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Space Weather Effects on Satellite Electronic Systems Impacts on GRACE in Low Earth Orbit

Space Weather Effects on Satellite Electronic Systems Impacts on GRACE in Low Earth Orbit. A joint study of the University of Göttingen (1) and Astrium (2) Volker Bothmer 1 , Jan Dobschinski 1 , Markus Kinzler 2 , Wolfgang Keil 2 , Eckard Settelmeyer 2 , Stefan Dreizler 1.

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Space Weather Effects on Satellite Electronic Systems Impacts on GRACE in Low Earth Orbit

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  1. Space Weather Effects on Satellite Electronic SystemsImpacts on GRACE in Low Earth Orbit A joint study of the University of Göttingen (1) and Astrium (2) Volker Bothmer1, Jan Dobschinski1, Markus Kinzler2, Wolfgang Keil2, Eckard Settelmeyer2, Stefan Dreizler1 Third European Space Weather Week 13-17 November 2006 Brussels, Belgium

  2. Energetic particles at MeV energies impact (through atomic interactions) electronic systems:- Single Event Upsets (SEUs): remarkable as soft, non-destructive errors that appear as transient pulses in logic or support circuitry, or bitflips in memory cells or registers. - Single Event Latchups (SELs): resulting in high operating currents, above device specifications, which must be cleared by power resets. - Burnouts of power MOSFETS, gate ruptures, frozen bits, and noise in CCDs.

  3. Joint studies undertaken through collaborations by industry and scientific organizations to help clarify Space Weather Effects on Satellite Systems are currently in its infancy!

  4. The goal of the joint unique study by the University of Göttingen (science) and Astrium (industry) is to provide an in depth analysis of the causes of Single Event Upsets (SEUs) registered during the GRACE (Gravity Recovery And Climate Experiment) mission in low Earth‘s orbit (LEO).The GRACE SEU data set is provided by Astrium (Markus Kinzler, Wolfgang Keil, Eckard Settelmeyer) and scientifcally analyzed by the Institute for Astrophysics at University Göttingen (Jan Dobschinski, Volker Bothmer).

  5. Launch: 17 March 2002. Status: operational. Twin satellite system with mean distance of ~220 km. Satelite mass ~500 kg (each).Five scientific instruments. Orbit height ~500 km, inclination 90°, orbital period of 95 min.Science goals: Obtain high-resolution measurements of the Earth‘s gravitational field,establish global maps of the total ionospheric electron content (TEC) and characterize temperature and water vapour distribution in the Earth‘s atmosphere.

  6. Time Series of SEUs for GRACE 1 Main Memory after in depth data analysis. Major Events Superimposed on Background Background

  7. The GRACE 1 and 2 data analysis showed a systematic variation of the background rate with time, superimposed by major (> ~10 times) SEU rates during specific time-periods, at the order of days, registered by both satellies.Next Step: Investigation of the causes of both effects.

  8. The two time periods of major SEU rates during the GRACE misison were:28 – 30 October 2003 and20 January 2005.Both events occured in the aftermath of superfast (>2500 km/s) coronal mass ejections (CMEs) at the Sun based on analysis of SoHO observations.

  9. Solar Activity in October 2003 and January 2005 – SoHO/EIT 195 Å

  10. Correlated GOES, SoHO and ACE measurements GRACE SEUs

  11. Detailed Analysis of GRACE 2 SEUs during 26 Oct. – 1 Nov. 2003 Effects of CME 1 The Dip Effects of CME 2

  12. Correlated GOES, SoHO and ACE measurements GRACE SEUs

  13. Intensity-time profile of SEPs with respect to ICME center Cane et al., 1988.

  14. 30 day averages of GRACE 1 SEUs and Cosmic Ray Intensity

  15. Conclusions Major (>~10 times above background level) SEUs registered during the GRACE mission by both satelliteswere caused byintense proton (heavy ion) fluxes with Energies >~ 50 MeV caused by superfast (>~2500 km/s) frontside halo and W-limb CMEs. The normal SEU rate varies with Cosmic Ray Intensity - registered as individual particle impacts by GRACE 1 and GRACE 2. The role of the radiation belt populations and direct particle impacts through incident cosmic rays are under investigation as well as those of protons and heavy ions with respect to orbit parameters, shielding, tests of electronic memories, etc. Modeling with CREME96.

  16. Acknowledgemens Astrium for Data provision of the GRACE SEU data set and technical support. Jan Dobschinski for the in depth data analysis which he currently continues at Astrium/Friedrichshafen.

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