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X-ray measurements are critical for the understanding of cycles of matter and energy in the Universe, for understanding the nature of dark matter and dark energy, and for probing gravity in the extreme limit of matter accretion onto a black hole. We propose a program to mature the current x-ray microcalorimeter technology, while developing transformational technology that will enable megapixel arrays. X-ray calorimeters based on superconducting transition-edge sensors achieve the highest energy resolution of any non-dispersive detector technology. The performance of single x-ray calorimeter pixels has reached that required for many possible future missions such as IXO, RAM, and Generation-X, but further optimization is still useful. In the last years, we have made progress in developing techniques to control and engineer the properties of the superconducting transition. We propose to continue this single-pixel optimization, and to improve both the practical and theoretical understanding of the correlation between alpha, beta, and noise to identify favorable regions of parameter space for different instruments. A greater challenge is the development of mature TES x-ray calorimeter arrays with a very large number of pixels. Advances in the last several years have been significant. We have developed modestly large (256 pixel) x-ray calorimeter arrays with time-division SQUID multiplexing, and demonstrated Walsh code-division SQUID multiplexing, which has the potential to allow scaling to much larger arrays. Here we propose to extend this work, and also to introduce a new code-division SQUID multiplexing circuit with extremely compact, low-power elements. Using this approach, it is possible for the first time to fit all of the detector biasing and multiplexing elements underneath an x-ray absorber, allowing in-focal-plane multiplexing. This approach eliminates the requirement to bring leads from each pixel out of the focal plane, while reducing the power dissipati

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<p> N/A</p>

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<p>  </p> <p style="margin: 0px; font-family: Calibri; "> NASA has plans to fly stratospheric ULDBs for missions of 100 days or more in the next few years. As these balloons circumnavigate the globe multiple times, the risk of complete data loss in the case of adverse wind patterns or balloon failure will begin to outweigh the benefits of continued data acquisition. This could be mitigated if the complete data could be transferred from the balloon periodically throughout the mission. For missions with high data rates (such as a wide field telescope), downloading the data via ground stations used for balloons may be prohibitively slow and unable to match the data rate. Other methods, such as using the Tracking and Data Relay Satellite System (TDRSS) or line of sight communications with multiple ground stations have in the past proven to be prohibitively expensive. We are developing AIRS (Automated Information Retrieval System), a lightweight glider capable of descending from 30km balloon altitude, autonomously compensating for the jet stream to land in a predetermined GPS coordinate. AIRS carries a solid-state drive capable of withstanding much more than the mild G forces encountered on landing. A prototype has been built and tested at low flight altitudes successfully. Production costs of AIRS are anticipated to be about $1000 for parts and labor. In a one-day workshop we will explore various methods of retrieving balloon data in flight. We will compare the costs and risks of TDRSS, multiple line of sight ground stations, and AIRS. Collaborative efforts, and funding possibilities, to explore these concepts further will be discussed. The outcome will be an economical way to buy down a mission risk on ambitious future balloon missions. We will write a report on our findings and coordinate this with continued development of AIRS, which we plan to flight test (using a different funding source).</p>

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<p> The understanding of the line emission from heavy ions is still incomplete and often inaccurate, resulting in missing or incorrect line assignments and missing or incorrect flux. This limits the utility both of spectral predictions and of space-based equipment used for observing the solar spectrum. An example of this is the 195 Å channel of TRACE, which is centered on the FeXII line. Recent changes in the atomic data used to model the spectral emission near 195 Å have dramatically (up to an order of magnitude) changed the temperature response of this channel. A similar situation is likely to recur for the Atmospheric Imaging Assembly (AIA) instrument, which is to be launched as part of the Solar Dynamics Observatory. Here the responses of the six iron line channels, centered on lines from FeIX, FeXII, FeXIV, FeXVI, FeXVIII, FeXX, FeXXIII, and FeXXIV, sensitively depend on the correct position and strength of neighboring lines that fall within the instrumental response. Current predictions from various theoretical models describing the emission covered by these channels are in disagreement, and definitive experimental observations at the level of detail needed for establishing an authoritative model are nonexistent. Given the impending launch of the Solar Dynamics Observatory, which is a key mission in the Heliophysics Research Program, a resolution of the spectral modeling issues by definitive laboratory measurements is not only timely but urgently needed. Here we propose to conduct the definitive laboratory measurements required for calibrating the temperature response of the six AIA iron channels. Our work will provide highly accurate wavelength and intensity information of all relevant lines falling into the wavelength bands of the six Fe channels. This will provide the data for producing the high-confidence spectral modeling codes needed for use in calibrating the response of each iron line channel as well as for the successful evaluation and utilization of the observational data from the six AIA iron line channels.</p>

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<p> The readout technique for “tilt locking” has been widely adopted in a range of scientific areas from quantum optics to spectroscopy since first being demonstrated in 1999 [1,2], but it has not been applied to high-performance laser frequency stabilization. Common laser stabilization systems transfer the length stability of an optical reference cavity to the laser frequency (or wavelength) using the standard RF interrogation technique (Pound-Drever Hall (PDH) locking), which employs electro-optic phase modulation of the carrier and RF demodulation as shown in Figure A below. In tilt locking, the reference signal relies instead on interference between overlapping spatial modes on reflection from the cavity, realized simply by intentionally tilting the laser beam and reading out a DC signal level difference between two halves of a two-element photodiode. The use of this DC signal allows the elimination of the phase modulator, RF signal generator and mixer electronics, as shown in Figure B. In addition, the DC operation largely reduces the susceptibility to a commonly limiting noise source: parasitic etalons. To demonstrate tilt-locking as a viable laser frequency stabilization technique we will construct a tilt-locking system comprising a laser, an ultra-stable optical reference cavity in vacuum, along with associated optics and electronics. [1] D. A. Shaddock et al. Opt Lett 24 1499 (1999) [2] B. J. J. Slagmolen, et al. IEEE J. Q. E., 38, 11, (2002)</p>

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<p>We have developed carbon nanotube formulations primarily geared towards enhanced stray light control on a variety of instruments.  IRAD has supported development of this technology to make it 10 to 100 times blacker than alternate surface treatments from the Near UV to Far Infrared and a large variety of substrates suitable for space flight instrumentation.   In addition, we have performed the first growth on catalyst applied to substrates using Atomic Layer Deposition (ALD).  Catalyst is normally deposited using thermal or e-beam evaporation which allows for coating flat surfaces.  Many baffles are dimensional, curved or complex, requiring conformal deposition.  The development of a conformal nanotube process is enabling to many applications.  We have demonstrated ALD of iron catalyst out of house and hope to achieve an in-house capability.  Ellipsometry performed on the part verified sub nanometer uniformity of catalyst across a test part .  The compact coronagraph baffle is larger and more complex which will pose a significant challenge in maintaining uniformity over a larger third dimension.   In addition, we must solve the problem of managing feedstock gas flow in our nanotube furnace during chemical vapor deposition (CVD).  We have seen significant shadowing and non uniformity of growth due to laminar flow at substrate edges.  Modeling of the gas flow has begun and will be useful in solving this problem.  In addition we are performing our occulter growth using a reflector to direct feedstock gas to the shadowed side of the mask.  Our goal will be to address these challenges and deliver a solar chronographic mask that is applicable to other scientific observations.</p>

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<p>Demonstrate efficacy of a novel growth technique for planar waveguides (PWG) Enable PWG laser technology with improved performance, efficiency and manufacturability. Manufacture a planar waveguide more like a fiber, instead of building it piece-by-piece. Build an optimized PWG amplifier prototype using this technique Evaluate its performance Demonstrate potential of new technique Collaborators: NP Photonics, Inc.</p>

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<p> <span style="font-family: Calibri; ">The objectives of this study are to adapt an existing JPL dewar and electronics for use with the STA device for observation at Palomar using an existing array (expected to have delta doped detectors produced with the MBE RTD), characterize and calibrate the performance of the array and the camera system in the laboratory (iterate), deploy to Palomar for a test run (first light check), and optimize devices and dewar configuration based on feedback.</span></p>

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<p>The Cleaning Lenses and Mirrored Surfaces with Electrons tasks include: Development of Fractal Wand Geometries; Vacuum Chamber testing of Fractal Wand Prototypes; and selection of best prototype.</p>

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<p> Our task is evaluating a specialized detector for guidance, navigation and control (GNC) applications. The detector being evaluated is a 15 microsecond Latency Asynchronous Temporal Contrast Vision Sensor, referred to as a spiking sensor. It detects change in intensity on the detector at for very high rate applications. Each pixel on the detector operates independently, and detects intensity changes on the pixel. When the change in intensity exceeds a threshold and an event is generated. The events are reported from the detector as an asynchronous stream of digital pixel addresses and time tag (to an accuracy ~10 microseconds). This results in a highly reduced set of data returned from detector. Hence, only points of interest, not image frame data is output, which reduces data volume > 100x. The device is very low power (~25mW). Since the detection of the events is done on the detector, not in a processor, the requirements on processing are reduced. Because the events are asynchronous, the timing is tied to the event, not a frame rate, such as with imagers. For GNC characterization, we performed testing on laboratory targets that included a star simulator and Mars terrain targets, as well as field testing on star patterns, planets, and International Space station (as a beacon test) passes. During the testing, we gained understanding of the details of detector biases and operations, and developed processing algorithms for clustering and noise rejection on collected data. The current detector design has high dark current and low (9%) QE; devices are in design that will give the technology a 100x SNR improvement by changes in manufacturing processes (silcon process), and front side vs backside illumination. The projection for GNC of the future device is part of this task (to be completed at end of May 2012).</p>

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<p>Background. NASA missions undergo wide variation in communications link conditions. Over the course of months, the range changes dramatically from launch, to cruise, to say, Mars orbit, but link conditions change on much shorter time scales, as well. For example, a typical track of MRO tracked by the Deep-Space Network might start at antenna elevation 11°, rise to 72°, and then fall to 8° over a twelve hour period. Recent and near-future NASA missions have their data rates limited by dynamic effects such as weather (e.g., MRO Ka-band links), solar scintillation (e.g. Solar Probe), on-board interference (e.g., MRO CRISM interference), launch plumes, and other effects. A 2005 Mars Technology Program study reported that up to 50% more data can be returned on a typical Mars-lander to Mars-orbiter link when adaptive data rates are used on the link. Our task is to extend the concept of adaptive data rates to variable and adaptive coded modulation, in which the dynamic power and bandwidth resources can be much more effectively utilized. A 2010 study by ESA determined that in one practical scenario, a VCM system could more than double the total data volume returned. Our task is to make effective use of the CCSDS standard coded-modulations, thereby allowing us to operate close to the unconstrained capacity limit, regardless of link conditions. To do this, we will develop a physical-layer design that allows the transmitter to switch between coded modulations on a codeword-to-codeword basis, a mechanism to inform the receiver which coded modulation is being used, and the receiver tracking structures necessary to identify the coded-modulation and demodulate and decode the data appropriately.</p>

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<p>Current methods for monitoring the water used on the ISS rely heavily on ground analysis of archival samples. Air monitors presently on board the ISS could be used for trace analysis of the water samples. Electrospray ionization (ESI) is a powerful and widely used ionization technique for analysis of bio-molecules in solution and provides a potential means for introducing water into the current monitors. Ions are formed in liquid droplets and these droplets behave differently depending on the composition of the liquid. A ground study is important to characterize the spray produced from different liquid compositions in an ESI source as a first step to proposing an ESI flight experiment. This study will serve as the baseline for the flight experiment, where the effect of microgravity on electrospray is unknown. Different liquid compositions will be used in an attempt to affect the surface tension and conductivity, and, therefore, the power requirements to form an electrospray. Solutions mimicking the ISS water samples will be tested to determine if the sprays produced require different parameters from those produced using different dopants. The intended product of this project will be a report detailing the effects of solution composition, needle size, and solution flow rate using the ESI source. These results will provide a baseline for an on-orbit ESI experiment, which might eventually lead to a new ionization source for water sample analysis. A successful completion of this project will lead to a proposal aimed at studying ESI as a station detailed test objective. As ESI is currently used in ground-based studies of biomolecules, further testing of this technique for on-orbit medical monitoring may be pursued.</p>

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<p> <span style="font-family: Calibri; ">A new navigation technique known as LiAISON (Linked Autonomous Interplanetary Satellite Orbit Navigation) may be used to propel the benefits of GPS to new orbits, including GEO, lunar, L1, and L2 orbits.</span></p>

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<p> N/A</p>

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<p> What causes the Sun to vary? The Sun gives off magnetic fields, bulk plasma (the solar wind) and energetic particles moving up to nearly the speed of light, and all of these vary spatially and temporally. The three dimensional structure of solar wind turbulence, coronal mass ejections (CME) and magnetic clouds can only be understood with concurrent, multipoint measurements. Rapid advancements in CubeSat technology and the NASA OCT funding of Interplanetary CubeSats has opened the possibility of developing a flotilla of tiny spacecraft carrying magnetometers or simple plasma instruments to conduct these investigations. CubeSats are already demonstrating their cost effectiveness in Earth orbit. Heliophysics is a particularly fruitful field for extension of CubeSats to interplanetary constellations because many scientific investigations can only be accomplished with concurrent, spatially distributed measurements and the fields and particles instrumentation may fit within CubeSat volume constraints. While many CubeSat subsystems developed for Earth orbit are directly applicable to interplanetary mission, many subsystems will have to be totally redesigned to meet the requirements of deep space missions. This workshop will identify the scientific investigations enabled by a flotilla of small instruments in Earth-trailing and Earth-leading orbits. It will outline a mission concept and the technology challenges of the instruments and spacecraft systems necessary to conduct these investigations. This new approach, a flotilla of simple instruments, could help NASA develop a new approach to heliophysics research.</p>

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<p>The project focuses on key physico-chemical process technologies for Atmosphere Revitalization Systems (ARS) that increase reliability, capability, and consumable mass recovery as well as reduce requirements for power, volume, heat rejection, and crew involvement. For the Environmental Monitoring Systems (EMS) effort, the project is developing and demonstrating onboard analysis capabilities which will replace the documented need to return air and water samples to earth for ground analysis. This effort is addressing these challenges by adopting a new architecture that is based on the modular integration of multiple sensing modalities, employing a hybrid combination of simple, rugged technologies and, where needed, highly capable complex approaches, to completely address monitoring needs of the future. It incorporates Microelectromechanical Systems (MEMS) technologies to enable significant miniaturization over current systems, and selects elements offering both low resources and high reliability operation for affordability. The project is developing, demonstrating and/or testing leading process technology candidates and system architectures that will meet or exceed current requirements and fill capability gaps or significantly improve the efficiency, safety, and reliability over the State-of-Art (SOA). The project’s main goal is to demonstrate test articles (at various technology readiness levels) in a ground test facility under relevant flight conditions.</p>

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<p>The University of Maryland is proposing to use a dielectric barrier discharge (DBD) as a means to dissociate N2O. DBD uses alternating high voltage differences between two electrodes to create strong electric fields. One or both of the electrodes is covered in a dielectric, and a gap in between allows gas to pass through. Nitrous Oxide sent through the gap between the electrodes has its free electrons accelerated by the large E-field, and in the process the electrons collide with N2O molecules.</p>

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<p>Incorporate PF into GSFC’s Orbit Determination Toolbox (ODTBX). Augment PF with ODTBX’ unique ability to partition error sources into subspaces for analysis. Utilize multi-core server to facilitate fast simulation of large particle populations.</p>

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<p align="LEFT"> <span style="font-size: 12px;"><span style="font-family: times new roman,times,serif;">The telescope design is a direct continuation of the development from NIXT to TRACE and AIA: we propose a Ritchey-Chr´etien with plate scale sufficient to provide 0.1 arcsec pixel size, and multilayer coatings on two D-shaped halves, so that there are two wavelength channels available. The detector is a large-format back-illuminated CCD, providing high quan tum efficiency and rapid readout for high im age cadence. Channel selection is made via selectable focal plane filters. An H-telescope with NTSC (TV) output is included for real-time pointing verification during the flight.</span></span></p> <p align="LEFT"> <span style="font-size: 12px;"><span style="font-family: times new roman,times,serif;">Major components of this new payload have been developed and qualified for the Hinode XRT instrument, SDO program (AIA & HMI) and for the Solar Ultraviolet Magnetograph Investigation (SUMI) sounding rocket. This has helped keep the development costs for Hi-C sig nificantly lower than they otherwise would have been. </span></span></p> <p align="LEFT"> <font face="CMR10" size="3"><font face="CMR10" size="3"><font face="CMR10" size="3"><font face="CMR10" size="3"><span style="font-size: 12px;"><span style="font-family: times new roman,times,serif;">The vehicle layout includes all major components needed for the flight demonstration. . It has a to total length of 108.9 inches and a launch weight of 562.9 pounds. The vehicle is the standard NASA 22-inch diameter shell. The proposed experiment design is based on the SAO NIXT and TXI instrument designs. A detailed weight breakdown is provided in Figure 5. As evidenced by Table 1, every component in the proposed mission has heritage in multiple successful instruments. Now we propose to ex tend the telescope magnification to the diffrac</span></span></font></font></font></font></p> <p> <span style="font-size: 12px;"><font face="CMR10"><font face="CMR10"><font face="CMR10"><font face="CMR10"><font face="CMR10"><font face="CMR10"><span style="font-family: times new roman,times,serif;">tion limit. AIA chose to extend the TRACE resolution to a full-sun field of view and now we are proposing to extend TRACE by increasing the magnification on the secondary mirror. The technologies required to build AIA are identical to that for Hi-C and every major contribution to the development of Hi-C is performed by the teams that built AIA (SAO, LMSAL)</span></font></font></font></font></font></font></span></p> <p align="LEFT">  </p> <p>  </p>

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<p>Integration of graphene as the top metal on GaN Schottky. This will replace platinum, which is 50% transparent at the desired wavelength, with graphene, which has higher mobility and much higher transparency (>90%). Develop a fabrication process for GaN Schottky and a chemical vapor deposition process for large area graphene. Develop a process to cleanly integrate single or multilayer graphene on GaN devices and pattern them. Develop a characterization scheme to determine the Schottky barrier height of graphene and device QE.</p>

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<p>Build and test in a relevant environment a Mars propellant production plant of an appropriate scale for an initial demonstration on Mars. It will produce sufficient propellants for a small science hopper vehicle to hop 2 km every 30 days. Specific objectives include: • Validate the performance of specific components included in the design from ref. 2 • Acquire data for a range of operating conditions for the CO2 acquisition devices to enable design improvements • Develop realistic estimates of the mass and volume of the ‘other’ components (valves, plumbing, wiring, etc.)</p>

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<p> The objective of the proposed research is to develop and test a prototype of an innovative and simple detector technique to identify moderate energy (a few MeV) positrons in space. Positron measurements at such energies have never been made in space. Measurement of the Galactic cosmic ray (GCR) positron fraction at low energies will provide new information about the transport and modulation of particles in the Local Interstellar Medium (LISM) and the Heliosphere. Also, positrons are unique among observable stable high energy particles since they are formed only as secondaries from high energy charged particle interactions in the Solar atmosphere during Solar particle events (SPEs). Positron measurements of this type will open a new channel for the study of Solar particle events which could address issues such as the determination of plasma and magnetic field parameters during high energy particle acceleration at the Sun, time evolution of Solar flare processes, and magnetic connectivity between acceleration sites and the interplanetary medium.</p> <p> Our detector scheme, the Positron Identification by Coincident Annihilation Photons (PICAP) technique, is based upon simple, reliable, well-proven and robust detectors. PICAP was inspired by the participation of the P.I. in a measurement of the β+ half-life of 54Mn (for cosmic-ray chronometry) at Argonne National Laboratory using a similar technique [Wuosmaa et al. 1998]. The proposed project will develop and build a prototype PICAP instrument and expose it to negatrons and positrons at Jefferson Laboratory to demonstrate detection efficiencies and—equally important—PICAP's efficiency in discriminating against negatrons as false positrons. The prototype will also be exposed to protons at Indiana University Cyclotron Facility to demonstrate PICAP's efficiency in rejecting protons as false electrons. The goal is a proven detector system that, in a stand-alone instrument or, more likely, as part of a charged particle instrument/suite, can measure the energetic particle population at moderate energies (1-100's of MeV/nucleon), and can simultaneously measure the electron flux and positron fraction at previously unexplored energies. An instrument incorporating PICAP would be particularly attractive as to cost, mass, power and telemetry requirements, making it well suited to a variety of space missions in contrast to more complex and massive magnetic spectrometer techniques.</p> <p> The new addition to previous charged particle instrument designs is the additional capability to precisely measure the positron fraction. We propose to build a PICAP prototype, proving the positron detection capability, and optimized for the identification of 5-10 MeV positrons. A PICAP instrument may easily be tailored to measure other energies, depending upon specific science goals. A PICAP capability could be easily incorporated into a standard charged particle instrument designed to measure all moderate energy charged particles in space.  </p> <p> N/A</p>

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<p>Strong interest in whispering gallery mode resonators (WGMR) for use in chip-scale photonic devices is motivated by their high optical quality, mechanical simplicity and extremely compact form. In these circular resonators, the light propagates around the circumference, localized by total internal reflection at the dielectric boundary. The typical WGMR geometry is constrained because the full mode intensity is not accessible. Only a small portion of the mode volume, the evanescent field that exists just outside the disc perimeter, is exposed for external optomechanical coupling or molecular sensing applications. In this research, we make use of focused ion beam (FIB) microfabrication to mill features into the WGMR. FIB engineered disc (FIBED) resonators can be formed with open structure, i.e. a milled notch creates a free space gap within the mode volume. The gap provides access to the internal fields of the resonator, and therefore the full mode intensity. This novel approach allows direct interaction of external mechanisms, atoms, or molecules with the resonant light field. We have demonstrated a calcium fluoride FIBED resonator with optical quality factor (Q) exceeding a million. With our developed FIB process, charge collection and material re-deposition issues have been mitigated, and we observe no effects of gallium ion contamination. In our initial demonstrations, the optical Q appears to be limited by Rayleigh scattering losses from the notch surface roughness. The FIB milling can ultimately achieve 20 times better surface finish, which will greatly enhance the optical Q. This novel open cavity WGMR allows interaction of external mechanisms with the full intensity of the resonant light field. In particular, a mechanical resonator can be engineered within the high-Q cavity to realize a monolithic optomechanical device. Optomechanical coupling to the WGMR field yields extremely high sensitivity to the displacement and motion of the mechanical resonator.</p>

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<p> Develop an etalon front end receiver (FIDDL) and combine it with the Optical Autocovariance Wind Lidar (OAWL) for an integrated direct detection (IDD) wind lidar.<br /> Demonstrate the IDD hybrid system measuring winds from both molecular and aerosol returns using a single lidar.<br /> The hybrid system will significantly reduce the size and cost of a 3D Winds mission (on the order of 20-30% based on aperture size) compared to the current hybrid 2-laser approach.<br /> Performance goals are < 1 m/s wind estimate precision for the etalon sub-system.</p>

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<p> </p><p>The idea is to develop a graphene/polyethylene layer that can be laminated to other thin films as is commonly done in the food packaging industry.  A typical food packaging film has more than five layers of materials that confer altogether the desired physical and mechanical properties of the package.  The proposal encompasses the feasibility study of graphene/polyethylene films for use in lightweight and safe food packaging.</p><p>The focus of this project is the construction, characterization, and demonstration of a flexible, impermeable membrane for use in any application where gases are required to be contained or excluded, such as food and drug packaging, or inflatable modules and habitats.  Graphene is essentially single-layer graphite, and can be thought of as an unrolled nanotube.  Graphene has shown promise to be impermeable to all gases.  It has been observed that as little as a single atomic layer of graphene is impenetrable by gases, including helium [J. S. Bunch et al., Nano Lett., 8, 2458 (2008)].  This property can be exploited to fabricate impermeable membranes.  Graphene will be embedded within polymer films for fabrication of these impermeable membranes.                    </p><p> </p>