Planetary Science Data Dictionary Document
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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................................. -
Analysis of Planetary and Solar-Induced Perturbations on Trans-Martian Trajectory of Mars Missions Before and After Mars Orbit Insertion
Analysis of planetary and solar-induced perturbations on trans-Martian trajectory of Mars missions before and after Mars orbit insertion V U J Nwankwo1 and S K Chakrabarti1,2* 1S N Bose National Centre for Basic Sciences, Kolkata 700 098, West Bengal, India 2Indian Center for Space Physics, Kolkata 700 084, West Bengal, India Abstract: Interplanetary missions are susceptible to gravitational and nongravitational perturbing forces at every tra- jectory phase, assuming, of course, that the man made rockets and thrusters work as expected. These forces are mainly due to planetary and solar-forcing-induced perturbations during geocentric, heliocentric and Martian trajectories, and before orbit insertion. In this study, we review and/or analyze Mars orbiters mission associated perturbing forces and their possible impacts before Mars Orbit Insertion viz Earth’s oblateness, Third body (solar and lunar), solar radiation pressure, solar energetic radiation environment and atmospheric drag forces. We also model the significance of atmospheric drag force on Mangalyaan Mars orbiter mission, as a function of appropriate space environmental parameters during its 28 days in Earth’s orbit (around and during perigee passage), 300 days of heliocentric and 100 days of Martian trajectory. We have found that for a total perigee height boost of about 250 km, the cumulative orbit decay can be approximately 720 m. The approximate altitude variation could be up to 158 m with respect to the sun during 300 days of interplanetary journey toward Mars. After Mars orbit insertion, the total decay experienced by the spacecraft could be up to 701 m with decay rate of up to 9 m/day during 100 days of Martian trajectory, based on Mars–Earth atmosphere density ratio. -
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). -
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. -
Theoretical and Experimental Investigation of Hall Thruster Miniaturization by Noah Zachary Warner
Theoretical and Experimental Investigation of Hall Thruster Miniaturization by Noah Zachary Warner S.B., Aeronautics and Astronautics, Massachusetts Institute of Technology, 2001 S.M., Aeronautics and Astronautics, Massachusetts Institute of Technology, 2003 SUBMITTED TO THE DEPARTMENT OF AERONAUTICS AND ASTRONAUTICS IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF DOCTOR OF PHILOSOPHY AT THE MASSACHUSETTS INSTITUTE OF TECHNOLOGY JUNE 2007 © 2007 Massachusetts Institute of Technology. All rights reserved. Signature of Author . Department of Aeronautics and Astronautics May 25, 2007 Certified by . Manuel Martínez-Sánchez Professor of Aeronautics and Astronautics Thesis Supervisor Certified by . Jack Kerrebrock Professor Emeritus of Aeronautics and Astronautics Certified by . Oleg Batishchev Principal Research Scientist in Aeronautics and Astronautics Certified by . Vladimir Hruby President, Busek Company, Inc. Accepted by . Jaime Peraire Professor of Aeronautics and Astronautics Chair, Committee on Graduate Students 2 Theoretical and Experimental Investigation of Hall Thruster Miniaturization by Noah Zachary Warner Submitted to the Department of Aeronautics and Astronautics on May 25, 2007 in partial fulfillment of the requirements for the degree of Doctor of Philosophy in Aeronautics and Astronautics in the field of Space Propulsion ABSTRACT Interest in small-scale space propulsion continues to grow with the increasing number of small satellite missions, particularly in the area of formation flight. Miniaturized Hall thrusters have been identified as a candidate for lightweight, high specific impulse propul- sion systems that can extend mission lifetime and payload capability. A set of scaling laws was developed that allows the dimensions and operating parameters of a miniaturized Hall thruster to be determined from an existing, technologically mature baseline design. -
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 -
Earth to Mars Areostationary Mission Optimization Analysis
Earth to Mars areostationary mission optimization analysis M. M. Sánchez-García, G. Barderas and P. Romero Instituto de Matemática Interdisciplinar. U. D. Astronomía y Geodesia, Facultad de Ciencias Matemáticas, Universidad Complutense de Madrid, Madrid, Spain ([email protected], [email protected], [email protected]) Abstract Mars has become one of the priorities in the planetary exploration programs. The analysis of space mission costs has become a key factor in mission planning. The determination of optimal trajectories aiming to lower costs in terms of impulses allows for more massive payloads to be transported at a minimum energy cost. Areostationary satellites are considered the most efficient and robust candidates to satisfy the control needs of the missions to Mars. Mars Areostationary Relay Satellites providing continuous coverage of a specific region of Mars are being considered for a near future. In this work, we analyze the optimization of an areostationary mission. We first determine the launch and arrival dates for an optimal minimum energy Earth-Mars transfer trajectory. Then, the minimum thrust maneuvers to capture the spacecraft from the hyperbolic arrival trajectory to Mars and place it in the areostationary orbit are analyzed. XIV.0 Reunión Científica 13-15 julio 2020 Context of the research: Previous studies The number of missions to Mars has increased over the last years, particularly robotic missions which need to be tele- commanded from the Earth. The need to control the different missions in Mars in almost real time with a relay system that provides continuous coverage of a specific region has been proposed by several authors such as Edwards et al. -
Saturn Satellites As Seen by Cassini Mission
Saturn satellites as seen by Cassini Mission A. Coradini (1), F. Capaccioni (2), P. Cerroni(2), G. Filacchione(2), G. Magni,(2) R. Orosei(1), F. Tosi(1) and D. Turrini (1) (1)IFSI- Istituto di Fisica dello Spazio Interplanetario INAF Via fosso del Cavaliere 100- 00133 Roma (2)IASF- Istituto di Astrofisica Spaziale e Fisica Cosmica INAF Via fosso del Cavaliere 100- 00133 Roma Paper to be included in the special issue for Elba workshop Table of content SATURN SATELLITES AS SEEN BY CASSINI MISSION ....................................................................... 1 TABLE OF CONTENT .................................................................................................................................. 2 Abstract ....................................................................................................................................................................... 3 Introduction ................................................................................................................................................................ 3 The Cassini Mission payload and data ......................................................................................................................... 4 Satellites origin and bulk characteristics ...................................................................................................................... 6 Phoebe ............................................................................................................................................................................... -
ESA Space Weather STUDY Alcatel Consortium
ESA Space Weather STUDY Alcatel Consortium SPACE Weather Parameters WP 2100 Version V2.2 1 Aout 2001 C. Lathuillere, J. Lilensten, M. Menvielle With the contributions of T. Amari, A. Aylward, D. Boscher, P. Cargill and S.M. Radicella 1 2 1 INTRODUCTION........................................................................................................................................ 5 2 THE MODELS............................................................................................................................................. 6 2.1 THE SUN 6 2.1.1 Reconstruction and study of the active region static structures 7 2.1.2 Evolution of the magnetic configurations 9 2.2 THE INTERPLANETARY MEDIUM 11 2.3 THE MAGNETOSPHERE 13 2.3.1 Global magnetosphere modelling 14 2.3.2 Specific models 16 2.4 THE IONOSPHERE-THERMOSPHERE SYSTEM 20 2.4.1 Empirical and semi-empirical Models 21 2.4.2 Physics-based models 23 2.4.3 Ionospheric profilers 23 2.4.4 Convection electric field and auroral precipitation models 25 2.4.5 EUV/UV models for aeronomy 26 2.5 METEOROIDS AND SPACE DEBRIS 27 2.5.1 Space debris models 27 2.5.2 Meteoroids models 29 3 THE PARAMETERS ................................................................................................................................ 31 3.1 THE SUN 35 3.2 THE INTERPLANETARY MEDIUM 35 3.3 THE MAGNETOSPHERE 35 3.3.1 The radiation belts 36 3.4 THE IONOSPHERE-THERMOSPHERE SYSTEM 36 4 THE OBSERVATIONS ........................................................................................................................... -
'.';King Navigation
1980012912 -' JPL PUBLICATION 78-38 '.';king Navigation W. J. O'Neil, R. P. Rudd, D. L. Farless, C. E. Hildebrand, R. T. Mitchell, K. H. Rourke, et al. Jet Propulsion Laboratory E. A. Euler Martin Marietta Aerospace (N,%SA-C[_-l_,2517) VIklt_G ._AVIGA'IION (Jet t, u0-213_-_ : Pcopulsio[, L,_c.) 322 p _lC Alq/MF A01 _:d[,U CSCL Z2.t; hd0-_|4dj •_ [J_;c ]. a_ GJ/15 l,t7 5 'JJ ± November 15, 1979 _',r:.'> ;Y/l&_',,/I_cC7.'/',_/, : < X* ",t ,'" t National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Pasadena, California # 1980012912-002 JPL PUBLICATION 78-38 Viking Navigation W. J. O'Neil, R. P. Rudd, D. L. Farless, C. E. Hildebrand, R. T. Mitchell, K. H. Rourke, et al. Jet Propulsion Laboratory E. A. Euler Martin Marietta Aerospace November 15, 1979 National Aeronautics and Space Administration Jet Propulsion Laboratory : California Institute of Technology Pasadena, California 1980012912-003 The research descnbed bnth_s pubhcat_onwas camed out by the Jet Propulsion Laboratory, Cahforn_aInstitute of Technology, under NASA Contract No NAS7-100 i 1980012912-004 Abstract NASA soft-landed two Viking spacecraft on Mars in the summer t,f 1976. These were the free world's first landings on another planet. This report provides a final, comprehensive description of the navigation of the Viking spacecraft throughout their flight from Earth launch to Mars landing. The flight path design, actual int]lght control, and postflight reconstruction ale discussed in detail. The report Is comprised of an introductory chapter followed by five Olapters which essenually correspond to the organization of the Viking navigation operations, namely, Trajectory Descriptton, Interplanetary Orbit Determination, Satellite Orbit Determination, ._haneuver Analysis, and Lander Flight Path Analysis. -
Cassini-Huygens
High Ambitions for an Outstanding Planetary Mission: Cassini-Huygens Composite image of Titan in ultraviolet and infrared wavelengths taken by Cassini’s imaging science subsystem on 26 October. Red and green colours show areas where atmospheric methane absorbs light and reveal a brighter (redder) northern hemisphere. Blue colours show the high atmosphere and detached hazes (Courtesy of JPL /Univ. of Arizona) Cassini-Huygens Jean-Pierre Lebreton1, Claudio Sollazzo2, Thierry Blancquaert13, Olivier Witasse1 and the Huygens Mission Team 1 ESA Directorate of Scientific Programmes, ESTEC, Noordwijk, The Netherlands 2 ESA Directorate of Operations and Infrastructure, ESOC, Darmstadt, Germany 3 ESA Directorate of Technical and Quality Management, ESTEC, Noordwijk, The Netherlands Earl Maize, Dennis Matson, Robert Mitchell, Linda Spilker Jet Propulsion Laboratory (NASA/JPL), Pasadena, California Enrico Flamini Italian Space Agency (ASI), Rome, Italy Monica Talevi Science Programme Communication Service, ESA Directorate of Scientific Programmes, ESTEC, Noordwijk, The Netherlands assini-Huygens, named after the two celebrated scientists, is the joint NASA/ESA/ASI mission to Saturn Cand its giant moon Titan. It is designed to shed light on many of the unsolved mysteries arising from previous observations and to pursue the detailed exploration of the gas giants after Galileo’s successful mission at Jupiter. The exploration of the Saturnian planetary system, the most complex in our Solar System, will help us to make significant progress in our understanding