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Title: Flight Instrument Development in the Instrument Systems and Technology Division


1
Flight Instrument Development in the Instrument
Systems and Technology Division
  • Past, Present Future
  • Rich Barney
  • Chief, Instrument Systems Technology Division
  • Goddard Space Flight Center, NASA
  • February 6, 2007

2
There is no I in Team. Developing
Instruments at NASA/GSFC requires Teams of
diverse people from NASA, industry, other
government agencies, academia, worldly
collaborators, etc.Instruments shown in this
presentation were led by Principal Investigators
and Co-Investigators from the Science and
Exploration Directorate (Code 600).All
NASA/GSFC Branches, Divisions, and Directorates
contribute to the development of in-house
instruments.
Opening Notes
3
Riddle The Light Bulb
  • There are 2 rooms, one with 3 light bulbs (that
    never burn out) mounted on the wall, one with 3
    switches (that never wear out). Your goal to
    figure out which switch goes to which light bulb.
  • These 2 rooms are separate and once inside one,
    you cannot not see inside the other. The room
    with the 3 switches has 1 switch connected to 1
    light bulb in the other room. You are allowed to
    go into the room with the 3 light bulbs as often
    and for as long as you like, but you cannot
    damage anything (to look at the wiring, for
    instance). Once you do go into the room with the
    3 switches, you can flip the switches on and off
    as often and for as long as you like but as soon
    as you leave that room, you cannot return. You
    can then go back to the other room, but then you
    have to give your answer at that point.

A
Enter once
1 2 3
C
B
4
Riddle The Light Bulb
  • There are 2 rooms, one with 3 light bulbs (that
    never burn out) mounted on the wall, one with 3
    switches (that never wear out). Your goal to
    figure out which switch goes to which light bulb.
  • These 2 rooms are separate and once inside one,
    you cannot not see inside the other. The room
    with the 3 switches has 1 switch connected to 1
    light bulb in the other room. You are allowed to
    go into the room with the 3 light bulbs as often
    and for as long as you like, but you cannot
    damage anything (to look at the wiring, for
    instance). Once you do go into the room with the
    3 switches, you can flip the switches on and off
    as often and for as long as you like but as soon
    as you leave that room, you cannot return. You
    can then go back to the other room, but then you
    have to give your answer at that point.
  • ANSWER
  • You turn one on for 5-10 minutes, turn it off and
    turn another one on, then go to the other room
    and the warm off bulb is the first switch you
    hit, the on one is the second switch, and by
    default the last bulb (off, cold) is the switch
    you didnt touch.

5
Agenda
  • The Case for Instruments Development _at_ GSFC
  • Science Instruments 101
  • The Instrument Systems Technology Division
  • Science Instruments and Sensors at GSFC
  • Past
  • Present
  • Future
  • The how behind our success.
  • Instrument Development Process
  • Case Study
  • Best Practices
  • My Favorite Aerosmith Song

6
Why Should We Build Instruments?
Answers to questions as old as human curiosity
have always seemed beyond the reach of
science.. UNTIL NOW!
  • Understand the fundamental physical processes of
    the space environment from the Sun to Earth,
    to other planets, and beyond to the interstellar
    medium.
  • Observe, understand, and model the Earth system
    to discover how it is changing and to understand
    the consequences for life on Earth
  • Define the origins and societal impacts of
    variability in the Sun-Earth connection.
  • How did the solar system form?
  • How does life begin?
  • How can Humans explore Mars?
  • How did the Universe begin?
  • Does time have a beginning and an end?
  • Are we alone?

7
Exploration Science
Classical Science
Hypothesis driven
Robotic Precursors, human missions
Flight Demos of new capabilities
Integrated Exploration catalyzes Science!
Engineering Capability Driven
Measurement driven
Applied Science
Science Enabling
Human on-site Activities
Science Pathways for Human Exploration of
Moon/Mars involve all 3 facets
8
(No Transcript)
9
Science Instrument Development _at_ GSFC
  • Instrument Development enables NASA to pioneer
    the future . . . to explore . . . to do what has
    never been done before.
  • The message is simple -- Only the combined
    creativity of engineers and scientists working
    together can develop instruments for measuring
    the previously "unmeasured" or "unmeasurable".
    That's what we do! And that's why NASA is unique
    and its what brings back the fantastic
    discoveries that rewrite textbooks and inspires
    us to go further!!!So, we need breakthrough
    measurement systems especially at places like
    Mars and to our own planet Earth, and someday at
    places as inhospitable as Venus.
  • GSFC is leading the world in development of
    challenging technology that will be used to
    enable future scientific measurements.
  • We build instruments to explore ourselves, the
    world and the universe while answering compelling
    science questions.

10
Agenda
  • The Case for Instruments Development _at_ GSFC
  • Science Instruments 101
  • The Instrument Systems Technology Division
  • Science Instruments and Sensors at GSFC
  • Past
  • Present
  • Future
  • The how behind our success.
  • Instrument Development Process
  • Case Study
  • Best Practices
  • My Favorite Aerosmith Song

11
What is an Instrument?
12
Direct Sensing Instruments
  • Direct-sensing instruments interact with
    phenomena in their immediate vicinity and
    register characteristics of them.
  • Measure the strength and orientation of electric
    and magnetic FIELDS.
  • Measure the species, density and temperature of
    neutral (atoms/molecules) and charged
    (electrons/ions) PARTICLES
  • Examples of In Situ or Direct Sensing Instruments
  • High-energy Particle Detectors
  • Low-Energy Charged-Particle Detectors
  • Plasma Instruments
  • Dust Detectors
  • Magnetometers
  • Plasma Wave Detector

MAG/ER Magnetometer/Electron Reflector launched
aboard the Mars Global Surveyor on November 7,
1996.
INMS Ion Neutral Mass Spectrometer launched
aboard the Cassini spacecraft on October 15, 1997.
NGIMS Neutral Gas and Ion Mass Spectrometer
launched aboard the Contour spacecraft on July 3,
2002.
13
Passive Remote Sensing
  • Passive Remote Sensing instruments detect natural
    energy that is reflected or emitted from the
    observed scene.
  • Passive instruments sense only radiation emitted
    by the object being viewed or reflected by the
    object from a source other than the instrument.
  • Reflected sunlight is the most common external
    source of radiation sensed by passive
    instruments.
  • Examples of Passive Remote Sensing Instruments
  • Planetary Radio Astronomy Instruments
  • Imaging Instruments
  • Polarimeters
  • Photometers
  • Spectrometers

Spitzer/ Infrared Array Camera
14
A Few Examples of Passive Remote Sensing
Instruments Developed at GSFC
XRS-2 X-Ray Spectrometer Launched aboard the
Suzaku spacecraft on July 10, 2005.
DMR, FIRAS, DIRBE Microwave and Infrared Remote
Sensing Instruments launched aboard COBE on
November 18, 1989.
CIRS Composite Infrared Spectrometer Launched
aboard the Cassini spacecraft on October 15, 1997.
CoSMIR Conically Scanning Millimeter-Wave
Imaging Radiometer has flown several times aboard
the ER-2.
LAC LEISA Atmospheric Corrector launched
aboard EO-1 on November 21, 2000.
15
Active Remote Sensing
  • Active instruments provide their own energy
    (electromagnetic radiation) to illuminate the
    object or scene they observe.
  • They send a pulse of energy from the sensor to
    the object and then receive the radiation that is
    reflected or backscattered from that object.
  • Examples of Active Remote Sensing Instruments
  • Radar (Radio Detection and Ranging)
  • Scatterometer
  • LIDAR (Light Detection and Ranging)
  • Laser Altimeter

ICESat/Geoscience Laser Altimeter System
16
A Few Examples of Active Remote Sensing
Instruments Developed at GSFC
MOLA-2 Mars Orbiting Laser Altimeter launched
aboard the Mars Global Surveyor on November 7,
1996.
MLA Mercury Laser Altimeter launched aboard
the Messenger spacecraft on August 3, 2004.
Mercury arrival is 2011.
CRS Cloud Radar System has completed Many
Cal/Val flights.
Aquarius L-Band Microwave Radiometer For ESSP
future mission.
17
Agenda
  • The Case for Instruments Development _at_ GSFC
  • Science Instruments 101
  • The Instrument Systems Technology Division
  • Science Instruments and Sensors at GSFC
  • Past
  • Present
  • Future
  • The how behind our success.
  • Instrument Development Process
  • Case Study
  • Best Practices
  • My Favorite Aerosmith Song

18
Instrument Systems Technology Division
Our Mission To enable scientific discovery and
exploration by developing state-of-the-art
technologies and world -class flight instruments.
We research, develop, design, build, integrate,
test laser electro-optic components systems
for present future space flight deployment or
ground/air validation.
We provide optical engineering expertise in the
design, development and testing of
state-of-the-art optical instruments, subsystems,
and components.
We provide space flight cryogenic Cooling
systems from room temperature to as close as
possible to absolute zero.
We build a wide range of products, from custom
detectors to entire turn-key systems that span
the electromagnetic spectrum.
We provide engineering and technology expertise
enabling end-to-end conceptualization and
development of microwave instrument systems.
We provide technical leadership for the full life
cycle of instrument development.
19
Code 550 Organization Chart
Division Chief Rich Barney Admin Officer Shelly
Standiford Secretary Becky Richardson
Associate Division Chiefs Peter Maymon Felicia
Jones-Selden (detail) Mark Matsumura
Assistant Division Chief Howard Branch
Secretary Susan Wright
Senior Staff Chief Engineer Dr. Murzy
Jhabvala Instrument Engineering Dr. Jay
Smith Senior Staff Lee Feinberg
Assistant Chief for Technology Carl Stahle
Assoc. Chief (501) In-House Instruments Elaine
Slaugh Institution Resource Analyst Donna Drummond
Information Technology Engineering Manager Art
Maples
Optics Head Pete Maymon (acting) Assoc. Head
Rene A Boucarut Assoc. Head Kim Mehalick
Detector Systems Head Pete Shu Assoc. Head Dr.
Carl Stahle Assoc. Head Laddawan Miko
Lasers and Elector-Optics Head Dr. Mike
Krainak Assoc. Head Tony Seas
Cryogenic and Fluids Head Dr. Susan Breon Assoc.
Head Judy Gibbon
Microwave Instruments Technology Head Cathy
Long Assoc. Head Terry Doiron
Instrument Systems Head John Leon Assoc. Head
(IM) Juan Rivera Assoc. Head (ISE) Frank
Kirchman
20
Code 551 Optics Branch
  • Optical System Design and Analysis
  • Materials and Thin Films
  • Opto-Mechanical Design and Fabrication
  • Optical Component Development and Test
  • Optical System Alignment and Test
  • Wavefront Sensing and Control

Grazing Incidence Optics
Diffraction Grating Evaluation Facility
Optical Coatings
HST WFC 3
Sub mm Far-IR
IR VIS
UV X-RAY ?-RAY
Single Crystal Si Mirror
Wavefront Sensing and Control
Cryogenic Optical Alignment and Testing
Diffractive Optics
21
Code 552 Cryogenicsand Fluids Branch
  • Cryogenic Research
  • Cryogenic Applications

Adiabatic Demagnetization Refrigerator
RHESSI Cryocooler
XRS ADR
NICMOS Cryo Cooler
4 - 10 K Cryocooler
Cryocooler
AMS cryocoolers
Temperature, Kelvin
22
Code 553 Detector Systems Branch
  • Focal Plane Systems
  • Cryogenic Detectors
  • Solid-state Detectors
  • MEMS Technology

MEMs Colloidal Thruster
Transition Edge Sensor Calorimeters
CdZnTe Arrays
Pop Up Detector
Sub mm Far-IR
IR VIS
UV X-RAY ?-RAY
GaN Detectors
Gallium Arsenide (GaAs) QWIP Detectors
6x6 calorimeter
MEMS-Micro Shutters
23
Code 554 Laser Electro Optics Branch
  • Power, Efficiency, Reliable
  • Improved Sampling
  • Wavelength Control

Laser Risk Reduction Program Diode Array Test and
Qualification Wavelength Conversion 1 micron
Laser Testbed Effort
Fiber Laser
Tropospheric Winds CO2, Ozone, Clouds Imaging
LIDAR
Laser Interferometer Space Antenna (LISA)
Diode pumped, NdYAG slab oscillator Laser
Transmitter (LTs)
Mercury Laser Altimeter
24
Code 555 MicrowaveInstrument TechnologyBranch
  • Deployables
  • Low Power Components
  • High Speed Data Systems
  • Wavefront Correction

Deployable Antenna for Radiometry
The Cloud Radar System
Aquarius L-Band Microwave Radiometer
Salinity Ultrastable Radiometer Testbed
Low Power Components for Radiometry
Conically Scanning MMW Imaging Radiometer
L-Band Imaging Scatterometer
25
  • Instrument Systems Engineering
  • Instrument Management
  • Proposal Management

Code 556 Instrument Systems Branch
Icesat/GLAS
XTE Proportional Counting Array
EO-1/LEISA AC
Astro-E/XRS2 GLAST/ACD NGST/IRMOS,RIVMOS SIRTIF/IR
AC SOFIA/SAFIRE,HAWC Swift/BAT VCL/MBLA Stereo/COR
1 Messenger/MLA HST/WFP3 Constellation X Inst.
Incubator Program
Cassini INMS, GCMS, CIRS
COBE DIRBE, FIRAS, DMR
26
Code 556 Instrument Systems Branch Work
Other (8) 20 Source Boards, Review Boards and
Technical Support
January 2007
January 2006
27
Major ISTD Facilities
  • The Diffraction Grating Evaluation Facility
    (DGEF) is a world-class, advanced resource that
    was developed at GSFC to evaluate optical
    components such as diffraction gratings, mirrors,
    and filters as well as detection systems used in
    space instrumentation with specific emphasis on
    the ultraviolet.
  • The Cryogenic Test Facility consists of numerous
    cryogenic dewars that enable testing of
    components, subsystems, and complete instruments.
  • The Detector Development Laboratory (DDL)
    contains modern semiconductor fabrication
    equipment for photolithography, wet chemical
    etching, reactive ion etching, oxidation,
    diffusion, thin film deposition, metallization,
    ion implantation and device characterization.
  • The Detector Characterization Laboratory (DCL) is
    a world-class resource in characterizing large
    format detector arrays. Current projects include
    HST, JWST, and ground based astrometrics
    instrument.
  • The Laser and Electro-Optics Laboratory consists
    of 7 individual laboratories with measurement
    capabilities that include optical communications
    (up to 700 Mbit/s) performance testing, fully
    automated laser diode accelerated performance
    station, fully automated diode pumped laser
    accelerated performance station, fully automated
    photon counting detector performance station,
    cryogenic laser diode test station, and a host of
    measurement equipment for laser diode, optical
    filter, photon counting detector, acousto-optic
    and electro-optic device and instrument testing
    (e.g., FTIR spectrometers).

28
Agenda
  • The Case for Instruments Development _at_ GSFC
  • Science Instruments 101
  • The Instrument Systems Technology Division
  • Science Instruments and Sensors at GSFC
  • Past
  • Present
  • Future
  • The how behind our success.
  • Instrument Development Process
  • Case Study
  • Best Practices
  • My Favorite Aerosmith Song

29
GSFC In- House Instrument Development History
Since 1988
30
GSFC In- House Instrument Development History
Since 1988
31
GSFC In- House Instrument Development History
Since 1988
32
Cosmic Background Explorer
This is the first Nobel Prize ever by a NASA
civil servant scientist. COBE was built entirely
in-house by NASA, including all instruments. The
Nobel Prize in Physics is the biggest prize in
Science.
33
Spitzer-Infrared Array Camera
Why IR Remote Sensing?
34
Cassini Composite Infrared Spectrometer
Cassini/CIRS was built in-house at GSFC
35
Cassini-Composite Infrared Spectrometer
36
Composite Infrared Spectrometer-Discovery of a
Lifetime! H2O on Enceladus
37
Cassini-Huygens Probe / Gas Chromatograph Mass
Spectrometer
Atmospheric Experiments Laboratory
The Cassini spacecraft and Huygens probe were
launched at 443 a.m. EDT, on October 15, 1997.
On December 24, 2004 (US Eastern Time), Cassini
deployed the Huygens probe. The probe descended
into the depths of Titan's atmosphere on January
14, 2005. The atmosphere entry phase of the
mission lasted 147 minutes. The probe continued
operations on the surface of Titan for an
additional 71 minutes.
38
SWIR Hyperspectral ImagerHeritage
Complete LEISA focal plane with spectral filter
LEISA AC on EO-1 Launch 2000
LEISA on LEWIS Launch 1997
LEISA on Ralph (Pluto) Launch 2006
39
Astro-E (X-Ray Spectrometer)
  • ASTRO-E was to be the Japan's fifth X-ray
    astronomy mission, but was unfortunately lost
    during launch (10 Feb 2000).
  • NASA approved a new mission which was a rebuild
    of Astro-E and launched July 10, 2005.
  • After launch, the X-ray Spectrometer (XRS) was
    activated and performed to specifications for
    almost three weeks.
  • Over the next week, helium gas entered the dewar
    vacuum space resulting in the liquid helium
    boiling off and venting to space.
  • Without the helium cryogen, the XRS instrument
    can no longer provide the planned science.
  • Next Step..fly XRS in space!!

Microcalorimeters
XRT (GSFC ISAS)
XRS (GSFC ISAS)
GSFCHe Insert (includes the ADR)
40
Time History of Spaceflight Lasers
41
IceSAT Mission
  • 1. Surface Altimetry
  • Range to ice, land, water, clouds
  • Time of flight of 1064 nm laser pulse
  • Digitizes transmit received 1064-nm waveforms
  • Resolutions 1 nsec for digitizer
  • Noise floor in altimetry 2.4 cm
  • 2. Laser pointing
  • Laser-beam pointing from star-trackers, laser
    camera gyro
  • lt10 cm single shot range resolution
  • lt1.5 arcsec angular resolution
  • 3. Atmospheric lidar
  • Laser back-scatter profiles from clouds
    aerosols
  • Uses 1064 nm 532 nm pulses
  • 75 m vertical resolution
  • Analog (1064 nm) photon counting (532nm)
    detection
  • Simultaneous, co-located measurements with
    altimeter

42
IceSat-Geoscience Laser Altimeter System
43
Geoscience Laser Altimeter System (GLAS) on the
ICESat Mission
gt 1 Billion laser measurements of Earths surface
and atmosphere through 11/05 and 8 campaigns
ICESat/ GLAS measured shaded relief map
ICESat/GLAS measured shaded relief map
Profiles across surface above Lake Vostok show lt
2.4 cm height resolution (15 times better
vertical resolution than MOLA)
The floating ice shelves act to hold back inland
grounded ice that can impact sea level
44
MESSENGER (Mercury Spacecraft) Mercury Laser
Altimeter (MLA)
Courtesy of MESSENGER Laser Team
45
SWIFT Gamma-Ray Bursts Hunter
What are Gamma-Ray Bursts (GRBs)?
  • Gamma-ray bursts (GRBs) are the brightest and
    most powerful events in the Universe since the
    Big Bang.
  • During their peak they emit more energy than all
    the Stars and Galaxies in the universe combined

Where do GRBs come from?
  • They come from all different directions of the
    sky and last from a few milliseconds to a few
    hundred seconds.

Burst Alert Telescope - BAT October, 1999 NASA
Selects Swift September, 2002 S/C arrives at
GSFC November 20, 2004 LAUNCH
How often do GRBs occur ?
  • They occur approximately once per day and are
    brief, but intense, flashes of gamma radiation.

What causes the GRBs?
  • So far scientists do not know what causes them.

Instrument Manager - Greg Frazier Instrument
Systems Engineer - Oscar Gonzalez Instrument IT
Manager - Dave Sohl Lead Scientist - Scott
Barthelmy
46
SWIFT Gamma-Ray Bursts Hunter
Coded Mask
UVOT
XRT
Power Converter Box
Tagged Source (2)
Thermal Radiator
37
Detector Array (16 Blocks)
64.5
44
Image Processor (2)
SWIFT
array
47
Swift Progression of Images
  • Rapid position determination of GRBs to
    sub-arcseconds
  • Burst Alert Telescope triggers on GRB, calculates
    position on sky to lt 4 arcmin
  • Spacecraft autonomously slews to GRB position in
    20-70 s
  • X-ray Telescope determines position to 3
    arcseconds
  • UV/Optical Telescope images field, transmits
    finding chart to ground

48
Earth Science Instruments
  • Blue Marble Tour
  • The original Blue Marble was a composite of
    Moderate Resolution Imaging Spectroradiometer
    (MODIS) observations with a spatial resolution
    (level of detail) of 1 square kilometer per pixel.

History of a Hurricane The Aqua AMSR-E is a
cooperative effort between NASA and the National
Space Development Agency (NASDA) of Japan, with
the collaboration of scientific and industry
organizations in both countries.
49
Agenda
  • The Case for Instruments Development _at_ GSFC
  • Science Instruments 101
  • The Instrument Systems Technology Division
  • Science Instruments and Sensors at GSFC
  • Past
  • Present
  • Future
  • The how behind our success.
  • Instrument Development Process
  • Case Study
  • Best Practices
  • My Favorite Aerosmith Song

50
GSFC In- House Instruments Under Development
51
Sea Surface Salinity
Radiometer
PI Dr. Gary Lagerloef, ESR Deputy PI Dr. David
LeVine, NASA/GSFC, Code 975
N. Martin, IM F. Pellerano, ISE
  • The Aquarius radiometer will provide the first
    global observations of sea surface salinity.
  • The measurement objectives are
  • Accuracy of 0.2 (Practical Salinity Scale) or
    lt0.1 K radiometer sensitivity
  • 100 kilometer resolution, weekly revisits
  • 3-year mission duration
  • The instrument is complemented with a
    scatterometer for surface roughness corrections.

Radiometer Back End (3)
Current Measurements
Radiometer Front End (3)
Deployable Boom
Sun Shade
Aquarius Measurements
Aquarius is a mission that addresses NASA ESE
questions about the global cycling of water and
ocean circulations response to climate change,
by measuring global ocean radiometric emission at
L-band which is influenced by surface salinity.
  • ESSP-3 selection on July 2002.
  • Launch date March 2009
  • Radiometer delivery August 2007
  • The mission is in the critical design phase.
  • Radiometer CDR is scheduled for August 22-23,
    2006
  • A radiometer engineering model has been
    fabricated and is currently in testing.
  • GSFC Co-PI, DPM, radiometer, operations
  • ESR PI, science
  • JPL PM, Inst.subsystems, scatterometer
  • CONAE Spacecraft, secondary payloads

52
Lunar Orbiter Laser Altimeter
PI Dr. David E. Smith, NASA/GSFC, Code
690 Deputy PI Dr. Maria T. Zuber, MIT
G. Jackson, IM R. Zellar, Deputy IM J. Cavanaugh,
ISE
406 mm
LOLA MEB OTA Power 34.4 watts Mass 12.3
kg Data 27.6 kbps
LOLA pulses an infrared laser that illuminates
the lunar surface with five distinct beams. The
instrument detects the reflected light yielding
measurements for range to the surface, roughness,
and reflectance. These measurements will provide
the data necessary to select interesting and safe
landing sites on the Moon along with the models
and reference system needed to navigate to those
sites.
432 mm
490 mm
Optic Transceiver Assembly (OTA)
Main Electronics Box (MEB)
  • Critical Design Review July 2006
  • Mission Critical Design Review November 2006
  • LOLA Pre-Environmental Review May 2007
  • LOLA Pre-Ship Review October. 2007
  • Delivery to LRO October 15, 2007

Beam Expander
Receiver Telescope
O. Aharonson CalTech J. Head Brown F.
Lemoine NASA GSFC G. Neumann MIT M.
Robinson NWU X. Sun NASA GSFC
  • Selected for LRO Payload December 2004
  • Preliminary Design Complete October 2005
  • EM testing and final design in progress
  • Long Lead flight fabrication in progress

53
JWST NIRSpec Detector Subsystem
DS PI Bernard Rauscher, NASA/GSFC, Code
665 NIRSpec PI Peter Jakobsen, ESA
S. Manthripragada, IM B. Derro and W. Roher ISE
NIRSpec Detector Subsystem Architecture
Focal Plane Electronics (FPE)
The Detector Subsystem (DS ) is part of the James
Webb Space Telescopes (JWST) NIRSpec Instrument,
a state-of-the-art near infrared, multi-object
spectrograph that measures redshift, metallicity,
and star formation rate in first light galaxies.
NIRSpec is capable of obtaining spectra of 100 or
more astronomical sources simultaneously over the
0.6 5 micron wavelength range at spectral
resolutions of R100, 1000 and 3000. The DS
architecture consists of a Focal Plane Assembly
(FPA), two SIDECAR ASICs, Focal Plane Electronics
(FPE), cryogenic harness and DS Flight Software.
The FPA includes two Mercury Cadmium Telluride
2048x2048 pixel2 Sensor Chip Assemblies (SCAs).
The SIDECARs are cryogenic mixed signal ASICs
that provide clocks and biases to the SCAs,
perform 16-bit A/D conversion of SCA data and
transmit digital SCA data to the FPE. The FPE
contains redundant Power Distribution Units
(PDUs), FPE controller logic and FPA temperature
control circuits. The Flight Software commands
and monitors FPE functions, transmits exposure
commands and receives digital exposure data.
Focal Plane Assembly (FPA)
Temp Control Harness
SIDECAR-FPA Harness
FPE-SIDECAR Harness
SIDECAR ASICs
STM DS Delivery 12/06 ETU DS Delivery
4/07 Flight DS Delivery 1/08 NIRSpec
Instrument Delivery (to ISIM) 3/09 JWST
Launch No earlier than 7/13
The Detector Subsystem is part of the European
Space Agency (ESA) provided NIRSpec Instrument.
NIRSpec is one of four infrared instruments in
James Webb Space Telescopes Integrated Science
Instrument Module (ISIM).
Rockwell Scientific Company (FPA and SIDECAR ASIC
Provider) ITT Industries (FPA Packaging
Provider) EADS Astrium (NIRSpec Primary
Contractor Ottobrun, Germany)
Completed DS Preliminary Design Review.
Proceeding with plan to build and test prototype
hardware.
54
JWST NIRSpec Micro Shutter Subsystem
PI S. Harvey Moseley, NASA/GSFC, Code 665
D. Sohl, IM L. Sparr, ISE
The Micro Shutter Array (MSA) is a silicon-based
field-selectable programmable aperture mask for
the JWST Near-IR Spectrometer (NIRSpec).
Ground-based spectrometers traditionally use
drilled plates to permit light spectra from only
selected objects to reach the detectors. The MSA
replaces the drilled plates with four 2-D
addressable arrays of Si shutters (365 X 171),
allowing numerous source combinations to be
observed.
Microshutter Assembly Arrays are shown as quads
  • SM Micro-Shutter Assembly November 2006
  • DM Micro-Shutter Assembly (MSA) April 2007
  • DM MSA Control Electronics (MCE)April 2007
  • DM MSA to MSA Harness April 2007
  • Flight Micro-Shutter Assembly May 2008

The MSA (produced by GSFC) is part of the
European Space Agency - provided NIRSpec. The
NIRSpec is one of several instruments in JWSTs
Integrated Science Instrument Module (ISIM).
Currently producing 365 X 171 arrays for our
delivery models. The MSA design is proceeding
very well and initial model components are being
procured and tested. MSS Team is preparing for a
Summer TRL 6 Demo for the arrays.
None.
First fully-assembled substrate
55
MMS SMART
C. Principe, IM A. Ericsson, IM J. Lobell, ISE
SwRI PI James Burch
  • Overall Scientific Objectives To discover the
    detailed physics of the reconnection process
    including the factors that control it, its
    spatial distribution, and its temporal behavior.
  • Primary Science Questions
  • What are the kinetic processes responsible for
    collisionless magnetic reconnection, and how is
    reconnection initiated?
  • Where does reconnection occur in the magnetopause
    and in the magnetotail, and what influences where
    it occurs?
  • How does reconnection vary with time and what
    factors influence its temporal behavior?
  • How do flux transfer events and
    plasmoids/magnetotail flux ropes form, and how do
    they evolve?

Phase A - 9/03 to 5/05 Phase C/D - 6/08 to
1/14 Bridge Phase - 5/05 to 12/06 Launch Window -
10/13 Phase B - 1/07 to 5/08 Phase E - 1/14 to
1/17
The SMART plasma composition instrument is a new
design that, for the first time, will solve the
problem of identifying minor ions within regions
of high proton fluxes. SMART will also solve
known difficulties associated with low-energy
plasma and electric field measurements by
including a flight proven charge neutralization
device and an electric0drift electric field
detector.
MDR 9/06 ICR 12/06 PDR 1/08 MCR 6/08
CDR 3/09 PER 7/10 LRD
9/13 Launch 10/13
GSFC, MSFC, APL, LANL UNH, UCLA, CU, UI, Rice
Lockheed Martin, Aerospace Corp. Austrian,
Japanese, French, United Kingdom, Sweden, German
The mission is in an extended Bridge Phase A
period.
56
Sample Analysis at Mars
PI Dr. Paul Mahaffy, NASA/GSFC, Code 699
J. Kellogg, ISE
Quadrupole Mass Spectrometer (QMS)
  • SAM is designed to reveal the potential for life
    on Mars through a comprehensive investigation of
    organics, aqueous processing, oxidants, and
    isotopes using a suite of instruments. GSFC is
    responsible for the suite design, assembly, test,
    calibration, and delivery.
  • SAM suite instruments
  • Quadrupole Mass Spectrometer (QMS) - GSFC
  • Gas Chromatograph (GC) U. of Paris
  • Tunable Laser Spectrometer (TLS) - JPL

Gas Chromatograph (GC)
Tunable Laser Spectrometer (TLS)
  • SAM CDR December 2006
  • Flight Unit IT Start May 2007
  • SAM delivery to MSL March 2008
  • MSL launch August 2009

There are numerous Co-Investigators from
academia, industry, and other institutions. Key
partners include Honeybee, Creare, Battel Eng.,
Swales, JPL, and U. of Paris
SAM successfully completed PDR in March 2006, and
is now in the detailed design phase. A full
Engineering Model of SAM is under development.
57
ST8 Thermal Loop Experiment
PI Jentung Ku, NASA/GSFC, Code 545
T. Pham, IM D. Douglas, ISE
Instrument Simulator with Evaporator and
Compensation Chamber (2x)
  • Thermal Loop experiment is an advanced thermal
    control system consisting of a miniature loop
    heat pipe with multiple evaporators and heat load
    sharing capability designed for future small
    system applications requiring low mass, low
    power, and compactness.
  • The objective is to validate in space a miniature
    loop heat pipe thermal control system consisting
    of two evaporators and two condensers that is
    capable of reliable start-ups, steady operation,
    heat load sharing, and can maintain operating
    temperature control within 0 to 35 C.

Spacecraft Interface (4x)
Condenser Embedded in Radiator (2x)
Mass 47 lbs. Dimensions 26 x 17 x 6 inches
(shown) without elec box
  • CDR Feb 7, 2007
  • PER Aug 1, 2007
  • Delivery to S/C for integration May 16, 2008
  • Launch readiness date February 28, 2009
  • Applicable to small spacecraft and instruments
    with multiple heat sources and/or requiring
    heating and cooling simultaneously
  • Technology will be validated as part of the New
    Millennium Program (NMP) Space Technology 8 (ST8)
    mission to be launched on Pegasus XL.
  • Completed breadboard unit ambient and thermal
    vacuum testing
  • Completed PDR in May 2006
  • Experiment is in detail design phase
  • Co-I JPL/ Mike Pauken
  • Swales
  • TTH Research

58
Wide Field Camera 3 (WFC3)
Instrument Scientist Dr. Randy Kimble,
NASA/GSFC, Code 667
J. Townsend, IM D. Fineberg, ISE
  • WFC3 will replace the Wide Field Planetary Camera
    2 currently in the Hubble Space Telescope.
  • WFC3 brings to the Hubble a new capability
    spanning from the near UV through the near IR
    (200 1700 nm).
  • Supports wide-ranging science program, e.g.
    studies of star formation, distant galaxies, dark
    energy.
  • Components developed by GSFC and industry.
  • Integration and test at GSFC.

Dimension 7.5 x 7 x 2.5 ft Mass 900 lbs
300 lbs Power 240 W
  • UVIS detector assembly 06/03
  • IR detector assembly 01/07
  • Acoustic test 11/06
  • Thermal-Vacuum test 11/06
  • Integrated mission test 03/07
  • Launch 12/07
  • Dual detectors ultraviolet to visible (UVIS)
    detector and infrared (IR) detector.
  • UVIS uses 2 e2v (formerly Marconi) 2K x 4K
    CCDs.
  • IR channel uses Rockwells 1K x 1K HgCdTe
  • Rework due to liens identified during fast track
    to thermal vac phase nearing completion.
    Re-integration flow on schedule to support
    Thermal Vacuum 2 in 11/06 and launch in 12/07
  • New IR detector build underway with delivery
    expected in January 2007.
  • GSFC, Space Telescope Science Institute,
  • Ball Aerospace, JPL, OSC, Mantech International,
  • Swales Aerospace, Jackson and Tull

59
Agenda
  • The Case for Instruments Development _at_ GSFC
  • Science Instruments 101
  • The Instrument Systems Technology Division
  • Science Instruments and Sensors at GSFC
  • Past
  • Present
  • Future
  • The how behind our success.
  • Instrument Development Process
  • Case Study
  • Best Practices
  • My Favorite Aerosmith Song

60
Science Instruments and Sensors Capability
Roadmap Overview
  • Prepared by the Capability Roadmap Team
  • August 25, 2005

NASA Co-Chair Rich Barney, NASA External
Co-Chair Maria Zuber, MIT Deputy Chair Juan
Rivera, NASA
61
Capability Breakdown Structure
Science Instruments and Sensors
Chair Richard Barney, NASA GSFC Co-Chair Maria
Zuber, MIT Deputy Juan Rivera, NASA GSFC
12.0
Microwave Instruments and Sensors
Multi-Spectral Imaging/Spectro-scopy (VIS-IR-FIR)
Multi-Spectral Sensing (UV-Gamma)
Laser/LIDAR Remote Sensing
Direct Sensing of Particles, Fields, and Waves
In Situ Instrumentation
CAPABILITIES
12.1
12.2
12.3
12.4
12.5
12.6
Chair Soren Madsen, JPL Co-Chair Chris Ruf, UM
Chair Craig McCreight, ARC Co-Chair Ron
Polidan, NGST
Chair Brian Ramsey, MSFC Co-Chair David
Chenette, LM
Chair Maria Zuber, MIT Co-Chair Rich Barney,
GSFC
Chair Dick McEntire, APL Co-Chair Carl Stahle,
GSFC
Chair Tim Krabach, JPL Co-Chair Rich Dissly,
BATC
Radar Altimetry
Imaging/ Microscopy
Energetic Particle and Plasma Imagers and
Spectrometers
Visible Imagers, Photometers, Radiometers,
Sounders
UV Imaging and Spectrometry
Altimeters
12.1.1
12.6.1
12.4.1
12.2.1
12.5.1
12.3.1
Real Aperture Radar
Mineralogical/ Elemental Analysis
12.1.2
Visible Spectrometers/ Interferometers
High Energy Particle Detector Systems
UV Interferometry
Transponders
12.6.2
Synthetic Aperture Radar
12.1.3
12.4.2
12.5.2
12.2.2
12.3.2
Chemical Detection and Identification
Interferometric SAR
12.6.3
Atmospheric LIDARS
Visible Spectral (and Hyperspectral Imagers)
12.1.4
Magnetometers
X-ray Imaging and Spectrometry
Isotope Analysis/ Age Dating
Radar Subsurface Sounding
12.4.3
12.2.3
12.5.3
12.3.3
SUB-CAPABILITIES
12.6.4
12.1.5
X-ray Timing and Polarimetry
Spectrometers
Electric Fields and Wave Instruments
Passive Microwave Real Aperture Imager
IR/FIR Imagers. Photometers, Radiometers, Sounders
Biological Detection and Identification
12.1.6
12.4.4
12.2.4
12.6.5
12.5.4
12.3.4
Passive Microwave Synthetic Aperture Imager
IR/FIR Spectrometers/ Interferometers
Geophysical Measurements
Gravitational Waves and Fields Instruments
X-ray Interferometry
12.1.7
Interferometers
12.6.6
Passive Microwave Sounder
12.4.5
12.2.5
12.3.5
12.5.5
12.1.8
Sample Handling and Preparation
IR/FIR Spectral (and Hyperspectral Imagers)
Gamma Ray Imaging and Spectrometry
GPS-Radio Time-of-Flight Triangulation
12.6.7
12.1.9
12.2.6
12.3.6
In Situ Instrument Engineering
Other Technology
12.6.8
12.1.10
62
Mission Drivers
Astrobiology Field Lab
Constellation-X
Large-Aperture UV/Optical Observatory
Uranus Orbiter with Probes
Lunar Recon. Orbiter
TPF-C
Europa Geophysical Orbiter
Neptune Orbiter
Jupiter Polar Orbiter with Probes
Mars Sample Return
GEO Global Precipitation
SAFIR
GEO/MEO InSAR
Planet Imager
LISA
2010
2020
2030
63
Major Technical Challenges
Major Technical Challenge Requirements to Enable Driving Reference Missions Requirements to Enable Driving Reference Missions Requirements to Enable Driving Reference Missions
Major Technical Challenge 2006-2010 2010-2020 2020 and Beyond
Large lightweight electronically scanned RF arrays (12.1) 60 efficiency L-Band T/R modules Lightweight apertures, membranes or panels (lt8kg/m2) 1 W Tx _at_ W-band T/R module 250 mW DC digitizing receiver at 200 GHz Very large apertures (1000 m2) with integrated electronics, L-band and Ka-band.
Quantum limited heterodyne receivers (12.1) 1x103 pixels _at_ 30 -100 GHz low power dissipation Broadband receivers near quantum limit to 12 THz gt 4 octave spectrometry Large low power, broad bandwidth, tunable arrays
Large format focal plane arrays (12.1, 12.2 12.3) 5x108 BLIP CCD pxls at 140 K _at_ Vis/IR 2eV X-ray resolution 1x103 polarimetric BLIP array _at_ FIR 1x108 pixel array _at_ IR 1x109 pixel _at_ UV 1x107 pixel X ray, 1eV resolution, response gt 6 keV Synthesize 1x107pixel mm-wave imager with thinned focal plane array 1x108 pixel UV/Vis.
Improved LASER energy, lifetime, tuning, noise efficiency (12.4) 3 W _at_ 1-2 micron lifetime gt 5 yr move current technology to relevant environment demo Tunable over 5 GHz gt 1 J/pulse 300 W with 110-13 stability lifetime gt 5 yr
Miniaturized particles and fields instruments (12.5) Thicker, larger SSD arrays with associated lower power, radiation-hard readout and processing electronics Plasma isotopic composition Energetic neutral atom conversion surfaces, imaging, composition
Comprehensive biomarker and organic assessment (12.6) Bulk sample characterization of organic content at ppb levels Broad survey sub ppt-level sensitivities in a flight package Microfluidic, lab on a chip bioassay biopolymer identification
Sample handling systems (12.6) 40K sample handling with minimal volatile loss 130K sample containment Sample handling with minimal alteration or contamination selective subsampling in core Low-power drilling in environments lt40 K with quantitative volatile preservation
Radiation-hard reprogrammable logic and massively parallel ASIC DSP (crosscutting) 100 Mps/W microprocessor 1-10 TIPS digital correlator, Hi-Rad ASIC 8 GHz BW digital spectrometer 100 TIPS digital correlator 1 Mradiation-hard processor 100 TIPS digital correlator _at_ lt 50 W
Space qualified cryocoolers (crosscutting) 5 K high efficiency cooler continuous 50 mK cooler _at_ 5 microwatts load 0.1 K cooler _at_ 100 mW load Continuous 50 mK cooler _at_ 50 microwatts load
64
NASA Decadal Survey Missions
65
Exploration-enabling Measurements (Moon)
  • Needs GSFC Competencies
  • Land on the Moon safely
  • Required knowledge Measurement possibilities
  • Lunar topography - Laser altimeter
  • Lunar gravity field - Orbital dynamic
    measurements
  • Radiation environment - Energetic particles
    plasma sensors
  • - Solar activity measurements
  • Surface magnetic electrical environment -
    Magnetometer
  • - Electric field measurements
  • Dust environment - Optical sensors
  • 2. Determine preferable locations
  • Required knowledge Measurement possibilities
  • Location of water/ice (polar regions) -
    Neutron gamma ray spectrometer

66
Exploration-enabling Measurements (Mars)
  • Needs GSFC Competencies
  • Land on Mars safely
  • Required knowledge Measurement possibilities
  • Mars topography - Laser altimeter
  • Martian gravity field - Orbital dynamic
    measurements
  • Radiation environment sensors - Energetic
    particles and plasma - Solar activity
    measurements
  • Surface magnetic electrical environment -
    Magnetometer
  • - Electric field measurements
  • Dust environment - Optical sensors
  • Martian Weather - Hyperspectral imaging
  • - Weather Satellites
  • - Environmental measurements

67
Exploration-enabling Measurements (Mars)
continued
  • Needs GSFC Competencies
  • 2. Determine preferable locations (cont.)
  • Required knowledge Measurement possibilities
  • Surface temperature - Infrared radiometer
  • Resources to sustain exploration - In-situ
    resource measurement and processing
  • - Analysis of returned samples
  • Sustained and safe human habitation on Mars
  • Required knowledge Measurement possibilities
  • Resources - In-situ measurements
  • Radiation environment - Energetic particle
    sensors
  • - Solar activity measurements

68
Internal Research and Development (IRAD)
  • IRAD is a critical resource for development of
    ISTD technologies and instruments.
  • ISTD actively participates in IRAD program in the
    following roles
  • Principal Investigator
  • Co-Investigator
  • Reviewer
  • Strategic Investment Area Lead
  • ISTD strategy is to partner on IRAD proposals
    with engineers and scientists across 500 and 600.

69
Summary of FY07 IRAD Awards
Active as PI or Co-I in all Investment Areas!
70
Wake Up
Take 1000 and add 40 to it. Add 1000 to that
number and add 30 to that. Now add 1000, then
another 20 to that number Add another 1000 then
add 10 What is your answer??
71
Wake Up
Take 1000 and add 40 to it. Add 1000 to that
number and add 30 to that. Now add 1000, then
another 20 to that number Add another 1000 then
add 10 What is your answer?? Did you get 5000?
72
Wake Up
Take 1000 and add 40 to it. Add 1000 to that
number and add 30 to that. Now add 1000, then
another 20 to that number Add another 1000 then
add 10 What is your answer?? Did you get
5000? Wrong! Correct answer is 4100!!
73
Agenda
  • The Case for Instruments Development _at_ GSFC
  • Science Instruments 101
  • The Instrument Systems Technology Division
  • Science Instruments and Sensors at GSFC
  • Past
  • Present
  • Future
  • The how behind our success.
  • Instrument Development Process
  • Case Study
  • Best Practices
  • My Favorite Aerosmith Song

74
Scope of Instrument Development
  • GSFC instrument development and staffing
    encompasses the full range of possibilities
  • In-house development
  • Contracted development (Industry and Academia)
  • Other NASA Centers
  • Other U.S. Government Agencies
  • International sources
  • At GSFC, instruments are developed which cover
    the full range of sophistication and scrutiny
  • Instrument Incubator Program (IIP)
  • Aircraft
  • Balloons
  • Trailers
  • Flight Instruments

75
Modes of Instrument Development
  • In-House
  • Reasons for developing Instruments in-house
  • When there is a key technology we want to develop
    in order to maintain our core competency.
  • When there is significant development risk with
    that technology that private industry would not
    be willing to develop it.
  • NASA/GSFC is the only institution (in the world)
    that can do it.
  • To maintain our ability to be smart buyers of
    contracted instruments.
  • Advantages of in-house instrument development
  • Allows GSFC personnel to develop or maintain
    hands-on expertise
  • Maintain GSFCs leadership in core technologies
  • Develop key targeted technologies for the future
  • Involves you in every detail, including personnel
    issues
  • Contracted (out-of-house)
  • May involve COTR function
  • More programmatic issues

76
Checks and Balances in Instrument (Project)
Development
Center Director Decisions
Principal Investigator, Project Scientist
Chief Engineer
GPMC Recommendations
OSSMA Monthly Review
AETD Project Monthly Review
MSR and/or PMC Meetings
AETD Champion Team Review
Formal Launch Decision Process
Pre-MSR
Div. Tech. Status Reviews
IIRT
Project Reviews
Systems Assurance and Safety Reviews
In-process Technical Reviews
Lower Level Programmatic Rvws
Peer Reviews
Peer Reviews
Technical Staff
PROJECT-DRIVEN PROCESS(ES)
SMA-DRIVEN PROCESS(ES)
ENGINEERING-DRIVEN PROCESS(ES)
77
Case Study Astro-E2 XRS Instrument Small Team
Big Heart
G O D D A R D S P A C E F L I
G H T C E N T E R
78
Astro-E2 XRS Instrument Overview
Mission The XRS instrument is the center piece
of a powerful X-ray observatory developed
jointly by the U.S. and Japan (Institute of Space
and Astronautical Science). Science XRS will
employ a state of the art x-ray micro-calorimeter
providing high resolution x-ray spectroscopy.
Launch date Jul 9, 2005 Lifetime 2
years Orbit 550 km 31 deg incl. Launch
Vehicle Japanese M -V rocket Range Kagoshima
Space Center Three Stage Cooling System ADR -
0.060K Super-fluid He - 1.3K Solid Neon - 17K
He Insert provided by GSFC
Neon Dewar (ISAS)
79
Astro-E2 Spacecraft Hardware Overview
Astro-E2
XRT (GSFC ISAS)
XIS (ISAS)
HXD (ISAS)
XRS (GSFC ISAS)
GSFC He Insert
80
Problems along the way One size fits all
  • Case 1 Small Problem
  • Fastener Redesign Defining the Team
  • Case 2 Medium Problem
  • Liquid Helium Leak Character Building
  • Case 3 Big Problem
  • Tank Rupture
  • Gut Check

81
Case 1 Fastener Redesign
New fastener with more strength and higher
reliability
Original design hand machined - vulnerable to
torsion
82
Case 2 Cryostat Helium Tank Leak 2 months and
counting? Leak still a mystery!
  • Lower tank weld
  • Testing did not
  • point directly to weld
  • Repair plan established
  • Rear dome skin
  • Low probability (thickness 60 mils)
  • Patch process evaluated
  • Burst Disk
  • Does not leak
  • Interfaces above
  • rear dome
  • Leak not suspected per testing in Aug
  • Disk-Tank
  • Interface
  • Does not leak

83
Cryostat top view ( 50 tank interfaces)Theres
the leak, over there!
84
Close Up of Bellows to Heat Exchange Joint
Welded Bellows Joint TO Brazed Copper Heat
Exchange
Leak detected on weld side
85
Case 3 Ground Support Equipment Helium Tank
Rupture
Bad Day at the Office But failure is not an
option for this team
86
Three Cases One Recurring ThemeAttack All
Problems Using the Same Process
Response To Failure
  • Gather your team (on-site)
  • Put away your pointer finger (good ground rule)
  • Get the facts straight (follow the data what
    happened, when, etc.)
  • Investigate root cause(s) and contributing
    factors (every time!)
  • Establish mitigation plan and recovery plan (keep
    the hope alive)
  • Conduct one-on-one talks with each team member
    stating the importance of the recovery and the
    value of their contribution (if you are sincere,
    they most likely will give you 110 )
  • Execute the plan (if the PM lets up, others will
    follow)
  • Cheer along the way (dont wait for the finish
    line to tell team members they are appreciated)

87
Best Practices from Instrument Development Teams
  • People are the most important resource! You are
    only as successful as those around you.
  • "Do it right the first time." It's great as
    long as there -is- time to do it right . the way
    it should be. Otherwise, duck tape and tie wraps
    work well.
  • Getting your team members to take ownership is
    probably the most important thing. More important
    than requirements!
  • Maintain your documentation as if you plan to
    rebuild the same hardware five or ten years
    later. You never know when you might be asked
    to.
  • Have a sense of the why behind your
    requirements definition and flow down.
  • If it isnt broke . dont fix it . unless the
    challenge is unbearable!
  • Flight Software is a bona fide subsystem just
    like the rest, which must be involved and thought
    of as an equal from day one.
  • Heritage Hardware Don't expect a design to
    speak entirely for itself it needs to come with
    the people that designed it.

88
Questions
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