SPDF Presentation (By Lan Jian)
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VI FORSKER PÅ MARS Kort Om Aktiviteten I Mange Tiår Har Mars Vært Et Yndet Objekt for Forskere Verden Over
VI FORSKER PÅ MARS Kort om aktiviteten I mange tiår har Mars vært et yndet objekt for forskere verden over. Men hvorfor det? Hva er det med den røde planeten som er så interessant? Her forsøker vi å gi en oversikt over hvorfor vi er så opptatt av Mars. Hva har vi oppdaget, og hva er det vi tenker å gjøre? Det finnes en planet i solsystemet vårt som bare er bebodd av roboter -MARS- Læringsmål Elevene skal kunne - gi eksempler på dagsaktuell forskning og drøfte hvordan ny kunnskap genereres gjennom samarbeid og kritisk tilnærming til eksisterende kunnskap - utforske, forstå og lage teknologiske systemer som består av en sender og en mottaker - gjøre rede for energibevaring og energikvalitet og utforske ulike måter å omdanne, transportere og lagre energi på VI FORSKER PÅ MARS side 1 Innhold Kort om aktiviteten ................................................................................................................................ 1 Læringsmål ................................................................................................................................................ 1 Mars gjennom historien ...................................................................................................................... 3 Romkappløp mot Mars ................................................................................................................... 3 2000-tallet gir rovere i fleng ....................................................................................................... 4 Hva nå? ...................................................................................................................................................... -
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]). -
University of Iowa Instruments in Space
University of Iowa Instruments in Space A-D13-089-5 Wind Van Allen Probes Cluster Mercury Earth Venus Mars Express HaloSat MMS Geotail Mars Voyager 2 Neptune Uranus Juno Pluto Jupiter Saturn Voyager 1 Spaceflight instruments designed and built at the University of Iowa in the Department of Physics & Astronomy (1958-2019) Explorer 1 1958 Feb. 1 OGO 4 1967 July 28 Juno * 2011 Aug. 5 Launch Date Launch Date Launch Date Spacecraft Spacecraft Spacecraft Explorer 3 (U1T9)58 Mar. 26 Injun 5 1(U9T68) Aug. 8 (UT) ExpEloxrpelro r1e r 4 1915985 8F eJbu.l y1 26 OEGxOpl o4rer 41 (IMP-5) 19697 Juunlye 2 281 Juno * 2011 Aug. 5 Explorer 2 (launch failure) 1958 Mar. 5 OGO 5 1968 Mar. 4 Van Allen Probe A * 2012 Aug. 30 ExpPloiorenre 3er 1 1915985 8M Oarc. t2. 611 InEjuxnp lo5rer 45 (SSS) 197618 NAouvg.. 186 Van Allen Probe B * 2012 Aug. 30 ExpPloiorenre 4er 2 1915985 8Ju Nlyo 2v.6 8 EUxpKlo 4r e(rA 4ri1el -(4IM) P-5) 197619 DJuenc.e 1 211 Magnetospheric Multiscale Mission / 1 * 2015 Mar. 12 ExpPloiorenre 5e r 3 (launch failure) 1915985 8A uDge.c 2. 46 EPxpiolonreeerr 4130 (IMP- 6) 19721 Maarr.. 313 HMEaRgCnIe CtousbpeShaetr i(cF oMxu-1ltDis scaatelell itMe)i ssion / 2 * 2021081 J5a nM. a1r2. 12 PionPeioenr e1er 4 1915985 9O cMt.a 1r.1 3 EExpxlpolorerer r4 457 ( S(IMSSP)-7) 19721 SNeopvt.. 1263 HMaalogSnaett oCsupbhee Sriact eMlluitlet i*scale Mission / 3 * 2021081 M5a My a2r1. 12 Pioneer 2 1958 Nov. 8 UK 4 (Ariel-4) 1971 Dec. 11 Magnetospheric Multiscale Mission / 4 * 2015 Mar. -
Generate Viewsheds of Mastcam Images from the Curiosity Rover, Using Arcgis® and Public Datasets
TECHNICAL Coupling Mars Ground and Orbital Views: Generate REPORTS: METHODS Viewsheds of Mastcam Images From the Curiosity 10.1029/2020EA001247 Rover, Using ArcGIS® and Public Datasets Key Points: 1 2 1 3 4 • Mastcam images from the Curiosity M. Nachon , S. Borges , R. C. Ewing , F. Rivera‐Hernández , N. Stein , and rover are available online but lack a J. K. Van Beek5 public method to be placed back in the Mars orbital context 1Department of Geology and Geophysics, Texas A&M University, College Station, TX, USA, 2Department of Astronomy • This procedure allows users to and Planetary Sciences—College of Engineering, Forestry, and Natural Sciences, Northern Arizona University, Flagstaff, generate Mastcam image viewsheds: 3 4 locate in a map view the Mars AZ, USA, Department of Earth Sciences, Dartmouth College, Hanover, NH, USA, Division of Geological and Planetary 5 terrains visible in Mastcam images Sciences, California Institute of Technology, Pasadena, CA, USA, Malin Space Science Systems, San Diego, CA, USA • This procedure uses ArcGIS® and publicly available Mars datasets Abstract The Mastcam (Mast Camera) instrument onboard the NASA Curiosity rover provides an Supporting Information: exclusive view of Mars: High‐resolution color images from Mastcam allow users to study Gale crater's • Dataset S1 geologic terrains along Curiosity's path. These ground observations complement the spatially broader • Dataset S2 • Dataset S3 views of Gale crater provided by spacecrafts from orbit. However, for a given Mastcam image, it can be • Table S1 challenging to locate the corresponding terrains on the orbital view. No method for locating Mastcam images • Table S2 onto orbital images had been made publicly available. -
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. -
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 -
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. -
Mariner to Mercury, Venus and Mars
NASA Facts National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Pasadena, CA 91109 Mariner to Mercury, Venus and Mars Between 1962 and late 1973, NASA’s Jet carry a host of scientific instruments. Some of the Propulsion Laboratory designed and built 10 space- instruments, such as cameras, would need to be point- craft named Mariner to explore the inner solar system ed at the target body it was studying. Other instru- -- visiting the planets Venus, Mars and Mercury for ments were non-directional and studied phenomena the first time, and returning to Venus and Mars for such as magnetic fields and charged particles. JPL additional close observations. The final mission in the engineers proposed to make the Mariners “three-axis- series, Mariner 10, flew past Venus before going on to stabilized,” meaning that unlike other space probes encounter Mercury, after which it returned to Mercury they would not spin. for a total of three flybys. The next-to-last, Mariner Each of the Mariner projects was designed to have 9, became the first ever to orbit another planet when two spacecraft launched on separate rockets, in case it rached Mars for about a year of mapping and mea- of difficulties with the nearly untried launch vehicles. surement. Mariner 1, Mariner 3, and Mariner 8 were in fact lost The Mariners were all relatively small robotic during launch, but their backups were successful. No explorers, each launched on an Atlas rocket with Mariners were lost in later flight to their destination either an Agena or Centaur upper-stage booster, and planets or before completing their scientific missions. -
Elements of Astronomy and Cosmology Outline 1
ELEMENTS OF ASTRONOMY AND COSMOLOGY OUTLINE 1. The Solar System The Four Inner Planets The Asteroid Belt The Giant Planets The Kuiper Belt 2. The Milky Way Galaxy Neighborhood of the Solar System Exoplanets Star Terminology 3. The Early Universe Twentieth Century Progress Recent Progress 4. Observation Telescopes Ground-Based Telescopes Space-Based Telescopes Exploration of Space 1 – The Solar System The Solar System - 4.6 billion years old - Planet formation lasted 100s millions years - Four rocky planets (Mercury Venus, Earth and Mars) - Four gas giants (Jupiter, Saturn, Uranus and Neptune) Figure 2-2: Schematics of the Solar System The Solar System - Asteroid belt (meteorites) - Kuiper belt (comets) Figure 2-3: Circular orbits of the planets in the solar system The Sun - Contains mostly hydrogen and helium plasma - Sustained nuclear fusion - Temperatures ~ 15 million K - Elements up to Fe form - Is some 5 billion years old - Will last another 5 billion years Figure 2-4: Photo of the sun showing highly textured plasma, dark sunspots, bright active regions, coronal mass ejections at the surface and the sun’s atmosphere. The Sun - Dynamo effect - Magnetic storms - 11-year cycle - Solar wind (energetic protons) Figure 2-5: Close up of dark spots on the sun surface Probe Sent to Observe the Sun - Distance Sun-Earth = 1 AU - 1 AU = 150 million km - Light from the Sun takes 8 minutes to reach Earth - The solar wind takes 4 days to reach Earth Figure 5-11: Space probe used to monitor the sun Venus - Brightest planet at night - 0.7 AU from the -
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. -
A Possible Flyby Anomaly for Juno at Jupiter
A possible flyby anomaly for Juno at Jupiter L. Acedo,∗ P. Piqueras and J. A. Mora˜no Instituto Universitario de Matem´atica Multidisciplinar, Building 8G, 2o Floor, Camino de Vera, Universitat Polit`ecnica de Val`encia, Valencia, Spain December 14, 2017 Abstract In the last decades there have been an increasing interest in im- proving the accuracy of spacecraft navigation and trajectory data. In the course of this plan some anomalies have been found that cannot, in principle, be explained in the context of the most accurate orbital models including all known effects from classical dynamics and general relativity. Of particular interest for its puzzling nature, and the lack of any accepted explanation for the moment, is the flyby anomaly discov- ered in some spacecraft flybys of the Earth over the course of twenty years. This anomaly manifest itself as the impossibility of matching the pre and post-encounter Doppler tracking and ranging data within a single orbit but, on the contrary, a difference of a few mm/s in the asymptotic velocities is required to perform the fitting. Nevertheless, no dedicated missions have been carried out to eluci- arXiv:1711.08893v2 [astro-ph.EP] 13 Dec 2017 date the origin of this phenomenon with the objective either of revising our understanding of gravity or to improve the accuracy of spacecraft Doppler tracking by revealing a conventional origin. With the occasion of the Juno mission arrival at Jupiter and the close flybys of this planet, that are currently been performed, we have developed an orbital model suited to the time window close to the ∗E-mail: [email protected] 1 perijove. -
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 .........................................................