Faculty Profiles - AKAHOSHI Yasuhiro

Papers - AKAHOSHI Yasuhiro

Division display >> ／ All the affair displays1 - 84 of about 84

2A02 A New Attempt of Education in Strength of Material (Part 2)

AKAHOSHI Yasuhiro

Proceedings of Annual Conference of Japanese Society for Engineering Education ( Japanese Society for Engineering Education ) 2024 ( 0 ) 94 - 95 2024.01

Estimation of ejecta generation and mitigation measures for large-scale structures on geostationary orbit Reviewed International journal

Kawamoto S., Harada R., Joudoi D., Kimoto Y., Izumiyama T., Akahoshi Y.

Journal of Space Safety Engineering 11 ( 3 ) 507 - 517 2024.01

Study of the effects of projectile strength and density in the asteroid deflection by hypervelocity impact Reviewed International journal

Wakatsuki Y., Akahoshi Y., Koura T., Takahara H.

International Journal of Impact Engineering 180 2023.10

STUDY OF THE EFFECTS OF PROJECTILE STRENGTH AND DENSITY IN THE ASTEROID DEFLECTION BY HYPERVELOCITY IMPACT Reviewed International journal

Wakatsuki Y., Koura T., Akahoshi Y.

Proceedings of the 16th Hypervelocity Impact Symposium, HVIS 2022 2023.01

STUDY ON HYPERVELOCITY IMPACT OF SRM SLAG WITH VOIDS Reviewed International journal

Fujii M., Nitta K., Higashide M., Akahoshi Y., Koura T.

Proceedings of the 16th Hypervelocity Impact Symposium, HVIS 2022 2023.01

A New Attempt of Education in Strength of Material

AKAHOSHI Yasuhiro

Proceedings of Annual Conference of Japanese Society for Engineering Education ( Japanese Society for Engineering Education ) 2021 ( 0 ) 218 - 219 2021.01

Evolution of ISO's space debris mitigation standards Reviewed International journal

Stokes H., Akahoshi Y., Bonnal C., Destefanis R., Gu Y., Kato A., Kutomanov A., LaCroix A., Lemmens S., Lohvynenko A., Oltrogge D., Omaly P., Opiela J., Quan H., Sato K., Sorge M., Tang M.

Journal of Space Safety Engineering 7 ( 3 ) 325 - 331 2020.09

Study of the asteroid orbit change by hypervelocity impact and explosive

KOGA Sota, IKEDA Masaya, YOSHIDA Toi, KOURA Takao, AKAHOSHI Yasuhiro

The Proceedings of Conference of Kyushu Branch ( The Japan Society of Mechanical Engineers ) 2019 ( 0 ) C12 2019.01

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

Near Earth Objects (NEOs) are asteroids and comets which come close to Earth's orbit each year. So there is a high possibility of impacts for example, in February 2013, an asteroid created an airburst near Chelyabinsk State in Russia, causing an estimated damage of approximately 33M$ and injuring an estimated damage of approximately 1500 people. To avoid asteroid impacts it is necessary to change NEO's orbit. Impacting at a hypervelocity is one of the methods that we consider to change NEO's orbits. Hypervelocity impacts intend to change the orbit by making a spacecraft impacts on the NEO. In our study we examined the orbit change induced by hypervelocity impacts and explosives to further improve the effect. The influence on the orbit by explosives depends on the shape of the crater created by an impactor. Thus we will optimize its shape by making impact tests with a Two Stage Light Gas Gun in order to accelerate impactors with different shapes. As a result, we analyzed of the influence by explosive with AUTODYN from the shape of craters obtained by the experiment and we found that the shape of crater has an optimum condition.

DOI： 10.1299/jsmekyushu.2019.72.C12

CiNii Article

CiNii Research

Other Link： https://ci.nii.ac.jp/naid/130007801936

Evaluation of impact resistance of the CFRP material for aircraft

HAYASHI Taito, AKAHOSHI Yasuhiro, Juhyo Lee, KOURA Takao

The Proceedings of Conference of Kyushu Branch ( The Japan Society of Mechanical Engineers ) 2019 ( 0 ) G14 2019.01

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

To reduce fuel consumption on airplanes, we need nowadays lighter materials which absolutely need to withstand bird strikes. CFRP (Carbon fiber reinforced plastic) is one of the best materials for this, considering its high strength modulus and low density, but still lacks impact resistance. In this study, we simulated a fragment of aircraft impacting on a fan case in order to develop a CFRP with a better strength and impact resistance than conventional CFRP. For this experiment, we used the gas gun installed in our laboratory, and a rigid rectangle projectile as an impactor. Then, we compared our new lamination structure with conventional CFRP according to the amount of absorbed energy and to the delamination area (internal separation of layers). The amount of energy is obtained by the difference of energy before and after the impact, and the higher the energy absorbed, the more resistant the material is. In the case of the delaminationarea, the smaller it is, the lower the damages are. In new CFRP (called E2-E), the conventional [45, -45] degree layer is changed to a [30, -30] degree layer and a 0 degree layer is added between the 30 and -30 layers. The conventional lamination structure is [(0/45/-45/0)3(45/-45)(0/-45/45/0)3], and the E2-E's lamination structure is [(0/30/0/-30/0)2(30/0/-30)2]s. As a result, for the same amount of energy the CFRP E2-E was not penetrated unlike conventional CFRP. Moreover, the absorbed enegy was higher and the delamination area was smaller, which means the E2-E materialshowed better performances than coventional CFRP.

DOI： 10.1299/jsmekyushu.2019.72.G14

CiNii Article

CiNii Research

Other Link： https://ci.nii.ac.jp/naid/130007801977

Evaluation of durability in harpoon for space debris capture

YOSHIDA Keno, OHMORI Saika, FUJII Satoshi, KOURA Takao, AKAHOSHI Yasuhiro

The Proceedings of Conference of Kyushu Branch ( The Japan Society of Mechanical Engineers ) 2019 ( 0 ) C11 2019.01

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

One of the promising ways to remove space debris is to attach an electrodynamic tether (EDT) to debris by shooting a harpoon from an active debris removal satellite. There is a possibility for the harpoon to be removed from the surface of debris because of the tensile load of the EDT. The purpose of this research is to evaluate the pull-out force in a novel harpoon designed for the debris capturing system. This new harpoon with a barb is composed of an inner harpoon and an outer harpoon. After the penetration, the outer harpoon is deformed by the inner harpoon and so creates a barb on the tip. Harpoon shooting tests were conducted using a debris capture gun in order to study the impact of the harpoon into the aluminum alloy plate. After firing tests, pull-out tests were conducted by the universal tensile testing machine. During these tests, the harpoon was deformed after the penetration and opened a barb on the tip so the function of barb system could be confirmed. Moreover, the maximum pull-out load the harpoon can handle without being separated from the plate is measured. For some harpoons with the barb system, pull-out load was superior to the non-barb systems. In this way, the efficiency of this design of harpoon is proved, with a maximum loading of 7000 to 16000 N.

DOI： 10.1299/jsmekyushu.2019.72.C11

CiNii Article

CiNii Research

Other Link： https://ci.nii.ac.jp/naid/130007801937

Verification of the revision proposal for ISO11227 considering Ejecta oblique impact test and analysis

HANAKUSA Takafumi, AKAHOSHI Yasuhiro, TAGAMI Shogo, MURATAKE Nanase, KOURA Takao

The Proceedings of Conference of Kyushu Branch ( The Japan Society of Mechanical Engineers ) 2019 ( 0 ) C14 2019.01

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

At present, Space debris have a lot of problems in the space industry. They are the crush to spacecrafts and making the restriction of orbit in space. ISO 112227 was enacted in 2012 as a measure against microscopic secondary Space debris called Ejecta among space debris. However, this protocol did not take into account oblique impacts of projectiles, and a draft revision is made for the purpose of implementing oblique impact experiments. In this research, as a verification of the revision proposal, a 1 mm diameter projectile simulating micro debris is collided with a two-stage light gas gun at a speed of 5 km.s-1 using a target of A2024-T3, usually used as a spacecraft material. The impact angles are 0 (vertical impact), 45, 60 and 75 degrees. About the evaluation method, it is based on the generation amount of Ejecta and its distribution throughout impact marks. Since the target is a ductile body, the amount of Ejecta generated is small, and so it is difficult to calculate accurate ejecta mass at 60 and 75 degrees. Since the angle also increases the distribution of impact marks, scavenging of Ejecta is insufficient. In order to solve this problem, the way of collecting Ejecta is reviewed in oblique impact experiments.

DOI： 10.1299/jsmekyushu.2019.72.C14

CiNii Article

CiNii Research

Other Link： https://ci.nii.ac.jp/naid/130007801938

Hypervelocity impact phenomena of LPSO-magnesium alloys Reviewed

Nishida M., Kodama F., Hayashi K., Akahoshi Y., Hokamoto K., Kawamura Y.

EPJ Web of Conferences 183 2018.09

International Standardization of Hypervelocity Impact Test Procedure and its Future Plan

AKAHOSHI Yasuhiro

The Proceedings of Conference of Kyushu Branch ( The Japan Society of Mechanical Engineers ) 2018 ( 0 ) J31 2018.01

Study of the Effects of Projectile Shape in the Asteroid Orbit Change by Spacecraft Impact Reviewed International journal

Ikeda M., Tanaka M., Yokoo D., Koura T., Akahoshi Y.

Procedia Engineering 204 138 - 145 2017.01

Lip Formation and Ejecta from LPSO-type Magnesium Alloy Plates in Hypervelocity Impact Reviewed International journal

Nishida M., Ishida K., Kodama F., Hayashi K., Akahoshi Y., Hokamoto K., Mayama T., Yamasaki M., Kawamura Y.

Procedia Engineering 173 65 - 72 2017.01

Ejecta from LPSO-Type Magnesium Alloy Targets in Hypervelocity Impact Experiments Reviewed International journal

Nishida M., Kodama F., Hayashi K., Akahoshi Y., Hokamoto K., Mayama T., Yamasaki M., Kawamura Y.

Procedia Engineering 204 270 - 275 2017.01

Discharge on Solar Array Coupon by Debris Impact Reviewed International journal

Tagami S., Quesada M.R., Koura T., Akahoshi Y.

Procedia Engineering 204 323 - 328 2017.01

Fracture Properties and Ejecta Evaluation of LPSO-Mg Plates in Hypervelocity Impact Experiment

KODAMA Fumiya, NISHIDA Masahiro, ISHIDA Kaito, HAYASHI Koichi, AKAHOSHI Yasuhiro, HOKAMOTO Kazuyuki, MAYAMA Tsuyoshi, YAMAZAKI Michiaki, KAWAMURA Yoshihito

The Proceedings of the Materials and Mechanics Conference ( The Japan Society of Mechanical Engineers ) 2016 ( 0 ) OS01 - 19 2016.01

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

Long period stacking ordered type magnesium (LPSO-Mg) alloys have low density, excellent mechanical strength and ignition resistance. LPSO-Mg have a great potential as structural materials of satellites. Lip formation and ejecta size were examined when spherical projectiles strikes thin plates made of LPSO-type magnesium alloy at hypervelocity of 5 km/s. Witness plates were placed in front and behind of each target to determine the scattering area. After impact experiments, ejecta were collected from test chamber and lips near penetration hole was observed. Results of LPSO-type magnesium alloy plates were compared with those of aluminum alloy (A6061-T6).

DOI： 10.1299/jsmemm.2016.OS01-19

CiNii Article

CiNii Research

Other Link： https://ci.nii.ac.jp/naid/130007120202

Effects of target temperature on size distribution of ejecta in hypervelocity impact : Toward revision of ISO11227 Reviewed

NISHIDA Masahiro, MIYOKAWA Naoto, KODAMA Fumiya, HAYASHI Koichi, FAURE Pauline, NORIMATSU Koichi, FUJIMURA Yusuke, AKAHOSHI Yasuhiro

Mechanical Engineering Journal ( The Japan Society of Mechanical Engineers ) 3 ( 6 ) 16 - 00148-16-00148 2016.01

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

As a preliminary study, the effects of target temperature on ejecta size were examined at an impact velocity of 3.5 km/s with the goal of improving the ISO11227. At first, the size of each ejecta collected from test chamber, was examined by the image analysis software using a photograph of each ejecta (direct method). The cumulative number distributions of ejecta size were discussed. The effects of target temperature on ejecta size were small within a predictable range. After that, we compared the ejecta size distribution of the direct method with the results of the international standard method using witness plate (indirect method). The number of ejecta impact craters evaluated by the international standard method was very small at the high temperature. The results of international standard method using witness plate were easily influenced by temperature of target at the high temperature. It is highly possible that the international standard method underestimate the ejecta from target at high temperature.

DOI： 10.1299/mej.16-00148

CiNii Article

CiNii Research

Other Link： https://ci.nii.ac.jp/naid/130005250539

OS0106-474 Crater Shape and Ejecta Size Distribution from Hypervelocity Impact of Spherical Projectiles on LPSO Type Magnesium Alloy

ISHIDA Kaito, NISHIDA Masahiro, HAYASHI Koichi, AKAHOSHI Yasuhiro, HOKAMOTO Kazuyuki, KAWAMURA Yoshihito

2015 "OS0106 - 474-1"-"OS0106-474-2" 2015.11

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)

2015 ( 14 ) 2015.10

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

3 1964 - 1969 2015.01

Comparison of impact crater shape and splat on various targets for estimating projectile velocity Reviewed

1 247 - 251 2015.01

Effects of temperature of targets on ejecta size distribution in hypervelocity impact Reviewed

3 2007 - 2026 2014.01

2H22 International Standardization of Test Procedure of Hypervelocity Impact : Establishing process of ISO11227 and education of standardization

AKAHOSHI Yasuhiro

Proceedings of Annual Conference of Japanese Society for Engineering Education ( Japanese Society for Engineering Education ) 2014 ( 0 ) 408 - 409 2014.01

812 The Development of a Plasma Gun to Accelerate Micro-Particles

UCHINO Takaaki, AKAHOSHI Yasuhiro, KOURA Takao, NAKAMURA Ryuki, KIKUTA Takumi

The Proceedings of Conference of Kyushu Branch ( The Japan Society of Mechanical Engineers ) 2014 ( 0 ) _812 - 1_-_812-2_ 2014.01

814 Evaluation of ejecta generation by hypervelocity-impact tests

NORIMATSU Koichi, AKAHOSHI Yasuhiro, KOURA Takao, PAULI Faure, NAKAMOTO Hiroshi, FUJIMURA Yosuke

The Proceedings of Conference of Kyushu Branch ( The Japan Society of Mechanical Engineers ) 2014 ( 0 ) _814 - 1_-_814-2_ 2014.01

816 Consideration of Experimental Condition for Bird-impact Test

HORIGUCHI Tsukasa, AKAHOSHI Yasuhiro, KOURA Takao, MATSUMOTO Kensuke, NAKAJO Haruki

The Proceedings of Conference of Kyushu Branch ( The Japan Society of Mechanical Engineers ) 2014 ( 0 ) _816 - 1_-_816-2_ 2014.01

Small carry-on impactor of Hayabusa2 mission Reviewed

84 227 - 236 2013.01

Verification on hypervelocity impact tests of ejecta and data analysis of witness plates after the impact tests Reviewed

3 1986 - 1989 2011.12

Small carry-on impactor of HAYABUSA-2 mission Reviewed

2 1343 - 1348 2011.12

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

991 - 996 2011.12

Study on precise measurement of solid ejecta fragments from hypervelocity impact Reviewed

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

2010.07

A consideration of impact head design on crater formation for asteroid exploration Reviewed

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

38th COSPAR Scientific Assembly B04 - 0046-10 2010.07

Threshold of Sustained Arc due to Space Debris Impact on Solar Array Reviewed

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

11th Hypervelocity Impact Symposium 2010.04

Measurement of Size and Velocity Distribution of Ejecta due to Space Debris Impact Reviewed

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

11th Hypervelocity Impact Symposium 2010.04

Modeling of Spacecraft Fragmentation Process for Hypervelocity Impact Reviewed

Tomohiro Narumi,Yasuhiro Akahoshi,Junko Murakami,Toshiya Hanada

11th Hypervelocity Impact Symposium 2010.04

INTACT MEASUREMENT OF FRAGMENTS IN EJECTA DUE TO HYPERVELOCITY IMPACT Reviewed

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

60th International Astronautical Congress IAC-09-A6.3.06 2009.10

IN-SITU MEASUREMENT OF EJECTA USING FLASH X-RAY Reviewed

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

60th International Astronautical Congress IAC-09.A6.P.13 2009.10

Comparison of Estimation Using Debris Environment Models for International Standardization Reviewed

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

27th International Symposium on Space Technology and Science 2009-r-2-06p 2009.07

Development of Four-Stage Light Gas Gun Reviewed

Yasutaka Otsuji,Yasuhiro Akahoshi,Takao Koura,Hiroto Nagai,Satoshi Iima,Hiroshi Takakura

27th International Symposium on Space Technology and Science 2009-r-2-08p 2009.07

Threshold of Sustained Arc due to Space Debris Impact on Solar Array Reviewed

Kazuhiro Aso,Toshikazu Nagasaki,Yasuhiro Akahoshi,Keiko Watanabe,Kenshou Sugahara,Masato Fukuyama,Takao Koura,Mengu Cho,Hiroto Nagai

27th International Symposium on Space Technology and Science 2009-r-2-07p 2009.07

Debris cloud distributions at oblique impacts Reviewed

M. Higashide,T. Koura,Y. Akahoshi,S. Harada

International Journal of Impact Engineering 2008.04

Influence of space debris impact on solar array under power generation Reviewed

Y. Akahoshi,T. Nakamura,S. Fukushige,N. Furusawa,S. Kusunoki,Y.Machida,T. Koura, K. Watanabe,S. Hosoda,T. Fujita,M. Cho

International Journal of Impact Engineering 2008.04

Investigation and comparison between new satellite impact testresults and NASA standard breakup model Reviewed

K. Sakuraba,Y. Tsuruda,T. Hanada,J.-C. Liou,Y. Akahoshi

International Journal of Impact Engineering 2008.04

Development and Evaluation of a TSLGG- Application of an ETC Gun System to its First Stage Reviewed

Akahoshi,Y. Kitagawa,J. Koura,T. Fukushige,S. Tadaoka,M.

IEEE Transactions on Magnetics 43 ( 1 ) 279 - 283 2007.01

Hypervelocity impact tests against metallic meshes Reviewed

M. Higashide,M. Tanaka,Y. Akahoshi,S. Harada and F. Tohyama

International Journal of Impact Engineering 33 ( 1-12 ) 335 - 342 2006.12

Preliminary study on sustained arc due to plasma excited by hypervelocity impact of space debris on the solar array coupon Reviewed

T. Harano,Y. Machida,S. Fukushige,T. Koura,S. Hosoda,M. Cho and Y. Akahoshi

International Journal of Impact Engineering 33 ( 1-12 ) 326 - 334 2006.12

Preliminary study of counter impact with two-stage light gas gun using electrothermalchemical gun technology Reviewed

M. Tadaoka,Y. Akahoshi,T. Koura,S. Fukushige,E. Matsuda,J. Kitagawa and Y. Qu

International Journal of Impact Engineering 33 ( 1-12 ) 11 - 23 2006.12

Development of perforation hole detection system for space debris impact Reviewed

S. Fukushige,Y. Akahoshi,T. Koura and S. Harada

International Journal of Impact Engineering 33 ( 1-12 ) 273 - 284 2006.12

New Measurement of Velocity of Debris Cloud Using X-ray Radiograph Reviewed

Taisei Okumura,Yasuhiro Akahoshi,Keiko Watanabe,Takao Koura,Masumi Higashide

25th ISTS 2006-r-2-04 2006.06

Damage Evaluation of Solar Panel Impacted by Debris Reviewed

Yu Machida,Yasuhiro Akahoshi,Toshiya Hanada,Shinya Fukushige,Takayuki Harano

25th ISTS 2006-r-2-24 2006.06

Estimation of Debris Cloud Generated by Oblique Impacts Reviewed

Masumi Higashide,Taisei Okumura,Osamu Hayashi ,Takao Koura,Keiko Watanabe

25th ISTS 2006-r-2-03 2006.06

Hypervelocity Impact Test to Solar Array for Evaluation of Possibility of Sustained Arc Reviewed

Shinya Fukushige,Yasuhiro Akahoshi,Keiko Watanabe,Takayuki Harano,Yu Machida

25th ISTS 2006-r-2-25 2006.06

Using NASA Standard Breakup Model to Describe Low-Velocity Impacts on Spacecraft Reviewed

Toshiya Hanada,Tetsuo Yasaka,Hidehiro Hata,Yasuhiro Akahoshi

Journal of Spacecraft and Rockets 42 ( 2 ) 859 - 864 2005.09

NASA標準破砕モデルの低速衝突への適用性の検討（第２報:静止軌道上物体間における最大衝突速度の考慮） Reviewed

波多英寛,花田俊也,赤星保浩,八坂哲雄,原田昭治

日本航空宇宙学会論文集，第53巻、第615号，pp.160-165 53 ( 615 ) 160 - 165 2005.04

Hypervelocity Impact Tests Against Metallic Meshes Reviewed

M.Higashide,M.Tanaka,Y.Akahoshi,F.Tohyama

Proceedings of the 4th European Conference on Space Debris 395 - 400 2005.04

Low-Velocity Catastrophic Impact on Micro Satellite Reviewed

K.Nakashima,T.Hanada,Y.Akahoshi,T.Harano,Y.Machida,S.Fukushige

Proceedings of the 4th European Conference on Space Debris 701 - 704 2005.04

Measurement of Delay Time From Propellant Ignition to Projectile Launch in Two-Stage Light Gas Gun Using Electrothermal-Chemical Gun Technology Reviewed

Y.Akahoshi,Y.Qu,T.Koura,S.Fukushige,M.Tadaoka,J.Kitagawa

Proceedings of the 4th European Conference on Space Debris 391 - 39 2005.04

抵抗膜上の直流電位差を利用したデブリ衝突に対する面センサの提案

福重進也,赤星保浩,高良隆男

九州工業大学研究報告, 工学 ( 77 ) 17 - 23 2005.04

ETCガン技術を適用した二段式軽ガス銃による推進剤の着火から飛翔体発射までの作動時間測定

赤星保浩,高良隆男,松田英二

九州工業大学研究報告, 工学 ( 77 ) 25 - 29 2005.04

せん断ひずみ下におけるCuナノクラスタと刃状転位の相互作用 Reviewed

福田忠生,赤星保浩,原田昭治

日本機械学会論文集 71 420 - 427 2005.03

A Consideration on Size and Area-to-mass Distributions for Breakup Fragments Reviewed

Hidehiro Hata,Toshiya Hanada,Tetsuo Yasaka,Yasuhiro Akahoshi,Shoji Harada

Proceedings of 55th International Astronautical Congress, IAC-04-IAA.5.12.1.09 2004.10

NASA標準破砕モデルの低速衝突への適用生の検討 Reviewed

波多英寛,倉員靖雄,花田俊也,赤星保浩,八坂哲雄,原田昭治

日本航空宇宙学会論文集 52 ( 607 ) 342 - 347 2004.08

Construction of Fragment Model Based on Hypervelocity Impact Test Reviewed

Hidehiro Hata,Yasuhiro Akahoshi,Yasutake Migita,Shoji Harada

Proceedings of the 24th International Symposium on Space Technology and Science 343 - 348 2004.06

Control of Variation of Time Delay from Ignition to Launch in ETC gun Reviewed

Yasuhiro Akahoshi,Eiji Matuda,Hidehiro Hata

Materials Science Forum 465-466 185 - 188 2004.03

Model Improvement for Low-Velocity Collision Possible in Space Reviewed

H.Hata,Y.Kurakazu,Y.Akahoshi,T.Hanada,T.Yasaka,S.Harada

International Journal of Impact Engineering 29 323 - 332 2003.12

Development of Structure with Secondary Defense Function Against Space Debris Impact Reviewed

Y.Akahoshi,C.Kitamoto,S.Fukushige,H.Hata

International Journal of Impact Engineering 29 1 - 12 2003.12

Measurement of Mass, Spray Angle and Velocity Distribution of Fragment Cloud Reviewed

Y.Akahoshi,M.Kaji,H. Hata

International Journal of Impact Engineering 29 845 - 853 2003.12

Estimation of Decompression Time Based on Hypervelocity Impact Test Results of Structure with Secondary Defence Function Reviewed

Yasuhiro Akahoshi,Shinya Fukushige,Chihiro Kitamoto,Hidehiro Hata

Advances in the Astronautical Sciences 117 ( AAS03-451 ) 907 - 918 2003.12

Measurement of Secondary Debris in High-Velocity Collision Reviewed

Hidehiro Hata,Yasuhiro Akahoshi,Toshiya Hanada,Yasuo Kurakazu,Tetsuo Yasaka,Shoji Harada

Advances in the Astronautical Sciences 117 ( AAS03-449 ) 889 - 898 2003.12

New Test Range for Two-Stage Light Gas Gun in Kyushu Institute of Technology Reviewed

Yasuhiro Akahoshi,Kouji Furukawa,Eiji Matsuda,Hidehiro Hata

Advances in the Astronautical Sciences 117 ( AAS03-452 ) 919 - 926 2003.12

Measurement of Secondary Debris Clouds After Hypervelocity Impact Reviewed

Yasuhiro Akahoshi,Yasutake Migita,Motoki Kaji,Hidehiro Hata

Advances in the Astronautical Sciences 117 ( AAS03-450 ) 899 - 905 2003.12

LMCによるCuクラスタリング過程の定量的評価 Reviewed

福田忠生,赤星保浩,黒島義人,原田昭治

日本機械学会論文集 69 538 - 544 2003.03

Development of a lightweight space debris shield using high strength fibers Reviewed

M.Tanaka,Y.Moritaka,Y.Akahoshi,R.Nakamura,A.Yamori,S.Sasaki

International Journal of Impact Engineering 26 761 - 772 2001.12

Development of bumper shield using low density materials Reviewed

Y.Akahoshi,R.Nakamura and M.Tanaka

International Journal of Impact Engineering 26 13 - 19 2001.12

Construction of mass, three-dimensional and velocity distribution for the second debris clouds Reviewed

Y.Akahoshi,T.Nakamura

International Journal of Impact Engineering 26 1 - 11 2001.12

Development of self-shielding bumper against space debris Reviewed

H.Hata,Y.Akahoshi

Advances in the Astronautical Sciences 110 ( AAS01-553 ) 395 - 404 2001.11

Evaluation of bumper shield with protuberants under space debris impact Reviewed

Y.Akahoshi,D.Watanabe

Advances in the Astronautical Sciences 110 ( AAS01-552 ) 385 - 394 2001.11

FEMにおけるオブジェクト指向の応用 Reviewed

関東康祐,三村泰成,赤星保浩

計算工学 1 ( 2 ) 62 - 68 1996.04

分子動力学法によるナノスケール多結晶体の作成とその応用 Reviewed

井上秀行,赤星保浩,原田昭治,長原秀健

日本機械学會論文集. A編 61 ( 588 ) 1819 - 1824 1995.08

分子動力学法によるナノスケール多結晶体の引張解析 : 解析温度依存性の解析 Reviewed

井上秀行,赤星保浩,原田昭治,長原秀健

日本機械学會論文集. A編 61 ( 588 ) 1813 - 1818 1995.08

分子動力学法援用による破壊記述パラメータ Reviewed

井上秀行,赤星保浩,原田昭治

日本機械学會論文集. A編 60 ( 578 ) 2236 - 2241 1994.10

不完全コレスキー分解による前処理の高速化 : ベクトル計算機向き手法の開発 Reviewed

矢川元基,赤星保浩

日本シミュレーション学会シミュレーション 8 ( 1 ) 49 - 55 1989.03

　PREV-NEXT　

<AKAHOSHI Yasuhiro>

Papers - AKAHOSHI Yasuhiro