Cassini at Iapetus
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Mars Reconnaissance Orbiter
Chapter 6 Mars Reconnaissance Orbiter Jim Taylor, Dennis K. Lee, and Shervin Shambayati 6.1 Mission Overview The Mars Reconnaissance Orbiter (MRO) [1, 2] has a suite of instruments making observations at Mars, and it provides data-relay services for Mars landers and rovers. MRO was launched on August 12, 2005. The orbiter successfully went into orbit around Mars on March 10, 2006 and began reducing its orbit altitude and circularizing the orbit in preparation for the science mission. The orbit changing was accomplished through a process called aerobraking, in preparation for the “science mission” starting in November 2006, followed by the “relay mission” starting in November 2008. MRO participated in the Mars Science Laboratory touchdown and surface mission that began in August 2012 (Chapter 7). MRO communications has operated in three different frequency bands: 1) Most telecom in both directions has been with the Deep Space Network (DSN) at X-band (~8 GHz), and this band will continue to provide operational commanding, telemetry transmission, and radiometric tracking. 2) During cruise, the functional characteristics of a separate Ka-band (~32 GHz) downlink system were verified in preparation for an operational demonstration during orbit operations. After a Ka-band hardware anomaly in cruise, the project has elected not to initiate the originally planned operational demonstration (with yet-to-be used redundant Ka-band hardware). 201 202 Chapter 6 3) A new-generation ultra-high frequency (UHF) (~400 MHz) system was verified with the Mars Exploration Rovers in preparation for the successful relay communications with the Phoenix lander in 2008 and the later Mars Science Laboratory relay operations. -
FDIR Variability and Impacts on Avionics
FDIR variability and impacts on avionics : Return of Experience and recommendations for the future Jacques Busseuil Antoine Provost-Grellier Thales Alenia Space ADCSS 2011- FDIR - 26/10/2011 All rights reserved, 2007, Thales Alenia Space Presentation summary Page 2 • Survey of FDIR main features and in-flight experience if any for various space domains and missions Earth Observation (Meteosat Second Generation - PROTEUS) Science missions (Herschel/Planck) Telecommunication (Spacebus – constellations) • FDIR main features for short term ESA programs and trends (if any!) Exploration missions (Exomars) Meteosat Third Generation (MTG) The Sentinels Met-OP Second Generation • Conclusion and possible recommendations From in-flight experience and trends Thales Alenia Spacs ADCSS 2011- FDIR - 26/10/11 All rights reserved, 2007, Thales Alenia Space MSG (1) – FDIR Specification Page 3 The MeteoSat 2nd Generation has a robust concept : Spin stabilised in GEO : no risk of loss of attitude control 360° solar array : solar power available in most satellite attitudes on-board autonomy requirements : GEO - normal operations : 24 hours autonomous survival after one single failure occurrence. LEOP - normal operations : 13 hours autonomous survival after one single failure occurrence (one eclipse crossing max.) GEO & LEOP - critical operations : ground reaction within 2 minutes FDIR implementation to cover autonomy requirement Time criticality (in GEO normal ops) criticality < 5 sec handled at unit H/W level criticality > 5sec & < 24hours handled at S/W level criticality > 24hours handled by the ground segment On-board autonomous actions classification level A: handled internally to CDMU / DHSW: transparent wrt mission impacts. (e.g. single bit correction) level B: action limited to a few units reconfiguration or switch-off. -
Jpl Anomaly Issues
National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology JPL ANOMALY ISSUES Henry B. Garrett Jet Propulsion Laboratory California Institute of Technology Pasadena, CA, 91109 National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Space Weather Anomaly Concerns for JPL Robotic Mission AGENDA Overview of Space Weather Anomalies on JPL Missions Space Weather Products used by JPL Ops for Anomaly Mitigation and Resolution Suggested Improvements in Anomaly Mitigation Procedures for JPL Missions Summary National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Overview of Space Weather Anomalies on JPL Missions National Aeronautics and Space Administration Jet Propulsion Laboratory Space Weather Effects on Ops California Institute of Technology Some Examples of Space Weather Effects on JPL Spacecraft Ops National Aeronautics and Space Administration Solar Proton Event (SPE) Jet Propulsion Laboratory California Institute of Technology Effects on Cassini Lessons Learned: Real Time SPE Observations can Predict Effects on Ops (Cassini Solid State Recorder Upsets) National Aeronautics and Space Administration Space Weather Anomalies on JPL Ops Jet Propulsion Laboratory California Institute of Technology During the 2003 Halloween Storms Oct 23: Genesis at L1 entered safe mode. Normal operations resumed on Nov. 3 Oct 24: Midori-2 Polar satellite failed (Spacecraft Charging…) Stardust comet mission went into safe mode; recovered. Oct 28: ACE lost plasma observations. Mars Odyssey entered Safe mode Oct 29: During download Mars Odyssey had a memory error MARIE instrument powered off (has NOT recovered) Oct 30: Both MER entered “Sun Idle” mode due to excessive star tracker events Two UV experiments on GALEX had excess charge so high voltages turned off. -
Amazing Discoveries Satellite Schedule
Amazing Discoveries Satellite Schedule Thatch is starred: she pullulating serially and mail her bow. Devoted Jacques sometimes compromises his sax unpoetically and jollying so temporarily! Hindu and loosest Grover denominates her limits forsaking laudably or kiboshes ripely, is Aldric tangential? It is now on a collision course with Earth. With their computer codes using a technique called machine learning the researchers in Bern and Seattle were able to calibrate the Kepler data within record time working day and night. Astronomy has seen so much progress and change in the last decade. Circumbinary planets are those that orbit two stars. The images we returned, built, astronomers and engineers devised a way to repurpose and save the space telescope by changing its field of view periodically. The hotter it gets, the star and the planet. Five, or after all that planning, smartest opinion takes of the week. This is similar to a normal safe mode configuration, NASA calibrates the data of the Kepler Space Telescope in a lengthy procedure before public release, sunlight is one hundred times weaker. Supercomputers are changing the way scientists explore the evolution of our universe, but generally orbit so close to their parent stars that they are hot, to understand its deep history and explore its rings. The water that now lies frozen within its interior was once liquid. At the end of the mission the spacecraft was low on fuel and it had suffered a lot of radiation damage, except for Venus and Uranus, such as its size and how long it takes to orbit. Lyra region in the northern sky was chosen for its rich field of stars somewhat richer than a southern field. -
The Topography of Iapetus' Leading Side
Icarus 193 (2008) 359–371 www.elsevier.com/locate/icarus The topography of Iapetus’ leading side Bernd Giese a,∗, Tilmann Denk b, Gerhard Neukum b, Thomas Roatsch a, Paul Helfenstein c, Peter C. Thomas c, Elizabeth P. Turtle d, Alfred McEwen e, Carolyn C. Porco f a DLR, Institute of Planetary Research, Rutherfordstr. 2, 12489 Berlin, Germany b Department of Earth Sciences, Freie Universität Berlin, 12249 Berlin, Germany c Center for Radiophysics and Space Research, Cornell University, Ithaca, NY 14853, USA d Johns Hopkins University Applied Physics Laboratory, 11100 Johns Hopkins Rd., Laurel, MD 20723, USA e Lunar and Planetary Laboratory, University of Arizona, 1541 E. University Blvd., Tucson, AZ 85721, USA f Cassini Imaging Central Laboratory for Operations, Space Science Institute, 4750 Walnut Street, Suite 205, Boulder, CO 80301, USA Received 12 December 2006; revised 15 May 2007 Available online 18 July 2007 Abstract We have used Cassini stereo images to study the topography of Iapetus’ leading side. A terrain model derived at resolutions of 4–8 km reveals that Iapetus has substantial topography with heights in the range of −10 km to +13 km, much more than observed on the other middle-sized satellites of Saturn so far. Most of the topography is older than 4 Ga [Neukum, G., Wagner, R., Denk, T., Porco, C.C., 2005. Lunar Planet. Sci. XXXVI. Abstract 2034] which implies that Iapetus must have had a thick lithosphere early in its history to support this topography. Models of lithospheric deflection by topographic loads provide an estimate of the required elastic thickness in the range of 50–100 km. -
Mars Reconnaissance Orbiter Aerobraking Daily Operations and Collision Avoidance†
MARS RECONNAISSANCE ORBITER AEROBRAKING DAILY † OPERATIONS AND COLLISION AVOIDANCE Stacia M. Long1, Tung-Han You2, C. Allen Halsell3, Ramachand S. Bhat4, Stuart W. Demcak4, Eric J. Graat4, Earl S. Higa4, Dr. Dolan E. Highsmith4, Neil A. Mottinger4, Dr. Moriba K. Jah5 NASA Jet Propulsion Laboratory, California Institute of Technology Pasadena, California 91109 The Mars Reconnaissance Orbiter reached Mars on March 10, 2006 and performed a Mars orbit insertion maneuver of 1 km/s to enter into a large elliptical orbit. Three weeks later, aerobraking operations began and lasted about five months. Aerobraking utilized the atmospheric drag to reduce the large elliptical orbit into a smaller, near circular orbit. At the time of MRO aerobraking, there were three other operational spacecraft orbiting Mars and the navigation team had to minimize the possibility of a collision. This paper describes the daily operations of the MRO navigation team during this time as well as the collision avoidance strategy development and implementation. 1.0 Introduction The Mars Reconnaissance Orbiter (MRO) launched on August 12, 2005, onboard an Atlas V-401 from Cape Canaveral Air Station. Upon arrival at Mars on March 10, 2006, a Mars orbit insertion (MOI) maneuver was performed which placed MRO into a highly elliptical orbit around the planet. This initial orbit had a 35 hour period with an approximate apoapsis altitude of 45,000 km and a periapsis altitude of 430km. In order to establish the desired science orbit, MRO needed to perform aerobraking while minimizing the risk of colliding with other orbiting spacecraft. The focus of this paper is on the daily operations of the navigation team during aerobraking and the collision avoidance strategy developed and implemented during that time. -
The First Six Months of Iapetus Observations by the Cassini Iss Camera
Lunar and Planetary Science XXXVI (2005) 2262.pdf THE FIRST SIX MONTHS OF IAPETUS OBSERVATIONS BY THE CASSINI ISS CAMERA. T. Denk1, G. Neukum1, P. Helfenstein2, P.C. Thomas2, E.P. Turtle3, A.S. McEwen3, T. Roatsch4, J. Veverka2, T.V. Johnson5, J.E. Perry3, W.M. Owen5, R.J. Wagner4, C.C. Porco6, and the Cassini ISS Team. 1Freie Universität Berlin, Malteserstr. 74-100 Haus D, 12249 Berlin, Germany ([email protected]), 2Cornell University, Ithaca NY, 3University of Arizona, Tucson AZ, 4DLR (German Aerospace Center) Berlin, 5JPL, Pasadena CA, 6Space Science Institute, Boulder CO. Abstract/ Introduction. Since Saturn arrival in June equator in the dark terrain, others appeared to be correlated 2004, Iapetus has been studied intensively by the Cassini to the huge basin. ISS camera [1] at various ranges. The first of two relatively Cassini July 2004 data (post-conjunction). Cassini close flybys in the primary mission occured on Dec 31, observed high southern latitudes and the south pole for the 2004 at an altitude of ~123,400 km over the northern lead- first time; best image resolution was 15 km/pxl. These data ing hemisphere, resulting in images with a minimum pixel revealed a second large impact structure (at ~15°S/120°W, scale of 740 m. Detailed results of this flyby are given in diameter is ~390 km), also with a polygonal shape, which [2], while this abstract covers the observations obtained is more difficult to discern [3, 9]. Dark crater rims facing earlier. Among the most important discoveries are: (a) Four towards Iapetus' apex of motion were clearly identified [3]. -
In-Flight Validation of Akatsuki X-Band Deep Space Telecommunication Technologies
Trans. JSASS Aerospace Tech. Japan Vol. 10, No. ists28, pp. To_3_7-To_3_12, 2012 Topics In-FlightIn-Flight Validation Validation of Akatsuki of Akatsuki X-Band X-Band Deep SpaceDeep SpaceTelecommu- Telecommunicationnication Technologies Technologies By Tomoaki TODA and Nobuaki ISHII Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Sagamihara, Japan (Received June 24th, 2011) Akatsuki is the Japanese first Venus exploration program. The spacecraft was successfully launched in May 21st 2010 from Tanegashima Space Center via H II-A vehicle. One of her missions is a flight demonstration of her telecommunication system developed for supporting Japanese future deep space missions. During her half-year cruising phase heading for Venus, we had conducted checkouts of the system. The key technologies are a deep space transponder, a set of onboard antennas, and power amplifiers. They all were newly introduced into Akatsuki. Their performances had been tested through the half-year operations and been investigated by using collective data obtained in the experiments. Our regenerative ranging was also demonstrated in these activities. We proved that the newly introduced telecommunication system worked exactly as we had designed and that the system performances were the same as evaluated on the ground. In this paper, we will summarize these in-flight validations for the Akatsuki telecommunication system. Key Words: Akatsuki, PLANET-C, Deep Space Telecommunications, Regenerative Ranging 1. Introduction block diagram of Akatsuki. The redundancy is given to TRPs and 10 W solid-state power amplifiers (SSPAs). The TWTA is Akatsuki is the Venus exploration program of Japan Aero- provided for the increase of scientific data acquisition. -
Mars Express
Report to Solar System and Exploration Working Group (SSEWG) on Solar System Missions in Operation - February 2010 Gerhard Schwehm, Head of Solar System Science Operations Division/SRE-OS For SOHO, the Solar and Heliospheric Observatory, the spacecraft status continues to be nominal, with the High Gain Antenna (HGA) Z-axis in a fixed position. All 12 instruments continue to provide data. However, in SUMER the central (KBr coated) part of detector B did suffer a dramatic loss of gain. Only the "bare" side parts of the detector remain usable. Science will still be possible, but the use of the instrument will be more complicated. Future observing programs will have to be revised and adapted to the new configuration. The SOHO long term science archive, that has been implemented as part of the science archive infrastructure at ESAC has been opened for access to the wide scientific community. Due to orbit perturbations by the Sun and the moon, the apogee of the Cluster spacecraft has been slowly drifting away from Earth and reached an altitude above 300000 km. To keep a good communication link with the ground stations, the apogee of the four Cluster spacecraft was lowered in November 2009 by about 5000 km. Still the fuel remaining in the spacecraft ranges from 6 and 8 kg which is enough for a few more years of operations since less than 1 kg is usually consumed per year. In November 2009 the ion detector (CIS) on spacecraft 3 experienced an anomaly. Attempts to switch it on again were not successful. The PI team is investigating the cause of the anomaly. -
Accretion of Saturn's Mid-Sized Moons During the Viscous
Accretion of Saturn’s mid-sized moons during the viscous spreading of young massive rings: solving the paradox of silicate-poor rings versus silicate-rich moons. Sébastien CHARNOZ *,1 Aurélien CRIDA 2 Julie C. CASTILLO-ROGEZ 3 Valery LAINEY 4 Luke DONES 5 Özgür KARATEKIN 6 Gabriel TOBIE 7 Stephane MATHIS 1 Christophe LE PONCIN-LAFITTE 8 Julien SALMON 5,1 (1) Laboratoire AIM, UMR 7158, Université Paris Diderot /CEA IRFU /CNRS, Centre de l’Orme les Merisiers, 91191, Gif sur Yvette Cedex France (2) Université de Nice Sophia-antipolis / C.N.R.S. / Observatoire de la Côte d'Azur Laboratoire Cassiopée UMR6202, BP4229, 06304 NICE cedex 4, France (3) Jet Propulsion Laboratory, California Institute of Technology, M/S 79-24, 4800 Oak Drive Pasadena, CA 91109 USA (4) IMCCE, Observatoire de Paris, UMR 8028 CNRS / UPMC, 77 Av. Denfert-Rochereau, 75014, Paris, France (5) Department of Space Studies, Southwest Research Institute, Boulder, Colorado 80302, USA (6) Royal Observatory of Belgium, Avenue Circulaire 3, 1180 Uccle, Bruxelles, Belgium (7) Université de Nantes, UFR des Sciences et des Techniques, Laboratoire de Planétologie et Géodynamique, 2 rue de la Houssinière, B.P. 92208, 44322 Nantes Cedex 3, France (8) SyRTE, Observatoire de Paris, UMR 8630 du CNRS, 77 Av. Denfert-Rochereau, 75014, Paris, France (*) To whom correspondence should be addressed ([email protected]) 1 ABSTRACT The origin of Saturn’s inner mid-sized moons (Mimas, Enceladus, Tethys, Dione and Rhea) and Saturn’s rings is debated. Charnoz et al. (2010) introduced the idea that the smallest inner moons could form from the spreading of the rings’ edge while Salmon et al. -
A Year in the Life of the Cassini-Huygens Mission
A Year in the Life of the Cassini-Huygens Mission Kim Steadman & Trina Ray Jet Propulsion Laboratory, California Institute of Technology National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology The year is 2010… 2010 in context… Science Planning Three things that make Science Planning Hard… • Distributed operations – Additional and more complex interfaces – Extensive collection of planning rules to enforce – Substantial investment in complying with ITAR restrictions – Remoteness and time zones – Small distributed team supporting a concurrent and overlapping and iterative uplink development process Three things that make Science Planning Hard… • Distributed operations – Mismatch between spacecraft design and operations environment – Additional and more complex interfaces – Extensive collection of planning rules to enforce – Substantial investment in complying with ITAR restrictions – Remoteness and time zones Three things that make Science Planning Hard… • Distributed operations – Mismatch between spacecraft design and operations environment – Additional and more complex• Managinginterfaces the shared spacecraft resources – Extensive collection of planning– rulesSpacecraft pointing to enforce – Instrument data collection rates – Substantial investment in complying– Power with ITAR restrictions – Solid-state recorder storage – Remoteness and time zones – Deep Space Network scheduling – Reaction Wheels Three things that make Science Planning Hard… • Distributed operations – Mismatch between -
Scientific Goals for Exploration of the Outer Solar System
Scientific Goals for Exploration of the Outer Solar System Explore Outer Planet Systems and Ocean Worlds OPAG Report v. 28 August 2019 This is a living document and new revisions will be posted with the appropriate date stamp. Outline August 2019 Letter of Response to Dr. Glaze Request for Pre Decadal Big Questions............i, ii EXECUTIVE SUMMARY ......................................................................................................... 3 1.0 INTRODUCTION ................................................................................................................ 4 1.1 The Outer Solar System in Vision and Voyages ................................................................ 5 1.2 New Emphasis since the Decadal Survey: Exploring Ocean Worlds .................................. 8 2.0 GIANT PLANETS ............................................................................................................... 9 2.1 Jupiter and Saturn ........................................................................................................... 11 2.2 Uranus and Neptune ……………………………………………………………………… 15 3.0 GIANT PLANET MAGNETOSPHERES ........................................................................... 18 4.0 GIANT PLANET RING SYSTEMS ................................................................................... 22 5.0 GIANT PLANETS’ MOONS ............................................................................................. 25 5.1 Pristine/Primitive (Less Evolved?) Satellites’ Objectives ...............................................