**Part 11. TECHNOLOGY TRANSFER AND INFUSION**

**1. INTRODUCTION**

One important purpose of the EO-1 mission is to, wherever possible,
maximize the transfer and infusion of EO-1 validated technologies into
other applications and missions. Described below are the technologies
that have been transferred and infused or have strong potential for
such.

**1.1 Landsat Data Continuity Mission (LDCM)**

The EO-1 Advanced Land Imager (ALI) instrument was designed to serve as
a testbed to demonstrate technologies that would be suitable to infuse
into the design of an earth imaging instrument for the follow-on mission
to Landsat 7, i.e. LDCM. ALI spatial and spectral resolution performance
has demonstrated that, in comparison to the Landsat 7 Enhanced Thematic
Mapper Plus (ETM+) instrument, a corresponding ALI based instrument
would have a significantly superior S/N ratio while requiring 1/5 the
power to operate, be reduced in mass by a factor of four, and have the
strong potential for being less costly. There are two individual ALI
elements whose technologies of themselves were demonstrated to be most
worthy of transfer and infusion. They are the Wide Field of View Silicon
Optics and the Non-Cryogenic Focal Plane System.

**1.2 New Millennium ST6 Autonomous Sciencecraft Experiment**

The Autonomous Sciencecraft Experiment (ASE), part of the New Millennium
Program Space Technology 6 (ST6) project, was demonstrated on-board the
EO-1. The ASE technology objective is to improve a spacecraft's ability
to autonomously make intelligent decisions on what information to gather
and send back to the ground. The ASE software has enabled EO-1 to
autonomously detect and respond to science events such as: volcanic
activity, flooding, and water freeze/thaw events. ASE uses
classification algorithms to analyze imagery on-board to detect change
and science events. Detection of these events is then used to trigger
follow-up imagery. On-board mission planning software then develops a
response plan that accounts for target visibility and operations
constraints. This plan is then executed using a task execution system
that can deal with run-time anomalies. The ASE running on the EO-1
spacecraft has demonstrated several integrated autonomy technologies to
enable autonomous science. For example, on-board science algorithms have
been used to analyze science data, and the science algorithms outputs
serve as inputs to CASPER, an on-board robust goal oriented software
scheduling system, that contains decision-making algorithms capable of
modifying spacecraft observation plans so as to capture high value
science events. Although the ASE software was run on the EO-1
spacecraft, the long-term goal is to infuse the software into
interplanetary space missions.

As an application example, the ASE Science Team has developed scene
classifiers to detect thermal emission in both day and nighttime
Hyperion data. Once uploaded, the thermal scene classifier effectively
turns the EO-1 spacecraft into an autonomously operating and reacting
volcanic activity detector. It is possible to envision such a capability
on spacecraft observing volcanism on Io and Triton, autonomously
identifying and classifying activity, identifying sites deserving of
closer scrutiny, and re-tasking the spacecraft to observe them, thus
fulfilling NASA\'s goal of fully-autonomous, science-driven spacecraft.
The team has also developed other scene classifiers for ice, snow, water
and land for possible future release and flight on EO-1. The pattern to
shift toward highly autonomous spacecraft will enable future NASA
missions to achieve significantly greater science returns with reduced
risk and reduced operations cost.

Anticipated missions, that the EO-1 validated spacecraft operations
autonomy and automation activities are being considered for infusion,
are the Flora earth science mission and the Mars Exploration Rover (MER)
and Mars Odyssey planetary missions.

**1.3. Livingstone 2 Artificial Intelligence Model-Based Diagnostic
Engine**

Livingstone 2 (L2), developed at NASA Ames Research Center, is an
artificial intelligence model-based on-board software system that is
designed to find and analyze errors in a spacecraft's system. L2 is a
reusable diagnostic tool for monitoring complex systems. It is capable
of tracking the system state during nominal operations, detecting
abnormalities in operations and isolating failures to their root cause
fault. L2 supports reporting of ambiguity groups consisting of multiple
diagnostic candidates with associated probabilities, and hypothesis
revision given new evidence about the state of the system from sensor
observations.

The model-based approach facilitates reuse of the L2 diagnostic software
across applications. Only the model of the system to be diagnosed and
monitor software to discretize telemetry points, has to be built for
each application. Model and telemetry monitors can be changed with no
impact to the L2 software. If the system under diagnosis has a scalable
architecture and is expected to evolve substantially over its lifetime,
as for the International Space Station, the model-based approach has a
definite advantage over rule-based expert systems and limit-checking
fault protection systems, as these do not scale well. The L2 model is
composed into hierarchies, supporting the modularity and expandability
required for integrated system health management of envisioned
systems-of-systems.

L2 is a successor to the previous version, L1, which flew on Deep Space
1 in 1999 as part of the Remote Agent autonomy experiment (RAX). The
original Livingstone, L1, was written in LISP whereas the next
generation Livingstone 2 (L2) is written in C++. L1 could give only a
single possible cause (candidate) for the fault. L2 diagnoses multiple
alternate candidates and ranks them according to probability. Also, L2
has temporal extensions that allow it to revise its hypothesis of what
occurred based on new observations received, in effect \'changing its
mind\' given new evidence. L1 had to wait until the system was quiescent
before checking for faults. L2 can check for faults even when the system
is changing, such as when commands are being issued in parallel to
different components of the system, or when physical transients in the
system are settling out. Finally, L2 was tested with a larger suite of
fault scenarios and has demonstrated long-term operations in space.

By using a computerized model of spacecraft subsystems, L2 predicts
nominal state transitions initiated by control commands, monitors the
spacecraft sensors, and, in the case of a failure, isolates the fault
based on the discrepant observations. Through the use of artificial
intelligence tools, fault detection and isolation is done by determining
a set of component modes, including most likely failures, which satisfy
the current observations. In this infusion experiment, Livingstone 2 was
uploaded to the EO-1 satellite and integrated with the Autonomous
Sciencecraft Experiment (ASE) for the purpose of monitoring the
performance of the ASE. The ASE autonomously controls all the EO-1
operation modes. Using a model of the EO-1 spacecraft subsystems, L2
predicted nominal state transitions initiated by ASE control commands,
monitored the spacecraft sensors, and, if the EO-1 did not respond
properly to ASE control, L2 would detect the error, make a diagnosis by
isolating the fault based on the discrepant observations, and transmit
its analysis to mission control. As a result of isolating a fault, L2
has the capability to provide several hypotheses of what might have gone
wrong.

The major benefits of this advanced health management technology are to
increase mission duration and reliability through intelligent fault
protection and robust autonomous operations with reduced dependency on
supervisory operations from Earth. The work-load for operators is
reduced by telemetry of processed state-of-health information rather
than raw data. Detecting faults onboard has several important advantages
for Lunar and planetary missions: first, onboard diagnosis software has
immediate access to all telemetry without the need to wait for downlink
windows; second, if faults are found, they can be passed immediately to
the fault recovery software and possibly prevent further damage to the
spacecraft or system; and, finally, on-board planning software may be
able to re-plan in order to work around known component failures.

From this infusion experiment of utilizing EO-1 as a testbed, it has
been demonstrated that L2 is matured to the point that it is ready for
technology transfer to industry. It is believed that L2 could be used to
find errors and offer corrective action in robots or rovers exploring
Mars or other planetary bodies. As human beings venture deeper into
space, crews will need automatic tools like L2 to identify spacecraft
problems early and make prompt repairs. Examples of potential infusion
into planetary missions are Mars Exploration Rover (MER) and Mars
Odyssey. Another example of potential opportunity for infusion is the
Laser Interferometer Space Antenna (LISA) mission.

The L2 source code has been made open source and is available to the
public at
[http://opensource.arc.nasa.gov](http://opensource.arc.nasa.gov/).

**1.4 Electric Propulsion for Spacecraft Control**

Based on the success of the EO-1 Pulsed Plasma Thrusters (PPT's)
validation and coupled with the trend toward smaller spacecraft and the
need for precision propulsion, there has been a resurgence of interest
in Pulsed Plasma Thrusters (PPT's). The PPT provides small, controlled
impulse bits at high specific impulse in a self-contained package with
storable solid propellant and a simple spacecraft interface. Studies
have shown the mass benefits of the PPT for constellation
stationkeeping, small satellite primary and attitude control propulsion,
and precision propulsion for missions such as optical interferometers.

PPT technology is being utilized to meet the need of the United States
Air Force for reliable, highly maneuverable micro-satellites. In
response to this need, the Air Force Research Laboratory (AFRL) has
developed the Micro-PPT. The AFRL Micro-PPT is the leading technology
that will enable the mass of micro-satellites to be reduced to the 25 kg
class. This development is being made possible by utilizing the
Micro-PPT as a dual-capability thruster by providing attitude control in
conjunction with primary propulsion for the spacecraft. This AFRL
Micro-PPT design will be flight demonstrated on the FlaconSat 3
micro-satellite which is a USAF Academy cadet-run mission to be launched
in FY07.

**1.5. Hyperspectral Remote Sensing Technology**

Hyperion, operating on the Earth Observing One (EO-1) spacecraft, is the
first spaceborne hyperspectral remote imaging spectrometer instrument.
It has 220 spectral bands, each with a 10 nm bandwidth, covering a
spectral range of 0.4 to 2.4 microns. This high spectral resolution,
coupled with its moderate spatial resolution (30 m) and the ability to
image virtually any location on earth in a timely manner, has generated
a demand for space acquired hyperspectral data.

The U.S. Geological Survey (USGS) has served as the public interface for
sales and distribution of Hyperion data. They have been successful in
selling over 2600 data sets through FY 2005 and in reducing the cost to
\$250 for an archived product and to \$750 for a customer-requested 42
km swath of a particular location. This extensive distribution of image
data has resulted in the application of hyperspectral remote sensing
data to a wide variety of disciplines (e.g. agriculture, forestry,
classified military, invasive plant species control, vegetation fire
hazard assessment, water quality assessment, etc.). In addition,
workshops have been conducted that served to promote cutting-edge
applications of hyperspectral imagery. As a consequence, there has been
a very active transfer and infusion of hyperspectral imaging technology
into the earth remote sensing community as proven by the 600+
publications, presentations, and articles that have emerged based on
Hyperion acquired data.

The knowledge and lessons learned gained from extensive studies of EO-1
Hyperion hyperspectral data have been applied to formulating a number of
proposed, approved, and operational spaceborne remote sensing missions
that contain hyperspectral (imaging spectrometer) instruments. Examples
are the NASA MRO Compact Reconnaissance Imaging Spectrometer for Mars
(CRISM) instrument, the Moon Mineral Mapper (M3) mission, and the Flora
earth observing mission; the U.S. Air Force/Raytheon ARTEMIS mission;
and the international CHRIS (Compact High Resolution Imaging
Spectrometer)-Proba (ESA), HERO (Canadian), SPECTRA (ESA), and EnMAP
(German) missions.

**1.6 LEISA Atmospheric Corrector (LAC)**

The EO-1 Linear Etalon Imaging Spectral Array (LEISA) Atmospheric
Corrector (LAC) wedge-filter spectral-imager on EO-1 was designed to
correct for systematic errors in the apparent surface reflectances
caused by atmospheric effects. These errors are common to all
measurements obtained by high spatial resolution multispectral remote
sensing imagers. The EO-1 LAC is the precursor of the LEISA sensor on
the New Horizons (NH) mission to Pluto and the Kuiper Belt. The basic
engineering design of LEISA on New Horizons is identical to that of
LEISA on EO-1. The two instruments differ in that filter bandpass and
detector response specifications are derived from the New Horizons
mission science objectives.

The New Horizons LEISA will map the chemical composition across the
sunlit surfaces of Pluto and its moons, recording the amounts of
nitrogen, methane, carbon monoxide, frozen water and other materials,
including organic compounds. It will also map surface temperatures by
sensing the spectral features of frozen nitrogen, water and carbon
monoxide. The New Horizons spacecraft was launched January 19, 2006 and
arrival at Pluto will be July 2015.

The New Horizons spacecraft will be the first to explore the
trans-Neptunian region of our solar system. The extended mission offers
the possibility of subsequent encounters with the primitive bodies of
the Kuiper Belt. The New Horizons mission will provide valuable insights
into the origin of the outer solar system and the ancient outer solar
nebula. An important early mission encounter with Jupiter occurs 15
months after launch. New Horizons will fly 3 to 4 times closer to
Jupiter than the Cassini spacecraft and record important new data of the
large planet.

The legacy of NASA's EO-1 technology is carried by New Horizons to the
planet Pluto and beyond. LEISA is set to return data from an encounter
at Jupiter, Pluto and its moons, and remote Kuiper Belt Objects and help
achieve NASA's goals for the NH mission.