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Brookhaven National Laboratory Tandem Van de Graaff

The Tandem Van de Graaff is the Brookhaven accelerator most of the published planetary single event effect results were taken on. Its distinguishing property for a test planner is that ion energy is tunable at the machine rather than by putting a degrader in the beam, so there is no straggling in the energy distribution reaching the part, and a single event effects campaign can be turned around in a week [2].

Exposures are run in vacuum, and the energies are the lowest of the four accelerators on the radiation testing page: ranges in silicon of 30 to 200 micrometers, so parts are delidded and flip chips thinned, or at the high-LET tune not tested at all [1].

Two other Brookhaven beams are not this facility. The NASA Space Radiation Laboratory runs at energies whose ranges in silicon allow a whole circuit card assembly to be irradiated without delidding; its envelope, its spilled beam structure and the error that structure introduces are recorded on the radiation testing page. The Alternating Gradient Synchrotron was used to deliver 10 GeV per nucleon gold ions at 12 MeV-cm2/mg linear energy transfer at normal incidence, at a range far exceeding that of 200 MeV proton recoils, which was sufficient to latch up any device with a measurable cross section below that LET [6].

ParameterValue
OperatorBrookhaven National Laboratory [2]
LocationUpton, New York, United States
CommissionedNot published
TypeTandem electrostatic accelerator, heavy ion single event effects
Floor areaNot published
CapabilitiesHeavy ion beam line
Simulant or terrainNot applicable
InstrumentationNot published
Ground truthNot published. Test methods follow ASTM F1192 or JEDEC JESD57 [4][5]
Fidelity limitsMonoenergetic single-species beam; 30 to 200 micrometer range in silicon [1]
AccessUser facility. One week campaign turnaround achievable [2]
Cited byradiation testing, sensors and IMUs

No operator-written facility description is held. The envelope below comes from two users’ facility comparisons and from the ion, energy and range figures recorded in the campaigns themselves [1][2][3].

ParameterValue
Working volumeVacuum chamber; dimensions not published [4]
Test article limitsCeramic cover removed; flip chip thinned, or not tested at the high LET tune [1]
VacuumYes. Heavy ion exposures are run in vacuum [4]
TemperatureSet by the user. Campaigns here report room temperature to 90 C [3]
IlluminationNot applicable
SlopeNot applicable
Gravity offloadNot applicable
InstrumentationSupplied by the user

Two tunes. The low-LET tune covers 1 to 6 MeV-cm2/mg at 85 to 200 micrometers of range in silicon, with the ceramic cover removed, flip chips thinned, and no heat spreader or heat sink [1]. The high-LET tune covers 6 to 85 MeV-cm2/mg at 30 to 85 micrometers, and flip-chip parts should not be tested on it at all.

The ranges the campaign records give are consistent with that: bromine-81 at 287 MeV reaches 36 micrometers in silicon at LET 37.5 MeV-cm2/mg at normal incidence, and silicon-28 at 187 MeV reaches 74 micrometers at LET 7.8 [3].

Because ion energy is tunable at the machine, no degrader is needed to reach an intermediate energy, and the beam therefore arrives without the energy spread a degrader introduces [2]. That is what makes a one week turnaround possible.

The spectrum. Monoenergetic, single-species, as at every accelerator here. See the radiation testing page.

Penetration. The shortest ranges of the four facilities, 30 micrometers at the high-LET tune, so every part is opened and many are thinned [1]. A result taken here is a result on a modified part.

A stated envelope. Nothing held is written by the operator. The two tune rows above come from a JPL test-engineering guideline whose author states in its own foreword that the facility table was already out of date at publication [1].

MEMS accelerometer latchup against temperature, reported 2018. Two Colibrys parts were exposed under bromine-81 and silicon-28 [3]. The SF1600S showed a non-destructive latchup threshold between LET 7.88 and 11.44 MeV-cm2/mg above 70 C at maximum recommended bias, and the MS1002A between 11.44 and 19.71 above 70 C. The temperature dependence is the result worth carrying: on the MS1002A the latchup cross section at LET 37.5 and 1e7 ions/cm2 was 6.1e-6 cm2 at 75 C against 1.5e-6 cm2 at room temperature, a factor of four [3]. A latchup screen run at ambient understates the flight case by that factor for this part.

JPL compendia heavy ion exposures, 2007 to 2012. The vacuum heavy ion half of both JPL compendia was run here, with the in-air and longer-range work at Texas A&M [4][5]. Entries taken in this configuration include the Elpida EDS5104ABTA-75 512 Mbit SDRAM, upsetting above LET 2.7 MeV-cm2/mg, with a recoverable mode-register functional interrupt above 3.8 and a run of over a thousand consecutive errors above 5.4, the latter clearing on rewrite or power cycle [4]. The same part family in the later compendium upset and suffered functional interrupts below LET 2 at about 2e-9 cm2 per bit [5]. The sample size and method caveats that apply to every compendium entry are on the Texas A&M page.

References

  1. Guertin, S. M. (2018). Guideline for Single-Event Effect (SEE) Testing of System on a Chip (SOC) Devices . NASA, 20190002148. Source
    BibTeX
    @techreport{guertin2018guideline,
      title = {Guideline for Single-Event Effect (SEE) Testing of System on a Chip (SOC) Devices},
      author = {Guertin, Steven M.},
      number = {20190002148},
      institution = {NASA},
      year = {2018},
      url = {https://ntrs.nasa.gov/citations/20190002148},
      abstract = {The use of complex single and multicore processors with significant cache memory, on-chip peripherals, memory controllers, and high speed input/output (IO) that integrate many of the parts of a traditional computer system is becoming more common in space applications. Such devices are often referred to as system on a chip devices (SOCs), even though the term is used somewhat inaccurately due to the lack of analog and mixed signal subcircuits. These devices are complex combinations of single- or multi-core processors with memory controllers, high-speed input/output (IO), and other peripheral structures that formerly would have been handled by off-chip resources. In the past the processors were tested for single event effects (SEE) separately, and the peripherals were often put into custom application-specific integrated circuits (ASICs) along with other resources required by the user. Performance and cost pressures have pushed commercial devices to incorporate many of the functional blocks into a single chip, an SOC. The NASA Electronic Parts and Packaging Program (NEPP) has been examining ways to perform SEE radiation hardness assurance (RHA) testing of these processor-centric SOCs to achieve reasonable understanding of their performance in space missions.}
    }
  2. Thorbourn, D. (2013). JPL Radiation Effects Facilities . JPL Open Repository. Source
    BibTeX
    @inproceedings{thorbourn2013jpl,
      title = {JPL Radiation Effects Facilities},
      author = {Thorbourn, Dennis},
      booktitle = {JPL Open Repository},
      year = {2013},
      url = {https://dataverse.jpl.nasa.gov/dataset.xhtml?persistentId=hdl:2014/42836}
    }
  3. Daniel, A. C. and Allen, G. R. (2018). Heavy-Ion Test Results of Several Commercial Components for Use in a JPL Class D Interplanetary Mission Payload . JPL Open Repository. Source
    BibTeX
    @inproceedings{daniel2018heavy,
      title = {Heavy-Ion Test Results of Several Commercial Components for Use in a JPL Class D Interplanetary Mission Payload},
      author = {Daniel, Andrew C. and Allen, Gregory R.},
      publisher = {JPL Open Repository},
      year = {2018},
      url = {https://dataverse.jpl.nasa.gov/dataset.xhtml?persistentId=hdl:2014/48478}
    }
  4. McClure, S. S., Allen, G. R., Irom, F., Scheick, L. Z., Adell, P. C. and Miyahira, T. F. (2010). Compendium of test results of recent single event effect tests conducted by the Jet Propulsion Laboratory . IEEE Radiation Effects Data Workshop. Source
    BibTeX
    @inproceedings{mcclure2010compendium,
      title = {Compendium of test results of recent single event effect tests conducted by the Jet Propulsion Laboratory},
      author = {McClure, Steven S. and Allen, Gregory R. and Irom, Farokh and Scheick, Leif Z. and Adell, Philippe C. and Miyahira, Tetsuo F.},
      booktitle = {IEEE Radiation Effects Data Workshop},
      pages = {6-6},
      publisher = {IEEE},
      year = {2010},
      doi = {10.1109/redw.2010.5619495},
      abstract = {This paper reports heavy ion and proton-induced single event effect (SEE) results from recent tests for a variety of microelectronic devices. The compendium covers devices tested over the last two years by the Jet Propulsion Laboratory.}
    }
  5. Allen, G. R., Guertin, S. M., Scheick, L. Z., Irom, F. and Zajac, S. (2012). Compendium of recent test results of single event effects conducted by the Jet Propulsion Laboratory . IEEE Radiation Effects Data Workshop. Source
    BibTeX
    @inproceedings{allen2012compendium,
      title = {Compendium of recent test results of single event effects conducted by the Jet Propulsion Laboratory},
      author = {Allen, Gregory R. and Guertin, Steven M. and Scheick, Leif Z. and Irom, Farokh and Zajac, Stephanie},
      booktitle = {IEEE Radiation Effects Data Workshop},
      pages = {1-10},
      publisher = {IEEE},
      year = {2012},
      doi = {10.1109/redw.2012.6353747},
      abstract = {This paper reports heavy ion, proton, and laser induced single event effects results for a variety of microelectronic devices targeted for possible use in NASA spacecrafts. The compendium covers devices tested within the years of 2010 through 2012.}
    }
  6. Reddell, B. D. (1999). Orbiter Avionics Radiation Handbook . NASA, 20180002644. Source
    BibTeX
    @techreport{reddell1999orbiter,
      title = {Orbiter Avionics Radiation Handbook},
      author = {Reddell, Brandon D.},
      number = {20180002644},
      institution = {NASA},
      year = {1999},
      url = {https://ntrs.nasa.gov/citations/20180002644},
      abstract = {This handbook was assembled to document he radiation environment for design of Orbiter avionics. It also maps the environment through vehicle shielding and mission usage into discrete requirements such as total dose. Some details of analytical techniques for calculating radiation effects are provided. It is anticipated that appropriate portions of this document will be added to formal program specifications. }
    }