Low Temperature Electronics for Space and Terrestrial Applications - - PowerPoint PPT Presentation

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Low Temperature Electronics for Space and Terrestrial Applications - - PowerPoint PPT Presentation

Oct 16, 2022 48 likes •422 views

Low Temperature Electronics for Space and Terrestrial Applications Richard L. Patterson Ahmad Hammoud NASA Glenn Research Center QSS Group MS 309-2 NASA Glenn Research Center Cleveland, OH 44135 Cleveland, OH 44135

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SLIDE 1

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

Low Temperature Electronics for Space and Terrestrial Applications

Richard L. Patterson Ahmad Hammoud

NASA Glenn Research Center QSS Group MS 309-2 NASA Glenn Research Center Cleveland, OH 44135 Cleveland, OH 44135 Richard.L.Patterson@grc.nasa.gov Ahmad.Hammoud@grc.nasa.gov

Scott S. Gerber Malik Elbuluk

ZIN Engineering University of Akron NASA Glenn Research Center Electrical & Computer Engineering Dept. Cleveland, OH 44135 Akron, OH 44325 Scott.S.Gerber@grc.nasa.gov melbuluk@uakron.edu

Eric Overton John Dickman

NASA Glenn Research Center NASA Glenn Research Center MS- 301-5 MS 302-2 Cleveland, OH 44135 Cleveland, OH 44135 Eric.Overton1@grc.nasa.gov John.Dickman@grc.nasa.gov

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SLIDE 2

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

OUTLINE

  • 1. Deep Space Temperature Requirements

And Applications

  • 2. Terrestrial Applications
  • 2. Low Temperature Electronics at NASA GRC
  • 3. Power Electronic Components, Circuits and Systems
  • 4. Selected Results
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SLIDE 3

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

44 K -229 °C Pluto 51 K -222 °C Neptune 64 K -209 °C Uranus 90 K -183 °C Saturn 122 K -151 °C Jupiter 226 K -47 °C Mars 279 K 6 °C Earth 328 K 55 °C Venus 448 K 175 °C Mercury

Spacecraft Temperature

(Sphere, Abs. = 1, Emiss. = 1 Internal Power = 0)

Distance from Sun

Temperature Data for Planetary Missions

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SLIDE 4

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

Deep Space Electronics Temperature Requirements

Requirements

  • Electronics Capable of Low Temperature Operation
  • High Reliability and Long Life Time
  • Improved Energy Density and System Efficiency

Benefits of Low Temperature Electronics

  • Survive Deep Space Hostile Cold Environments
  • Eliminate Radioisotope and Conventional Heating Units
  • Improve System Reliability by Simplified Thermal Management
  • Reduce Overall Spacecraft Mass Resulting in Lower Launch Costs
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SLIDE 5

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

Low Temperature Electronics Program

Goals

  • Provide a technology base for the development of lightweight electronic

components and systems capable of low temperature operation with long lifetimes

  • Develop and characterize state-of-the-art components which operate at low

temperatures

  • Integrate advanced components into mission-specific low temperature circuits

and systems

  • Establish low temperature electronic database and transfer technology to mission

groups

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SLIDE 6

Glenn Research Center

_____________________________________________________________________________

Power and On-Board Propulsion Tech. Div. at Lewis Field

Space Applications of Low Temperature Electronics

  • Mars 2003 Lander/Rover
  • Mars Flyer
  • JWST (NGST)
  • Pluto Flyby
  • Jupiter Probe
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SLIDE 7

JAMES WEBB SPACE TELESCOPE (formerly NGST)

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

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SLIDE 8

L2 Point – Location of JWST

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

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SLIDE 9

Terrestrial Applications of Low Temperature Electronics

  • SMES
  • ICARUS
  • AMANDA / ICE BURG
  • Magnetic Levitation

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

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SLIDE 10

SMES Superconducting Magnetic Energy Storage

  • An energy storage system, used by electric utilities,

to stabilize voltages on power grids

  • The energy storage device is about the size of

a small number of 55 gallon drums

  • Typical energy storage is about 1 MegaJoule
  • System is mobile and about the size of a truck trailer
  • Used by the Tennessee Valley Authority, PacifiCorp,

Wisconsin Public Service, Scotland’s Orkney Islands, and an aluminum foundry in Austria

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

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SLIDE 11

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

ICARUS Imaging Cosmic and Rare Underground Signals

  • A neutrino detector (no charge and very little mass)
  • A large tank of liquid argon (-180 °C)
  • Needs some electronic components to operate at (-180 °C)
  • Located inside a mountain in northern Italy
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Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

ICARUS

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SLIDE 13

Amanda and Ice Cube Neutrino Detection System

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

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ICE CUBE NEUTRINO SENSOR SYSTEM Ice Cube Sensor Configuration

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

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SLIDE 15

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

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SLIDE 16

AMANDA / ICE CUBE PHOTOMULTIPLIER SENSOR

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

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SLIDE 17

AMANDA NEUTRINO DETECTION SYSTEM Inserting One Sensor into the Melted Hole

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

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SLIDE 18

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field Low Temperature Electronics Program Facilities

  • Three environmental chambers
  • Programmable rate for thermal cycling and long term soaking
  • Simultaneous and automated operation
  • Temp range from –193 °C to +250C
  • Ultra-low temperature environmental chamber for electronic testing to 20K
  • Instrumentation to evaluate digital and analog circuits
  • Computer controlled CV/IV semiconductor device characterization
  • Inframetrix infrared camera system
  • Multiple high voltage, HIGH current source measure units
  • Two programmable precision RLC instruments
  • Surface and volume resistivity chamber, film dielectric and capacitance test fixture,

breakdown voltage test cell

  • Passive components high-power test circuitry
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SLIDE 19

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

Facilities

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SLIDE 20

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

Analog Input (V) Digital Output (V) @ 25 °C Digital Output (V) @ -100 °C Digital Output (V) @ -190 °C 0.007 0.010 0.010 0.5 0.505 0.498 0.508 1 1.004 1.006 1.004 2 2.000 2.002 1.993 5 4.994 4.994 5.001 7.25 7.241 7.228 7.226 10 9.983 9.963 9.963 10.1 10.000 10.000 10.000

Digital Outputs at Three Temperatures for Various Analog Inputs

Commercial Off-the-Shelf 12-Bit Serial CMOS Analog-to-Digital Converter (Rated for Operation Between –40 °C and +85 °C)

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SLIDE 21

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

FACILITIES Digital to Analog Test Setup

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SLIDE 22

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

Low Temperature Electronics Program Products

  • Components

Magnetic Devices: Inductors & Transformers Capacitors Semiconductor Switches Batteries Transducers

  • Circuits

DC/DC Converters A/D Converters Oscillators PWM Control Circuits Other ICs

  • Systems

Energy Storage Power Conditioning Communication & Control

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SLIDE 23

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

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SLIDE 24

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

  • 200-180-160-140-120-100 -80 -60 -40 -20

20 40

Temperature ( C)

1 2 3 4 5 6 7 8 9 10

Output Voltage (V)

72Vin/0.5Aout 36Vin/0.5Aout 72Vin/4.0Aout 36Vin/4.0Aout

Output Voltage of a DC/DC Converter at Various Temperatures

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SLIDE 25

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

  • 200-180-160-140-120-100 -80 -60 -40 -20

20 40

Temperature ( C)

1 2 3 4

Output Voltage (V) 36Vin/0.5Aout 18Vin/0.5Aout 36Vin/2.5Aout 18Vin/2.5Aout

Output Voltage of Another DC/DC Converter At Various Low Temperatures

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SLIDE 26

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

EXPERIMENTAL SETUP & RESULTS

COMMERCIAL DC-DC CONVERTER MODULES

  • SPECIFICATIONS

Module Input Voltage (V) Output Voltage (V) Power (W) Operating Temp (°C) 1 9 –36 3.3 10

  • 40 to 60

2 36-72 3.3 10

  • 40 to 85

3 18-36 3.3 10

  • 40 to 70

4 18-36 3.3 13

  • 40 to 85

5 9-36 3.3 10

  • 40 to 85
  • TEST TEMPERATURE RANGE:

20°C to -190°C

  • TEST PARAMETERS:
  • INPUT VOLTAGE:

9-72V

  • LOAD CURRENT:

0 – 3.0 A

  • MEASURED PARAMETERS:
  • EFFICIENCY
  • OUTPUT VOLTAGE REGULATION
  • CURRENT RIPPLE CHARACTERISTICS
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SLIDE 27

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

EVALUATION SUMMARY OF SOME DC/DC CONVERTERS

Converter Specifications GRC Evaluations Mod # Input Voltage (V) Output Voltage (V) Power (W) Operating Temp. (°C) Observations & Comments Ceased Operation at (°C) 1 9 –36 3.3 10

  • 40 to 60

Vo dropped to 2.4 V at –140 °C; chip functioned down to –160 °C.

  • 160

2 36-72 3.3 10

  • 40 to 85

Vo lost regulation at –100 °C; converter still functioned to –196 °C.

  • 196

3 18-36 3.3 10

  • 40 to 70

Chip worked very well down to -120 °C. Input current oscillations occurred at all temperatures under heavy loading.

  • 120

4 18-36 3.3 13

  • 40 to 85

Oscillations in input current started at –80 °C.

  • 120

5 9-36 3.3 10

  • 40 to 85

Oscillations in input current observed at – 140 °C under heavy loading.

  • 180
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SLIDE 28

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

Time (10 us/div) (a) Temperature = 25°C Time (10 us/div) (b) Temperature = -190°C

(1 V/div) Reference Voltage (1 V/div) Reference Voltage (1 V/div) CT Ramp Signal (5 V/div) Output Voltage (1 V/div) CT Ramp Voltage (5 V/div) Output Voltage

Output Waveforms of a Pulse Width Modulation Controller At Room Temperature and –190 °C

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SLIDE 29

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

CAPACITORS

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SLIDE 30

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

CAPACITORS (Continued)

LEAKAGE CURRENT (nA) Type Unaged (RT) Aged (RT) In LN2 Polypropylene 1 1.80 1.20 0.02 Polypropylene 2 8.30 2.45 1.20 Polypropylene 3 9.50 5.00 0.06 Polycarbonate 3.20 2.64 0.14 Mica 7.10 10.80 0.10 Solid Tantalum 27.50 22.60 0.08

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SLIDE 31

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

NASA Langley Laminated Flexible Printed Circuit Board

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SLIDE 32

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

Control Computer

M M M M M M M

Temperature = 40 K Room Temperature Sun Shield

1 4

Motor Phase Drive Motor Select Motor Select Commands Parallel To Serial Serial To Parallel Power Supply

JAMES WEBB SPACE TELESCOPE MOTOR CONTROLLER

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SLIDE 33

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

  • 300
  • 200
  • 100
  • 250
  • 150
  • 50

50

Temperature (C)

0.1 0.2 0.3

Motor Power Supply Current (A)

Lin Engineering Stepper Motor Model 213-10-12 (Rated 0.3 Amps / phase) High Side Motor Selection Transistor Base Currents Approx 7 mA SGA9289 SiGe HBT, Vm=2.2V SGA9289 SiGE HBT, Vm=2.2V 2N1302 Ge npn bipolar, Vm=2.5V

STEPPER MOTOR CONTROLLER / SELECTOR SEMICONDUCTORS FOR USE AT ULTRALOW TEMPERATURES

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SLIDE 34

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

Switching Characteristics of a MOSFET Device At Various Temperatures Before Cycling

VGS = 4.0V VGS = 5.0V VGS = 7.0V VGS = 8.0V VGS = 12.0V VGS = 6.0V

0.0 0.5 1.0 1.5 2.0

VDS, Drain-to-source Voltage (V) (25 °C)

4 8 12 16 20

ID , Drain Current (A)

VGS = 5.0V VGS = 7.0V VGS = 8.0V VGS = 12.0V VGS = 6.0V

0.0 0.5 1.0 1.5 2.0

VDS, Drain-to-source Voltage (V) (-185 °C)

4 8 12 16 20

ID , Drain Current (A)

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SLIDE 35

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

Switching Characteristics of a MOSFET Device At Various Temperatures After Cycling

VGS = 4.0V VGS = 5.0V VGS = 7.0V VGS = 8.0V VGS = 12.0V VGS = 6.0V

0.0 0.5 1.0 1.5 2.0

VDS, Drain-to-source Voltage (V) (25 °C)

4 8 12 16 20

ID , Drain Current (A)

VGS = 5.0V VGS = 7.0V VGS = 8.0V VGS = 12.0V VGS = 6.0V

0.0 0.5 1.0 1.5 2.0

VDS, Drain-to-source Voltage (V) (-125 °C)

4 8 12 16 20

ID , Drain Current (A)

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SLIDE 36

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

CONCLUSIONS

  • LOW TEMPERATURE ELECTRONICS APPLICATIONS

DEEP SPACE MISSIONS SATELLITES CRYOGENIC INSTRUMENTATION

  • CAN COMPONENTS SURVIVE?

EXTREME TEMPERATURES HARSH ENVIRONMENTS

  • NEED TO SATISFY :

COMPACTNESS REDUCED WEIGHT RELIABILITY INCREASED EFFICIENCY

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SLIDE 37

Glenn Research Center

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Power and On-Board Propulsion Tech. Div. at Lewis Field

CONCLUSIONS (Continued)

  • COTS COMPONENTS, DEVICES, CIRCUITS AND SYSTEMS HAVE BEEN

CHARACTERIZED AT LOW TEMPERATURES NEED-BASED TECHNOLOGY-BASED TEMPERATURE RANGE BEYOND SPECIFICATIONS (-40OC OR -55 OC)

  • ADVANCED COMPONENTS ARE INTEGRATED INTO MISSION-SPECIFIC LOW

TEMPERATURE CIRCUITS AND SYSTEMS

  • MODIFY EXISTING
  • DEVELOP NEW TECHNOLOGIES