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This PDF file contains the front matter associated with SPIE Proceedings Volume 8739, including the Title Page, Copyright information, Table of Contents, and the Conference Committee listing.
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Pervasive Technologies Supporting Responsive Space
The Space Ultra Compact Hyperspectral Imager is a long wave infrared hyperspectral imager being built at the
University of Hawaii. The sensor will be the primary payload on the HiakaSat small satellite scheduled for launch on the
Office of Responsive Space ORS-4 mission, and planned for a 6 month primary mission which is extendable up to two
years of operation on orbit. SUCHI is based on a variable-gap Fabry-Perot interferometer employed as a Fourier
transform spectrometer and uses an uncooled 320x256 microbolometer array to collect the images. The sensor is low
volume (16” x 4” x 5") and low mass (<9kg), to conform to the volume, mass, and power requirements of the small
satellite. The commercial microbolometer camera and vacuum-sensitive electronics are contained within a sealed vessel
pressurized to 1 atm. The sensor will collect spectral radiance data in the long wave infrared region (8-14 microns) and
demonstrate the potential of this instrument for advancing the geological sciences (e.g. mapping of major rock-forming
minerals) as well as for volcanic hazard assessment (mapping volcanic ash, quantification of volcanic sulfur dioxide
pollution and lava flow cooling rates). The sensor is scheduled for delivery to the satellite in Spring 2013, with launch
scheduled for Fall 2013.
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Ian Garrick-Bethell, Robert P. Lin, Hugo Sanchez, Belgacem A. Jaroux, Manfred Bester, Patrick Brown, Daniel Cosgrove, Michele K. Dougherty, Jasper S. Halekas, et al.
We have developed a mission concept that uses 3-unit cubesats to perform new measurements of lunar magnetic fields,
less than 100 meters above the Moon’s surface. The mission calls for sending the cubesats on impact trajectories to
strongly magnetic regions on the surface, and transmitting measurements in real-time to a nearby spacecraft, or directly
to the Earth, up until milliseconds before impact. The cubesats and their instruments are partly based on the NSF-funded
CINEMA cubesat now in Earth orbit. Two methods of reaching the Moon as a secondary payload are discussed: 1) After
launching into geostationary transfer orbit with a communication satellite, a small mother-ship travels into lunar orbit
and releases the cubesats on impact trajectories, and 2) The cubesats travel to the Moon using their own propulsion after
release into geosynchronous orbit. This latter version would also enable other near-Earth missions, such as
constellations for studying magnetospheric processes, and observations of close-approaching asteroids.
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Recent work, specifically the Lawrence Livermore National Laboratory (LLNL) Eyeglass and the DARPA MOIRE
programs, have evaluated lightweight, easily packaged and deployed, diffractive/refractive membrane transmissive
lenses as entrance apertures for large space and airborne telescopes. This presentation describes a new, innovative
approach to the theory of diffractive and refractive effects in lenses used as telescope entrance apertures and the
fabrication of the necessary large membrane optics. Analyses are presented to indicate how a broadband, highly
transmissive diffractive / refractive membrane lens can be developed and fabricated, and potential applications in defense
and astronomy are briefly discussed.
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Characterization activities related to near-Earth asteroids (NEAs) provide several societal benefits. This work can serve
as a precursor to a human exploration mission, it can facilitate the assessment of targets for resource extraction, and it
can serve as preparation for intervention against the threat posed by an Earth impactor (EI). One objective of ongoing
work at the University of North Dakota is to develop the capabilities required for NEA characterization. A CubeSatclass
spacecraft will serve to demonstrate and test these required technologies on-orbit.
This 1U CubeSat, which is compliant with NASA ELaNA CubeSat Launch Initiative requirements, will be comprised of
standard subsystems (excluding propulsion) and a payload consisting of a visible light camera, a limited radio science
package and a GPS receiver. The craft will also feature extensive onboard computing capabilities to allow it to process
data to perform mosaicking, super-resolution and rudimentary image feature identification and analysis.
This paper focuses on the onboard computing subsystem of this spacecraft which consists of a standard flight computer
based on the AMTEL AT91SAM9G20 chipset and a supplemental processing unit based on several GumStix computeron-
module (COM) units. The key design requirement: having an always-on primary processing unit and supplemental
capabilities (including a digital signal processor) that can be powered on for use only when required and how the current
design meets these requirements is reviewed.
A detailed review of the spacecraft’s design and mission operations plan is presented. The numerous trades required to
allow the requisite payload and onboard processing hardware to fit within the size and weight limitations posed by the
1U CubeSat form factor are discussed. Finally, the paper concludes with a review of the functionality provided by the
spacecraft and the future capabilities that this functionality will facilitate.
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The Hawaii Space Flight Laboratory (HSFL) at the University of Hawaii at Manoa is developing the capabilities to
design, build, and operate constellations of small satellites than can be tailored to efficiently execute a variety of remote
sensing missions. With the Operationally Responsive Space (ORS) Office, HSFL is developing the Super Strypi launch
vehicle that on its initial mission in 2013 will launch the HSFL 55-kg HawaiiSat-1 into a near polar orbit, providing the
first deployment of these technologies. This satellite will be carrying a miniature hyperspectral thermal imager
developed by the Hawaii Institute of Geophysics and Planetology (HIGP). HSFL has also developed a method to
efficiently deploy a constellation of small satellites using a minimal number of launch vehicles.
Under a three-year NASA grant, HSFL is developing a Comprehensive Open-architecture Space Mission Operations
System (COSMOS) to support these types of missions. COSMOS is being designed as a System of Systems (SoS)
software integrator, tying together existing elements from different technological domains. This system should be easily
adaptable to new architectures and easily scalable. It will be provided as Open Source to qualified users, so will be
adoptable by even universities with very restricted budgets. In this paper we present the use of COSMOS as a System of
Systems integrator for satellite constellations of up to 100 satellites and numerous ground stations and/or contact nodes,
including a fully automated “lights out” satellite contact capability.
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Space Payload Technologies for Dual Military-Civil Operations
This paper designs a ground motion compensation servo system based on two-dimensional pointing mirror. The servo
system is mainly composed of digital control unit, analog driving unit and driving motor. Besides, the control algorithm
and strategy of driving motor would be given, and based on the control strategy, a closed-loop controller which consists
of current loop, velocity loop and position loop is designed and simulated. Especially, the speed loop adopts pseudo
differential feed-forward (PDFF) controller to avoid extensive overshoot. Finally, the experiment results show that the
designed servo system has fast response and small overshoot.
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Satellites have limited awareness of nearby objects that might pose a collision hazard. Small, relatively inexpensive onboard
optical local area sensors have been proposed as a means of providing additional awareness. However, such
sensors often have limited performance. Proposed are methods to increase the Local Area Awareness provided by such
sensors by means of classical and novel image processing techniques. The local area of the sensor platform is defined,
for our purposes, as a sphere of radius 500 km surrounding the sensor platform, or observing satellite. This analysis
utilizes image differencing-based techniques, in the development of a detection algorithm and proposes a novel objectvelocity
classifier. This classifier may provide a means of rapidly distinguishing local area objects that pose a possible
collision hazard when an orbital two-line element set is not available.
Derivation of a novel classifier is based on the speed of the projected object moving across the focal plane array of the
detector. This technique relies on the assumption that detection from the sensor platform allows for tracking of the
object over all times the object is within the local area of the sensor platform. This alternative to intensity-based, signalto-
noise ratio detection methods is performed by exploiting the stellar background as a reference from a space-based
observing satellite. Results presented in this paper further demonstrate the ability of the proposed classifier to provide a
means of rapidly distinguishing objects that pose a possible hazard within the local area of the sensor platform. These
preliminary results act to substantiate this claim and therefore lay out a pathway for relevant and meaningful future work
in the area of Local Area Awareness for satellites.
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Large satellites and exquisite planetary missions are generally self-contained. They have, onboard, all of the
computational, communications and other capabilities required to perform their designated functions. Because of this,
the satellite or spacecraft carries hardware that may be utilized only a fraction of the time; however, the full cost of
development and launch are still bone by the program. Small satellites do not have this luxury. Due to mass and volume
constraints, they cannot afford to carry numerous pieces of barely utilized equipment or large antennas.
This paper proposes a cloud-computing model for exposing satellite services in an orbital environment. Under this
approach, each satellite with available capabilities broadcasts a service description for each service that it can provide
(e.g., general computing capacity, DSP capabilities, specialized sensing capabilities, transmission capabilities, etc.) and
its orbital elements. Consumer spacecraft retain a cache of service providers and select one utilizing decision making
heuristics (e.g., suitability of performance, opportunity to transmit instructions and receive results – based on the orbits
of the two craft). The two craft negotiate service provisioning (e.g., when the service can be available and for how long)
based on the operating rules prioritizing use of (and allowing access to) the service on the service provider craft, based
on the credentials of the consumer.
Service description, negotiation and sample service performance protocols are presented. The required components of
each consumer or provider spacecraft are reviewed. These include fully autonomous control capabilities (for provider
craft), a lightweight orbit determination routine (to determine when consumer and provider craft can see each other and,
possibly, pointing requirements for craft with directional antennas) and an authentication and resource utilization
priority-based access decision making subsystem (for provider craft).
Two prospective uses for the proposed system are presented: Earth-orbiting applications and planetary science
applications. A mission scenario is presented for both uses to illustrate system functionality and operation. The
performance of the proposed system is compared to traditional self-contained spacecraft performance, both in terms of
task performance (e.g., how well / quickly / etc. was a given task performed) and task performance as a function of cost.
The integration of the proposed service provider model is compared to other control architectures for satellites including
traditional scripted control, top-down multi-tier autonomy and bottom-up multi-tier autonomy.
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Sensor Contamination Detection, Abatement, and Effects
PICARD is a spacecraft dedicated to the simultaneous measurement of the absolute total and spectral solar
irradiance, the diameter, the solar shape, and to probing the Sun’s interior by the helioseismology method. The
mission has two scientific objectives, which are the study of the origin of the solar variability, and the study
of the relations between the Sun and the Earth’s climate. The spacecraft was successfully launched, on June
15, 2010 on a DNEPR-1 launcher. PICARD spacecraft uses the MYRIADE family platform, developed by
CNES to use as much as possible common equipment units. This platform was designed for a total mass of
about 130 kg at launch. This paper focuses on the design and testing of the TCS (Thermal Control System)
and in-orbit performance of the payload, which mainly consists in two absolute radiometers measuring the total
solar irradiance, a photometer measuring the spectral solar irradiance, a bolometer, and an imaging telescope to
determine the solar diameter and asphericity. Thermal control of the payload is fundamental. The telescope of
the PICARD mission is the most critical instrument. To provide a stable measurement of the solar diameter over
three years duration of mission, telescope mechanical stability has to be excellent intrinsically, and thermally
controlled. Current and future space telescope missions require ever-more dimensionally stable structures. The
main scientific performance related difficulty was to ensure the thermal stability of the instruments. Space is a
harsh environment for optics with many physical interactions leading to potentially severe degradation of optical
performance. Thermal control surfaces, and payload optics are exposed to space environmental effects including
contamination, atomic oxygen, ultraviolet radiation, and vacuum temperature cycling. Environmental effects on
the performance of the payload will be discussed. Telescopes are placed on spacecraft to avoid the effects of the
Earth atmosphere on astronomical observations (turbulence, extinction, ...). Atmospheric effects, however, may
subsist when spacecraft are launched into low orbits, with mean altitudes of the order of 735 km.
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This paper focuses on recent progress in designing FallconSAT-7, a 33U CubeSat solar telescope designed to image the Sun from low Earth orbit. The telescope system includes a deployable structure that supports a membrane photon sieve under tension as well as secondary optics. To satisfy mission requirements to demonstrate diffraction limited imaging capability of this collapsible, f/2 diffractive primary we have completed studying a number off effects on membrane material that can affect system imaging quality.
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Shortly after the Earth observations with the VIIRS instrument launched onboard the Suomi NPP spacecraft have begun,
it was observed that responsivity of some of the instrument’s spectral bands decreases with time faster than expected. It
was determined that the VIIRS telescope mirror contamination with tungsten oxide is the root cause of the degradation,
and that the rate of the degradation is controlled by exposure of the mirrors to ultraviolet radiation. We have monitored
progress of the degradation using measurements of light reflected from the onboard calibrator’s solar diffuser and taking
into account seasonal changes of the solar illumination of the diffuser. The measurements were then used to develop an
empirical model of the degradation dynamics and predict future rate of the responsivity changes during the seven-year
lifetime of the Suomi NPP mission.
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We present a newly designed thermoelectric detector chip of high detectivity for the space mission BepiColombo to
Mercury. The sensor is part of the MERTIS radiometer, which enables radiometric measurements in the spectral range
from 7-40 micron to study the thermo-physical properties of the planet's surface material.
In collaboration with the DLR Institute of Planetary Research, the Institute of Photonic Technology has developed a
sensor array with a specific detectivity D* of 1.3 x 109 Jones in vacuum environment and 2 x 15 individual readable channels. In addition, it has an optical slit in the middle, which serves as the entrance slit of a spectrometer downstream.
The sensor area is coated with an absorbing layer, in this case silver black having an absorption coefficient of nearly 100
percent in a wavelength range from 0.4 up to 20 micron. To minimize the thermal cross talk between the individual
pixels, each pixel is separated by a 50 micron slit in the self-supporting silicon nitride membrane. For good mechanical
stability of the pixels, the pixel membrane is tensioned by 10 micron bridges like braces. The sensor is electrically
contacted with a star-flex PCB by direct wire bonding and both are mounted on milled aluminum housing.
At the Institute of Photonic Technology (IPHT), high detectivity radiation sensors are developed and based on the
thermoelectric principle. The thermoelectric materials used are the highly effective combination of n-bismuth(87%)-
antimony(13%) / p-antimony. The sensors are designed, in the main, as miniaturized multi-junction thermocouples and
made by state of the art thin film technologies allowing for achievable and reproducible detectivities D* in the range of
108 up to 2 x 109 Jones.
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Cognitive Optics and Advanced Technology Demonstration
We present new photonic-true-time-delay (PTTD) devices, which are a key component for phased array antenna (PAA)
and phased array radar (PAR) systems. These new devices, which are highly manufacturable, provide the previously
unattainable combination of large time delay tunability and low insertion loss, in a form factor that enables integration of
many channels in a compact package with very modest power consumption. The low size, weight, and power are
especially advantageous for satellite deployment. These devices are enabled by: i) “Optical Path Reflectors” or OPRs
that compresses a >20 foot change in optical path length, i.e., a >20 nsec tuning of delay, into a very compact package
(only centimeters), and ii) electro-optic angle actuators that can be used to voltage tune or voltage select the optical time
delay. We have designed and built OPRs that demonstrated: large time delay tunability (<30 nsecs), high RF bandwidth
(>40 GHz and likely much higher), high resolution (<200 psec), and low and constant insertion loss (< 1 dB and
varying by < 0.5 dB). We also completed a full design and manufacturing run of improved EO angle actuators that met
the PTTD scanner requirements. Finally, a complete optical model of these integrated devices will be presented,
specifically; the design for a multi-channel (400 channels) PTTD device will be discussed. The applicability and/or risks
for space deployment will be discussed.
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In this paper we present new electro-optic beam steering technology and propose to combine it with optical
telecommunication technology, thereby enabling low cost, compact, and rugged free space optical (FSO) communication
modules for small-sat applications. Small satellite applications, particularly those characterized as “micro-sats” are often
highly constrained by their ability to provide high bandwidth science data to the ground. This will often limit the
relevance of even highly capable payloads due to the lack of data availability. FSO modules with unprecedented cost and
size, weight, and power (SWaP) advantages will enable multi-access FSO networks to spread across previously
inaccessible platforms. An example system would fit within a few cubic inch volume, require less than 1 watt of power
and be able to provide ground station tracking (including orbital motion over wide angles and jitter correction) with a 50
to 100 Mbps downlink and no moving parts. This is possible, for the first time, because of emergent and unprecedented
electro-optic (EO) laser scanners which will replace expensive, heavy, and power-consuming gimbal mechanisms. In
this paper we will describe the design, construction, and performance of these new scanners. Specific examples to be
discussed include an all electro-optic beamsteer with a 60 degree by 40 degree field of view. We will also present
designs for a cube-sat to ground flight demonstration. This development would provide a significant enhancement in
capabilities for future NASA and other Government and industry space projects.
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As the demand for multiple radio frequency carrier bands continues to grow in space
communication systems, the design of a cost-effective compact optical transmitter that
is capable of transmitting selective multiple RF bands is of great interest, particularly for
NASA Space Communications Network Programs. This paper presents experimental
results that demonstrate the feasibility of a concept based on an optical wavelength
division multiplexing (WDM) technique that enables multiple microwave bands with
different modulation formats and bandwidths to be combined and transmitted all in one
unit, resulting in many benefits to space communication systems including reduced
size, weight and complexity with corresponding savings in cost. Experimental results will
be presented including the individual received RF signal power spectra for the L, C, X,
Ku, Ka, and Q frequency bands, and measurements of the phase noise associated with
each RF frequency. Also to be presented is a swept RF frequency power spectrum
showing simultaneous multiple RF frequency bands transmission. The RF frequency
bands in this experiment are among those most commonly used in NASA space
environment communications.
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Tracking, Telemetry, and Control for Space Situational Awareness
Improving orbital accuracy of space debris is one of the major prerequisite to performing reliable collision prediction in
low earth orbit. The objective is to avoid false alarms and useless maneuvers for operational satellites. This paper shows
how laser ranging on debris can improve the accuracy of orbit determination.
In March 2012 a joint OCA-Astrium team had the first laser echoes from space debris using the MéO (Métrologie
Optique) telescope of the Observatoire de la Côte d’Azur (OCA), upgraded with a nanosecond pulsed laser. The
experiment was conducted in full compliance with the procedures dictated by the French Civil Aviation Authorities.
To perform laser ranging measurement on space debris, the laser link budget needed to be improved. Related technical
developments were supported by implementation of a 2J pulsed laser purchased by ASTRIUM and an adapted photo
detection. To achieve acquisition of the target from low accuracy orbital data such as Two Lines Elements, a 2.3-degree
field of view telescope was coupled to the original MéO telescope 3-arcmin narrow field of view. The wide field of view
telescope aimed at pointing, adjusting and acquiring images of the space debris for astrometry measurement. The
achieved set-up allowed performing laser ranging and angular measurements in parallel, on several rocket stages from
past launches.
After a brief description of the set-up, development issues and campaigns, the paper discusses added-value of laser
ranging measurement when combined to angular measurement for accurate orbit determination. Comparison between
different sets of experimental results as well as simulation results is given.
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Observations of satellites in geosynchronous orbit (GEO) are routinely performed by optical sensors at night when the
phase angle—the angle between the satellite’s lines of sight to earth and to sun—is less than about 85 degrees. Daytime
optical observations of satellites in the GEO belt will be performed at larger phase angles. In afternoon and morning
hours, small phase angles are available, but at mid-day the phase angle is constrained to be greater than a minimum
value that depends upon the latitude of the sensor and time of year. On Maui at summer solstice, for example, the
minimum phase angle is 110 degrees at mid-day for observations of the GEO belt. In order to predict their visibility
during the daytime, observations of GEO satellites were conducted at night with a small-aperture telescope at the large
phase angles available soon after dusk and before dawn. Analysis of the satellite images reveals a flattening in the light
curve for phase angles greater than 100 degrees, and the data provide an empirical model of the expected satellite signal
at all phase angles.
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Anomaly detection has been considered as an important technique for detecting critical events in a wide
range of data rich applications where a majority of the data is inconsequential and/or uninteresting. We
study the detection of anomalous behaviors among space objects using the theory of conformal prediction
for distribution-independent on-line learning to provide collision alerts with a desirable confidence level. We
exploit the fact that conformal predictors provide valid forecasted sets at specified confidence levels under
the relatively weak assumption that the normal training data, together with the normal testing data, are
generated from the same distribution. If the actual observation is not included in the conformal prediction
set, it is classified as anomalous at the corresponding significance level. Interpreting the significance level
as an upper bound of the probability that a normal observation is mistakenly classified as anomalous, we
can conveniently adjust the sensitivity to anomalies while controlling the false alarm rate without having
to find the application specific threshold. The proposed conformal prediction method was evaluated for a
space surveillance application using the open source North American Aerospace Defense Command (NORAD)
catalog data. The validity of the prediction sets is justified by the empirical error rate that matches the
significance level. In addition, experiments with simulated anomalous data indicate that anomaly detection
sensitivity with conformal prediction is superior to that of the existing methods in declaring potential collision
events.
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The need for a global collaborating space situational awareness (SSA) network, including radars, optical and other sensors for communication and surveillance, has become a top priority for most countries who own or operate man-made space-crafts. Such a SSA system requires vast storage, powerful computing capacity and the ability to serve hundreds of thousands of users to access the same database. These requirements make traditional distributed networking system insufficient. Cloud computing, which features scalable and elastic storage and computing services, has been recognized as an ideal candidate that can meet the challenges of SSA systems' requirements. In this paper, we propose a Cloud-based information fusion system for SSA and examine a prototype that serves space tracking algorithms. We discuss the benefits of using Cloud Computing as an alternative for data processing and storage and explore details of Cloud implementation for a representative SSA system environment.
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Connectivity and Dissemination for Cognitive Space Communications
In this work, a Quality of Service (QoS)-aware routing (QAR) algorithm is developed for Low-Earth
Orbit (LEO) polar constellations. LEO polar orbits are the only type of satellite constellations where
inter-plane inter-satellite links (ISLs) are implemented in real world. The QAR algorithm exploits
features of the topology of the LEO satellite constellation, which makes it more efficient than general
shortest path routing algorithms such as Dijkstra’s or extended Bellman-Ford algorithms. Traffic
density, priority, and error QoS requirements on communication delays can be easily incorporated into
the QAR algorithm through satellite distances. The QAR algorithm also supports efficient load
balancing in the satellite network by utilizing the multiple paths from the source satellite to the
destination satellite, and effectively lowers the rate of network congestion. The QAR algorithm
supports a novel robust routing scheme in LEO polar constellation, which is able to significantly
reduce the impact of inter-satellite link (ISL) congestions on QoS in terms of communication delay
and jitter.
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Ubiquitous wireless networking requires efficient dynamic spectrum access (DSA) among
heterogeneous users with diverse transmission types and bandwidth demands. To meet user-specific
quality-of-service (QoS) requirements, the power and spectrum allocated to each user should lie inside
a power/spectral-shape bounded region in order to be meaningful for the intended application. Most
existing DSA methods aim at enhancing the total system utility. As such, spectrum wastage may arise
when the system-wide optimal allocation falls outside individual users’ desired regions for QoS
provisioning. In this work, novel QoS-aware DSA algorithms are developed for both non-cooperative
power allocation (QoSNCPA) and cooperative (QoSCPA) users in cognitive radio (CR) networks. The
algorithms maximize the “useful utilities” to the users, and minimize the power consumption and
mutual interference within the CR network. Simulations results of the QoSNCPA and QoSCPA for
single and multiple channel cases demonstrate the effectiveness of the algorithms for DSA.
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For worldwide, a satellite communication network is an integral component of the global networking infrastructure. In
this paper, we focus on developing effective routing techniques that consider both user preferences and network dynamic
conditions. In particular, we develop a weighted-based route selection scheme for the core satellite communication network.
Unlike the shortest path routing scheme, our scheme chooses the route from multiple matched entries based on the
assigned weights that reflect the dynamic condition of networks. We also discuss how to derive the optimal weights for
route assignment. To further meet user’s preference, we implement the multiple path routing scheme to achieve the high
rate of data transmission and the preemption based routing scheme to guarantee the data transmission for high priority
users. Through extensive simulation studies, our data validates the effectiveness of our proposed routing schemes.
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Networking technologies are exponentially increasing to meet worldwide communication requirements. The rapid
growth of network technologies and perversity of communications pose serious security issues. In this paper, we aim to
developing an integrated network defense system with situation awareness capabilities to present the useful information
for human analysts. In particular, we implement a prototypical system that includes both the distributed passive and active
network sensors and traffic visualization features, such as 1D, 2D and 3D based network traffic displays. To effectively
detect attacks, we also implement algorithms to transform real-world data of IP addresses into images and study the pattern
of attacks and use both the discrete wavelet transform (DWT) based scheme and the statistical based scheme to detect
attacks. Through an extensive simulation study, our data validate the effectiveness of our implemented defense system.
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Debugging Wireless Sensor Network (WSN) applications deployed on actual sensor nodes is difficult, since debuggers normally require a wired (e.g. USB) interface. In this paper we propose a mechanism for WSN application debugging that is based on remote access, through the wireless interface, and that uses the native environment in which the application was developed (i.e. it acts as a source-level debugger). The approach, called RSD-WSN, is based on creating continuous behavioral snapshots of a remotely located sensor node by binding it with a virtual node. Hence by using RSD-WSN, users can debug a WSN application node that is running remotely. This framework allows a programmer to develop an application using high level abstractions (finite state machine) and then automatically generate code for target platforms. The complied generated code could be then directly loaded on sensor nodes and the framework provides interfaces by which an application developer can bind execution sequences of a remote sensor node with a virtual simulated node, so that the developer can monitor node behavior and refine the application in case of unexpected behaviors.
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Processing, Exploitation, and Decision Support for Attributions and Tactical Planning I
In this paper, a high-degree cubature information filter (CIF) is proposed for multiple sensor estimation. Astatistical
linear error propagation method incorporates the high-degree cubature integration rule into the extended information
filtering (EIF) framework such that more accurate estimation can be achieved than the extended information filter as
well as the unscented information filter (UIF). In addition, the high-degree CIF maintains close performance to the
Gauss-Hermite Quadrature information filter (GHQIF) but uses significantly fewer quadrature points. As a result, the
curse of dimensionality problem existing in the tensor product based GHQIF can be greatly alleviated. Besides the
improved estimation accuracy and computational efficiency, the high-degree CIF also exhibits the desirable robustness
under unknown noise statistics. The proposed CIF is compared with other information filters (e.g., EIF, UIF, GHQIF)
via a target tracking problem and demonstrates the best performance.
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Over the last decade it has been established that medium- to long-range weather patterns are significantly affected by
stratospheric events, and it is well known that the severe storms are critically dependent on the winds aloft. However,
existing observations of the dynamical atmosphere above the cloud tops are sparse and irregular, and remote
measurements of upper atmospheric winds have historically proved challenging. Current numerical models must rely on
data from widely separated land-based instruments and satellite observations with modest precision and coverage. Even
less plentiful are observations of the neutral atmosphere above 100 km, despite the high potential impact of space
weather on global navigational and electrical systems. We present here a new instrument concept, the Doppler Wind
and Temperature Sounder (DWTS) that will enable global daily measurements of winds and temperature from 15 to 250
km with fine vertical and horizontal sampling. The measurement concept leverages the high spectral resolution
inherently available with gas-filter correlation radiometry. By exploiting the Doppler shifts resulting from a limbviewing
low Earth orbit satellite, DWTS spectrally resolves large ensembles of atmospheric emission features. From
this, we are able to extract horizontal wind vectors and kinetic temperature with unprecedented precision. Here we
review the DWTS measurement concept, present simulation results, and conclude by describing a low-cost operational
system that would quantify atmospheric dynamics from the lower stratosphere into the mid thermosphere for the first
time.
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A 16 element HgCdTe e-APD detector has been developed for lidar receivers that has significant improvements in
sensitivity in the spectral range from < 1μm to 4 μm. A demonstration detector consisting of a 4x4 APD detector array, with 80 μm square elements, a custom CMOS readout integrated circuit (ROIC), a closed cycle cooler-Dewar, and
support electronics has been designed, fabricated, and tested. The custom ROIC design provides > 6 MHz bandwidth
with low noise and 21 selectable gains. Ninety-six arrays were fabricated with 69% of the arrays meeting the dark
current spec in the center 4 pixels at 10 V bias where the APD gain was expected to be around 150. Measurements to 12
V on one array showed APD gains of 654 with a gain normalized dark currents of 1.2 fA to 3.2 fA. The lowest dark
current array showed a maximum dark current of 6.2 pA at 10 V and 77 K. The 4.4 μm cutoff detector was characterized
at an operating temperature of 77K with a 1.55 μm, 1μs wide, laser pulse. The photon conversion efficiency at unity
gain was 91%. The mean measured APD gain at 77 K was 308 at 11V, the responsivity was 782 μV/pW, the average
NEP was 1.04 fW/Hz1/2. The bandwidth was 6.8 MHz, and the broadband NEP was 2.97 pW. This detector offers a
wide spectral response, dynamic range, and substantially improved sensitivity and lifetime for integrated path
differential absorption (IPDA) lidar measurements of atmospheric trace gases such as CO2 and CH4.
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Previous astrophysical studies have explained the orbital dynamics of particles that acquire a high electrostatic charge.
In low Earth orbit, the charge collected by a microscopic particle or an ultra-small, low-mass satellite interacts with the
geomagnetic field to induce the Lorentz force which, in the ideal case, may be exploited as a form of propellantless
propulsion. Efficient mechanisms for negative and positive electrostatic charging of a so-called attosatellite are
proposed considering material, geometry, and emission interactions with the ionosphere’s neutral plasma with
characteristic Debye length. A novel model-based plasma physics study was undertaken to optimize the positive charge
mechanism quantified by the system charge-to-mass ratio. In the context of the practical system design considered, a
positive charge-to-mass ratio on the order of 1.9x10-9 C/kg is possible with maximum spacecraft potential equal to the
sum of the kinetic energy of electrons from active field emission (+43V) and less than +5V from passive elements. The
maximum positive potential is less than what is possible with negative electrostatic charging due to differences in
thermal velocity and number density of electronic and ionic species. These insights are the foundation of a practical
system design.
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A method is proposed for extracting attitude data from streaked star images using traditional image processing methods. The process enables collection of both attitude and angular velocity estimates from streaking star images, where traditional star identification methods would produce poor results. Star streak endpoints are localized as "corner-like" portions of a streak. A vector cross-product based method is developed to produce a proper grouping in time for endpoints. Star identification and single point attitude determination methods can be applied to each set of endpoints, retrieving two sets of data from a single image. Monte Carlo results are presented, and the implications of the results are discussed. Multiple corner detection methods are considered and compared. Future work needed to mature the process is discussed. Results indicate an endpoint detection accuracy of less than a tenth of a pixel for a camera angle to the rotation axis of greater than 20 degrees and streak lengths up to 40% of the field of view.
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Processing, Exploitation, and Decision Support for Attributions and Tactical Planning II
Automatic vehicle license plate recognition (LPR) is important for intelligent traffic surveillance systems. This paper
suggests a vehicle license plate algorithm, color component texture detection and template matching (CCTD-TM).
CCTD-TM has advantages of ease of implementation and highly efficient in calculation. We suggest a novel algorithm
of color component texture for license plate localization. This algorithm takes advantage of the feature of fixed color
texture of plate base and character. The image preprocessing and character recognition by template matching parts are
included in the LPR algorithm. The preliminary results demonstrate an average detection rate over 96.5% and an average
recognition rate over 89.9% on hundreds of vehicle images tested in the experiments.
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This paper presents a fuzzy based approach to segmenting color images in three steps. First, we discuss a fuzzy color
extractor to extract fuzzy color components. Second, we present techniques for iteratively generating reference patterns
(seeds) to extract color components. Finally, we use the region growing method to check connectivity of segmented subimages.
Different from the existing color segmentation methods that provide a crisp segmentation of color images, the proposed
approach herein generates a fuzzy color segmentation which classifies the same pixel into several fuzzy sets.
As an example, we apply the proposed approach to segment the chemical plumes from images taken in undersea
environments.
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Atmospheric clouds are commonly encountered phenomena affecting visual tracking from air-borne or space-borne
sensors. Generally clouds are difficult to detect and extract because they are complex in shape and interact with sunlight
in a complex fashion. In this paper, we propose a clustering game theoretic image segmentation based approach to
identify, extract, and patch clouds. In our framework, the first step is to decompose a given image containing clouds. The
problem of image segmentation is considered as a “clustering game”. Within this context, the notion of a cluster is
equivalent to a classical equilibrium concept from game theory, as the game equilibrium reflects both the internal and
external (e.g., two-player) cluster conditions. To obtain the evolutionary stable strategies, we explore three evolutionary
dynamics: fictitious play, replicator dynamics, and infection and immunization dynamics (InImDyn). Secondly, we use
the boundary and shape features to refine the cloud segments. This step can lower the false alarm rate. In the third step,
we remove the detected clouds and patch the empty spots by performing background recovery. We demonstrate our
cloud detection framework on a video clip provides supportive results.
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In this paper, we formulate the problem of infrared target tracking as a binary classification task and extend the online
multiple instance learning tracker (MILTracker) for the task. Compared with many color or texture based tracking
algorithms, the MILtracker highlights the difference between the target and the background or similar objects, and is thus
suitable for infrared target tracking which undergoes serious textual information loss. To address the specific challenges in
the infrared sequences, we extend the original MILtracker from two aspects. Firstly, an adaptive motion prediction procedure is integrated in to enhance the efficiency of the tracker. This step helps discriminate disturbing objects that are visual very similar to the target under tracking. Secondly, a spatial weight mask is introduced into the target representation to augment its robustness against similar background clutters, especially distracters. We apply the proposed approach on several challenging IR sequences. The experimental results clearly validate the effectiveness of our method with encouraging performances.
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