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Fourth NASA Space Weather and Robotic Mission Operations Workshop

National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology. Fourth NASA Space Weather and Robotic Mission Operations Workshop. Joseph C. Hunt Jr. Spitzer Deputy Mission Manger / Flight Director And Kennis Stowers

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Fourth NASA Space Weather and Robotic Mission Operations Workshop

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  1. National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Fourth NASA Space Weather and Robotic Mission Operations Workshop Joseph C. Hunt Jr. Spitzer Deputy Mission Manger / Flight Director And Kennis Stowers Spitzer Flight Control Team Lead / Flight Director September 27, 2012 Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive Pasadena, CA 91109-8099 USA

  2. Spitzer Observatory Dust Cover Telescope Solar Panels Spacecraft

  3. Mission Overview • The Spitzer Space telescope was launched on 25 August 2003 with a prime Cryogenic Mission Requirement of five years. • The helium depleted on 15 May 2009, ending the prime mission which started the Infrared Array Camera (IRAC) Warm Mission. • Second phase of extended mission - (FY ‘11 and FY ‘12). • As of August 2012 Spitzer completed 9 years of Science Operations. • Third phase of extended mission - (FY ‘13 and FY ’14).

  4. Instruments • Three science instruments • IRAC – Infrared Array Camera • Bands: 3.6 µm, 4.5 µm, 5.8 µm, and 8.0 µm • MIPS – Multi-band Imaging Photometer • Bands: 24 µm, 70 µm, and 160 µm • IRS – Infrared Spectrometer • Bands: 5.2 µm – 14.5 µm, 9.9 µm – 19.6 µm, 14.0 µm – 38.0 µm, and 18.7 µm – 37.2 µm • In the Cryogenic Mission, only one instrument was on at a time for a sequence duration of one to three weeks. • Primary mirror operates between 5.6 K and 12 K. • In the extended Warm Mission, only two bands of IRAC, 3.6 µm and 4.5 µm, will produce valid science data. • Primary mirror operates at ~26 K  

  5. (Current Orbit Information) • Spitzer is in a heliocentric, Earth-trailing orbit. It follows the Earth around the Sun. Its orbit is slightly more elliptical than the Earth’s, and most of the time it is farther away from the Sun than the Earth is, so it slowly recedes from Earth at about 0.1 AU/yr. • Current Orbit Information (Geocentric) • Distance = 159,781,376 km (~1.068 AU) • One-way light time = 532.92 s (~8m:53s) • Right Ascension (EME J2000) = 226.81 deg • Declination (EME J2000) = -18.09 deg

  6. Ground Segment Requirements Launch and Cryo Science Mission Phase • The Ground Segment, using both local and telemetry information, shall decide the time at which the Observatory is to resume science operations after a solar flare, and shall use real-time or stored sequence commands to accomplish this. • The Ground Segment shall recognize and respond to a solar flare event within 12 hours, including powering off non-essential loads as necessary to minimize radiation effects. • For impacts to the IRS and MIPS due to common electronics Warm Mission Science Phase • Monitor and annotate for S/C performance impacts and degraded science.

  7. Current Space Weather Monitor Sources • GOES • NOAA Alerts • GSFC SWRC-Space-Weather-Research-Center • SWRC Alerts • SWRC Model with Spitzer’s coordinates • SWRC Summary Reports

  8. MASTER ISA FORMAT • ISA #51348 Master ISA for space weather related events. • Two types of entries • Events with a weather alert message • Events without an alert message. • Event label format is "(Item Number) SWE_yyyy-mmdd_DOY“ or "(Item Number) NSE_yyyy-mmdd_DOY“ • Item Number is a two digit number beginning 01 in parentheses. • Allows for easier traceability from Description to Analysis • SWE is short for Space Weather Alert Event • NSE is short for Non Alert Space Weather Event • yyyy is the year of the weather alert message • mmdd is the month and day of the weather alert message • DOY is the Day of Year for the weather alert message. • In this ISA the "Description of Incident" contains the weather alert message information while all data analysis information is documented in the "Analysis and Impact" section of this ISA).

  9. Master Space Weather Summary

  10. Categories of Spitzer’s Space Weather Impacts • Mass Memory Card (MMC) Soft Scrub Errors • The EDAC continues to correct for single bit errors due to background radiation. The corrections are summed by the ratio of corrupted bits over time. (No functional impact to the Observatory or Science) • Solar Array Panel • Continuous trending provides performance statics for the output power. All deviations are correlated and dispositioned. (No functional impact to the Observatory or Science) • Star Tracker • STA component-level fault protection utilizes a series of checks to test the component health. We set a value to monitor the counter for fault persistence. (No functional impact to the Observatory or Science) • Infrared Array Camera (IRAC) Radhits • Based on the instrument exposure time the nominal observed Radhits are 4 per second with very little scatter (No functional impact to the Instrument, however Loss of 69.6 hours Science for event on DOY 067.)

  11. MMC Soft Scrub Errors EI-006 SWE_2012-0527_148

  12. MMC Soft Scrub Errors EI-002 SWE_2012-0307_067

  13. Solar Array Panel EI-004 SWE_2012-0416_106

  14. Star Tracker EI-006 SWE_2012-0527_148 STA Reset

  15. IRAC Instrument Radhits EI-002 SWE_2012-0307_067

  16. Spitzer Support to MSL • Spitzer provided Space Weather information to MSL based upon the Space Weather Alerts and right ascension orientation for both missions

  17. Summary • Since the Spacecraft continues to slowly recede from Earth at about 0.1 AU/yr, we constantly re-evaluate the contingency plan and use other data to augment GSFC-SWRC, GOES and STEREO data. • Spacecraft or IRAC instrument parameters may be used to assess space weather events. • Routine training sessions between the user community of the Space Weather Analysis Tool could further assist Flight Projects for space weather impacts. • An online subscription tool for the alert notification would streamline the process. • Could the disclaimer on the alert messages be reduced in size.

  18. Juno Project Overview • Salient Features • Juno is a Category 1, Class B mission • First solar-powered mission to the outer planets • Eight instrument payload to conduct gravity, magnetic and atmospheric investigations plus an E/PO camera • Polar orbiter spacecraft launches in August 2011 • 5 year cruise to Jupiter, JOI in July 2016 • 1 year operations, EOM via de-orbit into Jupiter in 2017 • Elliptical 11 day orbit swings below radiation belts to minimize radiation exposure • Key Juno partners: SwRI, JPL, ASI, LM-Denver and GSFC • Science • To improve our understanding of the origin of our solar system by understanding • the origin and evolution of Jupiter, Juno will: • Determine the global O/H ratio (water abundance) in Jupiter’s • atmosphere • Measure latitudinal variations in Jupiter’s deep atmosphere • (composition, temperature, cloud opacity, and dynamics) • Map Jupiter’s magnetic and gravitational fields • Characterize Jupiter’s polar magnetosphere and aurorae The technical data in this document is controlled under the U.S. Export Regulations; release to foreign persons may require an export authorization.

  19. Note from Juno Mission • Juno uses  the space weather alerts, however use is limited to inner cruise phase since the models do not go out beyond 2 AU.   • Can alert predictions model be scalable for missions beyond 2 AU? • While preparing for DSM-2 we observed the signature of the RF signal Doppler residuals shift as the signal traveled through the CME. • For reference DSM-2 executed at 2012-258T22:57 ERT. • Juno was exiting solar conjunction at ~2.3 AU from the Sun. • The alert visualization indicated the CME was ~2 AU from the Sun.

  20. Juno 2-way Doppler Residuals (9/14, DSS-14) 19:49 UTC, signal starts showing effect of going through CME during uplink & downlink 19:15 UTC, signal start showing effect of going through CME during downlink

  21. Juno Position on 9/14 (OWLT to Earth = 26.6 min)

  22. The analysis described in this paper was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. A large number of people from the Spitzer project, Juno project and support organizations at the Jet Propulsion Laboratory, Lockheed Martin Space System Company, and the Spitzer Science Center at the California Institute of Technology contributed to the development of the design and operations described herein.

  23. Back-up Material

  24. Current Orbit Information

  25. Cryo Phase Criteria used for Ops: notification alert based on Solar Flux level • When a 100pfu flux level is reached by solar protons of energy greater than 100MeV, an observation sequence will be terminated and the science instrument will be turned off. Operations will resume when the flux subsides. http://www.sec.noaa.gov/rt_plots/pro_3d.html

  26. SPITZER Monitors: by: FSW – Oct 2003

  27. SPITZER Monitors: by Flight Software – Jan 2005

  28. Spitzer Observatory Telescope • The primary mirror is 85 cm in diameter and made of beryllium. • The field-of-view angle of the telescope is 32′ (32 arcminutes). • The focal length is 10.2 m. • The total mass of the spacecraft at launch was 950 kg, including 50.4 kg of • liquid helium cryogen.

  29. Back-up material • In 1998, the science objectives for the Spitzer mission were defined as: • Deep surveys of oldest galaxies • Evolution and structure of ultra-luminous galaxies and quasars • Search for Brown Dwarfs • Evolution of stellar disks and planetary systems • For the extended warm, IRAC-only mission, the new science objectives are: • Study properties of extra-solar planets • Study galaxies during the first one billion years after the Big Bang • Complete census of the galaxy for young stars • Determine cosmic distance scale in the local universe

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