FLUXGATE MAGNETOMETER Suspended Version
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Juno Telecommunications
The cover The cover is an artist’s conception of Juno in orbit around Jupiter.1 The photovoltaic panels are extended and pointed within a few degrees of the Sun while the high-gain antenna is pointed at the Earth. 1 The picture is titled Juno Mission to Jupiter. See http://www.jpl.nasa.gov/spaceimages/details.php?id=PIA13087 for the cover art and an accompanying mission overview. DESCANSO Design and Performance Summary Series Article 16 Juno Telecommunications Ryan Mukai David Hansen Anthony Mittskus Jim Taylor Monika Danos Jet Propulsion Laboratory California Institute of Technology Pasadena, California National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Pasadena, California October 2012 This research was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. Reference herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise, does not constitute or imply endorsement by the United States Government or the Jet Propulsion Laboratory, California Institute of Technology. Copyright 2012 California Institute of Technology. Government sponsorship acknowledged. DESCANSO DESIGN AND PERFORMANCE SUMMARY SERIES Issued by the Deep Space Communications and Navigation Systems Center of Excellence Jet Propulsion Laboratory California Institute of Technology Joseph H. Yuen, Editor-in-Chief Published Articles in This Series Article 1—“Mars Global -
Survey of Juno Observations in Jupiter's Plasma Disk: Density
RESEARCH ARTICLE Survey of Juno Observations in Jupiter's Plasma Disk: 10.1029/2021JA029446 Density Key Points: E. Huscher1, F. Bagenal1 , R. J. Wilson1 , F. Allegrini2,3 , R. W. Ebert2,3 , P. W. Valek2 , • On most orbits, the densities exhibit J. R. Szalay4 , D. J. McComas4 , J. E. P. Connerney5,6 , S. Bolton2 , and S. M. Levin7 regular behavior mapping out a disk confined close to the centrifugal 1Laboratory for Atmospheric and Space Physics, University of Colorado, Boulder, CO, USA, 2Southwest Research equator 3 • Small-scale ( minutes) variabilities Institute, San Antonio, TX, USA, Department of Physics and Astronomy, University of Texas at San Antonio, San 4 5 may indicate∼ radial transport via Antonio, TX, USA, Department of Astrophysical Sciences, Princeton University, Princeton, NJ, USA, Space Research local instabilities Corporation, Annapolis, MD, USA, 6Goddard Space Flight Center, Greenbelt, MD, USA, 7Jet Propulsion Laboratory/ • Occasionally a uniformly tenuous California Institute of Technology, Pasadena, CA, USA outer disk indicates enhanced losses, perhaps triggered by solar wind compression Abstract We explore the variation in plasma conditions through the middle magnetosphere of Jupiter with latitude and radial distance using Juno-JADE measurements of plasma density (electrons, protons, Supporting Information: sulfur, and oxygen ions) surveyed on Orbits 5–26 between March 2017 and April 2020. On most orbits, the Supporting Information may be found in the online version of this article. densities exhibit regular behavior, mapping out a disk between 10 and 50 RJ (Jovian radii). In the disk, the heavy ions are confined close to the centrifugal equator which oscillates relative to the spacecraft due to the 10° tilt of Jupiter's magnetic dipole. -
+ New Horizons
Media Contacts NASA Headquarters Policy/Program Management Dwayne Brown New Horizons Nuclear Safety (202) 358-1726 [email protected] The Johns Hopkins University Mission Management Applied Physics Laboratory Spacecraft Operations Michael Buckley (240) 228-7536 or (443) 778-7536 [email protected] Southwest Research Institute Principal Investigator Institution Maria Martinez (210) 522-3305 [email protected] NASA Kennedy Space Center Launch Operations George Diller (321) 867-2468 [email protected] Lockheed Martin Space Systems Launch Vehicle Julie Andrews (321) 853-1567 [email protected] International Launch Services Launch Vehicle Fran Slimmer (571) 633-7462 [email protected] NEW HORIZONS Table of Contents Media Services Information ................................................................................................ 2 Quick Facts .............................................................................................................................. 3 Pluto at a Glance ...................................................................................................................... 5 Why Pluto and the Kuiper Belt? The Science of New Horizons ............................... 7 NASA’s New Frontiers Program ........................................................................................14 The Spacecraft ........................................................................................................................15 Science Payload ...............................................................................................................16 -
The Suitability of Quantum Magnetometers for Defence Applications
The Suitability of Quantum Magnetometers for Defence Applications UDT 2019 - 14th May 2019 Andrew Bond and Leighton Brown Presented by Nick Sheppard © Thales UK Limited 2019 The copyright herein is the property of Thales UK Limited. It is not to be reproduced, modified, adapted, published, translated in any material form (including storage in any medium by electronic means whether or not transiently or incidentally), in whole or in part nor disclosed to any third party without the prior written permission of Thales UK Limited. Neither shall it be used otherwise than for the purpose for which it is supplied. The information contained herein is confidential and, subject to any rights of third parties, is proprietary to Thales UK Limited. It is intended only for the authorised recipient for the intended purpose, and access to it by any other person is unauthorised. The information contained herein may not be disclosed to any third party or used for any other purpose without the express written permission of Thales UK Limited. If you are not the intended recipient, you must not disclose, copy, circulate or in any other way use or rely on the information contained in this document. Such unauthorised use may be unlawful. If you have received this document in error, please inform Thales UK Limited immediately on +44 (0)118 9434500 and post it, together with your name and address, to The Intellectual Property Department, Thales UK Limited, 350 Longwater Avenue, Green Park, Reading RG2 6GF. Postage will be refunded. www.thalesgroup.com OPEN Quantum Devices ▌Quantum technologies are beginning to move out of laboratory environments and into industrial applications. -
2018: Aiaa-Space-Report
AIAA TEAM SPACE TRANSPORTATION DESIGN COMPETITION TEAM PERSEPHONE Submitted By: Chelsea Dalton Ashley Miller Ryan Decker Sahil Pathan Layne Droppers Joshua Prentice Zach Harmon Andrew Townsend Nicholas Malone Nicholas Wijaya Iowa State University Department of Aerospace Engineering May 10, 2018 TEAM PERSEPHONE Page I Iowa State University: Persephone Design Team Chelsea Dalton Ryan Decker Layne Droppers Zachary Harmon Trajectory & Propulsion Communications & Power Team Lead Thermal Systems AIAA ID #908154 AIAA ID #906791 AIAA ID #532184 AIAA ID #921129 Nicholas Malone Ashley Miller Sahil Pathan Joshua Prentice Orbit Design Science Science Science AIAA ID #921128 AIAA ID #922108 AIAA ID #761247 AIAA ID #922104 Andrew Townsend Nicholas Wijaya Structures & CAD Trajectory & Propulsion AIAA ID #820259 AIAA ID #644893 TEAM PERSEPHONE Page II Contents 1 Introduction & Problem Background2 1.1 Motivation & Background......................................2 1.2 Mission Definition..........................................3 2 Mission Overview 5 2.1 Trade Study Tools..........................................5 2.2 Mission Architecture.........................................6 2.3 Planetary Protection.........................................6 3 Science 8 3.1 Observations of Interest.......................................8 3.2 Goals.................................................9 3.3 Instrumentation............................................ 10 3.3.1 Visible and Infrared Imaging|Ralph............................ 11 3.3.2 Radio Science Subsystem................................. -
The Pickup Ion-Mediated Solar Wind
The Astrophysical Journal, 869:23 (21pp), 2018 December 10 https://doi.org/10.3847/1538-4357/aaebfe © 2018. The American Astronomical Society. All rights reserved. The Pickup Ion-mediated Solar Wind G. P. Zank1,2 , L. Adhikari1 , L.-L. Zhao1 , P. Mostafavi2,3 , E. J. Zirnstein3 , and D. J. McComas3 1 Center for Space Plasma and Aeronomic Research (CSPAR), University of Alabama in Huntsville, Huntsville, AL 35805, USA 2 Department of Space Science, University of Alabama in Huntsville, Huntsville, AL 35899, USA 3 Department of Astrophysical Sciences, Princeton University, Princeton, NJ 08544, USA Received 2018 September 10; revised 2018 October 22; accepted 2018 October 24; published 2018 December 7 Abstract The New Horizons Solar Wind Around Pluto (NH SWAP) instrument has provided the first direct observations of interstellar H+ and He+ pickup ions (PUIs) at distances between ∼11.26 and 38 au in the solar wind. The observations demonstrate that the distant solar wind beyond the hydrogen ionization cavity is indeed mediated by PUIs. The creation of PUIs modifies the underlying low-frequency turbulence field responsible for their own scattering. The dissipation of these low-frequency fluctuations serves to heat the solar wind plasma, and accounts for the observed non-adiabatic solar wind temperature profile and a possible slow temperature increase beyond ∼30 au. We develop a very general theoretical model that incorporates PUIs, solar wind thermal plasma, the interplanetary magnetic field, and low-frequency turbulence to describe the evolution of the large-scale solar wind, PUIs, and turbulence from 1–84 au, the structure of the perpendicular heliospheric termination shock, and the transmission of turbulence into the inner heliosheath, extending the classical models of Holzer and Isenberg. -
New Horizons SOC to Instrument Pipeline ICD
New Horizons SOC to Instrument Pipeline ICD September 2017 SwRI® Project 05310 Document No. 05310-SOCINST-01 Contract NASW-02008 Prepared by SOUTHWEST RESEARCH INSTITUTE® Space Science and Engineering Division 6220 Culebra Road, San Antonio, Texas 78228-0510 (210) 684-5111 FAX (210) 647-4325 Southwest Research Institute 05310-SOCINST-01 Rev 0 Chg 0 New Horizons SOC to Instrument Pipeline ICD Page ii New Horizons SOC to Instrument Pipeline ICD SwRI Project 05310 Document No. 05310-SOCINST-01 Contract NASW-02008 Prepared by: Joe Peterson 08 November 2013 Revised by: Brian Carcich August, 2014 Revised by: Tiffany Finley March, 2016 Revised by: Tiffany Finley October, 2016 Revised by: Brian Carcich December, 2016 Revised by: Tiffany Finley, Brian Carcich, PEPSSI team April, 2017 Revised by: Tiffany Finley, PEPSSI team September, 2017 Contributors: ALICE specifics prepared by: Maarten Versteeg, Joel Parker, & Andrew Steffl LEISA specifics prepared by: George McCabe & Allen Lunsford LORRI specifics prepared by: Hal Weaver & Howard Taylor MVIC specifics prepared by: Cathy Olkin PEPSSI specifics prepared by: Stefano Livi, Matthew Hill, Lawrence Brown, & Peter Kollman REX specifics prepared by: Ivan Linscott & Brian Carcich SDC specifics prepared by: David James SWAP specifics prepared by: Heather Elliott Southwest Research Institute 05310-SOCINST-01 Rev 0 Chg 0 New Horizons SOC to Instrument Pipeline ICD Page iii General Approval Signatures: Approved by: ____________________________________ Date: ____________ Hal Weaver, JHU/APL, Project Scientist -
Precision Magnetometers for Aerospace Applications: a Review
sensors Review Precision Magnetometers for Aerospace Applications: A Review James S. Bennett 1,† , Brian E. Vyhnalek 2,†, Hamish Greenall 1 , Elizabeth M. Bridge 1 , Fernando Gotardo 1 , Stefan Forstner 1 , Glen I. Harris 1 , Félix A. Miranda 2,* and Warwick P. Bowen 1,* 1 School of Mathematics and Physics, The University of Queensland, St. Lucia, QLD 4072, Australia; [email protected] (J.S.B.); [email protected] (H.G.); [email protected] (E.M.B.); [email protected] (F.G.); [email protected] (S.F.); [email protected] (G.I.H.) 2 NASA Glenn Research Center, Cleveland, OH 44135, USA; [email protected] * Correspondence: [email protected] (F.A.M.); [email protected] (W.P.B.) † These authors contributed equally to this work. Abstract: Aerospace technologies are crucial for modern civilization; space-based infrastructure underpins weather forecasting, communications, terrestrial navigation and logistics, planetary observations, solar monitoring, and other indispensable capabilities. Extraplanetary exploration— including orbital surveys and (more recently) roving, flying, or submersible unmanned vehicles—is also a key scientific and technological frontier, believed by many to be paramount to the long-term survival and prosperity of humanity. All of these aerospace applications require reliable control of the craft and the ability to record high-precision measurements of physical quantities. Magnetometers deliver on both of these aspects and have been vital to the success of numerous missions. In this review Citation: Bennett, J.S.; Vyhnalek, paper, we provide an introduction to the relevant instruments and their applications. -
Determining the Small-Scale Structure and Particle Properties in Saturn's Rings from Stellar and Radio Occultations
University of Central Florida STARS Electronic Theses and Dissertations, 2004-2019 2018 Determining the Small-scale Structure and Particle Properties in Saturn's Rings from Stellar and Radio Occultations Richard Jerousek University of Central Florida Part of the The Sun and the Solar System Commons Find similar works at: https://stars.library.ucf.edu/etd University of Central Florida Libraries http://library.ucf.edu This Doctoral Dissertation (Open Access) is brought to you for free and open access by STARS. It has been accepted for inclusion in Electronic Theses and Dissertations, 2004-2019 by an authorized administrator of STARS. For more information, please contact [email protected]. STARS Citation Jerousek, Richard, "Determining the Small-scale Structure and Particle Properties in Saturn's Rings from Stellar and Radio Occultations" (2018). Electronic Theses and Dissertations, 2004-2019. 5840. https://stars.library.ucf.edu/etd/5840 DETERMINING THE SMALL-SCALE STRUCTURE AND PARTICLE PROPERTIES IN SATURN’S RINGS FROM STELLAR AND RADIO OCCULTATIONS by RICHARD GREGORY JEROUSEK M.S. University of Central Florida, 2009 A dissertation submitted in partial fulfillment of the requirements for the degree of Doctor of Philosophy in the Department of Physics in the College of Sciences at the University of Central Florida Orlando, Florida Spring Term 2018 Major Professor: Joshua E. Colwell © 2018 Richard G. Jerousek ii ABSTRACT Saturn’s rings consist of icy particles of various sizes ranging from millimeters to several meters. Particles may aggregate into ephemeral elongated clumps known as self-gravity wakes in regions where the surface mass density and epicyclic frequency give a Toomre critical wavelength which is much larger than the largest individual particles (Julian and Toomre 1966). -
Arxiv:2106.15843V1 [Physics.App-Ph] 30 Jun 2021 Ters (E.G., [20])
Precision Magnetometers for Aerospace Applications James S. Bennett,1, ∗ Brian E. Vyhnalek,2, ∗ Hamish Greenall,1 Elizabeth M. Bridge,1 Fernando Gotardo,1 Stefan Forstner,1 Glen I. Harris,1 F´elixA. Miranda,2, y and Warwick P. Bowen1, z 1School of Mathematics and Physics, The University of Queensland, St Lucia, Brisbane Queensland 4072, Australia 2NASA Glenn Research Center, Cleveland, Ohio 44135, The United States of America (Dated: July 1, 2021) Aerospace technologies are crucial for modern civilization; space-based infrastructure underpins weather forecasting, communications, terrestrial navigation and logistics, planetary observations, solar monitoring, and other indispensable capabilities. Extraplanetary exploration { including or- bital surveys and (more recently) roving, flying, or submersible unmanned vehicles { is also a key scientific and technological frontier, believed by many to be paramount to the long-term survival and prosperity of humanity. All of these aerospace applications require reliable control of the craft and the ability to record high-precision measurements of physical quantities. Magnetometers deliver on both of these aspects, and have been vital to the success of numerous missions. In this review paper, we provide an introduction to the relevant instruments and their applications. We consider past and present magnetometers, their proven aerospace applications, and emerging uses. We then look to the future, reviewing recent progress in magnetometer technology. We particularly focus on magnetometers that use optical readout, including atomic magnetometers, magnetometers based on quantum defects in diamond, and optomechanical magnetometers. These optical magnetometers offer a combination of field sensitivity, size, weight, and power consumption that allows them to reach performance regimes that are inaccessible with existing techniques. -
Team Persephone
AIAA TEAM SPACE TRANSPORTATION DESIGN COMPETITION TEAM PERSEPHONE Submitted By: Chelsea Dalton Ashley Miller Ryan Decker Sahil Pathan Layne Droppers Joshua Prentice Zach Harmon Andrew Townsend Nicholas Malone Nicholas Wijaya Iowa State University Department of Aerospace Engineering May 10, 2018 TEAM PERSEPHONE Page I Iowa State University: Persephone Design Team Chelsea Dalton Ryan Decker Layne Droppers Zachary Harmon Trajectory & Propulsion Communications & Power Team Lead Thermal Systems AIAA ID #908154 AIAA ID #906791 AIAA ID #532184 AIAA ID #921129 Nicholas Malone Ashley Miller Sahil Pathan Joshua Prentice Orbit Design Science Science Science AIAA ID #921128 AIAA ID #922108 AIAA ID #761247 AIAA ID #922104 Andrew Townsend Nicholas Wijaya Structures & CAD Trajectory & Propulsion AIAA ID #820259 AIAA ID #644893 TEAM PERSEPHONE Page II Contents 1 Introduction & Problem Background 2 1.1 Motivation & Background . 2 1.2 Mission Definition . 3 2 Mission Overview 5 2.1 Trade Study Tools . 5 2.2 Mission Architecture . 6 2.3 Planetary Protection . 6 3 Science 8 3.1 Observations of Interest . 8 3.2 Goals . 9 3.3 Instrumentation . 10 3.3.1 Visible and Infrared Imaging|Ralph . 11 3.3.2 Radio Science Subsystem . 12 3.3.3 Atmosphere . 14 3.3.4 Solar Wind Around Pluto . 14 3.3.5 Descent Probes . 16 4 Trajectory 19 4.1 Interplanetary Trajectory Design . 19 4.2 Earth Launch . 19 4.2.1 Launch Vehicle Selection . 19 4.2.2 Launch Vehicle Integration . 22 4.2.3 Launch Characteristics . 23 4.3 Interplanetary Cruise . 25 4.4 Jupiter Gravity Assist . 26 4.5 Pluto Orbit Insertion . 28 5 Primary Mission 30 5.1 Design Methodology . -
First Light of SWAP On-Board PROBA2
First light of SWAP on-board PROBA2 Jean-Philippe Halaina*, David Berghmansb, Jean-Marc Defisea, Etienne Renottea, Tanguy Thiberta, Emmanuel Mazya, Pierre Rochusa, Bogdan Niculab, Anik De Groofb, Dan Seatonc Udo Schühlec aCentre Spatial de Liège, Université de Liège, Liege Science Park, 4013 Angleur, Belgium bRoyal Observatory of Belgium, Avenue Circulaire, Uccle, Belgium cMax-Planck-Institut für Sonnensystemforschung, Lindau, Germany ABSTRACT The SWAP telescope (Sun Watcher using Active Pixel System detector and Image Processing) is an instrument launched on 2nd November 2009 on-board the ESA PROBA2 technological mission. SWAP is a space weather sentinel from a low Earth orbit, providing images at 174nm of the solar corona. The instrument concept has been adapted to the PROBA2 mini-satellite requirements (compactness, low power electronics and a-thermal opto-mechanical system). It also takes advantage of the platform pointing agility, on-board processor, Packetwire interface and autonomous operations. The key component of SWAP is a radiation resistant CMOS-APS detector combined with onboard compression and data prioritization. SWAP has been developed and qualified at the Centre Spatial de Liège (CSL) and calibrated at the PTB- Bessy facility. After launch, SWAP has provided its first images on 14th November 2009 and started its nominal, scientific phase in February 2010, after 3 months of platform and payload commissioning. This paper summarizes the latest SWAP developments and qualifications, and presents the first light results. Keywords: SWAP, CMOS-APS, PROBA2 1. SWAP ON PROBA2 The PROBA21 mission has been launched on 2nd November2009 with a Rockot launcher in a sun-synchronous orbit at an altitude of 725 km.