Electronics Design and Testing for Extreme Radiation and Cryo Environments

Transcription

1 Electronics Design and Testing for Extreme Radiation and Cryo Environments presentation to: Leora Peltz Boeing Research & Technology, Huntington Beach CA, USA Robert V. Frampton Boeing Space Exploration, Huntington Beach CA, USA BOEING is a trademark of Boeing Management Company. Copyright 2005 Boeing. All rights reserved.

2 Temperatures of Extreme Cold Astronomers have found the coldest spot in our solar system It's on our moon, right nearby. [Ref: Press in USA, Discovery Channel] NASA's new Lunar Reconnaissance Orbiter is making the first complete temperature map of the moon. Daytime and nighttime temperature observations of the lunar south pole recorded by the Diviner Radiometer Experiment, one of seven instruments on NASA's LRO. Image credit: NASA/JPL/UCLA

3 Exploration Missions to Follow the Water STUDY OF ICES IN SHACKLETON CRATER: Objective: determine the lateral extent, depth distribution, host mineral phase(s) and isotopic composition of hydrogen (and oxygen if hydrous phases are present) within regolith materials identified as potential "high hydrogen regions" by Clementine (lunar orbit, 1994, spectral mapping), Lunar Prospector (low polar orbit, 1998, looking for water), SMART-1 (low orbit, 2006). Clementine Shackleton crater Image from SMART-1 SMART-1 Lunar Prospector Ref: NASA and IEEE To explore and utilize in-situ resources, such as possible ice in dark Lunar craters (e.g. Shackleton at the Lunar South Pole), we need to develop instrumentation that can operate at cryogenic temperatures, down to 40K

4 Keeping the Electronics Warm (a few illustrative examples, which represent best current practices required today ) The Beagle 2 Probe shaded from the Sun by the body of Mars Express and also chilled by the extreme cold of deep space. To keep Beagle 2 warm, heaters are fitted at strategic locations and it is wrapped in 'multi-layer' spacecraft insulation. * Warm electronic boxes add weight and complexity * Thermal conditioning requires energy to operate heaters * Warm electronics boxes emphasize central architecture in larger systems

5 Approaches to Electronics for Cryogenic Temperatures (two illustrative examples from literature) 1. Application of Si technology (long-channel FETs and p_mosfets) Measured and modeling current of long channel FET at ~4K M.S.Carroll 1, E.Nordberg 1,2, T.Gurrieri 1, K.Eng 1, L.Tracy 1, G.TenEyck 1, K.Childs 1, J.Wendt 1, J.Stevens 1, M.P.Lilly 1, M.Eriksson 2 1 Sandia National Laboratories, Albuquerque USA 2 University of Wisconsin, Madison, USA Development of lateral quantum dots with cryogenic silicon circuit assisted read-out 216th ECS Meeting, Abstract #2321, The Electrochemical Society Characteristics of the p-mosfet ID-VDS characteristics at 1.8K T.Hirao l, Y.Hibi 1, M.Kawada 1, H.Nagata 1, H.Shibai 1, T.Watabe 1, M.Noda 2, and T.Nakagawa 3 1 Nagoya University, Furo-cho, Chikusa-ku, Nagoya, JAPAN 2 Nagoya City Science Museum, 17-1 Sakae 2-chorne, Naka-ku, Nagoya, JAPAN 3 The Institute of Space and Astronautical Science (ISAS), Yoshinodai, Sagamihara, Kanagawa, JAPAN Cryogenic readout electronics with silicon p-mosfets for the infrared astronomical satellite, ATRO-F Adv. Space Res. Vol. 30, No. 9, 2002

6 Approaches to Electronics for Cryogenic Temperatures (cont.) 2. Application of SiGe (silicon-germanium) technology: SiGe BiCMOS 43K SiGe HBT can operate over a wide range of temperatures. SiGe HBT 300K SiGe HBT SiGe HBT Reference: Georgia Institute of Technology and the RHESE SiGe Team As temperatures drop lower, the SiGe HBT current gain increases (opposite of Si BJT).

7 Development of SiGe Electronics for Extreme Environments * SiGe Integrated Electronics for Extreme Environments is part of the NASA RHESE program (Radiation Hardened Electronics for Space Exploration), funded under NASA ETDP (Exploration Technology Development Program). Program Manager: Dr. Andrew Keys, NASA MSFC (Marshall Space Flight Center) * SiGe Integrated Electronics for Extreme Environments is led by Georgia Institute of Technology. Principal Investigator: Prof. John D. Cressler * The SiGe team members include: Georgia Institute of Technology, JPL, Auburn University, University of Tennessee, Vanderbilt University, University of Maryland, University of Arkansas, Lynguent, BAE Systems, Boeing. System on a chip SiGe REU modular implementation Objective: Develop and demonstrate SiGe Electronics for Extreme Environments for distributed architecture for Moon and Mars. SiGe REU is a System-on-a-Chip that can operate at 43K without heaters. Also, SiGe HBTs are intrinsically Rad-Hard for TID.

8 Overview of Environmental Conditions on Europa Europa Geophysical Explorer has been designated by the Decadal Study as the highest priority flagship mission for planetary exploration, other than Mars. NASA is currently conducting a study for a Europa Orbiter mission. Credits: NASA High radiation environment at surface of Europa: 20 Mrad per month at the surface; dropping to 10-cm depth in europan ice is ~5 krad per month. The radiation dose is dominated by electrons and bremsstrahlung over depth values down to approximately 1 meter, below which protons dominate. Low Surface Temperature, varying from a low of 50 to 125K, with a mean of about 100K HIGH RADIATION + LOW TEMPERATURES

9 Overview of Environmental Conditions on Ganymede NASA has approved study of a Jupiter Systems Observer (JSO) Mission, which would orbit Ganymede (85-deg inclination) after a Jovian systems tour. Ganymede, with mean surface temp of ~120K, may also have sub-surface ocean, and also has its own intrinsic magnetic field. Radiation environment is several orders of magnitude less than at Europa orbit.

10 Overview of Environmental Conditions on Enceladus MODERATE RADIATION + LOW TEMPERATURES Temperatures in the areas of interest go as low as 65K craters Older features away from the South Pole Narrow angle camera images Tiger stripes at South Poles fractures Enceladus temperature map IR spectrometer data from the Cassini 3-rd flyby NASA/JPL/GSFC

11 Overview of Environmental Conditions on Titan The ESA TANDEM study envisions a mission to both Titan and Enceladus. NASA will be conducting a concurrent study for a Titan Mission. Eventually this will be a joint US/ESA mission if it is chosen (Titan is in competition with Europa and Ganymede to be the next Outer Planet flagship mission). Balloon would fly several km above surface at 75 Kelvin; it could drop small payloads to the surface, which has average temperature of 100 Kelvin. MODERATE RADIATION + LOW TEMPERATURES

12 Simulations Predict The Energy Spectrum of Radation JUPITER EUROPA SPECTRA, GIRE MODEL (Galileo Interim Radiation Electrons model, developed at JPL / Caltech) C EUROPA SPECTRA 0 deg inclination Integral & Diff. Fluence, #/cm 2 & #/cm 2 - MeV 1.E+17 1.E+16 1.E+15 1.E+14 1.E+13 1.E+12 1.E+11 1.E+10 1.E+09 1.E+08 1.E+07 1.E+06 1.E+05 1.E+04 1.E+03 1.E+02 1.E+01 1.E+00 1.E-01 Electron-Integral Ele ctr on-diff Proton-Integral Proton-Diff Particle Energy, MeV Ref: W. Atwell, Boeing IDS

13 Simulations Predict The Energy Spectrum of Radation JUPITER GANYMEDE SPECTRA, GIRE MODEL (Galileo Interim Radiation Electrons model, developed at JPL / Caltech) C Ref: W. Atwell, Boeing IDS

14 Simulations Predict the Energy Spectrum of Radiation SATURN ENCELADUS SPECTRA SATRAD MODEL Saturn moon, Enceladus Diff. 0 deg latitude - SATRAD Model Diff. Flux, #/cm 2 -MeV-day 1.E+13 1.E+12 1.E+11 1.E+10 1.E+09 1.E+08 1.E+07 1.E+06 1.E+05 1.E+04 1.E+03 1.E+02 1.E+01 1.E+00 1.E-01 1.E-02 1.E-03 1.E-04 1.E-05 1.E-06 1.E-07 1.E-08 1.E-09 electrons protons Particle Energy, MeV Ref: W. Atwell, Boeing IDS

15 Radiation Effects and Mitigations 1. TID effects (Total Ionizing Dose): definition: the cumulative long term damage resulting from impact of solar wind, trapped protons and trapped electrons. SiGe HBT has Multi-MRad MRad TID hardness, with no intentional hardening, due to its epitaxial base structure. SiGe transistor is intrinsically RadHard Reference: Georgia Institute of Technology, Vanderbilt University and the RHESE SiGe Team

16 Ground tests of effects of combined radiation + low temperature Technical Challenge: The environments encountered by missions to remote planets comprise both radiation and low temperature. How does low temperature influence the response of electronic circuits to radiation? I C, I B (A) Proton Irradiation Experiment 63MeV at 77K, on SiGe HBTs TID radiation effects on SiGe are less pronounced at low temperatures. tures. 1x10-2 1x10-3 1x10-4 1x10-5 1x10-6 1x10-7 1x10-8 1x10-9 5AM SiGe HBT Forward Gummel A E =0.5x1.0 μm 2 I C -Prerad I B -Prerad I B -600 krad I B -6 Mrad 300 K 77 K 1x V BE (V) β Peak (Post)/β Peak (Pre) Pre-rad Reference: Georgia Institute of Technology Forward Gain A E =0.5x1.0 μm 2 (5AM) A E =0.12x2.0 μm 2 (8HP) V CB =0 V 77 K 300 K Total Dose (krad(si))

17 Ground tests of combined radiation + low temperature effects (cont). Proton Irradiation Experiment 63MeV at 77K, on SiGe FETs 1x10-2 1x10-2 1x10-3 1x10-3 I D (A) 1x10-4 1x10-5 1x10-6 1x10-7 1x10-8 1x10-9 1x x x AM nfet W/L=10/1 V DS =50mV Irradiated@V GS =3.3V 77K Pre-rad 20 krad 50 krad 100 krad 300 krad 600 krad 1 Mrad V GS (V) I D (A) 1x10-4 1x10-5 5AM nfet W/L=10/1 1x10-6 V DS =3.3V 1x10-7 Irradiated@V GS =3.3V 1x K Pre-rad 20 krad 1x krad 1x krad 300 krad 1x krad 1 Mrad 1x V GS (V) Reference: Georgia Institute of Technology

18 Ground tests of combined radiation + low temperature effects. 2. SEE (Single Event Effects): definition: ionization when a single charged particle passes through a sensitive portion of an electronic device. 2.a No evidence of SEL (Single Event Latchup) ) in tests with SiGe Shift Registers operating at 50 GHz. 2.b Observed SEU sensitivity of SiGe Shift Registers operating at a 50 GHz. 50 GHz SiGe HBTs 1.6 Gb/sec Reference: Georgia Institute of Technology, Vanderbilt University and the RHESE SiGe Team Technical Challenge: Enhance the SEU of SiGe Electronics for Extreme Environments for operation at very high speeds.

19 Mitigation of combined radiation + low temperature effects. SiGe HBT SEU Mitigation by Circuit Design Latch-Level Circuit Hardening Scheme Reference: Georgia Institute of Technology leverage of NASA NEPP/DTRA Work in Progress: The SEU of SiGe Electronics for Extreme Environments is being enhanced by design at device level and at circuit level.

20 Testing approach for combined radiation+low temperature effects Tolerance of combined radiation + (cold) temperature environment CIRCUIT LAYOUT Design #1 P-tap; Substrate CIRCUIT LAYOUT DTI Y1 Z Z Z 7.6 um Z Z Z Z is defined by this design; same throughout Modeling/simulation provides initial evaluation of significance; motivates need for testing Y: This dimension will be fixed over all 4 designs Y = 2*Z + Tx length TCAD ION STRIKE SIMULATION Device and test-circuit level testing to validate modeling trends, allows calibration of models for circuit designs Models allow design optimization for radiation tolerance and provide required inputs for estimation of event / error rates. INTEGRATED DESIGN Circuit designers level COMPACT MODELS Used for efficient circuit design Included as part of mixed mode Full circuit level testing procedure supports pre-flight part qualification Reference: the RHESE SiGe Team ModLyng TM Generate radiation response model for compact model TCAD Device radiation Physics-based simulation of response device response Capture impact of multiple device effects Rad-Aware Compact models MIXED MODE More efficient than full TCAD Include operating context dynamics

21 VC (volts) Goal: Develop capability for SE testing at cryo Customized Dewar to enable in-situ SE testing, developed at Vanderbilt University in Nashville, TN USA. Ability to use both or either LHe/LN 2. (temperature ranges of Europa and Enceladus well-covered) Cold 10 MeV-cm2/mg; 5X mobility & lifetime 10 MeV-cm2/mg 0.5 Note: 5X increase in carrier mobility and lifetime Ve=0V represenative of reduced temperature Ion strike inside trench E E E E E E E E-06 Nominal Time (sec) Vb=0.51V VD=3.3V IC R=20 M Ω Ion R=500 Ω strike VC Vc=3.26V dim: 2.5μm Cold temp simulations: Questions of model fidelity Simulation size limits Experimental data required for calibration of simulation models, but very little available. Preliminary simulations of SE suggests radiation effects are harsher at cold temperatures. Goal: Acquire experimental data! Calibrate / validate models Qualify technology and circuits Reference: Georgia Institute of Technology, Vanderbilt University and the RHESE SiGe Team work in progress

22 In-Space Platforms for Testing and Validation The Van Allen Belts: can these be effective test-beds? Trapped Proton Differential Spectra Europa vs. GTO 1.E+17 1.E+15 1.E+13 Europa GTO Diff. Flux, #/cm 2 -MeV-day 1.E+11 1.E+09 1.E+07 1.E+05 Image credit: NASA 1.E+03 1.E+01 1.E Ref: W. Atwell, Boeing IDS Proton Energy, MeV

23 In-space Platforms for Testing and Validation (cont.) The Van Allen Belts: can these be effective test-beds? Trapped Electron Differential Spectra GTO vs. Europa 1.E+14 Europa GTO 1.E+12 Diff. Flux, #/cm 2 -MeV-day 1.E+10 1.E+08 Image credit: NASA 1.E+06 1.E Electron Energy, MeV Ref: W. Atwell, Boeing IDS

24 The life span of electronic circuits is curtailed by radiation. * Shielding adds undesired mass, and may also generate secondary particles, through spallation. Conventional electronics requires thermally-conditioned environments (warm-boxes). Concluding Summary * Warm boxes require heaters, which may lower the overall reliability of the subsystem. They expend energy which may become critical in many missions. * The range of temperatures encountered in a typical mission is wide from above 400K on the launch pad on Earth, to below 77K on the remote planet. This complicates significantly the thermal conditioning system. SiGe Electronics for Extreme Environments can reduce the required shield mass, and do away with the warm boxes.

25 References and Publications: Acknowledgments * The co-author of this paper * The SiGe Team * The NASA RHESE program, managed by Dr. Dr. A. Keys, MSFC. 1. H.B. Garrett, J.M. Ratliff, and R.W. Evans, Saturn Radiation (SATRAD) Model, NASA Jet Propulsion Laboratory JPL Publication 05-9, Pasadena, CA, October H.B. Garrett, I. Jun, J.M. Ratliff, R.W. Evans, G.A. Clough, and R.W. McEntire, Galileo Interim Radiation Electron Model, NASA Jet Propulsion Laboratory JPL Publication , Pasadena, CA, February J. Allison, et al., GEANT4 Developments and Applications, IEEE Transactions on Nuclear Science, vol. 53, issue 1, part 2, pp , Feb Information about MCNPX development can be found on the web site 5. Information about FLUKA development can be found on the web site

26 Acknowledgments

27 Thank you for listening to my presentation! Boeing campus High-bay building TPS shield and greetings from our hometown of Huntington Beach, Surf City USA