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NASA's Lunar Atmosphere and Dust Environment Explorer (LADEE)
Geophysical Research Abstracts Vol. 13, EGU2011-5107-2, 2011 EGU General Assembly 2011 © Author(s) 2011 NASA’s Lunar Atmosphere and Dust Environment Explorer (LADEE) Richard Elphic (1), Gregory Delory (1,2), Anthony Colaprete (1), Mihaly Horanyi (3), Paul Mahaffy (4), Butler Hine (1), Steven McClard (5), Joan Salute (6), Edwin Grayzeck (6), and Don Boroson (7) (1) NASA Ames Research Center, Moffett Field, CA USA ([email protected]), (2) Space Sciences Laboratory, University of California, Berkeley, CA USA, (3) Laboratory for Atmospheric and Space Physics, University of Colorado, Boulder, CO USA, (4) NASA Goddard Space Flight Center, Greenbelt, MD USA, (5) LunarQuest Program Office, NASA Marshall Space Flight Center, Huntsville, AL USA, (6) Planetary Science Division, Science Mission Directorate, NASA, Washington, DC USA, (7) Lincoln Laboratory, Massachusetts Institute of Technology, Lexington MA USA Nearly 40 years have passed since the last Apollo missions investigated the mysteries of the lunar atmosphere and the question of levitated lunar dust. The most important questions remain: what is the composition, structure and variability of the tenuous lunar exosphere? What are its origins, transport mechanisms, and loss processes? Is lofted lunar dust the cause of the horizon glow observed by the Surveyor missions and Apollo astronauts? How does such levitated dust arise and move, what is its density, and what is its ultimate fate? The US National Academy of Sciences/National Research Council decadal surveys and the recent “Scientific Context for Exploration of the Moon” (SCEM) reports have identified studies of the pristine state of the lunar atmosphere and dust environment as among the leading priorities for future lunar science missions. -
Mars Science Laboratory Entry Capsule Aerothermodynamics and Thermal Protection System
Mars Science Laboratory Entry Capsule Aerothermodynamics and Thermal Protection System Karl T. Edquist ([email protected], 757-864-4566) Brian R. Hollis ([email protected], 757-864-5247) NASA Langley Research Center, Hampton, VA 23681 Artem A. Dyakonov ([email protected], 757-864-4121) National Institute of Aerospace, Hampton, VA 23666 Bernard Laub ([email protected], 650-604-5017) Michael J. Wright ([email protected], 650-604-4210) NASA Ames Research Center, Moffett Field, CA 94035 Tomasso P. Rivellini ([email protected], 818-354-5919) Eric M. Slimko ([email protected], 818-354-5940) Jet Propulsion Laboratory, Pasadena, CA 91109 William H. Willcockson ([email protected], 303-977-5094) Lockheed Martin Space Systems Company, Littleton, CO 80125 Abstract—The Mars Science Laboratory (MSL) spacecraft TABLE OF CONTENTS is being designed to carry a large rover (> 800 kg) to the 1. INTRODUCTION ..................................................... 1 surface of Mars using a blunt-body entry capsule as the 2. COMPUTATIONAL RESULTS ................................. 2 primary decelerator. The spacecraft is being designed for 3. EXPERIMENTAL RESULTS .................................... 5 launch in 2009 and arrival at Mars in 2010. The 4. TPS TESTING AND MODEL DEVELOPMENT.......... 7 combination of large mass and diameter with non-zero 5. SUMMARY ........................................................... 11 angle-of-attack for MSL will result in unprecedented REFERENCES........................................................... 11 convective heating environments caused by turbulence prior BIOGRAPHY ............................................................ 12 to peak heating. Navier-Stokes computations predict a large turbulent heating augmentation for which there are no supporting flight data1 and little ground data for validation. -
First Year of Coordinated Science Observations by Mars Express and Exomars 2016 Trace Gas Orbiter
MANUSCRIPT PRE-PRINT Icarus Special Issue “From Mars Express to ExoMars” https://doi.org/10.1016/j.icarus.2020.113707 First year of coordinated science observations by Mars Express and ExoMars 2016 Trace Gas Orbiter A. Cardesín-Moinelo1, B. Geiger1, G. Lacombe2, B. Ristic3, M. Costa1, D. Titov4, H. Svedhem4, J. Marín-Yaseli1, D. Merritt1, P. Martin1, M.A. López-Valverde5, P. Wolkenberg6, B. Gondet7 and Mars Express and ExoMars 2016 Science Ground Segment teams 1 European Space Astronomy Centre, Madrid, Spain 2 Laboratoire Atmosphères, Milieux, Observations Spatiales, Guyancourt, France 3 Royal Belgian Institute for Space Aeronomy, Brussels, Belgium 4 European Space Research and Technology Centre, Noordwijk, The Netherlands 5 Instituto de Astrofísica de Andalucía, Granada, Spain 6 Istituto Nazionale Astrofisica, Roma, Italy 7 Institut d'Astrophysique Spatiale, Orsay, Paris, France Abstract Two spacecraft launched and operated by the European Space Agency are currently performing observations in Mars orbit. For more than 15 years Mars Express has been conducting global surveys of the surface, the atmosphere and the plasma environment of the Red Planet. The Trace Gas Orbiter, the first element of the ExoMars programme, began its science phase in 2018 focusing on investigations of the atmospheric composition with unprecedented sensitivity as well as surface and subsurface studies. The coordination of observation programmes of both spacecraft aims at cross calibration of the instruments and exploitation of new opportunities provided by the presence of two spacecraft whose science operations are performed by two closely collaborating teams at the European Space Astronomy Centre (ESAC). In this paper we describe the first combined observations executed by the Mars Express and Trace Gas Orbiter missions since the start of the TGO operational phase in April 2018 until June 2019. -
Insight Spacecraft Launch for Mission to Interior of Mars
InSight Spacecraft Launch for Mission to Interior of Mars InSight is a robotic scientific explorer to investigate the deep interior of Mars set to launch May 5, 2018. It is scheduled to land on Mars November 26, 2018. It will allow us to better understand the origin of Mars. First Launch of Project Orion Project Orion took its first unmanned mission Exploration flight Test-1 (EFT-1) on December 5, 2014. It made two orbits in four hours before splashing down in the Pacific. The flight tested many subsystems, including its heat shield, electronics and parachutes. Orion will play an important role in NASA's journey to Mars. Orion will eventually carry astronauts to an asteroid and to Mars on the Space Launch System. Mars Rover Curiosity Lands After a nine month trip, Curiosity landed on August 6, 2012. The rover carries the biggest, most advanced suite of instruments for scientific studies ever sent to the martian surface. Curiosity analyzes samples scooped from the soil and drilled from rocks to record of the planet's climate and geology. Mars Reconnaissance Orbiter Begins Mission at Mars NASA's Mars Reconnaissance Orbiter launched from Cape Canaveral August 12. 2005, to find evidence that water persisted on the surface of Mars. The instruments zoom in for photography of the Martian surface, analyze minerals, look for subsurface water, trace how much dust and water are distributed in the atmosphere, and monitor daily global weather. Spirit and Opportunity Land on Mars January 2004, NASA landed two Mars Exploration Rovers, Spirit and Opportunity, on opposite sides of Mars. -
Maven by Example I
Maven by Example i Maven by Example Ed. 0.7 Maven by Example ii Contents 1 Introducing Apache Maven1 1.1 Maven. What is it?....................................1 1.2 Convention Over Configuration...............................2 1.3 A Common Interface....................................3 1.4 Universal Reuse through Maven Plugins..........................3 1.5 Conceptual Model of a “Project”..............................4 1.6 Is Maven an alternative to XYZ?..............................5 1.7 Comparing Maven with Ant................................6 2 Installing Maven 10 2.1 Verify your Java Installation................................ 10 2.2 Downloading Maven.................................... 11 2.3 Installing Maven...................................... 11 Maven by Example iii 2.3.1 Installing Maven on Linux, BSD and Mac OS X................. 11 2.3.2 Installing Maven on Microsoft Windows...................... 12 2.3.2.1 Setting Environment Variables..................... 12 2.4 Testing a Maven Installation................................ 13 2.5 Maven Installation Details................................. 13 2.5.1 User-Specific Configuration and Repository.................... 14 2.5.2 Upgrading a Maven Installation.......................... 15 2.6 Uninstalling Maven..................................... 15 2.7 Getting Help with Maven.................................. 15 2.8 About the Apache Software License............................ 16 3 A Simple Maven Project 17 3.1 Introduction......................................... 17 3.1.1 Downloading -
Explore Digital.Pdf
EXPLORE “sic itur ad astra” ~ thus you shall go to the stars EXPERTISE FOR THE MISSION We’ve built more interplanetary spacecraft than all other U.S. companies combined. We’re ready for humanity’s next step, for Earth, the Sun, our planets … and beyond. We do this for the New capability explorers. And for us for a new space era Achieving in space takes tenacity. Lockheed Martin brings more We’ve never missed a tight (and finite) capability to the table than ever planetary mission launch window. before, creating better data, new Yet, despite how far we go, the most images and groundbreaking ways to important technologies we develop work. And we’re doing it with smarter improve life now, closer to home. factories and common products, Here on Earth. making our systems increasingly affordable and faster to produce. HALF A CENTURY AT MARS Getting to space is hard. Each step past that is increasingly harder. We’ve been a part of every NASA mission to Mars, and we know what it takes to arrive on another planet and explore. Our proven work includes aeroshells, autonomous deep space operations or building orbiters and landers, like InSight. AEROSHELLS VIKING 1 VIKING 2 PATHFINDER MARS POLAR SPIRIT OPPORTUNITY PHOENIX CURIOSITY INSIGHT MARS 2020 1976 1976 1996 LANDER 2004 2018 2008 2012 2018 2020 1999 ORBITERS MARS OBSERVER MARS GLOBAL MARS CLIMATE MARS ODYSSEY MARS RECONNAISSANCE MAVEN 1993 SURVEYOR ORBITER 2001 ORBITER 2014 1997 1999 2006 LANDERS VIKING 1 VIKING 2 MARS POLAR PHOENIX INSIGHT 1976 1976 LANDER 2008 2018 1999 Taking humans back to the Moon – We bring solutions for our customers that include looking outside our organization to deliver the best science through our spacecraft and operations expertise. -
Rtg Impact Response to Hard Landing During Mars Environmental Survey (Mesur) Mission
RTG IMPACT RESPONSE TO HARD LANDING DURING MARS ENVIRONMENTAL SURVEY (MESUR) MISSION A. Schock M. Mukunda Space ABSTRACT Since the simultaneous operation of large number of landers over a long period of time is required, the landers The National Aeronautics and Space Administration must be capable of long life. They must be simple so that (NASA) is studying a seven-year robotic mission (MESUR, a large number can be sent at affordable cost, and yet Mars Environmental Survey) for the seismic, meteorological, rugged and robust In order to survive a wide range of and geochemical exploration of the Martian surface by means landing and environmental conditions, of a network of -16 small, inexpensive landers spread from pole to pole. To permit operation at high Martian latitudes, NASA has basellned the use of Radioisotope NASA has tentatively decided to power the landers with small Thermoelectric Generators (RTGs) to power the probe, RTGs (Radioisotope Thermoelectric Generators). To support lander, and scientific Instruments. Considerations favoring the NASA mission study, the Department of Energy's Office of the use of RTGs are their applicability at both low and high Special Applications commissioned Fairchild to perform Martian latitudes, their ability to operate during and after specialized RTG design studies. Those studies indicated that Martian sandstorms, and their ability to withstand Martian the cost and complexity of the mission could be significantly ground impacts at high velocities and g-loads. reduced if the RTGs had sufficient impact resistance to survive ground impact of the landers without retrorockets. High Impact resistance of the RTGs can be of critical Fairchild designs of RTGs configured for high impact importance In reducing the complexity and cost of the resistance were reported previously. -
EJSM Origins White Document Recommendations by the Origins Working Group for EJSM Mission – JGO and JEO Spacecrafts
EJSM ORIGINS WORKING GROUP EJSM Origins White Document Recommendations by the Origins Working Group for EJSM Mission – JGO and JEO spacecrafts A. Coradini, D. Gautier, T. Guillot, G. Schubert, B. Moore, D. Turrini and H. J. Waite Document Type: Scientific Report Status: Final Version Revision: 4 Issued on: 1 April 2010 Edited by: Angioletta Coradini and Diego Turrini EJSM Origins White Document EJSM Origins White Document A. Coradini, D. Gautier, T. Guillot, B. Moore, G. Schubert, D. Turrini and H. Waite In the ESA Cosmic Vision 2015-2025 program the investigation of the conditions for planetary formation and that of the evolution of the Solar System were among the leading themes. These two themes, in fact, are strictly interlinked, since a clear vision of the origins of the Solar System cannot be achieved if we cannot discern those features which are due to the secular evolution from those which are primordial legacies of the formation time. In the context of the EJSM/Laplace proposal for a mission to Jupiter and the Jovian system, the Origins working group tried to identify the measurements to be performed in the Jovian system that could hold clues to unveil the formation histories of Jupiter and the Solar System. As we anticipated, part of the aspects to be investigated is entwined with the study of the evolution of the Solar and Jovian systems. The identified measures and their scientific domains can be divided into three categories, which will be described in the next sessions. Jupiter and the origins of giant planets As concerns the origin of Jupiter, the main interest of the EJSM mission lies in the investigation of Jupiter's composition and internal structure. -
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. -
The JIRAM (Jovian Infrared Auroral Mapper) Experiment
Lunar and Planetary Science XXXVII (2006) 1564.pdf The JIRAM (Jovian InfraRed Auroral Mapper) Experiment. A. Coradini1 , A. Adriani1, G. Filacchione2, J.Lunine1,3, G. Magni2 , M. Cosi4 and L. Tommasi4, 1 INAF-IFSI, Via Fosso del Cavaliere, 100, Rome, Italy, [email protected], 2INAF-IASF, Via Fosso del Cavaliere, 100, 00133, Rome, Italy, 3Lunar and Pla- netary Lab, University of Arizona, Tucson, AZ, USA, 4 Selex-Galileo Avionica, Via Albert Einstein 35, 50013 Campi Bisenzio (FI), Italy. + Introduction: The atmosphere of Jupiter requires aurora, the H3 is optimal for study. This molecule is multiple techniques at a variety of wavelengths. The formed at the base of the exosphere through the reac- + + present Juno payload is well-suited to a study of the tion H2 + H2 → H3 + H. The main roto-vibrational magnetic field and interior structure of Jupiter, as well band is around 4 µm and it is composed of more than as its plasma environment, but it will be strongly im- 200 possible transitions in the range 3.0 to 4.5 µm [1]. + proved by adding the capability to (a) image and make The H3 auroral spectrum was observed by Cassini spectra with high contrast of the Jovian aurora and (b) VIMS from a large distance in 2000, at much lower explore the region between roughly 1-10 bars where spatial resolution and signal-to-noise than that poten- water—Jupiter’s principal condensable because of the tially available from JIRAM. Figure 1 shows the capa- relatively high interior abundance of oxygen and ap- bility of imaging spectrometers to obtain excellent data propriate conditions in the 1-10 bar region—forms on emission features from which time-variability and clouds and aids energy transport by moist convection. -
Sojourner on Mars and Lessons Learned for Future Planetary Missions
981695 Sojourneron M arsand Lessons Learned forFuturePlanetary Rovers Brian W ilcox and Tam Nguyen NASA's JetPropulsion Laboratory C opyright© 1997 SocietyofAutom otive Engineers,Inc. ABSTRACT The sitelocations w ere designated by a hum an operator using engineering datacollected during previous On July 4, 1997, the M arsPathfinder spacecraft traversals and end-of-solstereo im ages captured by the successfullylanded on M arsinthe Ares Vallislanding lander IMP (Im ager for M arsPathfinder) cam eras. site and deployed an 11.5-kilogram m icrorover nam ed During the traversalsthe rover autonom ouslyavoided Sojourner.Thismicrorover accom plished itsprimary rock,drop-off,and slope hazards. Itchanged its course mission objectives inthe first 7 days, and continued to toavoidthese hazards and turned back tow ardits goals operatefora totalof83 sols(1 sol= M ars day = 1 Earth w henever the hazards w erenolonger inits w ay. The day + ~24 m ins)untilthe landerlostcom m unication w ith rover used "dead reckoning" counting w heel turns and Earth, probably due tolander batteryfailure. The using on-boardrate sensorsestimate position. Although microrover navigated to m any sites surrounding the the rover telem etryrecorded itsresponses to hum an lander, and conducted various science and technology driver com m ands in detail,the vehicle'sactualpositions experim entsusing itson-boardinstrum ents. were not know n untilexamination of the lander stereo im ages at the end of the sol.Acollection of stereo Inthis paper,the rover navigation perform ance is im ages containing rover tracks allow s reconstruction of analyzed on the basisofreceived rovertelem etry, rover the rover physicaltraversalpaththoughoutthe m ission. uplink com m ands and stereo im ages captured by the Since the primary purpose for a robotic vehicleon lander cam eras. -
NGIMS Team – PDS Atmospheres Node Rev
MAVEN NGIMS Team – PDS Atmospheres Node Rev. 1.3 Software Interface Specification 05/22/2015 Mars Atmosphere and Volatile Evolution (MAVEN) Mission Neutral Gas and Ion Mass Spectrometer (NGIMS) NGIMS PDS Software Interface Specification Document Number MAVEN-NGIMS-SIS-0001 Revision 1.3 May 22, 2015 Prepared by: Mehdi Benna Meredith Elrod Goddard Space Flight Center Greenbelt, Maryland National Aeronautics and Space Administration 1 MAVEN NGIMS Team – PDS Atmospheres Node Rev. 1.3 Software Interface Specification 05/22/2015 Configuration Management Plan This document is a Mars Atmosphere and Volatile Evolution Project controlled document. Changes to this document require prior approval of the MAVEN Project CCB Chairperson. Proposed changes shall be submitted to the MAVEN Project Configuration Management Office (CMO), along with supportive material justifying the proposed change. Questions or comments concerning this document should be addressed to: MAVEN Configuration Management Office MailStop 432 Goddard Space Flight Center Greenbelt, Maryland 20771 2 MAVEN NGIMS Team – PDS Atmospheres Node Rev. 1.3 Software Interface Specification 05/22/2015 REVIEW/APPROVAL PAGE All reviews and approvals are electronic via the MAVEN MIS at: https://mavenmis.gsfc.nasa.gov Prepared by Mehdi Benna; NGIMS Team (GSFC) Meredith Elrod; NGIMS Team (GSFC) Approved (date) Paul Mahaffy Principal Investigator, NGIMS (GSFC) Approved (date) Alex DeWolfe Science Data Center Lead (LASP) Approved (date) Reta Beebe PDS Atmospheres Node Manager (NMSU) Approved (date)