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Key and Driving Requirements for the Juno Payload Suite of Instruments
Key and Driving Requirements for the Juno Payload Suite of Instruments Randy Dodge1 and Mark A. Boyles2 Jet Propulsion Laboratory-California Institute of Technology, Pasadena, CA, 91109-8099 Chuck E. Rasbach3 Lockheed Martin-Space System Company, Denver, CO, 80201 [Abstract] The Juno Mission was selected in the summer of 2005 via NASA’s New Frontiers competitive AO process (refer to http://www.nasa.gov/home/hqnews/2005/jun/HQ_05138_New_Frontiers_2.html). The Juno project is led by a Principle Investigator based at Southwest Research Institute [SwRI] in San Antonio, Texas, with project management based at the Jet Propulsion Laboratory [JPL] in Pasadena, California, while the Spacecraft design and Flight System integration are under contract to Lockheed Martin Space Systems Company [LM-SSC] in Denver, Colorado. The payload suite consists of a large number of instruments covering a wide spectrum of experimentation. The science team includes a lead Co-Investigator for each one of the following experiments: A Magnetometer experiment (consisting of both a FluxGate Magnetometer (FGM) built at Goddard Space Flight Center [GSFC] and a Scalar Helium Magnetometer (SHM) built at JPL, a MicroWave Radiometer (MWR) also built at JPL, a Gravity Science experiment (GS) implemented via the telecom subsystem, two complementary particle instruments (Jovian Auroral Distribution Experiment, JADE developed by SwRI and Juno Energetic-particle Detector Instrument, JEDI from the Applied Physics Lab [APL]--JEDI and JADE both measure electrons and ions), an Ultraviolet Spectrometer (UVS) also developed at SwRI, and a radio and plasma (Waves) experiment (from the University of Iowa). In addition, a visible camera (JunoCam) is included in the payload to facilitate education and public outreach (designed & fabricated by Malin Space Science Systems [MSSS]). -
Book of Abstracts Ii Contents
2014 CAP Congress / Congrès de l’ACP 2014 Sunday, 15 June 2014 - Friday, 20 June 2014 Laurentian University / Université Laurentienne Book of Abstracts ii Contents An Analytic Mathematical Model to Explain the Spiral Structure and Rotation Curve of NGC 3198. .......................................... 1 Belle-II: searching for new physics in the heavy flavor sector ................ 1 The high cost of science disengagement of Canadian Youth: Reimagining Physics Teacher Education for 21st Century ................................. 1 What your advisor never told you: Education for the ’Real World’ ............. 2 Back to the Ionosphere 50 Years Later: the CASSIOPE Enhanced Polar Outflow Probe (e- POP) ............................................. 2 Changing students’ approach to learning physics in undergraduate gateway courses . 3 Possible Astrophysical Observables of Quantum Gravity Effects near Black Holes . 3 Supersymmetry after the LHC data .............................. 4 The unintentional irradiation of a live human fetus: assessing the likelihood of a radiation- induced abortion ...................................... 4 Using Conceptual Multiple Choice Questions ........................ 5 Search for Supersymmetry at ATLAS ............................. 5 **WITHDRAWN** Monte Carlo Field-Theoretic Simulations for Melts of Diblock Copoly- mer .............................................. 6 Surface tension effects in soft composites ........................... 6 Correlated electron physics in quantum materials ...................... 6 The -
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................................. -
Accessing Pds Data in Pipeline Processing and Web Sites Through Pds Geosciences Orbital Data Explorer’S Web-Based Api (Rest) Interface
45th Lunar and Planetary Science Conference (2014) 1026.pdf ACCESSING PDS DATA IN PIPELINE PROCESSING AND WEB SITES THROUGH PDS GEOSCIENCES ORBITAL DATA EXPLORER’S WEB-BASED API (REST) INTERFACE. K. J. Bennett, J. Wang, D. Scholes, Washington University in St. Louis, 1 Brookings Drive, Campus Box 1169, St. Louis, Missouri, 63130, {bennett, wang, sholes}@wunder.wustl.edu. Introduction: The Orbital Data Explorer (ODE) is tem (RSS). a web-based search tool (http://ode.rsl.wustl.edu) de- High Resolution Stereo Camera (HRSC), Mars Advanced Radar for Subsurface and Iono- veloped at NASA’s Planetary Data System’s (PDS) sphere Sounding (MARSIS), OMEGA Geosciences Node (http://pds-geosciences.wustl.edu/). Mars Express (Observatoire Mineralogie, Eau, Glaces, Through ODE, users can search, browse, and download Activite) Visible and Infrared Mineralogical a wide range of PDS Mars, Moon, Mercury, and Venus Mapping Spectrometer, and Planetary Fourier Spectrometer (PFS). data ([1,2,3,4]). Mars Orbiter Laser Altimeter (MOLA), and Mars Global In the fall of 2012, the Geosciences node intro- MOC Narrow Angle (NA) and Wide Angle Surveyor (MGS) duced a simple web-based API that allows non-PDS (WA) cameras. Gamma Ray Spectrometer (GRS) and Thermal web and processing tools to search for PDS products, Odyssey Emission Imaging System (THEMIS) obtain meta-data about those products, and download Viking Orbiter Visual Imaging Subsystem Camera A/B the products stored in ODE’s meta-data database. The Gamma Ray Spectrometer (GRS), Radio Sci- first version is now used by several teams in periodic MESSENGER ence Subsystem (RSS), Neutron Spectrometer processing and web sites. -
Abstracts of the 50Th DDA Meeting (Boulder, CO)
Abstracts of the 50th DDA Meeting (Boulder, CO) American Astronomical Society June, 2019 100 — Dynamics on Asteroids break-up event around a Lagrange point. 100.01 — Simulations of a Synthetic Eurybates 100.02 — High-Fidelity Testing of Binary Asteroid Collisional Family Formation with Applications to 1999 KW4 Timothy Holt1; David Nesvorny2; Jonathan Horner1; Alex B. Davis1; Daniel Scheeres1 Rachel King1; Brad Carter1; Leigh Brookshaw1 1 Aerospace Engineering Sciences, University of Colorado Boulder 1 Centre for Astrophysics, University of Southern Queensland (Boulder, Colorado, United States) (Longmont, Colorado, United States) 2 Southwest Research Institute (Boulder, Connecticut, United The commonly accepted formation process for asym- States) metric binary asteroids is the spin up and eventual fission of rubble pile asteroids as proposed by Walsh, Of the six recognized collisional families in the Jo- Richardson and Michel (Walsh et al., Nature 2008) vian Trojan swarms, the Eurybates family is the and Scheeres (Scheeres, Icarus 2007). In this theory largest, with over 200 recognized members. Located a rubble pile asteroid is spun up by YORP until it around the Jovian L4 Lagrange point, librations of reaches a critical spin rate and experiences a mass the members make this family an interesting study shedding event forming a close, low-eccentricity in orbital dynamics. The Jovian Trojans are thought satellite. Further work by Jacobson and Scheeres to have been captured during an early period of in- used a planar, two-ellipsoid model to analyze the stability in the Solar system. The parent body of the evolutionary pathways of such a formation event family, 3548 Eurybates is one of the targets for the from the moment the bodies initially fission (Jacob- LUCY spacecraft, and our work will provide a dy- son and Scheeres, Icarus 2011). -
Chapter 2 Tests of Magnetometer/Sun-Sensor Orbit Determination Using Flight Data*
Chapter 2 Tests of Magnetometer/Sun-Sensor Orbit Determination Using Flight Data* 2.1 Introduction Orbit determination is an old topic in celestial mechanics and is an essential part of satellite navigation. Traditional ground-based tracking methods that use range and range-rate measurements can provide an orbit accuracy as good as a few centimeters1. Autonomous orbit determination using only onboard measurements can be a requirement of military satellites in order to guarantee independence from ground facilities2. The rapid increase in the number of satellites also increases the need for autonomous navigation because of bottlenecks in ground tracking facilities3. A filter that uses magnetometer measurements provides one possible means of doing autonomous orbit determination. This idea was first introduced by Psiaki and Martel4 and has been tested by a number of researchers since then3,5-9. Magnetometers fly on most spacecraft (S/C) for attitude determination and control purposes. Therefore, successful autonomous orbit determination using magnetometer measurements can make the integration of attitude and orbit determination possible and lead to reduced mission costs. Although magnetometer-based autonomous orbit determination is unlikely to have better accuracy than ground-based tracking, a magnetometer-based system could be applied to a mission that does not need the accuracy of ground-station tracking. The Tropical Rainfall Measurement Mission * This chapter is from the published paper: Hee Jung and Mark L. Psiaki, “Tests of Magnetometer/Sun-Sensor Orbit Determination Using Flight Data,” Journal of Guidance, Control, and Dynamics, Volume 25, Number 3, pp. 582-590. [© 2002. The American Institute of Aeronautics and Astronautics, Inc]. 8 9 (TRMM), for example, requires 40 km position accuracy. -
Juno Magnetometer (MAG) Standard Product Data Record and Archive Volume Software Interface Specification
Juno Magnetometer Juno Magnetometer (MAG) Standard Product Data Record and Archive Volume Software Interface Specification Preliminary March 6, 2018 Prepared by: Jack Connerney and Patricia Lawton Juno Magnetometer MAG Standard Product Data Record and Archive Volume Software Interface Specification Preliminary March 6, 2018 Approved: John E. P. Connerney Date MAG Principal Investigator Raymond J. Walker Date PDS PPI Node Manager Concurrence: Patricia J. Lawton Date MAG Ground Data System Staff 2 Table of Contents 1 Introduction ............................................................................................................................. 1 1.1 Distribution list ................................................................................................................... 1 1.2 Document change log ......................................................................................................... 2 1.3 TBD items ........................................................................................................................... 3 1.4 Abbreviations ...................................................................................................................... 4 1.5 Glossary .............................................................................................................................. 6 1.6 Juno Mission Overview ...................................................................................................... 7 1.7 Software Interface Specification Content Overview ......................................................... -
The Cassini Ion and Neutral Mass Spectrometer (Inms) Investigation
THE CASSINI ION AND NEUTRAL MASS SPECTROMETER (INMS) INVESTIGATION 1, 2 3 4 J. H. WAITE ∗, JR., W. S. LEWIS ,W.T. KASPRZAK ,V.G. ANICICH , B. P. BLOCK1,T.E. CRAVENS5,G.G. FLETCHER1,W.-H. IP6,J.G. LUHMANN7, R. L. MCNUTT8,H.B. NIEMANN3,J.K.PAREJKO1,J.E. RICHARDS3, R. L. THORPE2, E. M. WALTER1 and R. V. YELLE9 1University of Michigan, Ann Arbor, MI, U.S.A. 2Southwest Research Institute, San Antonio, TX, U.S.A. 3NASA Goddard Space Flight Center, Greenbelt, MD, U.S.A. 4NASA Jet Propulsion Laboratory, Pasadena, CA, U.S.A. 5University of Kansas, Lawrence, KS, U.S.A. 6National Central University, Chung-Li, Taiwan 7University of California, Berkeley, CA, U.S.A. 8Johns Hopkins University Applied Physics Laboratory, Laurel, MD, U.S.A. 9University of Arizona, Flagstaff, AZ, U.S.A. (∗Author for correspondence, E-mail: [email protected]) (Received 13 August 1998; Accepted in final form 17 February 2004) Abstract. The Cassini Ion and Neutral Mass Spectrometer (INMS) investigation will determine the mass composition and number densities of neutral species and low-energy ions in key regions of the Saturn system. The primary focus of the INMS investigation is on the composition and structure of Titan’s upper atmosphere and its interaction with Saturn’s magnetospheric plasma. Of particular interest is the high-altitude region, between 900 and 1000 km, where the methane and nitrogen photochemistry is initiated that leads to the creation of complex hydrocarbons and nitriles that may eventually precipitate onto the moon’s surface to form hydrocarbon–nitrile lakes or oceans. -
In-Orbit Aerodynamic Coefficient Measurements Using SOAR
In-Orbit Aerodynamic Coefficient Measurements using SOAR (Satellite for Orbital Aerodynamics Research) N.H. Crispa,, P.C.E. Robertsa, S. Livadiottia, A. Macario Rojasa, V.T.A. Oikoa, S. Edmondsona, S.J. Haigha, B.E.A. Holmesa, L.A. Sinpetrua, K.L. Smitha, J. Becedasb, R.M. Dom´ınguezb, V. Sulliotti-Linnerb, S. Christensenc, J. Nielsenc, M. Bisgaardc, Y-A. Chand, S. Fasoulasd, G.H. Herdrichd, F. Romanod, C. Traubd, D. Garc´ıa-Almi~nanae, S. Rodr´ıguez-Donairee, M. Suredae, D. Katariaf, B. Belkouchig, A. Conteg, S. Seminarig, R. Villaing aThe University of Manchester, Oxford Rd, Manchester, M13 9PL, United Kingdom bElecnor Deimos Satellite Systems, Calle Francia 9, 13500 Puertollano, Spain cGomSpace A/S, Langagervej 6, 9220 Aalborg East, Denmark dInstitute of Space Systems (IRS), University of Stuttgart, Pfaffenwaldring 29, 70569 Stuttgart, Germany eUPC-BarcelonaTECH, Carrer de Colom 11, 08222 Terrassa, Barcelona, Spain fMullard Space Science Laboratory, University College London, Holmbury St. Mary, Dorking, RH5 6NT, United Kingdom gEuroconsult, 86 Boulevard de S´ebastopol, 75003 Paris, France Abstract The Satellite for Orbital Aerodynamics Research (SOAR) is a CubeSat mission, due to be launched in 2021, to investigate the interaction between different materials and the atmospheric flow regime in very low Earth orbits (VLEO). Improving knowledge of the gas-surface interactions at these altitudes and identification of novel materials that can minimise drag or improve aerodynamic control are important for the design of future spacecraft that can operate in lower altitude orbits. Such satellites may be smaller and cheaper to develop or can provide improved Earth observation data or communications link-budgets and latency. -
Planet Mars III 28 March- 2 April 2010 POSTERS: ABSTRACT BOOK
Planet Mars III 28 March- 2 April 2010 POSTERS: ABSTRACT BOOK Recent Science Results from VMC on Mars Express Jonathan Schulster1, Hannes Griebel2, Thomas Ormston2 & Michel Denis3 1 VCS Space Engineering GmbH (Scisys), R.Bosch-Str.7, D-64293 Darmstadt, Germany 2 Vega Deutschland Gmbh & Co. KG, Europaplatz 5, D-64293 Darmstadt, Germany 3 Mars Express Spacecraft Operations Manager, OPS-OPM, ESA-ESOC, R.Bosch-Str 5, D-64293, Darmstadt, Germany. Mars Express carries a small Visual Monitoring Camera (VMC), originally to provide visual telemetry of the Beagle-2 probe deployment, successfully release on 19-December-2003. The VMC comprises a small CMOS optical camera, fitted with a Bayer pattern filter for colour imaging. The camera produces a 640x480 pixel array of 8-bit intensity samples which are recoded on ground to a standard digital image format. The camera has a basic command interface with almost all operations being performed at a hardware level, not featuring advanced features such as patchable software or full data bus integration as found on other instruments. In 2007 a test campaign was initiated to study the possibility of using VMC to produce full disc images of Mars for outreach purposes. An extensive test campaign to verify the camera’s capabilities in-flight was followed by tuning of optimal parameters for Mars imaging. Several thousand images of both full- and partial disc have been taken and made immediately publicly available via a web blog. Due to restrictive operational constraints the camera cannot be used when any other instrument is on. Most imaging opportunities are therefore restricted to a 1 hour period following each spacecraft maintenance window, shortly after orbit apocenter. -
The Magsat Scalar Magnetometer
WINFIELD H. FARTHING THE MAGSAT SCALAR MAGNETOMETER The Magsat scalar magnetometer is derived from optical pumping magnetometers flown on the Orbiting Geophysical Observatories. The basic sensor, a cross-coupled arrangement of absorption cells, photodiodes, and amplifiers, oscillates at the Larmor frequency of atomic moments pre cessing about the ambient field direction. The Larmor frequency output is accumulated digitally and stored for transfer to the spacecraft telemetry stream. In orbit the instrument has met its principal objective of calibrating the vector magnetometer and providing scalar field data. INTRODUCTION (nT), was therefore used even though, from the The cesium vapor optical pumping magnetometer standpoint of resonance line width, it is the poorest used on Magsat is derived from the rubidium mag of the three. In the interim between OGO and netometers flown on the Orbiting Geophysical Ob Magsat, cesium-I33 came to be the most commonly servatories (OGO) between 1964 and 1971. The used isotope in alkali vapor magnetometry and was Polar Orbiting Geophysical Observatories (Pogo) thus the natural selection for Magsat. used rubidium-85 optical pumping magnetometers, ) while those on the Eccentric Orbiting Geophysical PRINCIPLE OF SENSOR OPERATION Observatories (Eogo) used the slightly higher gyro The alkali vapor magnetometer is based on the magnetic ratio of rubidium-87. phenomenon of optical pumping reported by Data generated by the Pogo instruments pro Dehmelt4 in 1957. The development of practical vided the principal data base for the U.S. input to magnetometers followed rapidly, evolving in one the World Magnetic Survey, 2 an international co form finally to the dual-cell, self-oscillating magne operative effort to survey and model the geomag tometerS shown in Fig. -
ODE Overview Web-Based
Checkout Version 2.0 K. J. Bennett, J. Wang, and D. Scholes, Washington University in St. Louis, 1 Brookings Drive, Campus Box 1169, St. Louis, Missouri, 63130, {bennett, wang , scholes}@wunder.wustl.edu Beta! ODE Overview http://ode.rsl.wustl.edu/ Planet Mission Instrument Shallow Radar (SHARAD), Compact Reconnaissance Imaging Spectrometer for Mars (CRISM), High Resolution Imaging Science Experiment (HiRISE), Context MRO Orbital Data Explorer Imager (CTX), Mars Color Imager (MARCI), Mars Climate Sounder (MCS), and Radio Science Subsystem (RSS). (ODE) was developed by RETRIEVE and High Resolution Stereo Camera (HRSC), Mars Advanced Radar for Subsurface and NASA’s Planetary Data View Products ESA’s Mars Ionosphere Sounding (MARSIS), OMEGA (Observatoire Mineralogie, Eau, Glaces, System (PDS)’s Mars Express Activite) Visible and Infrared Mineralogical Mapping Spectrometer, and Planetary Fourier Spectrometer (PFS). Geosciences Node. ODE Mars Orbiter Laser Altimeter (MOLA), and Mars Orbiter Camera (MOC) Narrow MGS provides web-based Angle and Wide Angle cameras. functions to search, Odyssey Thermal Emission Imaging System (THEMIS), Gamma Ray Spectrometer (GRS). retrieve, and download SEARCH for Viking Orbiter 1/2 Visual Imaging Subsystem Camera A/B Products data from multiple GRS, RSS, Neutron Spectrometer (NS), X-Ray Spectrometer (XRS), Mercury Atmospheric and Surface Composition Spectrometer (MASCS), Mercury Laser Mercury MESSENGER missions and instruments Altimeter (MLA), and Mercury Dual Imaging System (MDIS) Narrow Angle in the rapidly