Realising the Full Potential of X-‐Ray Astronomy in the UK
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X-Ray Telescope
Early results of the Hitomi satellite Hiro Matsumoto Ux group & KMI Nagoya Univ.1 Outline •Hitomi instruments •Early scientific results –DM in Perseus –Turbulence in Perseus –others 2 Japanese history of X-ray satellites Launch, Feb. 17, 2016 Weight Suzaku Ginga ASCA Hitomi Tenma Hakucho Rocket 3 International collaboration More than 160 scientists from Japan/USA/Europe 4 Attitude anomaly Loss of communication (Mar. 26, 2016) spinning Gave up recovery (Apr. 28, 2016)5 Hitomi Obs. List Target Date Perseus Cluster of galaxies Feb. 25—27, 2016 Mar. 4—8, 2016 N132D Supernova remnants Mar. 8—11, 2016 IGR J16318-4848 Pulsar wind nebula Mar. 11—15, 2016 RXJ 1856-3754 Neutron star Mar. 17—19, 2016 Mar. 23—25, 2016 G21.5-0.9 Pulsar wind nebula Mar. 19—23, 2016 Crab Pulsar wind nebula Mar. 25, 2016 6 Scienfitic Instruments 7 4 systems Name X-Ray Telescope SXS Soft Micro-calorimeter (E<10keV) SXI Soft CCD (E<10keV) HXI Hard Si/CdTe (E<80keV) SGD --- Si/CdTe (Compton) 8 Wide energy range (0.3—600keV) HXT 1keV∼ 107K SXT SGD SXI HXI SXS 9 SXT + SXS (0.3—12keV) Soft X-ray Telescope Soft X-ray Spectrometer (X-ray micro-calorimeter) f=5.6m 10 Soft X-ray Spectrometer (SXS) FOV: 3′ × 3′ Δ푇 ∝ ℎ휈 6 × 6 pix 11 Energy Resolution Hitomi SXS Suzaku CCD Δ퐸 = 5 푒푉@ 6푘푒푉 (cf. CCD Δ퐸 = 130 푒푉)12 Before Hitomi: gratings Point source Extended Not good for extended objects 13 X-ray microcalorimeter Extended Non-dispersive type. Spatial extension doesn’t matter. -
Achievements of Hayabusa2: Unveiling the World of Asteroid by Interplanetary Round Trip Technology
Achievements of Hayabusa2: Unveiling the World of Asteroid by Interplanetary Round Trip Technology Yuichi Tsuda Project Manager, Hayabusa2 Japan Aerospace ExplorationAgency 58th COPUOS, April 23, 2021 Lunar and Planetary Science Missions of Japan 1980 1990 2000 2010 2020 Future Plan Moon 2007 Kaguya 1990 Hiten SLIM Lunar-A × Venus 2010 Akatsuki 2018 Mio 1998 Nozomi × Planets Mercury (Mars) 2010 IKAROS Venus MMX Phobos/Mars 1985 Suisei 2014 Hayabusa2 Small Bodies Asteroid Ryugu 2003 Hayabusa 1985 Sakigake Asteroid Itokawa Destiny+ Comet Halley Comet Pheton 2 Hayabusa2 Mission ✓ Sample return mission to a C-type asteroid “Ryugu” ✓ 5.2 billion km interplanetary journey. Launch Earth Gravity Assist Ryugu Arrival MINERVA-II-1 Deployment Dec.3, 2014 Sep.21, 2018 Dec.3, 2015 Jun.27, 2018 MASCOT Deployment Oct.3, 2018 Ryugu Departure Nov.13.2019 Kinetic Impact Earth Return Second Dec.6, 2020 Apr.5, 2019 Target Markers Orbiting Touchdown Sep.16, 2019 Jul,11, 2019 First Touchdown Feb.22, 2019 MINERVA-II-2 Orbiting MD [D VIp srvlxp #534<# Oct.2, 2019 Hayabusa2 Spacecraft Overview Deployable Xband Xband Camera (DCAM3) HGA LGA Xband Solar Array MGA Kaba nd Ion Engine HGA Panel RCS thrusters ×12 ONC‐T, ONC‐W1 Star Trackers Near Infrared DLR MASCOT Spectrometer (NIRS3) Lander Thermal Infrared +Z Imager (TIR) Reentry Capsule +X MINERVA‐II Small Carry‐on +Z LIDAR ONC‐W2 +Y Rovers Impactor (SCI) +X Sampler Horn Target +Y Markers ×5 Launch Mass: 609kg Ion Engine: Total ΔV=3.2km/s, Thrust=5-28mN (variable), Specific Impulse=2800- 3000sec. (4 thrusters, mounted on two-axis gimbal) Chemical RCS: Bi-prop. -
Progress with Litebird
LiteBIRD Lite (Light) Satellite for the Studies of B-mode Polarization and Inflation from Cosmic Background Radiation Detection Progress with LiteBIRD Masashi Hazumi (KEK/Kavli IPMU/SOKENDAI/ISAS JAXA) for the LiteBIRD working group 1 LiteBIRD JAXA Osaka U. Kavli IPMU Kansei U. Tsukuba APC Paris T. Dotani S. Kuromiya K. Hattori Gakuin U. M. Nagai R. Stompor H. Fuke M. Nakajima N. Katayama S. Matsuura H. Imada S. Takakura Y. Sakurai TIT Cardiff U. I. Kawano K. Takano H. Sugai Kitazato U. S. Matsuoka G. Pisano UC Berkeley / H. Matsuhara T. Kawasaki R. Chendra LBNL T. Matsumura Osaka Pref. U. KEK Paris ILP D. Barron K. Mitsuda M. Inoue M. Hazumi Konan U. U. Tokyo J. Errard J. Borrill T. Nishibori K. Kimura (PI) I. Ohta S. Sekiguchi Y. Chinone K. Nishijo H. Ogawa M. Hasegawa T. Shimizu CU Boulder A. Cukierman A. Noda N. Okada N. Kimura NAOJ S. Shu N. Halverson T. de Haan A. Okamoto K. Kohri A. Dominjon N. Tomita N. Goeckner-wald S. Sakai Okayama U. M. Maki T. Hasebe McGill U. P. Harvey Y. Sato T. Funaki Y. Minami J. Inatani Tohoku U. M. Dobbs C. Hill K. Shinozaki N. Hidehira T. Nagasaki K. Karatsu M. Hattori W. Holzapfel H. Sugita H. Ishino R. Nagata S. Kashima MPA Y. Hori Y. Takei A. Kibayashi H. Nishino T. Noguchi Nagoya U. E. Komatsu O. Jeong S. Utsunomiya Y. Kida S. Oguri Y. Sekimoto K. Ichiki NIST R. Keskitalo T. Wada K. Komatsu T. Okamura M. Sekine T. Kisner G. Hilton R. Yamamoto S. Uozumi N. -
Optical Blocking Performance of Ccds Developed for the X-Ray
Optical Blocking Performance of CCDs Developed for the X-ray Astronomy Satellite XRISM Hiroyuki Uchidaa,∗, Takaaki Tanakaa, Yuki Amanoa, Hiromichi Okona, Takeshi G. Tsurua, Hirofumi Nodae,f, Kiyoshi Hayashidae,f, Hironori Matsumotoe,f, Maho Hanaokae, Tomokage Yoneyamae, Koki Okazakie, Kazunori Asakurae, Shotaro Sakumae, Kengo Hattorie, Ayami Ishikurae, Hiroshi Nakajimah, Mariko Saitod, Kumiko K. Nobukawad,b, Hiroshi Tomidag, Yoshiaki Kanemaruc, Jin Satoc, Toshiyuki Takakic, Yuta Teradac, Koji Moric, Hikari Kashimurah, Takayoshi Kohmurai, Kouichi Haginoi, Hiroshi Murakamij, Shogo B. Kobayashik, Yusuke Nishiokac, Makoto Yamauchic, Isamu Hatsukadec, Takashi Sakol, Masayoshi Nobukawal, Yukino Urabem, Junko S. Hiragam, Hideki Uchiyaman, Kazutaka Yamaokao, Masanobu Ozakip, Tadayasu Dotanip,q, Hiroshi Tsunemie, Hisanori Suzukir, Shin-ichiro Takagir, Kenichi Sugimotor, Sho Atsumir, Fumiya Tanakar aDepartment of Physics, Kyoto University, Kitashirakawa Oiwake-cho, Sakyo, Kyoto, Kyoto 606-8502, Japan bDepartment of Physics, Kindai University, 3-4-1 Kowakae, Higashi-Osaka, Osaka 577-8502, Japan cFaculty of Engineering, University of Miyazaki, 1-1 Gakuen Kibanadai Nishi, Miyazaki 889-2192, Japan dDepartment of Physics, Faculty of Science, Nara Women’s University, Kitauoyanishi-machi, Nara, Nara 630-8506, Japan eDepartment of Earth and Space Science, Osaka University, 1-1 Machikaneyama-cho, Toyonaka, Osaka 560-0043, Japan fProject Research Center for Fundamental Sciences, Osaka University, 1-1 Machikaneyama-cho, Toyonaka, Osaka 560-0043, Japan gJapan -
Highlights in Space 2010
International Astronautical Federation Committee on Space Research International Institute of Space Law 94 bis, Avenue de Suffren c/o CNES 94 bis, Avenue de Suffren UNITED NATIONS 75015 Paris, France 2 place Maurice Quentin 75015 Paris, France Tel: +33 1 45 67 42 60 Fax: +33 1 42 73 21 20 Tel. + 33 1 44 76 75 10 E-mail: : [email protected] E-mail: [email protected] Fax. + 33 1 44 76 74 37 URL: www.iislweb.com OFFICE FOR OUTER SPACE AFFAIRS URL: www.iafastro.com E-mail: [email protected] URL : http://cosparhq.cnes.fr Highlights in Space 2010 Prepared in cooperation with the International Astronautical Federation, the Committee on Space Research and the International Institute of Space Law The United Nations Office for Outer Space Affairs is responsible for promoting international cooperation in the peaceful uses of outer space and assisting developing countries in using space science and technology. United Nations Office for Outer Space Affairs P. O. Box 500, 1400 Vienna, Austria Tel: (+43-1) 26060-4950 Fax: (+43-1) 26060-5830 E-mail: [email protected] URL: www.unoosa.org United Nations publication Printed in Austria USD 15 Sales No. E.11.I.3 ISBN 978-92-1-101236-1 ST/SPACE/57 *1180239* V.11-80239—January 2011—775 UNITED NATIONS OFFICE FOR OUTER SPACE AFFAIRS UNITED NATIONS OFFICE AT VIENNA Highlights in Space 2010 Prepared in cooperation with the International Astronautical Federation, the Committee on Space Research and the International Institute of Space Law Progress in space science, technology and applications, international cooperation and space law UNITED NATIONS New York, 2011 UniTEd NationS PUblication Sales no. -
Attitude Control Dynamics of Spinning Solar Sail “IKAROS” Considering
Attitude Control Dynamics of Spinning Solar Sail “IKAROS” Considering Thruster Plume Osamu Mori, Yoji Shirasawa, Hirotaka Sawada, Ryu Funase, Yuichi Tsuda, Takanao Saiki and Takayuki Yamamoto (JAXA), Morizumi Motooka and Ryo Jifuku (Univ. of Tokyo) Abstract In this paper, the attitude dynamics of IKAROS, which is spinning solar sail, is presented. First Mode Model of out-of-plane deformation (FMM) and Multi Particle Model (MPM) are introduced to analyze the out-of-plane oscillation mode of spinning solar sail. The out-of-plane oscillation of IKAROS is governed by three modes derived from FMM. FMM is very simple and valid for the design of attitude controller. Considering the thruster configuration of IKAROS, the force on main body and sail by thruster plume as well as reaction force by thruster are integrated into MPM. The attitude motion after sail deployment or reorientation using thrusters can be analyzed by MPM numerical simulations precisely. スラスタプルームを考慮したスピン型ソーラーセイル「IKAROS」の姿勢制御運動 森 治,白澤 洋次,澤田 弘崇,船瀬 龍,津田 雄一,佐伯 孝尚,山本 高行(JAXA), 元岡 範純,地福 亮(東大) 摘要 本論文ではスピン型ソーラーセイル IKAROS の姿勢運動について示す.スピン型ソーラーセイル を解析するために一次面外変形モデルおよび多粒子モデルを導入する.まず,一次面外変形モデ ルから導出される 3 つのモードが IKAROS の面外運動を支配していることを示す.このモデルは 非常に簡易であり,姿勢制御設計に有効であると言える.一方,多粒子モデルに対しては, IKAROS のスラスタ配置を考慮して,スラスタの反力だけでなくスラスタプルームが本体や膜面 に及ぼす力を組み込み,セイル展開後およびスラスタによるマヌーバ後の姿勢運動を数値シミュ レーションにより詳細に解析する. 1. Introduction for the numerical model. Considering the thruster configuration of IKAROS, the force on main body and A solar sail 1) is a space yacht that gathers energy for sail by thruster plume as well as reaction force by propulsion from sunlight pressure by means of a thruster are integrated into MPM. The Fast Fourier membrane. The Japan Aerospace Exploration Agency Transform (FFT) results from IKAROS flight data are (JAXA) successfully achieved the world’s first solar sail compared with those from simulation data. -
Sg423finalreport.Pdf
Notice: The cosmic study or position paper that is the subject of this report was approved by the Board of Trustees of the International Academy of Astronautics (IAA). Any opinions, findings, conclusions, or recommendations expressed in this report are those of the authors and do not necessarily reflect the views of the sponsoring or funding organizations. For more information about the International Academy of Astronautics, visit the IAA home page at www.iaaweb.org. Copyright 2019 by the International Academy of Astronautics. All rights reserved. The International Academy of Astronautics (IAA), an independent nongovernmental organization recognized by the United Nations, was founded in 1960. The purposes of the IAA are to foster the development of astronautics for peaceful purposes, to recognize individuals who have distinguished themselves in areas related to astronautics, and to provide a program through which the membership can contribute to international endeavours and cooperation in the advancement of aerospace activities. © International Academy of Astronautics (IAA) May 2019. This publication is protected by copyright. The information it contains cannot be reproduced without written authorization. Title: A Handbook for Post-Mission Disposal of Satellites Less Than 100 kg Editors: Darren McKnight and Rei Kawashima International Academy of Astronautics 6 rue Galilée, Po Box 1268-16, 75766 Paris Cedex 16, France www.iaaweb.org ISBN/EAN IAA : 978-2-917761-68-7 Cover Illustration: credit A Handbook for Post-Mission Disposal of Satellites -
Science Exploration and Instrumentation of the OKEANOS Mission to a Jupiter Trojan Asteroid Using the Solar Power Sail
Planetary and Space Science xxx (2018) 1–8 Contents lists available at ScienceDirect Planetary and Space Science journal homepage: www.elsevier.com/locate/pss Science exploration and instrumentation of the OKEANOS mission to a Jupiter Trojan asteroid using the solar power sail Tatsuaki Okada a,b,*, Yoko Kebukawa c,d, Jun Aoki d, Jun Matsumoto a, Hajime Yano a, Takahiro Iwata a, Osamu Mori a, Jean-Pierre Bibring e, Stephan Ulamec f, Ralf Jaumann g, Solar Power Sail Science Teama a Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, 252-5210, Japan b The University of Tokyo, Hongo, Bunkyo, Tokyo, Japan c Faculty of Engineering, Yokohama National University, Japan d Graduate School of Science, Osaka University, Toyonaka, Japan e Institut dʼAstrophysique Spatiale, Orsay, France f German Aerospace Center, Cologne, Germany g German Aerospace Center, Berlin, Germany ARTICLE INFO ABSTRACT Keywords: An engineering mission OKEANOS to explore a Jupiter Trojan asteroid, using a Solar Power Sail is currently under Solar system formation study. After a decade-long cruise, it will rendezvous with the target asteroid, conduct global mapping of the Jupiter trojans asteroid from the spacecraft, and in situ measurements on the surface, using a lander. Science goals and enabling Solar power sail instruments of the mission are introduced, as the results of the joint study between the scientists and engineers Lander from Japan and Europe. Mass spectrometry OKEANOS 1. Introduction ocean water and life. Lucy (Levison et al., 2017), a Jupiter Trojan multi-flyby mission, has Jupiter Trojan asteroids are located in the long-term stable orbits been selected as a NASA Discovery class mission, which aims for un- around the Sun-Jupiter Lagrange points (L4 or L5) Most of them are derstanding the variation and diversity of Jupiter Trojans. -
Global Satellite Communications Technology and Systems
International Technology Research Institute World Technology (WTEC) Division WTEC Panel Report on Global Satellite Communications Technology and Systems Joseph N. Pelton, Panel Chair Alfred U. Mac Rae, Panel Chair Kul B. Bhasin Charles W. Bostian William T. Brandon John V. Evans Neil R. Helm Christoph E. Mahle Stephen A. Townes December 1998 International Technology Research Institute R.D. Shelton, Director Geoffrey M. Holdridge, WTEC Division Director and ITRI Series Editor 4501 North Charles Street Baltimore, Maryland 21210-2699 WTEC Panel on Satellite Communications Technology and Systems Sponsored by the National Science Foundation and the National Aeronautics and Space Administration of the United States Government. Dr. Joseph N. Pelton (Panel Chair) Dr. Charles W. Bostian Mr. Neil R. Helm Institute for Applied Space Research Director, Center for Wireless Deputy Director, Institute for George Washington University Telecommunications Applied Space Research 2033 K Street, N.W., Rm. 304 Virginia Tech George Washington University Washington, DC 20052 Blacksburg, VA 24061-0111 2033 K Street, N.W., Rm. 340 Washington, DC 20052 Dr. Alfred U. Mac Rae (Panel Chair) Mr. William T. Brandon President, Mac Rae Technologies Principal Engineer Dr. Christoph E. Mahle 72 Sherbrook Drive The Mitre Corporation (D270) Communications Satellite Consultant Berkeley Heights, NJ 07922 202 Burlington Road 5137 Klingle Street, N.W. Bedford, MA 01730 Washington, DC 20016 Dr. Kul B. Bhasin Chief, Satellite Networks Dr. John V. Evans Dr. Stephen A. Townes and Architectures Branch Vice President Deputy Manager, Communications NASA Lewis Research Center and Chief Technology Officer Systems and Research Section MS 54-2 Comsat Corporation Jet Propulsion Laboratory 21000 Brookpark Rd. -
Development of 60Μm Pitch Cdte Double-Sided Strip Detector for FOXSI-3 Rocket Experiment
Development of 60µm pitch CdTe double-sided strip detector for FOXSI-3 rocket experiment Kento Furukawa(U-Tokyo, ISAS/JAXA) Shin'nosuke Ishikawa, Tadayuki Takahashi, Shin Watanabe(ISAS/JAXA), Koichi Hagino(Tokyo University of Science), Shin'ichiro Takeda(OIST), P.S. Athiray, Lindsay Glesener, Sophie Musset, Juliana Vievering (U. of Minnesota), Juan Camilo Buitrago Casas , Säm Krucker (SSL/UCB), and Steven Christe (NASA/GSFC) 1 2 CdTe semiconductor and diode device Cadmium Telluride semiconductor : • High density • Large atomic number • High efficiency Issue : small µτ product especially for holes 260eV(FWHM) • Uniform & thin device @6.4keV 1400V,-40℃ • Schottky Diode (Takahashi et al. 1998 ) High bias voltage full charge collection + high energy resolution Takahashi et al. (2005) 3 Application of CdTe Diode Double-sided Strip Detector Watanabe et al. 2009 Anode(Pt): Ohmic contact Cathode(Al): Schottky contact Astrophysical Application • Hard X-ray Imager(HXI) onboard Hitomi(ASTRO-H) satellite • FOXSI rocket mission Medical Application • Small animal SPECT system (OIST/JAXA) 4 Hard X-ray study of the Sun Observation Target : the Sun Corona and flare Scientific Aim • Coronal Heating (thermal emission) • Particle Acceleration (non-thermal emission ) →Sensitive Hard X-ray imaging and spectral observation is the key especially for small scale flares study Soft X-ray image by Hinode (micro and nano) (NAOJ/JAXA) So far only Indirect Imaging e.g. RHESSI spacecraft (Rotational Modulation collimator) No direct imaging in hard X-ray band for solar mission 5 FOXSI rocket mission FOXSI experiment (UCB/SSL, NASA, UMN, ISAS/JAXA) Indirect Direct Imaging Spectroscopy with Focusing Optics in Hard X-ray Hard X-ray telescopes + CdTe focal plane detectors FOXSI’s hard X-ray telescope clearly identified a micro-flare with high S/N ratio Direct Telescope Angular resolution : 5 arcsec (FWHM) Focal plane detector 50µm on focal plane Krucker et al. -
List of RN/LPN Required to Complete Fingerprinting by June 30, 2021
List of RN/LPN Required to Complete Fingerprinting by June 30, 2021 RN 74156 ABAD CHARLES U RN 61837 ACASIO KYRA K RN 75958 ADVINCULA ROLAND D J RN 75271 ABAD GLORY GAY M RN 59937 ACCOUSTI NEAL O RN 42910 ADZUARA MARY JANE R RN 76449 ABALOS JUDY S RN 52918 ACEBO RUSSELL J RN 72683 AETO JUSTIN RN 38427 ABALOS TRICIA H M RN 43188 ACEVEDO JUNE D RN 86091 AFONG CLAREN C D RN 70657 ABANES JANE J RN 68208 ACIDERA NORIVIE S RN 72856 AGACID MARIE JOY H RN 46560 ABANIA JONATHAN R RN 59880 ACIO ROSARIO A D RN 78671 AGANOS DAWN Y A V RN 67772 ABARQUEZ BLESSILDA C RN 72528 ACKLIN JUSTIN P RN 85438 AGARAN NOBEMEN O RN 67707 ABATAYO LIEZL P RN 68066 ACOB FERLITA D RN 52928 AGARAN TINA K LPN 7498 ABBEY LORI J RN 35794 ACOBA BETH MARY BARN RN 33999 AGASID GLISERIA D RN 77337 ABE DAVID K RN 73632 ACOBA JULIA R LPN 18148 AGATON KRYSTLE LIAAN RN 57015 ABE JAYSON K RN 53744 ACOPAN MARK N RN 66375 AGBAYANI REYNANTE LPN 6111 ABE LORI R RN 55133 ACOSTA MARISSA R RN 58450 AGCAOILI ANNABEL RN 18300 ABE LYNN Y LPN 18682 ACOSTA MYLEEN G A RN 54002 AGCAOILI FLORENCE A RN 73517 ABE SUN-HWA K RN 69274 ACRE-PICKRELL ALEXAN RN 79169 AGDEPPA MARK J RN 84126 ABE TIFFANY K RN 45793 ACZON-ARMSTRONG MARI RN 41739 AGENA DALE S RN 69525 ABEE JENNIFER E RN 19550 ADAMS CAROLYN L RN 33363 AGLIAM MARILYN A RN 69992 ABEE KEVIN ANDREW RN 73979 ADAMS JENNIFER N RN 46748 AGLIBOT NANCY A RN 69993 ABELLADA MARINEL G RN 39164 ADAMS MARIA V RN 38303 AGLUGUB AURORA A RN 66502 ABELLANIDA STEPHANIE RN 52798 ADAMSKI MAUREEN RN 68068 AGNELLO TAI D RN 83403 ABERILLA JEREMY J RN 84737 ADDUCCI -
Tetsuya Nakano Safety and Mission Assurance Department Japan Aerospace Exploration Agency (JAXA)
JAXA Approach for Mission Success ~close coordination with contractors~ Tetsuya Nakano Safety and Mission Assurance Department Japan Aerospace Exploration Agency (JAXA) 2010.10.21 NASA Supply Chain Conference@NASA GSFC 1 JAXA Approach for Mission Success ~close coordination with contractors~ Contents 1. Recent JAXA Space Flights 2. JAXA’s Role and Responsibility 3. Major S&MA Activities 4. Technical Improvement Activities in Development Projects 2 1. Recent JAXA Space Flights Currently-operating JAXA’s satellites on-orbit CY2000 CY2005 CY2010 2005 Daichi (ALOS: Land observation) 2002 2009 Kodama (DRTS: Data relay) Ibuki(GOSAT: Greenhouse gas observation) 2006 Kiku8 (ETS-8: Technical Testing) 2008 Kizuna(WINDS: Super high-speed internet) 2010 2005 Michibiki (QZSS-1: Suzaku (Astro-EII:X-ray Astronomy) Global Positioning) 2006 2010 Akari (Astro-F: Infrared Akatsuki (Planet-C: Imaging) Venus Climate) 2006 2010 Hinode (SOLAR-B: Ikaros (Solar Power Solar Physics) Sail) 2003 Hayabusa (asteroid explorer) 2007 3 Kaguya (Lunar observation) 1. Recent JAXA Space Flights Japanese Launch vehicles H-2A (Standard) H-2B Epsilon(under development) GTO 4.0ton 8ton LEO 10ton 16.5ton (ISS orbit) 1.2ton 4 4 1. Recent JAXA Space Flights International Space Station Program “HTV” ISS “KIBO” Transportation Vehicle Japanese Experience Module (JEM) ©NASA ©NASA ©NASA Yamazaki 2010.4 Furukawa Noguchi Wakata 2011.Spring - 2009.12 – 2010.6 2009.3 – 2009.7 5 2. JAXA’s Role and Responsibility Emphasizing upstream process and front-loading • Apply Systems Engineering (SE) that emphasizes upstream process management in the project lifecycle • Allocate adequate resource to upstream process (front-loading) Define appropriate level of JAXA responsibilities and roles in development projects • JAXA is responsible for requirements/specification definition, and flight operations.