The Interplanetary Network K

Total Page:16

File Type:pdf, Size:1020Kb

The Interplanetary Network K Gamma-ray Bursts: 15 Years of GRB Afterglows A.J. Castro-Tirado, J. Gorosabel and I.H. Park (eds) EAS Publications Series, 61 (2013) 459–464 THE INTERPLANETARY NETWORK K. Hurley 1,I.G.Mitrofanov2,D.Golovin2,M.L.Litvak2,A.B.Sanin2, W. Boynton 3, C. Fellows 3,K.Harshman3,R.Starr3,S.Golenetskii4, R. Aptekar 4, E. Mazets 4,V.Pal’shin4,D.Frederiks4,D.Svinkin4, D.M. Smith 5,W.Hajdas6,A.vonKienlin7,X.Zhang7,A.Rau7, K. Yamaoka 8, T. Takahashi 8, M. Ohno 9, Y. Hanabata 9,Y.Fukazawa9,M.Tashiro10, Y. Terada 10,T.Murakami11,K.Makishima12,13,T.Cline14,15,S.Barthelmy14, J. Cummings 24,16,N.Gehrels14,H.Krimm25,17,D.Palmer18,J.Goldsten19, E. Del Monte20,M.Feroci20,M.Marisaldi21, V. Connaughton 22,M.S.Briggs22 and C. Meegan23 1 U.C. Berkeley Space Sciences Laboratory, 7 Gauss Way, Berkeley, CA 94720-7450, USA 2 Institute for Space Research, Profsojuznaja 84/32, Moscow 117997, Russian Federation 3 University of Arizona, Lunar and Planetary Laboratory, Tucson, AZ 85721, USA 4 Ioffe Physico-Technical Institute of the Russian Academy of Sciences, St. Petersburg 194021, Russian Federation 5 Department of Physics and Santa Cruz Institute for Particle Physics, U.C. Santa Cruz, CA 95064, USA 6 Paul Scherrer Institute, 5232 Villigen PSI, Switzerland 7 Max-Planck-Institut f¨ur extraterrestrische Physik, Giessenbachstrasse, Garching, 85748 Germany 8 Institute of Space and Astronautical Science, 3-1-1 Yoshinodai, Sagamihara, Kanagawa 229-8510, Japan 9 Department of Physics, Hiroshima University, 1-3-1 Kagamiyama, Higashi-Hiroshima, Hiroshima 739-8526, Japan 10 Department of Physics, Saitama University, 255 Shimo-Okubo, Sakura-ku, Saitama-shi, Saitama 338-8570, Japan 11 Department of Physics, Kanazawa University, Kadoma-cho, Kanazawa, Ishikawa 920-1192, Japan 12 Department of Physics, University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-0033, Japan 13 Makishima Cosmic Radiation Laboratory, The Institute of Physical and Chemical Research (RIKEN), 2-1 Hirosawa, Wako, Saitama 351-0198, Japan 14 NASA Goddard Space Flight Center, Code 661, Greenbelt, MD 20771, USA 15 Emeritus 16 Joint Center for Astrophysics, University of Maryland, Baltimore County, 1000 Hilltop Circle, Baltimore, MD 21250, USA 17 Universities Space Research Association, 10211 Wincopin Circle, Suite 500, Columbia, MD 21044, USA 18 Los Alamos National Laboratory, PO Box 1663, Los Alamos, NM 87545, USA 19 Applied Physics Laboratory, Johns Hopkins University, Laurel, MD 20723, USA 20 INAF/IASF-Roma, via Fosso del Cavaliere 100, 00133 Roma, Italy 21 INAF/IASF-Bologna, via Gobetti 101, 40129 Bologna, Italy 22 University of Alabama in Huntsville, NSSTC, 320 Sparkman Drive, Huntsville, AL 35805, USA 23 Universities Space Research Association, NSSTC, 320 Sparkman Drive, Huntsville, AL 35805, USA 24 UMBC/CRESST/NASA Goddard Space Flight Center, Code 661, Greenbelt, MD 20771, USA 25 CRESST/NASA Goddard Space Flight Center, Code 661, Greenbelt, MD 20771, USA c EAS, EDP Sciences 2013 DOI: 10.1051/eas/1361074 460 Gamma-ray Bursts: 15 Years of GRB Afterglows Abstract. We describe the current, 9-spacecraft Interplanetary Net- work (IPN). The IPN detects about 325 gamma-ray bursts per year, of which about 100 are not localized by any other missions. We give some examples of how the data, which are public, can be utilized. 1 Introduction The current IPN consists of one or more experiments on nine missions: AGILE, Fermi, RHESSI, Suzaku,andSwift, in low-Earth orbit; INTEGRAL, in a high apogee Earth orbit; Konus-Wind,atL1, ∼5.5 light-seconds from Earth; and MESSENGER and Odyssey, in orbit around Mercury and Mars, respectively. This configuration is an ideal one in many respects. The 5 low-Earth orbit missions assure that virtually every burst is detected by at least one Earth-orbiting mis- sion, providing an important vertex for triangulation. The two planetary missions give long baselines which make precise localizations possible. And INTEGRAL and Konus assure redundancy and overdetermination of the localizations in many cases. Indeed, even without the planetary missions, the mini-network of 5 low- Earth orbiters, plus INTEGRAL and Konus, often make it possible to obtain relatively small error boxes for many bursts. Figure 1 shows the configuration of the IPN, which is an all-sky, full-time monitor not only of GRBs, but also of magnetar bursts, and other high-energy phenomena. Fig. 1. The 9-spacecraft IPN. The near-Earth mini-network often produces small error boxes in the absence of detections by distant spacecraft. K. Hurley et al.: The Interplanetary Network 461 Fig. 2. A Venn diagram showing the relation be- tween the number of bursts per year detected by the IPN, Swift,andFermi. Swift observes an average of 162 bursts per year, counting those both inside (∼100) and outside (∼62) the coded field of view. Fermi observes a total of 245, and the IPN observes a total of 325. Of the 325 IPN bursts, 190 are also detected by Fermi, and 125 are also detected by Swift (of which ∼77 are inside the coded field of view). 73 bursts per year are detected by the IPN, Swift, and Fermi. 100 IPN bursts per year are not detected by either Swift or Fermi. Figure 2 shows the relation between bursts detected by the IPN and bursts detected by Swift and Fermi. Roughly 100 IPN GRBs/year are not detected by those missions. Moreover, about 70 of the 190 GRBs/year which are detected by the IPN and Fermi can be localized by the IPN to error box areas which are several orders of magnitude smaller than those of Fermi alone. Finally, Figure 3 shows the sensitivity of the IPN as a function of GRB peak flux. Another measure of sensitivity is to consider the redshifts of IPN bursts, which range from 0.7 to 4.5. 2SomeusesofIPNdata 2.1 Refining Fermi GBM and LAT localizations IPN error boxes are typically orders of magnitude smaller than Fermi GBM er- ror circles. Indeed, they are comparable in size to, or often smaller than, LAT error circles. Figure 4 shows one example. Refining these error circles helps the GBM team understand their systematic uncertainties, and aids the LAT team in identifying bursts with high-energy emission. 2.2 GRBs from optically detected energetic supernovae The optical signatures of energetic Type Ib/c supernovae are frequently found in GRB afterglow lightcurves. But can GRBs be identified by searching at the times and positions of optically-discovered energetic supernovae? IPN searches have now been conducted for 23 supernovae, from SN1997dq to SN2012ap (Hurley & Pian 2008; Sanders et al. 2012; Corsi et al. 2011; Soderberg et al. 2012; Margutti et al. 2012; Walker et al. 2013). The advantage of the IPN in these searches is its all-sky, full-time coverage. The negative results to date constrain the beaming and energetics of these SNe; the search is continuing. 462 Gamma-ray Bursts: 15 Years of GRB Afterglows Fig. 3. The IPN sensitivity to GRBs as a function of their peak flux. The peak flux is measured by the Swift BAT in the 15 − 150 keV energy range over 1 second. The dashed line shows the probability that any two or more IPN spacecraft will detect the burst. The solid line shows the probability that any two or more widely separated IPN spacecraft will detect it; the latter bursts can be localized to some extent. Fig. 4. Fermi GBM, LAT, and IPN localizations of GRB 090323. The two IPN annuli intersect to form the error box shaded in green. A zoom of this region shows the LAT error circle and the location of the optical afterglow (asterisk) in more detail (Hurley et al. 2009; Ohno et al. 2009; Updike et al. 2009). K. Hurley et al.: The Interplanetary Network 463 2.3 Non-electromagnetic emission from GRBs The IPN provided a large number of GRBs to the AMANDA project for searches for neutrino emission (Achterberg et al. 2008), and continues to collaborate with the IceCube project, where a search involving over 100 bursts is in progress. The LIGO and Virgo collaborations are looking at ∼380 IPN bursts which occurred during Science Run 5 (2005–2007), and ∼525 IPN bursts which occurred during Science Run 6 (2009–2010, preliminary results in Abadie et al. 2012). These are the most extensive searches for GRB-related gravitational radiation to date. The unique aspect of the IPN data is that there are ∼100 events/year that are not observed by Swift or Fermi, and, in addition, that the bursts tend to be the more nearby and/or energetic ones. 2.4 Some other projects IPN localizations are being used to search for polarization using the GAP po- larimeter on the Japanese IKAROS mission, and to derive the energy spectra of bursts observed by the Suzaku HXD WAM. By refining Fermi GBM localizations, the IPN is useful to the MAGIC and HAWC projects, which are searching for very high energy gamma-ray emission from bursts. IPN observations are also useful for determining the nature of candidate orphan afterglows. 3 Short bursts Since its inception, the IPN has had a high detection rate of short-duration GRBs. The first precise localization (∼800 sq. arcsec.) of a short GRB was published in Laros et al. (1981), and deep searches (magnitude 23.5) by Chevalier et al. (1981) revealed objects that were “probably distant galaxies unrelated to the burst source”. Today, the detection rate is about 20/year (Pal’shin et al. 2013). Although it is not possible to localize these bursts with the speed that Swift achieves, they nevertheless play an important role in many projects, particularly the LIGO/Virgo searches.
Recommended publications
  • Glossary of Acronyms and Definitions
    CASSINI FINAL MISSION REPORT 2018 CASSINI FINAL MISSION REPORT 2019 1 Glossary of Acronyms and Definitions A A/D Analog-to-Digital AACS Attitude and Articulation Control Subsystem AAN Automatic Alarm Notification AB Approved By ABS timed Absolute Timed AC Acoustics AC Alternating Current ACC Accelerometer ACCE Accelerometer Electronics ACCH Accelerometer Head ACE Aerospace Communications & Information Expertise ACE Aerospace Control Environment ACE Air Coordination Element ACE Attitude Control Electronics ACI Accelerometer Interface ACME Antenna Calibration and Measurement Equipment ACP Aerosol Collector Pyrolyzer ACS Attitude Control Subsystem ACT Actuator ACT Automated Command Tracker ACTS Advanced Communications Technology Satellite AD Applicable Document ADAS AWVR Data Acquisition Software ADC Analog-to-Digital Converter ADP Automatic Data Processing AE Activation Energy AEB Agência Espacial Brasileira (Brazilian Space Agency) AF Air Force AFC AACS Flight Computer AFETR Air Force Eastern Test Range AFETRM Air Force Eastern Test Range Manual 2 CASSINI FINAL MISSION REPORT 2019 AFS Atomic Frequency Standard AFT Abbreviated Functional Test AFT Allowable Flight Temperature AFS Andrew File System AGC Automatic Gain Control AGU American Geophysical Union AHSE Assembly, Handling, & Support Equipment AIT Assembly, Integration & Test AIV Assembly, Integration & Verification AKR Auroral Kilometric Radiation AL Agreement Letter AL Aluminum AL Anomalously Large ALAP As Low As Practical ALARA As Low As Reasonably Achievable ALB Automated Link
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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
    [Show full text]
  • 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.
    [Show full text]
  • The Interplanetary Network Database
    THE INTERPLANETARY NETWORK DATABASE Kevin Hurley UC Berkeley Space Sciences Laboratory Berkeley, CA And the current IPN team: T. Cline (Mars Odyssey, Konus), I. G. Mitrofanov, D. Golovin, M. L. Litvak, and A. B. Sanin (HEND-Odyssey), W. Boynton, C. Fellows, K. Harshman, H. Enos, and R. Starr (GRS-Odyssey), S. Golenetskii, R. Aptekar, E. Mazets, V. Pal'shin, D. Frederiks, D. Svinkin (Konus-Wind), D. M. Smith, R. P. Lin, J. McTiernan, R. Schwartz, W. Hajdas (RHESSI), A. von Kienlin, X. Zhang, A. Rau (INTEGRAL SPI-ACS), K. Yamaoka, M. Ohno, Y. Hanabata, Y. Fukazawa, T. Takahashi, M. Tashiro,Y. Terada, T. Murakami, and K. Makishima (Suzaku WAM), S. Barthelmy, J. Cummings, N. Gehrels, H. Krimm, and D. Palmer (Swift-BAT), J. Goldsten (MESSENGER GRNS), E. Del Monte, M. Feroci, F. Lazzarotto, M. Marisaldi (AGILE),V. Connaughton, M. S. Briggs, and C. Meegan (Fermi GBM) In The Beginning (ca. 1975 A.D.)… • The only way to get arcminute GRB positions was by triangulation • So the IPN has a long history, and over 30 spacecraft have participated in it • But it also has a present, and a future THE CURRENT IPN Mars (Odyssey) . Mercury . (MESSENGER) 600 l-s . LEO Spacecraft 24 light-ms l ● RHESSI AGILE l WIND 6 light-s Swift INTEGRAL 0.5 light-s Suzaku Fermi THE CURRENT IPN • Comprises 9 spacecraft (AGILE, Fermi, INTEGRAL, MESSENGER, Odyssey, RHESSI, Suzaku, Swift, Wind) – an excellent configuration • Detects 325 GRBs/year • Effectively acts as a full-time, all-sky monitor for gamma-ray transients (mainly SGRs and GRBs) • There is no time when all the
    [Show full text]
  • 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.
    [Show full text]
  • Planet Earth Taken by Hayabusa-2
    Space Science in JAXA Planet Earth May 15, 2017 taken by Hayabusa-2 Saku Tsuneta, PhD JAXA Vice President Director General, Institute of Space and Astronautical Science 2017 IAA Planetary Defense Conference, May 15-19,1 Tokyo 1 Brief Introduction of Space Science in JAXA Introduction of ISAS and JAXA • As a national center of space science & engineering research, ISAS carries out development and in-orbit operation of space science missions with other directorates of JAXA. • ISAS is an integral part of JAXA, and has close collaboration with other directorates such as Research and Development and Human Spaceflight Technology Directorates. • As an inter-university research institute, these activities are intimately carried out with universities and research institutes inside and outside Japan. ISAS always seeks for international collaboration. • Space science missions are proposed by researchers, and incubated by ISAS. ISAS plays a strategic role for mission selection primarily based on the bottom-up process, considering strategy of JAXA and national space policy. 3 JAXA recent science missions HAYABUSA 2003-2010 AKARI(ASTRO-F)2006-2011 KAGUYA(SELENE)2007-2009 Asteroid Explorer Infrared Astronomy Lunar Exploration IKAROS 2010 HAYABUSA2 2014-2020 M-V Rocket Asteroid Explorer Solar Sail SUZAKU(ASTRO-E2)2005- AKATSUKI 2010- X-Ray Astronomy Venus Meteorogy ARASE 2016- HINODE(SOLAR-B)2006- Van Allen belt Solar Observation Hisaki 2013 4 Planetary atmosphere Close ties between space science and space technology Space Technology Divisions Space
    [Show full text]
  • Science Instruments on Hayabusa Follow-On Missions
    Science Instruments on Hayabusa follow-on missions Yasuhiko Takagi (Aichi Toho University) (prepared by Masanao Abe (JAXA)) 1 Science instruments under examination Others 2 Basic concept of Hayabusa-IF* camera • Use Navigation camera as a scientific imager • Similar optics and CCD as AMICA, but with minor modifications on – Filters • ECAS -> special set for C-type • Remove ND flter , polarizer on CCD – Electronics • More flexible and autonomous operation • More effective compression • Larger onboard storage • Onboard data analysis 3 *Hayabusa-IF: Hayabusa Immediate Follow-on mission AMICA on Hayabysa Polarizer 4 Ground-based ECAS Quasi ECAS filters on AMICA5 A new filter set • Narrower band width (5~20 nm) – Remove ND filter – More accurate colorimetry • UV absorption as a thermal metamorphism indicator? • Phyllosilicate absorption around 700nm (430nm ?) • Nearby reference bands • Wide filter for imaging stars and the artificial orbiters (~TM) • Natural RGB for outreach purpose? • Several common bands with previous missions? (SSI/Galileo, MSI/NEAR, AMICA/Hayabusa, FC/ Dawn, NAC/Stardust, ??/Rosetta,etc, ) 6 Ground-based ECAS Thermal alteration Phyllosilicate absorption 7 8 Hayabusa NIRS • Wavelength range: 764-2247nm (△λ23.56nm) • FOV: 0.1x0.1deg(9m@5km distance) • Detector: InGaAs Liner Array (64channels) • F value: 1.00 • Effective diameter: 27mm • Operating temperature: 260K • A/D resolution (dynamic range) : 14bits 1 Average 0.1 Output [V] [V] Output Output 0.01 Standard Deviation 0.001 0.6 0.8 1.0 1.2 1.4 1.6 1.8 2.0 2.2 2.4 9 Wavelength
    [Show full text]
  • Securing Japan an Assessment of Japan´S Strategy for Space
    Full Report Securing Japan An assessment of Japan´s strategy for space Report: Title: “ESPI Report 74 - Securing Japan - Full Report” Published: July 2020 ISSN: 2218-0931 (print) • 2076-6688 (online) Editor and publisher: European Space Policy Institute (ESPI) Schwarzenbergplatz 6 • 1030 Vienna • Austria Phone: +43 1 718 11 18 -0 E-Mail: [email protected] Website: www.espi.or.at Rights reserved - No part of this report may be reproduced or transmitted in any form or for any purpose without permission from ESPI. Citations and extracts to be published by other means are subject to mentioning “ESPI Report 74 - Securing Japan - Full Report, July 2020. All rights reserved” and sample transmission to ESPI before publishing. ESPI is not responsible for any losses, injury or damage caused to any person or property (including under contract, by negligence, product liability or otherwise) whether they may be direct or indirect, special, incidental or consequential, resulting from the information contained in this publication. Design: copylot.at Cover page picture credit: European Space Agency (ESA) TABLE OF CONTENT 1 INTRODUCTION ............................................................................................................................. 1 1.1 Background and rationales ............................................................................................................. 1 1.2 Objectives of the Study ................................................................................................................... 2 1.3 Methodology
    [Show full text]
  • Iii. History of the Mission
    III. HISTORY OF THE MISSION 2011 Development phase 2014 Dec 3 Launch 5 Critical operations Launch 6 Initial function check Rocket - H-IIA-26 (type 202) Planned launch date - 30 Nov 2014 13:24:48 (Delayed due to weather) 2015 Actual launch date - 3 Dec 2014 13:22:04 Possible launch window - 30 Nov~9 Dec 2014 Mar Cruising phase Launch location - Tanegashima Space Center 2 Sub-payloads accompanying launch Dec Earth swing-by - Shin‘en 2 (Kyushu Institute of Technology) 3 - ARTSAT2-DESPATCH (Tama Art University) Southern hemisphere 4 - PROCYON (co-research by University of Tokyo and JAXA) station operations 2016 Critical operations - Solar array panel deployment, sun acquisition control - Sampling device horn extension Mar - Release launch lock on the retaining mechanism 22 Phase-1 Apr ion engine operation for the gimbal that controls ion engine direction - Confirm spacecraft tri-axial attitude control functions May 21 - Ground-based confirmation of functions for Nov precise trajectory determination system 22 Phase-2 ion engine operation Initial functional confirmation 2017 - Confirmation of ion engine, communications, power supply, attitude control, observation devices, etc. - Precise trajectory determination Apr 26 2018 Jan 10 Phase-3 Jun ion engine operation 3 27 Asteroid arrival HISTORY OF THE MISSION 23 H-IIA LAuNcH VEHIcLE H2A202 [Standard] 50m Satellite fairing (type 4S) H-IIA naming: H2A 1st/2nd stage / number of LRB / number of SRB-A Length - 53 m Mass - 289 ton Satellite fairing 2nd Stage - 1 SRB-A - 2 12m Hayabusa 2 1st Stage -
    [Show full text]