Juno Observations of Large-Scale Compressions of Jupiter's Dawnside
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Pressure Balance at the Magnetopause: Experimental Studies
Pressure balance at the magnetopause: Experimental studies A. V. Suvorova1,2 and A. V. Dmitriev3,2 1Center for Space and Remote Sensing Research, National Central University, Jhongli, Taiwan 2Skobeltsyn Institute of Nuclear Physics Moscow State University, Moscow, Russia 3Institute of Space Sciences, National Central University, Chung-Li, Taiwan Abstract The pressure balance at the magnetopause is formed by magnetic field and plasma in the magnetosheath, on one side, and inside the magnetosphere, on the other side. In the approach of dipole earth’s magnetic field configuration and gas-dynamics solar wind flowing around the magnetosphere, the pressure balance predicts that the magnetopause distance R depends on solar wind dynamic pressure Pd as a power low R ~ Pdα, where the exponent α=-1/6. In the real magnetosphere the magnetic filed is contributed by additional sources: Chapman-Ferraro current system, field-aligned currents, tail current, and storm-time ring current. Net contribution of those sources depends on particular magnetospheric region and varies with solar wind conditions and geomagnetic activity. As a result, the parameters of pressure balance, including power index α, depend on both the local position at the magnetopause and geomagnetic activity. In addition, the pressure balance can be affected by a non-linear transfer of the solar wind energy to the magnetosheath, especially for quasi-radial regime of the subsolar bow shock formation proper for the interplanetary magnetic field vector aligned with the solar wind plasma flow. A review of previous results The pressure balance states that the pressure of the flowing around solar wind plasma is balanced at the magnetopause by the pressure inside the magnetosphere [e.g. -
Marina Galand
Thermosphere - Ionosphere - Magnetosphere Coupling! Canada M. Galand (1), I.C.F. Müller-Wodarg (1), L. Moore (2), M. Mendillo (2), S. Miller (3) , L.C. Ray (1) (1) Department of Physics, Imperial College London, London, U.K. (2) Center for Space Physics, Boston University, Boston, MA, USA (3) Department of Physics and Astronomy, University College London, U.K. 1." Energy crisis at giant planets Credit: NASA/JPL/Space Science Institute 2." TIM coupling Cassini/ISS (false color) 3." Modeling of IT system 4." Comparison with observaons Cassini/UVIS 5." Outstanding quesAons (Pryor et al., 2011) SATURN JUPITER (Gladstone et al., 2007) Cassini/UVIS [UVIS team] Cassini/VIMS (IR) Credit: J. Clarke (BU), NASA [VIMS team/JPL, NASA, ESA] 1. SETTING THE SCENE: THE ENERGY CRISIS AT THE GIANT PLANETS THERMAL PROFILE Exosphere (EARTH) Texo 500 km Key transiLon region Thermosphere between the space environment and the lower atmosphere Ionosphere 85 km Mesosphere 50 km Stratosphere ~ 15 km Troposphere SOLAR ENERGY DEPOSITION IN THE UPPER ATMOSPHERE Solar photons ion, e- Neutral Suprathermal electrons B ion, e- Thermal e- Ionospheric Thermosphere Ne, Nion e- heang Te P, H * + Airglow Neutral atmospheric Exothermic reacAons heang IS THE SUN THE MAIN ENERGY SOURCE OF PLANERATY THERMOSPHERES? W Main energy source: UV solar radiaon Main energy source? EartH Outer planets CO2 atmospHeres Exospheric temperature (K) [aer Mendillo et al., 2002] ENERGY CRISIS AT THE GIANT PLANETS Observed values at low to mid-latudes solsce equinox Modeled values (Sun only) [Aer -
MARS SCIENCE LABORATORY ORBIT DETERMINATION Gerhard L. Kruizinga(1)
MARS SCIENCE LABORATORY ORBIT DETERMINATION Gerhard L. Kruizinga(1), Eric D. Gustafson(2), Paul F. Thompson(3), David C. Jefferson(4), Tomas J. Martin-Mur(5), Neil A. Mottinger(6), Frederic J. Pelletier(7), and Mark S. Ryne(8) (1-8)Jet Propulsion Laboratory, California Institute of Technology, 4800 Oak Grove Drive, Pasadena, California 91109, +1-818-354-7060, fGerhard.L.Kruizinga, edg, Paul.F.Thompson, David.C.Jefferson, tmur, Neil.A.Mottinger, Fred.Pelletier, [email protected] Abstract: This paper describes the orbit determination process, results and filter strategies used by the Mars Science Laboratory Navigation Team during cruise from Earth to Mars. The new atmospheric entry guidance system resulted in an orbit determination paradigm shift during final approach when compared to previous Mars lander missions. The evolving orbit determination filter strategies during cruise are presented. Furthermore, results of calibration activities of dynamical models are presented. The atmospheric entry interface trajectory knowledge was significantly better than the original requirements, which enabled the very precise landing in Gale Crater. Keywords: Mars Science Laboratory, Curiosity, Mars, Navigation, Orbit Determination 1. Introduction On August 6, 2012, the Mars Science Laboratory (MSL) and the Curiosity rover successful performed a precision landing in Gale Crater on Mars. A crucial part of the success was orbit determination (OD) during the cruise from Earth to Mars. The OD process involves determining the spacecraft state, predicting the future trajectory and characterizing the uncertainty associated with the predicted trajectory. This paper describes the orbit determination process, results, and unique challenges during the final approach phase. -
A Future Mars Environment for Science and Exploration
Planetary Science Vision 2050 Workshop 2017 (LPI Contrib. No. 1989) 8250.pdf A FUTURE MARS ENVIRONMENT FOR SCIENCE AND EXPLORATION. J. L. Green1, J. Hol- lingsworth2, D. Brain3, V. Airapetian4, A. Glocer4, A. Pulkkinen4, C. Dong5 and R. Bamford6 (1NASA HQ, 2ARC, 3U of Colorado, 4GSFC, 5Princeton University, 6Rutherford Appleton Laboratory) Introduction: Today, Mars is an arid and cold world of existing simulation tools that reproduce the physics with a very thin atmosphere that has significant frozen of the processes that model today’s Martian climate. A and underground water resources. The thin atmosphere series of simulations can be used to assess how best to both prevents liquid water from residing permanently largely stop the solar wind stripping of the Martian on its surface and makes it difficult to land missions atmosphere and allow the atmosphere to come to a new since it is not thick enough to completely facilitate a equilibrium. soft landing. In its past, under the influence of a signif- Models hosted at the Coordinated Community icant greenhouse effect, Mars may have had a signifi- Modeling Center (CCMC) are used to simulate a mag- cant water ocean covering perhaps 30% of the northern netic shield, and an artificial magnetosphere, for Mars hemisphere. When Mars lost its protective magneto- by generating a magnetic dipole field at the Mars L1 sphere, three or more billion years ago, the solar wind Lagrange point within an average solar wind environ- was allowed to directly ravish its atmosphere.[1] The ment. The magnetic field will be increased until the lack of a magnetic field, its relatively small mass, and resulting magnetotail of the artificial magnetosphere its atmospheric photochemistry, all would have con- encompasses the entire planet as shown in Figure 1. -
Observations of Solar Wind Penetration Into the Earth's Magnetosphere: the Plasma Mantle
ENNIO R. SANCHEZ, CHING-I. MENG, and PATRICK T. NEWELL OBSERVATIONS OF SOLAR WIND PENETRATION INTO THE EARTH'S MAGNETOSPHERE: THE PLASMA MANTLE The large database provided by the continuous coverage of the Defense Meteorological Satellite Pro gram polar orbiting satellites constitutes an important source of information on particle precipitation in the ionosphere. This information can be used to monitor and map the Earth's magnetosphere (the cavity around the Earth that forms as the stream of particles and magnetic field ejected from the Sun, known as the solar wind, encounters the Earth's magnetic field) and for a large variety of statistical studies of its morphology and dynamics. The boundary between the magnetosphere and the solar wind is pre sumably open in some places and at some times, thus allowing the direct entry of solar-wind plasma into the magnetosphere through a boundary layer known as the plasma mantle. The preliminary results of a statistical study of the plasma-mantle precipitation in the ionosphere are presented. The first quan titative mapping of the ionospheric region where the plasma-mantle particles precipitate is obtained. INTRODUCTION Polar orbiting satellites are very useful platforms for studying the properties of the environment surrounding the Earth at distances well above the ionosphere. This article focuses on a description of the enormous poten tial of those platforms, especially when they are com bined with other means of measurement, such as ground-based stations and other satellites. We describe in some detail the first results of the kind of study for which the polar orbiting satellites are ideal instruments. -
Lessons Learned from the Juno Project
Lessons Learned from the Juno Project Presented by: William McAlpine Insoo Jun EJSM Instrument Workshop January 18‐20, 2010 © 2010 All rights reserved. Pre‐decisional, For Planning and Discussion Purposes Only Y‐1 Topics Covered • Radiation environment • Radiation control program • Radiation control program lessons learned Pre‐decisional, For Planning and Discussion Purposes Only Y‐2 Juno Radiation Environments Pre‐decisional, For Planning and Discussion Purposes Only Y‐3 Radiation Environment Comparison • Juno TID environment is about a factor of 5 less than JEO • Juno peak flux rate is about a factor of 3 above JEO Pre‐decisional, For Planning and Discussion Purposes Only Y‐4 Approach for Mitigating Radiation (1) • Assign a radiation control manager to act as a focal point for radiation related activities and issues across the Project early in the lifecycle – Requirements, EEE parts, materials, environments, and verification • Establish a radiation advisory board to address challenging radiation control issues • Hold external reviews for challenging radiation control issues • Establish a radiation control process that defines environments, defines requirements, and radiation requirements verification documentation • Design the mission trajectory to minimize the radiation exposure Pre‐decisional, For Planning and Discussion Purposes Only Y‐5 Approach for Mitigating Radiation (2) • Optimize shielding design to accommodate cumulative total ionizing dose and displacement damage dose and instantaneous charged particle fluxes near Perijove -
Ganymede–Induced Decametric Radio Emission: In-Situ
manuscript submitted to Geophysical Research Letters 1 Ganymede{induced decametric radio emission: in-situ 2 observations and measurements by Juno 1 1 2;3 4 5 3 C. K. Louis , P. Louarn , F. Allegrini , W. S. Kurth , J. R. Szalay 1 4 IRAP, Universit´ede Toulouse, CNRS, CNES, UPS, (Toulouse), France 2 5 Southwest Research Institute, San Antonio, Texas, USA 3 6 Department of Physics and Astronomy, University of Texas at San Antonio, San Antonio, Texas, USA 4 7 Department of Physics and Astronomy, University of Iowa, Iowa City, Iowa, USA 5 8 Department of Astrophysical Sciences, Princeton University, Princeton, New Jersey, USA 9 Key Points: 10 • First detailed wave/particle investigation of a Ganymede-induced decametric ra- 11 dio source using Juno/Waves and Juno/JADE instruments 12 • Confirmation that the emission is produced by a loss-cone-driven Cyclotron Maser 13 Instability 14 • Ganymede-induced radio emission is produced by electrons of ∼ 4-15 keV, at a ◦ ◦ 15 beaming angle [76 -83 ], and a frequency 1:005 − 1:021 × fce Corresponding author: C. K. Louis, [email protected] {1{ manuscript submitted to Geophysical Research Letters 16 Abstract 17 At Jupiter, part of the auroral radio emissions are induced by the Galilean moons 18 Io, Europa and Ganymede. Until now, they have been remotely detected, using ground- 19 based radio-telescopes or electric antennas aboard spacecraft. The polar trajectory of 20 the Juno orbiter allows the spacecraft to cross the magnetic flux tubes connected to these 21 moons, or their tail, and gives a direct measure of the characteristics of these decamet- 22 ric moon{induced radio emissions. -
Five Aerojet Boosters Set to Lift New Horizons Spacecraft
January 15, 2006 Five Aerojet Boosters Set to Lift New Horizons Spacecraft Aerojet Propulsion Will Support Both Launch Vehicle and Spacecraft for Mission to Pluto SACRAMENTO, Calif., Jan. 15 /PRNewswire/ -- Aerojet, a GenCorp Inc. (NYSE: GY) company, will provide five solid rocket boosters for the launch vehicle and a propulsion system for the spacecraft when a Lockheed Martin Atlas® V launches the Pluto New Horizons spacecraft January 17 from Cape Canaveral, AFB. The launch window opens at 1:24 p.m. EST on January 17 and extends through February 14. The New Horizons mission, dubbed by NASA as the "first mission to the last planet," will study Pluto and its moon, Charon, in detail during a five-month- long flyby encounter. Pluto is the solar system's most distant planet, averaging 3.6 billion miles from the sun. Aerojet's solid rocket boosters (SRBs), each 67-feet long and providing an average of 250,000 pounds of thrust, will provide the necessary added thrust for the New Horizons mission. The SRBs have flown in previous vehicle configurations using two and three boosters; this is the first flight utilizing the five boosters. Additionally, 12 Aerojet monopropellant (hydrazine) thrusters on the Atlas V Centaur upper stage will provide roll, pitch, and yaw control settling burns for the launch vehicle main engines. Aerojet also supplies 8 retro rockets for Atlas Centaur separation. Aerojet also provided the spacecraft propulsion system, comprised of a propellant tank, 16 thrusters and various other components, which will control pointing and navigation for the spacecraft on its journey and during encounters with Pluto- Charon and, as part of a possible extended mission, to more distant, smaller objects in the Kuiper Belt. -
Juno Spacecraft Description
Juno Spacecraft Description By Bill Kurth 2012-06-01 Juno Spacecraft (ID=JNO) Description The majority of the text in this file was extracted from the Juno Mission Plan Document, S. Stephens, 29 March 2012. [JPL D-35556] Overview For most Juno experiments, data were collected by instruments on the spacecraft then relayed via the orbiter telemetry system to stations of the NASA Deep Space Network (DSN). Radio Science required the DSN for its data acquisition on the ground. The following sections provide an overview, first of the orbiter, then the science instruments, and finally the DSN ground system. Juno launched on 5 August 2011. The spacecraft uses a deltaV-EGA trajectory consisting of a two-part deep space maneuver on 30 August and 14 September 2012 followed by an Earth gravity assist on 9 October 2013 at an altitude of 559 km. Jupiter arrival is on 5 July 2016 using two 53.5-day capture orbits prior to commencing operations for a 1.3-(Earth) year-long prime mission comprising 32 high inclination, high eccentricity orbits of Jupiter. The orbit is polar (90 degree inclination) with a periapsis altitude of 4200-8000 km and a semi-major axis of 23.4 RJ (Jovian radius) giving an orbital period of 13.965 days. The primary science is acquired for approximately 6 hours centered on each periapsis although fields and particles data are acquired at low rates for the remaining apoapsis portion of each orbit. Juno is a spin-stabilized spacecraft equipped for 8 diverse science investigations plus a camera included for education and public outreach. -
THEMIS Telescope Images Analysed for Space Weather Traces
EPSC Abstracts Vol. 14, EPSC2020-1022, 2020 https://doi.org/10.5194/epsc2020-1022 Europlanet Science Congress 2020 © Author(s) 2021. This work is distributed under the Creative Commons Attribution 4.0 License. THEMIS telescope images analysed for space weather traces Melinda Dósa1, Valeria Mangano2, Zsofia Bebesi1, Stefano Massetti2, Anna Milillo2, and Anna Görgei3 1Wigner Research Centre for Physics, Space Physics and Space Technology, Budapest, Hungary ([email protected]) 2INAF/IAPS, Istituto Nazionale di Astrofisica, Roma, Italy 3Eötvös Loránd University, Institute of Physics The THEMIS solar telescope operating on Tenerife (Canary islands) has observed Mercury’s Na exosphere along several campaigns since 2007. A dataset of images taken between 2009 and 2013 are analysed here in relation with propagated solar wind data. A small subset of the images shows a low level of correlation between Na-emission and solar wind dynamic pressure. The amount of data at present is not sufficient to make a clear statement on whether the correlation is a coincidence or can be explained by other factors (position of Mercury and Earth, solar activity, etc.). Nevertheless, the authors present a comprehensive study taking into account all possible factors. Sodium plays a special role in Mercury’s exosphere: due to its strong resonance line it has been observed and monitored by Earth-based telescopes for decades. Different and highly variable patterns of Na-emission have been identified, the most common and recurrent being the high latitude double-peak pattern [1]. It is clear that the exosphere is linked to the surface and influenced by the interstellar medium and the solar wind deviated by the magnetosphere, but the role and weight of the single processes are still under discussion [2]. -
Diffuse Electron Precipitation in Magnetosphere-Ionosphere- Thermosphere Coupling
EGU21-6342 https://doi.org/10.5194/egusphere-egu21-6342 EGU General Assembly 2021 © Author(s) 2021. This work is distributed under the Creative Commons Attribution 4.0 License. Diffuse electron precipitation in magnetosphere-ionosphere- thermosphere coupling Dong Lin1, Wenbin Wang1, Viacheslav Merkin2, Kevin Pham1, Shanshan Bao3, Kareem Sorathia2, Frank Toffoletto3, Xueling Shi1,4, Oppenheim Meers5, George Khazanov6, Adam Michael2, John Lyon7, Jeffrey Garretson2, and Brian Anderson2 1High Altitude Observatory, National Center for Atmospheric Research, Boulder CO, United States of America 2Applied Physics Laboratory, Johns Hopkins University, Laurel MD, USA 3Department of Physics and Astronomy, Rice University, Houston TX, USA 4Bradley Department of Electrical and Computer Engineering, Virginia Tech, Blacksburg VA, USA 5Astronomy Department, Boston University, Boston MA, USA 6Goddard Space Flight Center, NASA, Greenbelt MD, USA 7Department of Physics and Astronomy, Dartmouth College, Hanover NH, USA Auroral precipitation plays an important role in magnetosphere-ionosphere-thermosphere (MIT) coupling by enhancing ionospheric ionization and conductivity at high latitudes. Diffuse electron precipitation refers to scattered electrons from the plasma sheet that are lost in the ionosphere. Diffuse precipitation makes the largest contribution to the total precipitation energy flux and is expected to have substantial impacts on the ionospheric conductance and affect the electrodynamic coupling between the magnetosphere and ionosphere-thermosphere. -
Cmes, Solar Wind and Sun-Earth Connections: Unresolved Issues
CMEs, solar wind and Sun-Earth connections: unresolved issues Rainer Schwenn Max-Planck-Institut für Sonnensystemforschung, Katlenburg-Lindau, Germany [email protected] In recent years, an unprecedented amount of high-quality data from various spaceprobes (Yohkoh, WIND, SOHO, ACE, TRACE, Ulysses) has been piled up that exhibit the enormous variety of CME properties and their effects on the whole heliosphere. Journals and books abound with new findings on this most exciting subject. However, major problems could still not be solved. In this Reporter Talk I will try to describe these unresolved issues in context with our present knowledge. My very personal Catalog of ignorance, Updated version (see SW8) IAGA Scientific Assembly in Toulouse, 18-29 July 2005 MPRS seminar on January 18, 2006 The definition of a CME "We define a coronal mass ejection (CME) to be an observable change in coronal structure that occurs on a time scale of a few minutes and several hours and involves the appearance (and outward motion, RS) of a new, discrete, bright, white-light feature in the coronagraph field of view." (Hundhausen et al., 1984, similar to the definition of "mass ejection events" by Munro et al., 1979). CME: coronal -------- mass ejection, not: coronal mass -------- ejection! In particular, a CME is NOT an Ejección de Masa Coronal (EMC), Ejectie de Maså Coronalå, Eiezione di Massa Coronale Éjection de Masse Coronale The community has chosen to keep the name “CME”, although the more precise term “solar mass ejection” appears to be more appropriate. An ICME is the interplanetry counterpart of a CME 1 1.