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II Publications, Presentations
II Publications, Presentations 1. Refereed Publications Izumi, K., Kotake, K., Nakamura, K., Nishida, E., Obuchi, Y., Ohishi, N., Okada, N., Suzuki, R., Takahashi, R., Torii, Abadie, J., et al. including Hayama, K., Kawamura, S.: 2010, Y., Ueda, A., Yamazaki, T.: 2010, DECIGO and DECIGO Search for Gravitational-wave Inspiral Signals Associated with pathfinder, Class. Quantum Grav., 27, 084010. Short Gamma-ray Bursts During LIGO's Fifth and Virgo's First Aoki, K.: 2010, Broad Balmer-Line Absorption in SDSS Science Run, ApJ, 715, 1453-1461. J172341.10+555340.5, PASJ, 62, 1333. Abadie, J., et al. including Hayama, K., Kawamura, S.: 2010, All- Aoki, K., Oyabu, S., Dunn, J. P., Arav, N., Edmonds, D., Korista sky search for gravitational-wave bursts in the first joint LIGO- K. T., Matsuhara, H., Toba, Y.: 2011, Outflow in Overlooked GEO-Virgo run, Phys. Rev. D, 81, 102001. Luminous Quasar: Subaru Observations of AKARI J1757+5907, Abadie, J., et al. including Hayama, K., Kawamura, S.: 2010, PASJ, 63, S457. Search for gravitational waves from compact binary coalescence Aoki, W., Beers, T. C., Honda, S., Carollo, D.: 2010, Extreme in LIGO and Virgo data from S5 and VSR1, Phys. Rev. D, 82, Enhancements of r-process Elements in the Cool Metal-poor 102001. Main-sequence Star SDSS J2357-0052, ApJ, 723, L201-L206. Abadie, J., et al. including Hayama, K., Kawamura, S.: 2010, Arai, A., et al. including Yamashita, T., Okita, K., Yanagisawa, TOPICAL REVIEW: Predictions for the rates of compact K.: 2010, Optical and Near-Infrared Photometry of Nova V2362 binary coalescences observable by ground-based gravitational- Cyg: Rebrightening Event and Dust Formation, PASJ, 62, wave detectors, Class. -
IVS NICT-TDC News No.39
ISSN 1882-3432 CONTENTS Proceedings of the 18th NICT TDC Symposium (Kashima, October 1, 2020) KNIFE, Kashima Nobeyama InterFErometer . 3 Makoto Miyoshi Space-Time Measurements Research Inspired by Kashima VLBI Group . 8 Mizuhiko Hosokawa ALMA High Frequency Long Baseline Phase Correction Using Band-to-band ..... 11 (B2B) Phase Referencing Yoshiharu Asaki and Luke T. Maud Development of a 6.5-22.5 GHz Very Wide Band Feed Antenna Using a New ..... 15 Quadruple-Ridged Antenna for the Traditional Radio Telescopes Yutaka Hasegawa*, Yasumasa Yamasaki, Hideo Ogawa, Taiki Kawakami, Yoshi- nori Yonekura, Kimihiro Kimura, Takuya Akahori, Masayuki Ishino, Yuki Kawa- hara Development of Wideband Antenna . 18 Hideki Ujihara Performance Survey of Superconductor Filter Introduced in Wideband Re- ..... 20 ceiver for VGOS of the Ishioka VLBI Station Tomokazu Nakakuki, Haruka Ueshiba, Saho Matsumoto, Yu Takagi, Kyonosuke Hayashi, Toru Yutsudo, Katsuhiro Mori, Tomokazu Kobayashi, and Mamoru Sekido New Calibration Method for a Radiometer Without Using Liquid Nitrogen ..... 23 Cooled Absorber Noriyuki Kawaguchi, Yuichi Chikahiro, Kenichi Harada, and Kensuke Ozeki Comparison of Atmospheric Delay Models (NMF, VMF1, and VMF3) in ..... 27 VLBI analysis Mamoru Sekido and Monia Negusini HINOTORI Status Report . 31 Hiroshi Imai On-the-Fly Interferometer Experiment with the Yamaguchi Interferometer . 34 Kenta Fujisawa, Kotaro Niinuma, Masanori Akimoto, and Hideyuki Kobayashi Superconducting Wide-band BRF for Geodetic VLBI Observation with ..... 36 VGOS Radio Telescope -
E-Region Auroral Ionosphere Model
atmosphere Article AIM-E: E-Region Auroral Ionosphere Model Vera Nikolaeva 1,* , Evgeny Gordeev 2 , Tima Sergienko 3, Ludmila Makarova 1 and Andrey Kotikov 4 1 Arctic and Antarctic Research Institute, 199397 Saint Petersburg, Russia; [email protected] 2 Earth’s Physics Department, Saint Petersburg State University, 199034 Saint Petersburg, Russia; [email protected] 3 Swedish Institute of Space Physics, 981 28 Kiruna, Sweden; [email protected] 4 Saint Petersburg Branch of Pushkov Institute of Terrestrial Magnetism, Ionosphere and Radio Wave Propagation of Russian Academy of Sciences (IZMIRAN), 199034 Saint Petersburg, Russia; [email protected] * Correspondence: [email protected] Abstract: The auroral oval is the high-latitude region of the ionosphere characterized by strong vari- ability of its chemical composition due to precipitation of energetic particles from the magnetosphere. The complex nature of magnetospheric processes cause a wide range of dynamic variations in the auroral zone, which are difficult to forecast. Knowledge of electron concentrations in this highly turbulent region is of particular importance because it determines the propagation conditions for the radio waves. In this work we introduce the numerical model of the auroral E-region, which evaluates density variations of the 10 ionospheric species and 39 reactions initiated by both the solar extreme UV radiation and the magnetospheric electron precipitation. The chemical reaction rates differ in more than ten orders of magnitude, resulting in the high stiffness of the ordinary differential equations system considered, which was solved using the high-performance Gear method. The AIM-E model allowed us to calculate the concentration of the neutrals NO, N(4S), and N(2D), ions + + + + + 4 + 2 + 2 N ,N2 , NO ,O2 ,O ( S), O ( D), and O ( P), and electrons Ne, in the whole auroral zone in the Citation: Nikolaeva, V.; Gordeev, E.; 90-150 km altitude range in real time. -
XIII Publications, Presentations
XIII Publications, Presentations 1. Refereed Publications E., Kawamura, A., Nguyen Luong, Q., Sanhueza, P., Kurono, Y.: 2015, The 2014 ALMA Long Baseline Campaign: First Results from Aasi, J., et al. including Fujimoto, M.-K., Hayama, K., Kawamura, High Angular Resolution Observations toward the HL Tau Region, S., Mori, T., Nishida, E., Nishizawa, A.: 2015, Characterization of ApJ, 808, L3. the LIGO detectors during their sixth science run, Classical Quantum ALMA Partnership, et al. including Asaki, Y., Hirota, A., Nakanishi, Gravity, 32, 115012. K., Espada, D., Kameno, S., Sawada, T., Takahashi, S., Ao, Y., Abbott, B. P., et al. including Flaminio, R., LIGO Scientific Hatsukade, B., Matsuda, Y., Iono, D., Kurono, Y.: 2015, The 2014 Collaboration, Virgo Collaboration: 2016, Astrophysical Implications ALMA Long Baseline Campaign: Observations of the Strongly of the Binary Black Hole Merger GW150914, ApJ, 818, L22. Lensed Submillimeter Galaxy HATLAS J090311.6+003906 at z = Abbott, B. P., et al. including Flaminio, R., LIGO Scientific 3.042, ApJ, 808, L4. Collaboration, Virgo Collaboration: 2016, Observation of ALMA Partnership, et al. including Asaki, Y., Hirota, A., Nakanishi, Gravitational Waves from a Binary Black Hole Merger, Phys. Rev. K., Espada, D., Kameno, S., Sawada, T., Takahashi, S., Kurono, Lett., 116, 061102. Y., Tatematsu, K.: 2015, The 2014 ALMA Long Baseline Campaign: Abbott, B. P., et al. including Flaminio, R., LIGO Scientific Observations of Asteroid 3 Juno at 60 Kilometer Resolution, ApJ, Collaboration, Virgo Collaboration: 2016, GW150914: Implications 808, L2. for the Stochastic Gravitational-Wave Background from Binary Black Alonso-Herrero, A., et al. including Imanishi, M.: 2016, A mid-infrared Holes, Phys. -
Orbit Options for an Orion-Class Spacecraft Mission to a Near-Earth Object
Orbit Options for an Orion-Class Spacecraft Mission to a Near-Earth Object by Nathan C. Shupe B.A., Swarthmore College, 2005 A thesis submitted to the Faculty of the Graduate School of the University of Colorado in partial fulfillment of the requirements for the degree of Master of Science Department of Aerospace Engineering Sciences 2010 This thesis entitled: Orbit Options for an Orion-Class Spacecraft Mission to a Near-Earth Object written by Nathan C. Shupe has been approved for the Department of Aerospace Engineering Sciences Daniel Scheeres Prof. George Born Assoc. Prof. Hanspeter Schaub Date The final copy of this thesis has been examined by the signatories, and we find that both the content and the form meet acceptable presentation standards of scholarly work in the above mentioned discipline. iii Shupe, Nathan C. (M.S., Aerospace Engineering Sciences) Orbit Options for an Orion-Class Spacecraft Mission to a Near-Earth Object Thesis directed by Prof. Daniel Scheeres Based on the recommendations of the Augustine Commission, President Obama has pro- posed a vision for U.S. human spaceflight in the post-Shuttle era which includes a manned mission to a Near-Earth Object (NEO). A 2006-2007 study commissioned by the Constellation Program Advanced Projects Office investigated the feasibility of sending a crewed Orion spacecraft to a NEO using different combinations of elements from the latest launch system architecture at that time. The study found a number of suitable mission targets in the database of known NEOs, and pre- dicted that the number of candidate NEOs will continue to increase as more advanced observatories come online and execute more detailed surveys of the NEO population. -
Stardust Comet Flyby
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Stardust Comet Flyby Press Kit January 2004 Contacts Don Savage Policy/Program Management 202/358-1727 NASA Headquarters, Washington DC Agle Stardust Mission 818/393-9011 Jet Propulsion Laboratory, Pasadena, Calif. Vince Stricherz Science Investigation 206/543-2580 University of Washington, Seattle, WA Contents General Release ……………………………………......………….......................…...…… 3 Media Services Information ……………………….................…………….................……. 5 Quick Facts …………………………………………..................………....…........…....….. 6 Why Stardust?..................…………………………..................………….....………......... 7 Other Comet Missions ....................................................................................... 10 NASA's Discovery Program ............................................................................... 12 Mission Overview …………………………………….................……….....……........…… 15 Spacecraft ………………………………………………..................…..……........……… 25 Science Objectives …………………………………..................……………...…........….. 34 Program/Project Management …………………………...................…..…..………...... 37 1 2 GENERAL RELEASE: NASA COMET HUNTER CLOSING ON QUARRY Having trekked 3.2 billion kilometers (2 billion miles) across cold, radiation-charged and interstellar-dust-swept space in just under five years, NASA's Stardust spacecraft is closing in on the main target of its mission -- a comet flyby. "As the saying goes, 'We are good to go,'" said project manager Tom Duxbury at NASA's Jet -
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. -
Building the Coolest X-Ray Satellite
National Aeronautics and Space Administration Building the Coolest X-ray Satellite 朱雀 Suzaku A Video Guide for Teachers Grades 9-12 Probing the Structure & Evolution of the Cosmos http://suzaku-epo.gsfc.nasa.gov/ www.nasa.gov The Suzaku Learning Center Presents “Building the Coolest X-ray Satellite” Video Guide for Teachers Written by Dr. James Lochner USRA & NASA/GSFC Greenbelt, MD Ms. Sara Mitchell Mr. Patrick Keeney SP Systems & NASA/GSFC Coudersport High School Greenbelt, MD Coudersport, PA This booklet is designed to be used with the “Building the Coolest X-ray Satellite” DVD, available from the Suzaku Learning Center. http://suzaku-epo.gsfc.nasa.gov/ Table of Contents I. Introduction 1. What is Astro-E2 (Suzaku)?....................................................................................... 2 2. “Building the Coolest X-ray Satellite” ....................................................................... 2 3. How to Use This Guide.............................................................................................. 2 4. Contents of the DVD ................................................................................................. 3 5. Post-Launch Information ........................................................................................... 3 6. Pre-requisites............................................................................................................. 4 7. Standards Met by Video and Activities ...................................................................... 4 II. Video Chapter 1 -
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. -
AKARI: Astronomical IR Satellite MLHES Mission Program
Probing Ancient Mass Loss with AKARI’s Extended Dust Emission Objects Rachael Tomasino1, Dr. Toshiya Ueta1,2, Dr. Yamamura Issei2, Dr. Hideyuki Izumiura3 1University of Denver, USA; 2Institute of Space and Astronomical Science, Japan Aerospace Exploration Agency (ISAS/JAXA), Japan, 3Okayama Astrophysical Observatory, Japan AKARI: Astronomical IR Satellite FIS-AKARI Slow-scan Tools! Extended Emission Calibration! AKARI (formerly ASTRO-F), is the second Japanese satellite FAST is a program that allows for interactive Original calibration of the FIS detector was done using diffuse galactic cirrus emission dedicated to infrared (IR) astronomy, from the Institute of assessment of the data quality and on-the-fly with low photon counts. On the other hand, bright point sources can cause the slow Space and Astronautical Science (ISAS) of the Japanese corrections to the time-series data on a pixel-by- transient response effect because of high photon counts. Marginally extended sources Aerospace Exploration Agency (JAXA). Its main objective is pixel basis in order to manually correct glitches consist of regions of high and low photon counts, and therefore, only parts of them suffer to perform an all-sky survey with better spatial resolution and that would have been missed in the pipeline from the slow transient response effect. Hence, we needed to devise a specific method to wider wavelength coverage than IRAS (first US, UK, Dutch process. These corrections include: (1) eliminate address the detector response as a whole. This method uses a contour aperture to include infrared satellite launched in 1983), mapping the entire sky in bad on-sky calibration sequences, (2) flag out both the faint and bright emission by setting a threshold of background + 3#.! six infrared bands. -
Miniature Space GPS Receiver by Means of Automobile-Navigation Technology
[SSC07-VIII-1] Miniature Space GPS Receiver by means of Automobile-Navigation Technology Hirobumi Saito Institute of Space and Astronautical Science, Japan Aerospace Exploration Agenc 3-1-1 Yoshinodai, Sagamihara, Kanagawa 229-8510 Japan; 81-42-759-8363 [email protected]/jp Takahide Mizuno*, Kousuke Kawahara*, Kenji Shinkai*, Takanao Saiki*, Yousuke Fukushima*, Yusuke Hamada**, Hiroyuki Sasaki***, Sachiko Katumoto*** and Yasuhiro Kajikawa**** *Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency 3-1-1 Yoshinodai, Sagamihara, Kanagawa 229-8510 Japan **Musashi Institute of Technology, 1-28-1 Tamazutsumi, Setahaya-ku, Tokyo, 158-8557 Japan ***Soka University, 1-236 Tangi-cho, Hachioji-city, Tokyo, 192-8577 Japan ****Tokyo Denki University, 2-2 kanda, Nishikicyou, chiyoda-ku, Tokyo, 101-8457 Japan ABSTRACT Miniature space GPS receivers have been developed by means of automobile-navigation technology. We expanded the frequency sweep range in order to cover large Doppler shift on orbit. The GPS receiver was modified to output pseudorange data with accurate time tag. We tested the performance in low earth orbits by means of a GPS simulator. The range error caused by the receiver is measured to be 0.9 meter in RMS. Receiver was on-boarded on INDEX (“REIMEI”) satellite, which was launched in 2005. Cold start positioning was confirmed repeatedly to finish within 30 minutes on orbit. The orbit determination was performed to evaluate the random position error of GPS receiver by means of the residual error. The random error of GPS position is as large as 2 meter for PDDP=2.5 on orbit. The RMS value of range error is evaluated to be 0.6m from the flight data. -
ASTRO-F Observer's Manual
ASTRO-F Observer’s Manual Version 3.2 — for Open Time Observation Planning — ASTRO-F User Support Team in Institute of Space and Astronautical Science / JAXA contact: iris [email protected] European Space Astronomy Centre / ESA contact: http://astro-f.esac.esa.int/esupport/ November 29, 2005 Version 3.2 (November 29, 2005) i Revision Record 2005 Nov. 29: Version 3.2 released. Updated description of IRC FoV and slit (Section 5.1.4 and 5.1.5). Updated IRC04 detection and saturation limits. Also improve the description (Section 5.5.9). Section 5.4.2 revised to clarify the point. Units for Ho given value in p.113. 2005 Nov. 8: Version 3.1 released. Updated Visibility Map for Open Time Users (Figure 3.4.3) Information for the handling of Solar System Object observations (Section 3.4) Updated saturation limits for FTS (FIS03) mode (Table 4.4.16) IRC04 detection limits for NG+Np added (Table 5.5.25,5.5.26) Updated worked examples using the latest versions of the Tools (Section B) ESAC web pages URL and Helpdesk contact address updated Numerous errors and typos corrected 2005 Sep.20: Version 3.0 released. Contents 1 Introduction 1 1.1Purposeofthisdocument............................... 1 1.2RelevantInformation.................................. 3 2 Mission Overview 5 2.1TheASTRO-FMission................................ 5 2.2 Satellite . ........................................ 6 2.2.1 TheBusModule................................ 6 2.2.2 AttitudeDeterminationandControlSystem................. 7 2.2.3 Cryogenics................................... 8 2.3Telescope........................................ 9 2.3.1 Specification.................................. 9 2.3.2 Pre-flightperformance............................. 10 2.4Focal-PlaneInstruments................................ 11 2.4.1 SpecificationOverview............................. 11 2.4.2 Focal-PlaneLayout..............................