Status of JUNO Experiment

Total Page:16

File Type:pdf, Size:1020Kb

Status of JUNO Experiment Status of the JUNO Experiment Gaosong Li Institute of High Energy Physics, CAS On behalf of the JUNO collaboration IAS Program on High Energy Physics Jan 20, 2021 1 JUNO Experiment Guang Zhou 2.5 h drive Lufeng Shen Zhen Huizhou NPP NPP Zhu Hai Daya Bay NPP Hong Kong Macau 53 km 53 km Taishan NPP Yangjiang NPP 2 Timeline 2022 • Detector ready for data taking 2019-2021 • Electronics production starts 2018 • Civil construction and • PMT potting lab preparation • Start delivery of completed 2017 surface building • Detector construction • PMT testing • Start production of start acrylic sphere 2016 • TT arrived • PMT production start Collaboration 2014 • CD parts production 2015 start • PMT production• Yellow book line setup published • CD parts R&D • Civil 2014 construction • International start collaboration established • Conceptual design 3 A Multipurpose Neutrino Observatory 26.6 GWth, 53 km ~60 / day 4 From J. Pedro Ochoa-Ricoux Mass Ordering DYB near DYB far JUNO • Determine mass ordering by resolving the tiny phase difference in the oscillated spectrum • 3휎 sensitivity to neutrino mass ordering with 6 years’ data • 4휎 with constraints from accelerator experiments 5 Precision Measurement of Oscillation Parameters • Sub-percent precision on 2 2 2 sin 휃12 , Δ푚21, Δ푚31 • Essential to test the neutrino oscillation framework precisely • An update of precision measurement is under preparation 6 Rich Physics Potential • Supernova neutrinos (SN) • 10k events (5000 IBD) for SN @ 10kpc • Sensitivity to flavor content, energy spectrum and time evolution • Diffusive supernova neutrino background (DSNB) • ~3휎 sensitivity with 10 years’ data • Atmospheric neutrinos • Mass ordering effect from MSW effect • Solar Neutrino • 60k ES signal and 30k background in 10 years’ data taking • Solar oscillation parameters using solar 휈푒 and reactor anti-휈푒 • Geo-neutrinos • Explore origin and thermal evolution of the earth with 400-500 events per year • Multi-messenger • Lower detector threshold to O(10) keV • Real time monitoring of the MeV transient neutrino sky • Proton decay • Competitive sensitivity through 푝 → 휈ҧ + 퐾+ 7 Country Institute Country Institute Country Institute Armeni Yerevan Physics China IMP-CAS Germany FZJ-IKP a Institute Universite libre de Belgium China SYSU Germany U. Mainz JUNO Collaboration Bruxelles Brazil PUC China Tsinghua U. Germany U. Tuebingen Brazil UEL China UCAS Italy INFN Catania Chile PCUC China USTC Italy INFN di Frascati Chile UTFSM China U. of South China Italy INFN-Ferrara China BISEE China Wu Yi U. Italy INFN-Milano INFN-Milano China Beijing Normal U. China Wuhan U. Italy Bicocca China CAGS China Xi'an JT U. Italy INFN-Padova China ChongQing University China Xiamen University Italy INFN-Perugia China CIAE China Zhengzhou U. Italy INFN-Roma 3 China DGUT China NUDT Latvia IECS China ECUST China CUG-Beijing Pakistan PINSTECH (PAEC) China Guangxi U. China ECUT-Nanchang City Russia INR Moscow Harbin Institute of China Croatia PDZ/RBI Russia JINR Technology China IHEP Czech Charles U. Russia MSU China Jilin U. Finland University of Jyvaskyla Slovakia FMPICU Taiwan- National Chiao-Tung China Jinan U. France LAL Orsay China U. Taiwan- China Nanjing U. France CENBG Bordeaux National Taiwan U. China Taiwan- China Nankai U. France CPPM Marseille National United U. China China NCEPU France IPHC Strasbourg Thailand NARIT China Pekin U. France Subatech Nantes Thailand PPRLCU German China Shandong U. FZJ-ZEA Thailand SUT y German China Shanghai JT U. RWTH Aachen U. USA UMD y German China IGG-Beijing TUM USA UC Irvine y 669 members from 77 institutes German China IGG-Wuhan U. Hamburg 8 y Detector Technology • A 20-kton liquid scintillator calorimeter • Key requirements • Excellent energy resolution: < 3%/√퐸 within [1, 8] MeV • Energy scale uncertainty < 1% • Low radioactive background • Pulse shape discrimination capability for PID • Based on LS photon emission time difference for different particle types • e-/e+ vs 훼/p/n-recoil 9 Central Detector • 35 m diameter acrylic sphere • Stainless steel truss • 20,000 tons purified liquid scintillator • 18,000 20-inch PMTs • 25,600 3-inch PMTs • Filling/Overflow/Circulation (FOC) system 1010 Liquid Scintillator • Four different plants for LS purification to achieve high • Low radioactive backgrounds attenuation length and low radioactive background • 10-15 g/g U/Th for reactor antineutrinos • Finished a pilot LS purification test at Daya Bay • 10-17 g/g U/Th for solar neutrinos • LS recipe: LAB + 2.5 g/L PPO + (1-4) mg/L bis-MSB (arXiv: • An online radioactivity investigation system 2007.00314) (OSIRIS) will be built • Attenuation Length: > 20 m @430 nm 11 20-inch PMTs • 18,000 20-inch PMTs • 13,000 MCP-PMT developed for JUNO by NNVT, use of transmission and reflection cathodes to increase quantum efficiency • 5,000 Dynode PMTs (Hamamatsu, R12860HQE), 2.7 ns FWHM TTS • Average photon detection efficiency 28.4% • HV divider mass production is ongoing • 7000 PMTs have been potted with multiple water- proof layers • Implosion protection covers were designed and produced 12 3-inch PMTs • 25,600 3-inch HZC Photonics PMTs • Double calorimetry system in JUNO together with the 20-inch PMT system • Correct non-linear response of 20-inch PMT • Increase dynamic range • Standalone measurement of solar neutrino oscillation parameters • All 3-inch PMTs have been produced 13 Calibration System • 1D: Automatic Calibration Unit (ACU) • 2D: Cable Loop System (CLS) and Guide Tube Calibration System (GTCS) • 3D: Remotely Operated Vehicle (ROV) • Auxiliary systems: Calibration house, Ultrasonic Sensor System (USS), CCD and A Unit for Researching Online the LSc tRAnsparency (AURORA) 14 Muon Veto System • Water Cerencov detector • ~2400 20-inch MCP-PMT used • 35 ktons ultrapure water with circulation • Shield CD from ambient radioactivity and neutrons induced by cosmic rays • Veto muon induced backgrounds • Detection efficiency is expected to be larger than 99% • Top tracker • Reuse the Target Tracker walls from the OPERA experiment • 3-layer plastic scintillator modules are already at JUNO site 15 Taishan Antineutrino Observatory CDR: arXiv 2005.08745 • TAO, a satellite experiment of JUNO • Precision measurement of the reactor anti-neutrino spectrum with sub-percent energy resolution in the major energy range (~2% @ 1 MeV) • Provide model-independent reference spectrum for JUNO • Provide a benchmark measurement to examine nuclear database • Conceptual design released • 10 m2 SiPM with QE=50% • 2.8 ton GdLS (FV mass 1 ton) at -50 oC • 4500 p.e./MeV from MC simulation • 30 m from Taishan reactor (4.6 GWth) • 2000 antineutrinos/day with 50% efficiency • Expected to start operation in 2022 16 Civil Construction • Slope tunnels and vertical shafts are finished. • Experimental cavern digging was just finished in Dec 2020. 17 Conclusion • JUNO is a multipurpose neutrino observatory with rich physics potential, including determining neutrino mass ordering, precisely measuring the oscillation parameters, observing supernova neutrinos, detecting atmospheric neutrinos, solar neutrinos, geo-neutrinos etc. • The sub-system R&D and production are well underway • JUNO is expected to start data taking in 2022 • Stay tuned! 18 Backup 19.
Recommended publications
  • Juno Telecommunications
    The cover The cover is an artist’s conception of Juno in orbit around Jupiter.1 The photovoltaic panels are extended and pointed within a few degrees of the Sun while the high-gain antenna is pointed at the Earth. 1 The picture is titled Juno Mission to Jupiter. See http://www.jpl.nasa.gov/spaceimages/details.php?id=PIA13087 for the cover art and an accompanying mission overview. DESCANSO Design and Performance Summary Series Article 16 Juno Telecommunications Ryan Mukai David Hansen Anthony Mittskus Jim Taylor Monika Danos Jet Propulsion Laboratory California Institute of Technology Pasadena, California National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Pasadena, California October 2012 This research was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. Reference herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise, does not constitute or imply endorsement by the United States Government or the Jet Propulsion Laboratory, California Institute of Technology. Copyright 2012 California Institute of Technology. Government sponsorship acknowledged. DESCANSO DESIGN AND PERFORMANCE SUMMARY SERIES Issued by the Deep Space Communications and Navigation Systems Center of Excellence Jet Propulsion Laboratory California Institute of Technology Joseph H. Yuen, Editor-in-Chief Published Articles in This Series Article 1—“Mars Global
    [Show full text]
  • Atlas V Juno Mission Overview
    Mission Overview Atlas V Juno Cape Canaveral Air Force Station, FL United Launch Alliance (ULA) is proud to be a part of NASA’s Juno mission. Following launch on an Atlas V 551 and a fi ve-year cruise in space, Juno will improve our understanding of the our solar system’s beginnings by revealing the origin and evolution of its largest planet, Jupiter. Juno is the second of fi ve critical missions ULA is scheduled to launch for NASA in 2011. These missions will address important questions of science — ranging from climate and weather on planet earth to life on other planets and the origins of the solar system. This team is focused on attaining Perfect Product Delivery for the Juno mission, which includes a relentless focus on mission success (the perfect product) and also excellence and continuous improvement in meeting all of the needs of our customers (the perfect delivery). My thanks to the entire ULA team and our mission partners, for their dedication in bringing Juno to launch, and to NASA making possible this extraordinary mission. Mission Overview Go Atlas, Go Centaur, Go Juno! U.S. Airforce Jim Sponnick Vice President, Mission Operations 1 Atlas V AEHF-1 JUNO SPACECRAFT | Overview The Juno spacecraft will provide the most detailed observations to date of Jupiter, the solar system’s largest planet. Additionally, as Jupiter was most likely the fi rst planet to form, Juno’s fi ndings will shed light on the history and evolution of the entire solar system. Following a fi ve-year long cruise to Jupiter, which will include a gravity-assisting Earth fl y-by, Juno will enter into a polar orbit around the planet, completing 33 orbits during its science phase before being commanded to enter Jupiter’s atmosphere for mission completion.
    [Show full text]
  • Lessons Learned from the Juno Project
    Lessons Learned from the Juno Project Presented by: William McAlpine Insoo Jun EJSM Instrument Workshop January 18‐20, 2010 © 2010 All rights reserved. Pre‐decisional, For Planning and Discussion Purposes Only Y‐1 Topics Covered • Radiation environment • Radiation control program • Radiation control program lessons learned Pre‐decisional, For Planning and Discussion Purposes Only Y‐2 Juno Radiation Environments Pre‐decisional, For Planning and Discussion Purposes Only Y‐3 Radiation Environment Comparison • Juno TID environment is about a factor of 5 less than JEO • Juno peak flux rate is about a factor of 3 above JEO Pre‐decisional, For Planning and Discussion Purposes Only Y‐4 Approach for Mitigating Radiation (1) • Assign a radiation control manager to act as a focal point for radiation related activities and issues across the Project early in the lifecycle – Requirements, EEE parts, materials, environments, and verification • Establish a radiation advisory board to address challenging radiation control issues • Hold external reviews for challenging radiation control issues • Establish a radiation control process that defines environments, defines requirements, and radiation requirements verification documentation • Design the mission trajectory to minimize the radiation exposure Pre‐decisional, For Planning and Discussion Purposes Only Y‐5 Approach for Mitigating Radiation (2) • Optimize shielding design to accommodate cumulative total ionizing dose and displacement damage dose and instantaneous charged particle fluxes near Perijove
    [Show full text]
  • Juno Spacecraft Description
    Juno Spacecraft Description By Bill Kurth 2012-06-01 Juno Spacecraft (ID=JNO) Description The majority of the text in this file was extracted from the Juno Mission Plan Document, S. Stephens, 29 March 2012. [JPL D-35556] Overview For most Juno experiments, data were collected by instruments on the spacecraft then relayed via the orbiter telemetry system to stations of the NASA Deep Space Network (DSN). Radio Science required the DSN for its data acquisition on the ground. The following sections provide an overview, first of the orbiter, then the science instruments, and finally the DSN ground system. Juno launched on 5 August 2011. The spacecraft uses a deltaV-EGA trajectory consisting of a two-part deep space maneuver on 30 August and 14 September 2012 followed by an Earth gravity assist on 9 October 2013 at an altitude of 559 km. Jupiter arrival is on 5 July 2016 using two 53.5-day capture orbits prior to commencing operations for a 1.3-(Earth) year-long prime mission comprising 32 high inclination, high eccentricity orbits of Jupiter. The orbit is polar (90 degree inclination) with a periapsis altitude of 4200-8000 km and a semi-major axis of 23.4 RJ (Jovian radius) giving an orbital period of 13.965 days. The primary science is acquired for approximately 6 hours centered on each periapsis although fields and particles data are acquired at low rates for the remaining apoapsis portion of each orbit. Juno is a spin-stabilized spacecraft equipped for 8 diverse science investigations plus a camera included for education and public outreach.
    [Show full text]
  • + New Horizons
    Media Contacts NASA Headquarters Policy/Program Management Dwayne Brown New Horizons Nuclear Safety (202) 358-1726 [email protected] The Johns Hopkins University Mission Management Applied Physics Laboratory Spacecraft Operations Michael Buckley (240) 228-7536 or (443) 778-7536 [email protected] Southwest Research Institute Principal Investigator Institution Maria Martinez (210) 522-3305 [email protected] NASA Kennedy Space Center Launch Operations George Diller (321) 867-2468 [email protected] Lockheed Martin Space Systems Launch Vehicle Julie Andrews (321) 853-1567 [email protected] International Launch Services Launch Vehicle Fran Slimmer (571) 633-7462 [email protected] NEW HORIZONS Table of Contents Media Services Information ................................................................................................ 2 Quick Facts .............................................................................................................................. 3 Pluto at a Glance ...................................................................................................................... 5 Why Pluto and the Kuiper Belt? The Science of New Horizons ............................... 7 NASA’s New Frontiers Program ........................................................................................14 The Spacecraft ........................................................................................................................15 Science Payload ...............................................................................................................16
    [Show full text]
  • 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.
    [Show full text]
  • Design and Status of JUNO
    Design and Status of JUNO Hans Theodor Josef Steiger on behalf of the JUNO Collaboration Physik-Department, Technische Universität München, James-Franck-Str. 1, 85748 Garching, Germany [email protected] Abstract. The Jiangmen Underground Neutrino Observatory (JUNO) is a 20 kton multi- purpose liquid scintillator detector currently being built in a dedicated underground laboratory in Jiangmen (PR China). JUNO’ s main physics goal is to determine the neutrino mass ordering using electron anti-neutrinos from two nuclear power plants at a baseline of about 53 km. JUNO aims for an unprecedented energy resolution of 3% at 1 MeV for the central detector, with which the mass ordering can be measured with 3 – 4 σ significance within six years of operation. Most neutrino oscillation parameters in the solar and atmospheric sectors can also be measured with an accuracy of 1% or better. Furthermore, being the largest liquid scintillator detector of its kind, JUNO will monitor the neutrino sky continuously for contributing to neutrino and multi-messenger astronomy. JUNO’s design as well as the status of its construction will be presented, together with a short excursion into its rich R&D program. 1. The JUNO Project – An Overview The Jiangmen Underground Neutrino Observatory (JUNO) is a Liquid Scintillator Antineutrino Detector currently under construction within a dedicated underground laboratory (~700 m deep) close to Jiangmen city (Guangdong province, PR China). After the completion, it will be the largest liquid scintillator detector ever built, consisting 20 kt target mass made of Linear Alkyl-Benzene (LAB) liquid scintillator (LS), monitored by about 18000 twenty-inch high-quantum efficiency (QE) photo- multiplier tubes (PMTs) and about 26000 three-inch PMTs providing a total photo coverage of ∼78%.
    [Show full text]
  • GRAIL: Achieving a Low Cost GDS Within a Multimission Environment
    Wallace Hu (JPL / Caltech) Patricia Liggett (JPL / Caltech) © 2013 by California Institute of Technology. Published by The Aerospace Corporation with permission. GRAIL : Gravity Recovery and Interior Laboratory . NASA Discovery Program . Two spacecrafts working in tandem to determine the structure and interior of Moon, and thermal evolution ▪ Spacecrafts provided by Lockheed Martin . Sally Ride Science (SRS) MoonKam ▪ Education Public Outreach ▪ Middle School students Identified points of interest on the moon ▪ 4 MoonKAM camera per spacecraft . Launched: September 10, 2011 . Completed: December 17, 2012 Successfully obtained gravity map of the Moon at a level of detail never obtained before GRAIL: Achieving a Low Cost GDS within a Multimission Env 2 . GRAIL ▪ MGSS (Multimission Ground System and Services) ▪ DSN (Deep Space Network) ▪ LM (Lockheed Martin) –External Partner GRAIL GDS (JPL) JPL LM MGSS DSN DSN ‐ Deep Space Network LM ‐ Lockheed Martin MOS ‐ Mission Operations System SDS ‐ Science Data Systems SRS ‐ Sally Ride Science GRAIL: Achieving a Low Cost GDS within a Multimission EnvDiagram courtesy of Glen Havens 3 MGSS (Multimission Ground System and Services ) . Shared Tools ▪ AMMOS (Advanced Multimission Operations System) ▪ Spacecraft Operations and Analysis ▪ Sequence generation ▪ Navigation . Shared Services (GRAIL / Odyssey / Juno) ▪ Delivery and Deployment ▪ Coordinated the deployment and delivery of AMMOS and Third Party Software to test and operational venues Planned and presented test and delivery review and ensure
    [Show full text]
  • Juno User Guide
    USER GUIDE Juno™ series Juno SB handheld Juno SC handheld NORTH & SOUTH AMERICA EUROPE & AFRICA ASIA-PACIFIC & MIDDLE EAST Trimble Navigation Limited Trimble GmbH Trimble Navigation 10355 Westmoor Drive Am Prime Parc 11 Singapore PTE Limited Suite #100 65479 Raunheim 80 Marine Parade Road Westminster, CO 80021 GERMANY #22-06 Parkway Parade USA Singapore, 449269 SINGAPORE www.trimble.com USER GUIDE Juno™ series Juno SB handheld Juno SC handheld Version 1.00 Revision B October 2008 F Trimble Navigation Limited Trimble; (ii) the operation of the Product under any specification other 10355 Westmoor Drive than, or in addition to, Trimble's standard specifications for its products; Suite #100 (iii) the unauthorized installation, modification, or use of the Product; Westminster, CO 80021 (iv) damage caused by: accident, lightning or other electrical discharge, USA fresh or salt water immersion or spray (outside of Product www.trimble.com specifications); or exposure to environmental conditions for which the Product is not intended; (v) normal wear and tear on consumable parts Legal Notices (e.g., batteries); or (vi) cosmetic damage. Trimble does not warrant or Copyright and Trademarks guarantee the results obtained through the use of the Product or Software, or that software components will operate error free. © 2008, Trimble Navigation Limited. All rights reserved. NOTICE REGARDING PRODUCTS EQUIPPED WITH TECHNOLOGY Trimble, the Globe & Triangle logo, and GPS Pathfinder are trademarks CAPABLE OF TRACKING SATELLITE SIGNALS FROM SATELLITE BASED of Trimble Navigation Limited, registered in the United States and in AUGMENTATION SYSTEMS (SBAS) (WAAS/EGNOS, AND MSAS), other countries. EVEREST, GeoBeacon, GeoXH, GeoXM, GeoXT, GPS OMNISTAR, GPS, MODERNIZED GPS OR GLONASS SATELLITES, OR Analyst, GPScorrect, H-Star, Juno, TerraSync, TrimPix, VRS, and Zephyr FROM IALA BEACON SOURCES: TRIMBLE IS NOT RESPONSIBLE FOR are trademarks of Trimble Navigation Limited.
    [Show full text]
  • MEASURING MAGNETIC FIELDS at OCEAN WORLDS. J. R. Espley1, G.A. Dibraccio1, and J. R. Gruesbeck1 1NASA's Goddard Space Flight C
    52nd Lunar and Planetary Science Conference 2021 (LPI Contrib. No. 2548) 1746.pdf MEASURING MAGNETIC FIELDS AT OCEAN WORLDS. J. R. Espley1, G.A. DiBraccio1, and J. R. Gruesbeck1 1NASA’s Goddard Space Flight Center (Code 695, Goddard Space Flight Center, Greenbelt, MD 20771, [email protected]) Summary: Magnetic field measurements have selective way. Collaborative approaches between the been a vital part of Solar System exploration for spacecraft team and experienced magnetometer decades. Measuring magnetic fields at ocean worlds instrument teams can often allow for relatively easy will yield important science results. Magnetometers are magnetic cleanliness programs. Often times, the easiest very low resource instruments (even with magnetic approach is simply a relatively long boom to keep the cleanliness). We welcome interest in collaborations for sensor away from the spacecraft. Such booms do cost future missions. spacecraft resources (mass, volume, and budget) but Ocean World Magnetometer Science Topics: often these costs are very modest and allow Magnetic fields tell us about a world’s: comparatively lax magnetic cleanliness programs. In all plasma environment (magnetosphere, ionosphere) cases, the most appropriate solution will depend on the volatile escape (e.g. plumes, atmospheric erosion), science requirements. An experienced magnetometer distribution of conducting materials (e.g. water, instrumentation team can easily help craft this metal) appropriate approach and keep the overall impact of the Example Ocean Worlds Destinations: The magnetic investigation modest compared to the very potential future targets for magnetic field investigations significant science results. are abundant (figures 1a-d). As examples, we could detect and characterize subsurface water or magma oceans (e.g.
    [Show full text]
  • NASA Response to the 2020 Planetary Mission Senior Review
    National Aeronautics and Space Administration Headquarters Washington, DC 20546-0001 Reply to Attn of: Science Mission Directorate/PSD January 8, 2021 NASA Response to the 2020 Planetary Mission Senior Review Background NASA’s Planetary Science Division is currently operating more than a dozen spacecraft across the solar system. Upon completion of their Prime Mission (PM), each of these missions may undergo a Senior Review every three years in order to assess whether operations should continue during an Extended Mission (EM). These extended missions leverage NASA’s large investment in order to perform continued science operations at a cost far lower than developing a new mission. In some cases, the extensions allow missions to continue to acquire valuable long- duration datasets, while in other cases, EMs allow missions to visit new targets, with entirely new science goals. 2020 Senior Review In the fall of 2020, NASA requested an external review of extended mission proposals submitted by the Juno and InSight mission teams. The proposals submitted were reviewed by independent panels of experts, with backgrounds in science, operations, and mission management. The panels reported to a Review Chair, who made recommendations to NASA. Prime Mission Accomplishments The review panels found that both the Juno and InSight missions have produced exceptional science and achieved all or most of their original science goals. The Juno spacecraft and its team have explored the internal structure of Jupiter and its diffuse core, have detected unexpected structure in Jupiter’s magnetic field, and have found the planet’s atmospheric dynamics to be far more complex than previously thought.
    [Show full text]
  • High Performance Computing for Flight Projects at JPL
    National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Pasadena, California High Performance Computing for Flight Projects at JPL Chris Catherasoo, Ph.D. California Institute of Technology HPC User Forum Meeting Bruyères-le-Châtel, France 3-4 October 2011 National Aeronautics and Space Administration Jet Propulsion Laboratory Outline California Institute of Technology Pasadena, California . Introduction . JPL and its mission . Current flight projects . HPC resources at JPL . Institutional HPC resources . HPC resources at NASA Ames . Examples of HPC usage by flight projects . Entry, descent and landing simulations . The Phoenix Mars Lander radar ambiguity . Mars Science Laboratory supersonic parachute design . Juno planetary protection trajectory analysis . Future work . Evolutionary computing . Low-thrust orbit optimization 2 HPC for Flight Projects at JPL 3-4 Oct 11 National Aeronautics and Space Administration Jet Propulsion Laboratory Outline California Institute of Technology Pasadena, California . Introduction . JPL and its mission . Current flight projects . HPC resources at JPL . Institutional HPC resources . HPC resources at NASA Ames . Examples of HPC usage by flight projects . Entry, descent and landing simulations . The Phoenix Mars Lander radar ambiguity . Mars Science Laboratory supersonic parachute design . Juno planetary protection trajectory analysis . Future work . Evolutionary computing . Low-thrust orbit optimization 3 HPC for Flight Projects at JPL 3-4 Oct 11 National
    [Show full text]