研究者詳細 - 赤星　保浩

論文 - 赤星　保浩

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OS9-12 Effects of Target Temperature on Size Distribution of Ejecta in Hypervelocity Impact : For revision of ISO 11227(Shock and Hypervelocity Impact,OS9 Recent advances in impact engineering,STRENGTH OF MATERIALS)

Nishida Masahiro, Miyokawa Naoto, Hayashi Koichi, Faure Pauline, Norimatsu Koichi, Fujimura Yusuke, Akahoshi Yasuhiro

Abstracts of ATEM : International Conference on Advanced Technology in Experimental Mechanics : Asian Conference on Experimental Mechanics 2015 ( 14 ) 2015年10月

IAC-15-A6.1.8 Development on in-situ sensors for micro-meteoroid and orbital debris measurement at JAXA 査読有り

Kitazawa Y., Matsumoto H., Okudaira O., Kimoto Y., Hanada T., Akahoshi Y., Sakurai A., Kunihiro F., Yasaka T., Nakaniura M., Kobayashi M., Hasegawa S.

Proceedings of the International Astronautical Congress, IAC 3 1964 - 1969 2015年01月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

Copyright © (2015) by International Astronautical Federation All rights reserved. The spacc debris monitor (SDM) is a large-Area impact sensor for in situ measurements of micro-mctcoroids and spacc debris of the sub-millimetre to millimetre size in the near-F.arth space environment. These meteoroid and debris particles arc very small to be detected by ground-based observations (radars and optical telcscopes) but are sufficiently large to cause serious damage to spacecraft equipment in the low Earth orbit region. The nominal detection area of the SDM is 0.1 m 2 (0.35 m ∗ 0.3 m), but its dimensions can be easily modified to accommodate different SDM constraints. The SDM is made from a flexible printed circuit, which is produced from a thin film of a nonconductive material (such as polyimide) on which thin conductivc stripes are formed in parallel. The stripe width is approximately 50 pin. and the spatial separation is approximately 100 pm. as shown in Figure 1. When a micro- debris particle with an effective diameter near to or larger than the spatial separation of the stripes (here approximately 100 pm) collides with the sensor film at a velocity sufficient to penetrate it. one or more of the stripes arc cut and become nonconductive. Debris impacts can thus be detected by monitoring the electrical conductivity (resistivity) of the stripes. This sensor system can measure the size of the incident micro-debris particles by detecting the number of severed stripes. The measurement concept is registered as a patent in many countries (US8564430, CA 2712411, CN ZL200980108349.4, UA 94873, JP 5492568, and EA1906). The first SDM was launched with HTV-5 on August 19, 2015 and represents the world's first micro-debris measurement demonstration experiment to be conductcd on the ISS using the concept of conductive (resistive) strip lines for debris detection. Another type of micro-debris sensor is also on board the HTV-5 mission and is based on an impact sensor that is a piezoelectric transducer. It comprises a Chiba-koudai Debris Monitor (CDM), where six piezoelectric sensors arc attached to a structure of KASPER to provide impact timing information and impact momentum. JAXA is currently conducting an analysis of the acquired data.

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Comparison of impact crater shape and splat on various targets for estimating projectile velocity 査読有り

Sakata K., Tagomori K., Sugiyama N., Oka D., Shinya Y., Sasaki H., Akahoshi Y., Norimatsu K., Fujimura Y., Fukuda Y., Koura T.

Proceedings of the International Thermal Spray Conference 1 247 - 251 2015年01月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

© Copyright (2015) by ASM International All rights reserved. In order to clarify the bonding mechanism and to control the quality of cold-sprayed coatings, it is necessary to accurately measure the in-flight velocity and impact velocity of a projectile. In this study, the in-flight velocity of an aluminum alloy (A2017) 1 mm sphere shot from a small two-stage light gas gun was measured as being 1 km/s using a laser-cut velocity measurement technique. So as to estimate the impact velocity of the projectile, the projectile was caused to impact targets made of aluminum (A1050), copper (C1012), mild steel (SPCC), and stainless steel (SUS304). After the impact tests, the impact crater shapes of the targets was measured using scanning electron microscopy (SEM), energy dispersive x-ray spectroscopy (EDS), and laser microscopy. The impact velocity of a projectile was estimated from obtained crater depth of the targets. In addition, microstructures of the interface between projectile and target were analyzed by EDS, electron backscattered diffraction (EBSD) and transmission electron microscopy (TEM).

Scopus

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Effects of temperature of targets on ejecta size distribution in hypervelocity impact 査読有り

Nishida M., Miyokawa N., Hayashi K., Faure P., Akahoshi Y.

Proceedings of the International Astronautical Congress, IAC 3 2007 - 2026 2014年01月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

Experiments were carried out for aluminum alloy plates subjected to hypervelocity impact of aluminum alloy spheres at different temperatures. 1. Little effect on distribution of ejecta length & projected area 2. Some effects on axial ratio distribution of ejecta when a > 4 mm 3. Some effects on crater lips : High temperature → Long lips Low temperature → Broken lips.

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2H22 超高速衝突実験手順の国際標準化 : ISO11227の制定過程と標準化教育((17)国際化時代における工学教育-II,口頭発表)

赤星保浩

工学教育研究講演会講演論文集 ( 公益社団法人日本工学教育協会 ) 2014 ( 0 ) 408 - 409 2014年01月

812 微粒子加速のためプラズマガン開発

内野隆暁, 赤星保浩, 高良隆男, 中村竜樹, 菊田卓見

日本機械学会九州支部講演論文集 ( 一般社団法人日本機械学会 ) 2014 ( 0 ) _812 - 1_-_812-2_ 2014年01月

814 超高速衝突によるEjecta放出の評価実験

乗松功一, 赤星保浩, 高良隆男, PAULI Faure, 中本裕史, 藤村洋佑

日本機械学会九州支部講演論文集 ( 一般社団法人日本機械学会 ) 2014 ( 0 ) _814 - 1_-_814-2_ 2014年01月

816 鳥衝突試験に向けた試験環境の構築

堀口司, 赤星保浩, 高良隆男, 松本賢祐, 中城晴喜

日本機械学会九州支部講演論文集 ( 一般社団法人日本機械学会 ) 2014 ( 0 ) _816 - 1_-_816-2_ 2014年01月

Small carry-on impactor of Hayabusa2 mission 査読有り

Saiki T., Sawada H., Okamoto C., Yano H., Takagi Y., Akahoshi Y., Yoshikawa M.

Acta Astronautica 84 227 - 236 2013年01月

記述言語：英語掲載種別：研究論文（学術雑誌）

A Japanese spacecraft, Hayabusa2, the successor of Hayabusa, which came back from the Asteroid Itokawa with sample materials after its 7-year-interplanetary journeys, is a current mission of Japan Aerospace Exploration Agency (JAXA) and scheduled to be launched in 2014. Although its design basically follows Hayabusa, some new components are planned to be equipped in Hayabusa2 mission. A Small Carry-on Impactor (SCI), a small explosive device, is one of the challenges that were not seen with Hayabusa. An important scientific objective of Hayabusa2 is to investigate chemical and physical properties of the internal materials and structures. SCI creates an artificial crater on the surface of the asteroid and the mother spacecraft observes the crater and tries to get sample materials. High kinetic energy is required to creating a meaningful crater. The SCI would become complicated and heavy if the traditional acceleration devices like thrusters and rocket motors are used to hit the asteroid because the acceleration distance is quite large and guidance system is necessary. In order to make the system simpler, a technology of special type of shaped charge is used for the acceleration of the impact head. By using this technology, it becomes possible to accelerate the impact head very quickly and to hit the asteroid without guidance system. However, the impact operation should be complicated because SCI uses powerful explosive and it scatters high speed debris at the detonation. This paper presents the overview of our new small carry-on impact system and the impact operation of Hayabusa2 mission. © 2012 Elsevier Ltd. All rights reserved.

DOI： 10.1016/j.actaastro.2012.11.010

Scopus

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Verification on hypervelocity impact tests of ejecta and data analysis of witness plates after the impact tests 査読有り

Akahoshi Y., Matsumoto S., Masuyama S., Faure P., Mtasumoto H., Kitazawa Y.

62nd International Astronautical Congress 2011, IAC 2011 3 1986 - 1989 2011年12月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

When small space debris or a meteoroid impacts a surface of a satellite, a lot of secondary debris is generated from the impact point. This secondary debris is called "ejecta". The amount of ejecta is deeply dependent on the surface material, the surface structure, the impact velocity, the impact angle and so on. So then it is significant to understand how much mass is ejected from the real space surface materials. However the hypervelocity impact test procedures are not perfectly equal one another among different impact test facilities in the world. As a result, the impact results cannot be compared directly among them. Under such situation the draft CDV11227 on a test procedure of hypervelocity impact upon ejecta was proposed by Dr.Mandeville to Working Group 6, Sub-Committee 14, Technical Committee 20, International Organization for Standardization (ISO/TC20/SC14/WG6) about four years ago, in which hypervelocity impact test conditions including projectile size, projectile material, impact velocity are specified as well as measurement method of crater size distribution on witness plates. The crater size distribution could be converted to the fragment size distribution in the ejecta under some assumptions on relationship between fragment size and crater size. In FY2009 calibration tests were done according to the chapter 5 in which a thick fused silica is used as a target.

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Small carry-on impactor of HAYABUSA-2 mission 査読有り

Saiki T., Sawada H., Okamoto C., Yano H., Takagi Y., Akahoshi Y., Yoshikawa M.

62nd International Astronautical Congress 2011, IAC 2011 2 1343 - 1348 2011年12月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

The Japanese asteroid explorer HAYABUSA launched in 2003 arrived at its target asteroid ITOKAWA in September, 2005. HAYABUSA has made amount of scientific discoveries and technological achievements during its stay at ITOKAWA and it came back to the Earth on June 13, 2010. Under this situation, the next asteroid exploration mission started. The spacecraft is called HAYABUSA-2. Although its design basically follows HAYABUSA, some new components are planned to be equipped in HAYABUSA-2 mission. A small carry-on impactor is one of the new challenges that were not seen with HAYABUSA. One of the most important scientific objectives of HAYABUSA-2 is to investigate chemical and physical properties of the internal materials and the internal structures in order to understand the formation history of small bodies. In order to achieve this objective, the impactor is required to remove the surface regolith and create an artificial crater on the surface of the asteroid. Ulis paper presents the overview of our small carry-on impactor system and impact operation of HAYABUSA-2 mission. And how to improve this impactor when it is applied to another small body exploration mission is also presented in this paper. Copyright ©2011 by the International Astronautical Federation. All rights reserved.

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Design, development and flight experiment of a small reusable rocket that glides using two-stage parachute 査読有り

Itakura K., Kobayashi T., Sasaki G., Ishibashi K., Shigeoka S., Sugii M., Ueta N., Nakachi Y., Nakayama Y., Inai S., Narumi T., Matsumoto T., Sagara S., Akahoshi Y., Kanemoto T., Yonemoto K.

2011 IEEE/SICE International Symposium on System Integration, SII 2011 991 - 996 2011年12月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

This paper introduces the design, development and flight result of a small reusable rocket that glides using parafoil. The mission is autonomous guidance using parafoil, because the rocket must be recovered safely at target point. In order to avoid tangling of parafoil strings, roll control using aileron is employed to keep the ejection door upward. The rocket was launched at an annual rocket launch campaign held in France. The launch and roll control were successful, however the guidance was failed because parafoil strings tangled with rocket due to opening shock. The rocket landed at 480 meters from the target point. © 2011 IEEE.

DOI： 10.1109/SII.2011.6147584

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Study on precise measurement of solid ejecta fragments from hypervelocity impact 査読有り

Shie Matsumoto,Kazuhiro Aso,Yasuhiro Akahoshi,Takao Koura,Tomohiro Narumi,Haruhisa Matsumoto,Yukihito KITAZAWA

未入力 2010年07月

A consideration of impact head design on crater formation for asteroid exploration 査読有り

Takushi YOSHIHARA,Yasuhiro Akahoshi,Tomohiro Narumi,Takao Koura,Yasutaka Otsuji,Susumu Fujii

38th COSPAR Scientific Assembly B04 - 0046-10 2010年07月

Threshold of Sustained Arc due to Space Debris Impact on Solar Array 査読有り

Kazuhiro Aso,Kenshou Sugahara,Tomohiro Narumi,Takao Koura,Mengu Cho,Yasuhiro Akahoshi,Hiroto Nagai,Keiko Watanabe

11th Hypervelocity Impact Symposium 2010年04月

Measurement of Size and Velocity Distribution of Ejecta due to Space Debris Impact 査読有り

Yasutaka Otsuji,Tomohiro Narumi,Hiroshi Takakura,Takao Koura,Yasuhiro Akahoshi

11th Hypervelocity Impact Symposium 2010年04月

Modeling of Spacecraft Fragmentation Process for Hypervelocity Impact 査読有り

Tomohiro Narumi,Yasuhiro Akahoshi,Junko Murakami,Toshiya Hanada

11th Hypervelocity Impact Symposium 2010年04月

INTACT MEASUREMENT OF FRAGMENTS IN EJECTA DUE TO HYPERVELOCITY IMPACT 査読有り

Kenshou SUGAHARA,Kazuhiro ASO,Yasuhiro AKAHOSHI,Takao KOURA,and Tomohiro NARUMI

60th International Astronautical Congress IAC-09-A6.3.06 2009年10月

IN-SITU MEASUREMENT OF EJECTA USING FLASH X-RAY 査読有り

Hiroshi TAKAKURA,Yasuhiro AKAHOSHI,Masumi HIGASHIDE,Yasutaka OTSUJI,Takao KOURA,and Hiroto NAGAI

60th International Astronautical Congress IAC-09.A6.P.13 2009年10月

Comparison of Estimation Using Debris Environment Models for International Standardization 査読有り

Naoyuki Tahara,Yasuhiro Akahoshi,Yakihito Kitazawa,Takeo Gota,Masato Uchino,Hiroto Nagai

27th International Symposium on Space Technology and Science 2009-r-2-06p 2009年07月

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