therefore, it is important to determine the amount of heat generation by the components as well as the heat transfer parameters between structure panels. The purpose of this study is to determine the parameters such as thermal contact conductance between structure panels and heat generation of the components. We conducted the thermal vacuum tests to improve the accuracy of the determination of these parameters. Finally, we analyzed the flight data and evaluated the validity of the parameter determination using data from the regular operations phase of the mission. The seasonal effects on the thermal design were also evaluated using data from the first 480 days after launch.
著者
Yusuke OZAWA Shota TAKAHASHI Javier HERNANDO-AYUSO Stefano CAMPAGNOLA Toshinori IKENAGA Tomohiro YAMAGUCHI Bruno V. SARLI
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.17, no.4, pp.496-505, 2019 (Released:2019-07-04)
参考文献数
12

OMOTENASHI is a 6U CubeSat that will be launched in 2019 by the Space Launch System (SLS) with the objective of landing on the Moon. The CubeSat is planned to perform two deterministic maneuvers. The first maneuver (DV1) by gas jet propulsion system transfers the probe from the nominal SLS trajectory to a lunar targeted trajectory. The second maneuver (DV2) is applied by the solid rocket motor before landing to counteract the vertical component of the S/C velocity. The high approach speed at the Moon, combined with large errors induced by the solid motor, requires the probe to approach the Moon with a shallow Flight Path Angle (FPA). If the angle is too steep, expected errors in the DV2 may cause the probe to crash. However, a shallow FPA increases the probability of a Moon-flyby or collision with the local topography. In this paper, we present a design method for Earth-Moon transfer trajectory robust to orbit determination (OD) and DV1 execution errors. First step consists of a grid search to determine the nominal DV1 vector with four candidates obtained. Subsequent error analysis suggests the need for a Trajectory Correction Maneuver (TCM). For the two scenarios of OD error provided by the navigation team, an error analysis was conducted including the TCM. Two realistic OD error scenarios were considered: 30 min or 3 hours of two-way Doppler and range measurement. Error analysis conducted considering TCM shows the need for 3 hours of OD to achieve nearly 100% of transfer success rate.
著者
Yuichi TSUDA Fuyuto TERUI Takanao SAIKI
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
巻号頁・発行日
vol.12, no.ists29, pp.Pd_33-Pd_39, 2014 (Released:2014-05-28)
被引用文献数
1

A kinetic impact to the asteroid 1999 JU3 by a 300kg-class impactor spacecraft is studied. This study is a part of conceptual studies conducted within the mission design of “Hayabusa-2”, the second Japanese asteroid sample-return mission. In contrast with the finally selected “Small Carry-on Impactor(SCI)” concept, the present paper shows a feasibility of a different option, the kinetic impact by a 300kg class dedicated spacecraft. This option is valuable in terms of its scientific outcome, as the impact energy is 100 times larger than the current SCI concept. This paper discusses the feasibility of the terminal impact guidance and navigation using an onboard optical telescope. The study assumes a ground operator-in-the-loop guidance scheme, which is deemed to be the lowest development risk within the limited schedule before launch. It is shown that the ground-based terminal guidance is achievable with the accuracy of 200-300m with a realistic amount of fuel and operational load.