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High peak power, high efficiency, high reliability lightweight, low cost QCW laser diode pump modules with up to 1000W of QCW output become possible with nLight's new laser diode package methodology. Following the design principles from our Phase I results, we propose an innovative packaging architecture to provide NASA with highly reliable 808nm laser diode pump sources for space based LADAR systems or other uses. nLight proposes a package development program to demonstrate up to 1000W of QCW pump power, with greater than 100E8 laser shot reliability.

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Many NASA space and Earth programs in the infrared range 1060-1550 nm are limited by the detector performance that require long exposure time due to their low sensitivity and/or high noise. Large format infrared photon counting arrays with ranging capability would provide a valuable tool to many space missions. Current state of the art fabrication of photon counting infrared detector arrays on non-silicon semiconductors is not mature enough to monolithically integrate complex readout circuitry at pixel level and large format array multiplexing. We proposed to develop novel fast readout integrated circuits (ROIC) to be integrated with large photon-counting infrared detector arrays into 3D imaging cameras with photon-counting sensitivity. These new cameras would support NASA missions in applications such as space docking, landing, remote mapping, and robotic vision. The goal of this program is to develop smart-pixel ROIC arrays in silicon with enhanced radiation tolerance, ready for hybrid integration with large infrared photon-counting avalanche photodiode arrays, that will enable large-area detectors with short integration time, sub-nanosecond timing resolution, and on-pixel logic. In Phase I, we have simulated, implemented, and successfully validated all the blocks of a ROIC array specifically developed for operation with infrared photon-counting arrays. In Phase II, we will improve, fabricate and qualify ROIC arrays with integrated timing functions at pixel level and capable of integration in flip-chip technology with large infrared photon counting detector arrays.

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Modern electronic systems tolerate only as many point failures as there are redundant system copies, using mere macro-scale redundancy. Fault Tolerant Electronics Supporting Space Exploration (FTESSE) creates an electronic design paradigm using reprogrammable FPGAs to create swappable Circuit Object Blocks (COBs) ? analogous to software objects ? for the first time enabling redundancy on a micro-scale. The result is an increased tolerance of point failures by several orders of magnitude over traditional approaches. In the FTESSE approach, FPGAs are partitioned into COBs (groups of gates), each performing a specific function. Bad areas can be mapped like the bad sector data on a disk drive, enabling COBs to be placed in areas of working gates to recover system performance. Hardware tested during Phase I verified point failures could be introduced into an example circuit and corrected. As in the Phase I model, circuits to be monitored reside on a Slave FPGA, and a Master FPGA monitors outputs of all COBs, sensing faults and mapping non-working gates on the Slave FPGA. The Master is a rad-hard, triple mode redundancy (TMR) FPGA, but the Slaves need not be, opening the doors to higher performance applications while maintaining high levels of fault tolerance.

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Applied Technology Associates (ATA) proposes to develop a new inertial sensor by combining two sensing phenomena in a single device. ATA has patented an advanced inertial sensing technology based on magnetohydrodynamics (MHD). Numerous researchers have patented and developed micro-electromechanical sensors (MEMS) that measures inertial angular motions. We believe that a composite sensor based on the best characteristics of both of these technologies is a promising new advancement. Our innovation is denoted the Hybrid Sensor (HYSENS) owing to its origins in two distinct inertial angle rate sensing principles. The MHD technology offers wide bandwidth, high sensitivity, with reasonable size and power. The MEMS offers small size and power. Initial analysis done by ATA and our MEMS technology partners indicates that it is possible to achieve performance goals that are at or near the state-of-the-art for inertial reference sensors. The proposed composite sensor fulfills the need for lightweight, compact, high-precision, high-bandwidth (0-2KHz) inertial reference sensors for use onboard spacecraft with optical communications payloads. The predicted noise performance for HYSENS is less than 0.1 microrad. Volume for this advanced sensor is expected to be under 2 cubic in; its weight under 150 grams; and its power draw under 200 mW.

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The completed Phase I work was directed at the application of nanotechnology to graphite/epoxy composites. A novel approach to the application of the nanotubes onto the carbon fiber surface was investigated. As a result, a very significant increase in compressive strength of 120% was attained, compared with 20% reported in the literature. The Phase II builds on the success of the Phase I. It will address the key issues of scale-up, reproducibility and component fabrication. The batch fiber coating process employed in the Phase I will be replaced with a continuous fiber coating process. Manual pre-pregging of the Phase I will be replaced with a continuous pre-pregging process. Specific CEV type composite applications will be identified. Subsequently, a cost/benefit ratio for CEV will be provided.

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Wide-bandgap SiC semiconductors have been recently investigated for use in power devices, because of their potential capabilities of operating at high power densities, high temperatures and at high frequencies and thus offering advantages such as high efficiency, small size and light weight. Currently a few power devices based on SiC technology have been demonstrated and commercialized. Therefore, an opportunity exists to develop and demonstrate a SiC power inverter, showing the system-level impacts of using commercially available SiC power devices compared with an Si-based inverter, and addressing the related technical issues/risks of implementing SiC technology. Following a successful demonstration of the concept feasibility in Phase I, Phase II research will fully develop, demonstrate, model, and characterize a three-phase all SiC inverter. The inverter will be constructed through the integration of several supporting technologies including circuit design and device paralleling, high temperature packaging and thermal management, high temperature gate based on SOI technology, and other passive components. In the Phase II, the underlying technical issues that govern the fabrication and performance of this SiC inverter will be addressed, and its technical/economical benefits will be analyzed. By implementing technology developed, a high-efficiency, compact SiC inverter technology can be anticipated for potential NASA and other applications.

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As the need for thermal control technology becomes more demanding Micro-Channel Embedded Pulsating Heat Pipes (ME-PHPs) represents a sophisticated and enabling solution. Currently laboratory tests indicate that a magnitude jump in thermal conductivity can be expected with ME-PHPs over conventional materials like aluminum and copper. ME-PHPs will give NASA and the spacecraft community a powerful tool for the thermal control of instruments, detectors, lasers, communication systems, MEMS and power systems. Especially those requiring tight thermal control to the micro Kelvin levels. By embedding heat pipes within a plane of a sheet or plate the heat exchanging media can be placed as close as physically possible to the warm source thus maintaining the narrowest possible temperature gradient. The thermal energy can then be easily transported to any other area within the plane of the sheet for dissipation purposes. ME-PHPs are stackable and scalable to any thermal load requirement.

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One of the critical issues for NASA missions requiring high contrast astrophysical imaging such as Terrestrial Planet Finder (TPF) is wavefront control. Without use of appropriate adaptive optics technology, it is impossible to obtain high quality imaging. Normal adaptive optics systems utilize a series of discreet components to satisfy the correction requirements. These consist of tip/tilt mirror and deformable mirrors. Xinetics has engaged in developing series of deformable mirrors and integrated adaptive optical components that will improve the optical quality of traditional wavefront control systems while simultaneously reducing system volume, weight and cost. Our innovative integrated wavefront corrector will combine new types of deformable mirror, Photonex Meniscus, with tip/tilt stage with Xinetics co-fired ceramic actuators. The proposed effort is the result of a strategic vision to develop small robust wavefront corrector designed to be employed in space based optical systems.

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Micron-thin surface hot-film gages are used to develop flow-angle and airspeed sensor system (FASS). Unlike Pitot-static and other pressure-based devices, which experience serious limitations in accuracy, pneumatic lags, and frequency response in thin upper atmospheres and at low speeds, FASS will measure airspeed all the way to zero knots and flow angularity to a fraction of a degree with practically zero-lag. It will perform equally well at sea level as well at high altitudes and even in the thin Martian atmosphere with relative immunity to EMI and RFI. Calibrated hot-film gages could also be used to simultaneously obtain total temperature. FASS addresses important flight-operation and flight research problems that have crucial impact on vehicle performance, stability & control, structural loads, and pilot action. FASS will permit direct integration with aircraft avionics systems including conventional instruments used for pressure, temperature, and density measurements. Hot-film gages are coated to withstand harsh environment and for protection from rain and ice. FASS is developed both as a stand-alone probe and as an embedded, non-intrusive system. Applications include aerospace and ground vehicles, submarines, ships, and measurements in the atmosphere, ocean, and in internal flows.

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In order to support systems such as the Momentum Exchange/Electrodynamic Reboost (MXER) Tether, NASA has identified the need for advanced electrodynamic-tether materials. A recently identified concern with present tether materials, particularly illustrated by the arcing after the tether break during the TSS-1R mission, is the need for arc suppression in the event that the insulation is breached by orbital debris and/or micrometeoroids. This concern applies to any high voltage application, including solar arrays, electric thruster components, and various scientific instruments. A significant hazard in and of itself to the tether application, the impact of the debris may release ionized and neutral particles which can instigate electrical arcing to the surrounding plasma, further weakening or severing the tether. The research program proposed here will identify, develop, and test advanced coatings for electrodynamic tethers that will suppress arc generation should the coating be breached. The proposed mechanism for suppressing the arc is including in the coating an encapsulated or entrapped electronegative gas that is released during the insulation breach and arcing event.

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ITN Energy Systems, Inc., in collaboration with the Center for Composite Materials (CCM) at the University of Delaware, proposes to design and develop multifunctional structure-battery panels for next generation space structures than can be integrated into exploration vehicles or space habitats. The multifunctional panels significantly reduce parasitic mass and volume thereby significantly increasing mission capability for future space missions. In its on-going pursuit of lightweight, low-cost systems, the space industry has made significant investments in "high payoff" technologies such as composite structures and high energy-density batteries. These individual technologies are now "mature", and are "standard" for most new space designs. Additional investment in these areas would yield only a few percent improvements over current performance. Faced with these "diminishing returns", it is clear that future progress demands revolutionary new concepts for space subsystems. ITN believes that this challenge can best be met using Multifunctional Structures (MFS). Structure and electrical power are the two heaviest subsystems on space platforms. In addition, batteries often represent the most voluminous component of the spacecraft bus. Therefore, structure and batteries have been the subject of intense R&D in efforts to reduce mass and improve performance.

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The proposed innovation is a 6DOF controllable mirror mount with high dynamic range and fast tip/tilt capability for space based applications. It will enable the actuation of large (~1m) mirrors over centimeter stroke with low bandwidth to correct deployment errors, provide sub-micron correction of thermal distorsion with picometer precision, and enable nanometer/nanoradian tip/tilt wavefront correction up to tens of Hz. The actuator will be designed to decouple the mirror from support resonances so that the mirror control system can suppress the system dynamic response. The mount will be optimized from a systems perspective, including thermal effects, total mass including the amplifiers and induced mechanical noise.

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nLight proposes to develop high-power, high-efficiency laser diodes emitting at 1907nm. Performance is expected to improve from the current state-of-the-art technology at 15C of 20% electrical-to-optical (E/O) conversion efficiency and 11.5W continuous-wave power (CW) to 25% E/O efficiency and 18W of CW power at the conclusion of Phase I. At the conclusion of Phase II, these values are expected to improve to 38% E/O efficiency and greater than 35W CW power. Quasi-CW power will be >>100W per laser bar. Such lasers meet the brightness and power requirements for the direct pumping of the quasi 4-level 5I7 to 5I8 transition in singly-doped Ho:YAG lasers. Compared to the diode-pumping of Thulium-sensitized Ho:YAG, direct diode pumping of Ho:YAG takes advantage of Holmium's much larger emission cross section, the absence of Ho:Tm up conversion, and Ho:YAG's large energy storage lifetime. Direct diode pumping of Ho:YAG also results in decreased system size, weight and complexity and an improvement in overall system efficiency when compared to pumping with a diode-pumped Th:YAG laser, all critical metrics for space and airborne platforms. This work could be extended to 18xxnm and 20xxnm quite readily with comparable power and efficiency performance.

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With the expected extension of duration of the space missions outlined in NASA's Vision of Space Exploration, such as a manned mission to Mars or the establishment of a lunar base, the need to produce potable water from onboard wastewater streams in a closed-loop system becomes critical for life support and health of crew members. Reverse osmosis (RO) is a compact process that has proven its ability to remove inorganic and organic contaminants from space mission wastewater. The objective of this Phase I study is to ascertain whether composite hollow fiber membrane elements are a more efficient alternative to the current generation of spiral wound membrane elements for the reclamation of space mission wastewater. In particular, the use of low-energy composite hollow fiber membrane elements being developed at SFST for treating multi-component (both inorganic and organic contaminants) wastewater streams found aboard spacecraft will be investigated. The higher membrane surface area of these composite hollow fiber membrane elements enables the RO membrane element to have 30% higher water productivity at substantially higher single-pass recoveries (60-75% vs 10-20% for spiral wound elements). Furthermore, we will also investigate possible solutions to minimize fouling of these hollow fiber membranes by increasing the hydrophilicity of the membrane surface using a variety of surface modification techniques. Such hollow fiber membranes are expected to show better resistance to fouling by hydrophobic compounds, and thus these membranes will be less likely to be clogged by potential foulants. These improvements to the RO membrane element have the potential to decrease the mass, size and power requirements of the RO subsystem, and also decrease the size of the pre-treatment unit.

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This proposal explains procedures of using regional and local geoid undulations to improve and convert the global positioning system (GPS) elevations (ellipsoidal heights) into orthometric heights. The Geoid Undulation Model (Geoid 2003) for the North America has reached the centimeter level accuracy. Although the GPS accuracy has reached to millimeter level, the elevation component (converted to orthometric height) has not been optimized to the same level of accuracy as X and Y. This research will select a test site in North Georgia covering a 2 x 2 of hilly as well as plain area. The test site will also include an urban area such as the City of Atlanta, and a large water body such as the Lake Lanier. The 2 x 2 area is divided into 1 x 1, 5' x 5', and 1' x 1' grid elements to compute global, regional, and local geoid undulations. Gravity data will be observed and compared against the gravity data obtained from the GRACE program. Also, the accuracy of existing geoid undulation in Georgia will be compared with the developed geoid undulation model, which will incorporate local and regional level gravity anomalies.

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This Small Business Innovation Research Phase I project seeks to prove the feasibility of creating high-temperature silicon-carbide (SiC) based motor drives for extreme environment exploratory robotic missions (such as Venus landers). SiC digital control ICs will be developed for controlling power electronics systems (such as motor drives) and integrated with SiC power switches into a multichip power module (MCPM) capable of reliably operating within extreme environments such as the surface of Venus without shielding. Avoiding complicated advanced active thermal management strategies not only improves reliability, but significantly reduces the complexity, weight, and volume of the overall electronics systems. SiC power electronics offer other potential advantages over silicon as well, including 1/10th the switching losses, 10? the power density, 10? the breakdown voltage, and switching frequencies into the 10s of GHz range. All of these advantages offer the potential to develop highly miniaturized, highly reliable, low weight extreme environment power electronics drive systems that can be integrated directly with DC motors or actuators.

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Toyon proposes to develop a low-power and compact reconfigurable radio specifically targeted to NASA mission needs. We envision the radio to be well matched to small satellites, terrestrial ground links, and autonomous vehicles. The design is based on the latest in field programmable gate array (FPGA) and general purpose processors (GPP). Typical software defined radios (SDRs) rely heavily on digital signal processors (DSPs) due to their ease of software development and ability to multitask well. Our emphasis will be on performing all baseband processing inside the FPGA due to its ability to offer over an order of magnitude increase in computational efficiency. While this approach does significantly decrease power consumption and associated platform size, it requires special considerations, particularly in terms of software development. As such, we will leverage Toyon's ongoing experience in computationally efficient waveform and associated software development using the latest in FPGA behavioral design tools. In addition, the architecture will stress logic component reuse between multiple waveforms to support rapid reconfiguration as well as reduce development time. Our RF front-end design will be a direct-conversion architecture to reduce size and provide frequency agility. The use of open-standards interfaces will provide for rapid systems integration.

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It is proposed to study and develop an innovative Turbo-block coded modulation scheme suitable for Orthogonal Frequency Division Modulation (OFDM) system. The new approach not only is capable of reaching the Shannon limit capacity, but it can also reduce the peak to envelope power ratio (PMEPR) of the OFDM symbols. This approach is unique since the design of high performance capacity achieving codes where all the OFDM signals produced by the codewords with low peak to average power ratio remains an extremely important, albeit a very difficult problem to solve, because a physical layer based on such codes can significantly reduce the cost of base stations. Typically, about 45% of the total cost of OFDM base stations corresponds to that of power amplifiers. This is due to the large linear region requirement of power amplifiers in these systems. OFDM transmission requires a large power amplifier linear region because of its relatively high peak to average power ratio signals. Thus OFDM power amplifiers are particularly expensive. Furthermore, reduction of PMEPR will reduce cost and power consumption for mobile units, enabling wider deployments and longer battery life.

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It is proposed to develop a process for producing arrays of hexagonal mirror segments with deviation from flatness smaller than 1nm RMS over a 600?m segment span, using novel microfabrication techniques. Each segment will be rigid enough to withstand actuation (piston, tip, and tilt) by a triad of flexure-based electrostatic actuators that have already been demonstrated by the project team. The base for the mirror will be a conventionally surface micromachined silicon film, augmented by a thick epitaxial layer of silicon. Subsequently, this layer will be polished, annealed to relieve stresses, and then coated with a thin film of protected silver. The combined result of thickening, polishing, and annealing will produce segments that are flatter, by more than an order of magnitude, than any micromachined mirror segments that are available today. Preliminary data demonstrate some promise that these processes can be combined effectively. Such an array of mirror segments would constitute a significant technological milestone and an essential component for the visible nulling coronagraph instruments planned for the terrestrial planet finding (TPF) mission. The project team has considerable experience in fabricating micromirror arrays for laser communication, astronomical imaging and visions science applications and BMC is a world leader in the production of commercial high resolution wavefront controllers. The project leverages a existing successful relationship between BMC and JPL.

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The innovation in this proposed effort is the development of lightweight, non-eroding nozzle materials for use in propulsion systems. Lightweight structures are desirable for space transportation vehicle systems in order to reduce launch costs, increase mission flexibility/efficiency, and add robustness with respect to the ability to add weight or additional materials to the mission with minimum sacrifice in performance. The use of non-eroding materials, coupled with lightweight materials, as rocket nozzles can further increase mission flexibility by allowing an increase in performance, higher maximum temperatures, greater speeds, greater range, bigger payloads, and longer lifetimes. The higher maximum temperatures may eliminate the need for cooling air, while simultaneously increasing engine efficiency. Higher maximum use temperature additionally allows for increased stagnation temperatures and pressures, increasing the propellant enthalpy, which, in return, can significantly increase the velocity and performance of the projectile. These benefits result in increased fuel savings. The advanced materials study will include monolithic ceramics, refractory metals, and high temperature ceramic matrix composite (CMC) materials. The manufacturing processes for the monolithic ceramics and refractory metal materials will include hot isostatic processing (HIP), vacuum plasma spraying (VPS), electrodeposition. The CMC fabrication processes will include braiding, filament winding, tape wrapping, and involute layup.

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In the proposed SBIR Phase I program LGR will develop and deploy a novel instrument ("Optical Thermometer") that provides real-time, in situ, non-contact measurements of substrate temperature in optical coating reactors. The instrument will employ an inexpensive diode laser, fiber optic components, and established laser interferometry methods to determine substrate temperature at multiple locations with a replicate precision of better than 0.01 degrees C in a measurement time of less than 0.01 seconds. The precision may be improved with increasing measurement time, if desired. The "Optical Thermometer" will be demonstrated on optical substrates made of a variety of materials in state-of-the-art industrial reactors specializing in UV, visible, near-IR and mid-IR optical coatings. The fast response of the sensor will enable coaters to use, for the first time, precise measurements of bulk substrate temperature to identify temperature nonuniformities during the coating process, refine and improve coating processes in real time, and minimize interwafer and batch-to-batch variations through closed-loop process control.

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The purpose of this NASA SBIR Phase I proposal is to develop the prototype of a compact single-frequency mode one longitudinal and one transverse mode laser oscillator (SFM) using a pulse pumped Er-doped multimode fiber as an active element inserted in the external cavity. The main feature of the proposed design is the use of volume transmitting or reflecting Bragg gratings for longitudinal and transverse mode selection in an external laser resonator. The technical approach for the development such a laser is based on application a new type of robust optical element as one of the cavity mirrors, a volume Bragg grating recorded in photo-thermo-refractive (PTR) glass. The selectivity of volume Bragg gratings to wavelengths, angles of incidence and at certain conditions to the state of incident polarization could be successfully applied in design of a novel type of a laser resonator. The use of volume Bragg gratings for mode selection instead of conventional fiber Bragg gratings will result in decreasing of power density by several orders of magnitude and, therefore, will increase threshold of laser damage and other nonlinear processes dramatically.

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The ability to precisely control the position of satellites is a critical enabling technology for space missions involving interferometric arrays. One proposed mission, LISA (Laser Interferometer Space Antenna), would use an array of 3 satellites whose relative position is monitored and controlled to an accuracy of 10 nm. Precise station-keeping such as this demands precise, high stability thrusters supplied with propellant flows on the order of microliters/min and producing micro-newtons of thrust. These requirements are difficult or impossible to meet with traditional thrusters and feed systems such as cold-gas thrusters or monopropellants. The proposed program will evaluate the use of electro-osmosis to supply and control the flow of ionic liquid propellants to micronewton colloid thrusters. In addition, the use of a gate electrode to control the surface charge and therefore the magnitude and direction of flow will be examined as will the use of AC fields to limit electrolysis effects. Phase I will provide basic information on the electro-osmotic behavior of ionic liquids using simple test devices and electrospray emitters. Phase II will involve detailed design work to fabricate a practical propellant feed system using electro-osmotic pumps.

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This proposal describes a Phase II SBIR project to develop high-resolution, ultraflat micromirror array devices using advanced silicon surface micromachining technology and building on process innovations demonstrated in a successful Phase I research effort. Each device will be comprised of 331 close-packed hexagonal mirror segments. Each segment will be controlled to nanometer-scale tolerances in rotation (tilt) and surface normal translation (piston) using electrostatic actuators. The architecture used in the micromirror design and fabrication processes used, are scaleable to array sizes up to 1027 mirror segments with 3081 independent control points. The completed device will be delivered to the Jet Propulsion Laboratory for evaluation in the High Contrast Imaging Testbed. If successful, this project will result in enabling hardware for wavefront control, as needed for starlight canceling coronagraphic instruments. The Phase I project demonstrated actuator designs and mirror segment manufacturing processes that were capable of meeting the unprecedented demands of such instruments with regard to segment optical quality, segment planarity during actuation, and actuation precision and range. In the Phase II effort, these designs and processes will be used to produce a functional, packaged micromirror array that will meet the immediate wavefront control needs for visible nulling coronagraphic testbed instrument. The device is being designed and fabricated to be suitable for space-based operation as part of a future observatory mission.

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Description

Membrane Optical Shell Technology (MOST) is an innovative combination of 1) very low areal density (40 to 200g/m2) optically smooth (<20 nm rms), metallic coated reflective membrane thin films, 2) advanced fabrication techniques that transform the films into self supporting shells through the introduction of permanent optically relevant double curvature, and 3) discrete active boundary control to enable rigid body alignment and maintainment of surface figure in face of environmental disturbances. Areal densities of better than 2 kg/m2 (including actuators) are projected. Current measured surface figure is ≈1 to 10 microns rms at up to the 15 cm size, and we are poised for further improvements. Demonstrated material and fabrication techniques are scaleable to at least the 2m+ diameter single surface apertures and larger apertures are possible through segmentation techniques. Proven stowage and deployment techniques enable space flight application. We propose advancing 1) the basic fabrication technology and 2) the TRL level of MOST apertures for ground and space based apertures. The key resulting innovation is implementation of low areal density, compact roll stowable approaches to realize low mass, low cost reflective apertures for RF/Microwave to LIDAR. Other NASA and DOD applications are expected as precision and aperture size increase.