Summary

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Solar sails are an attractive means for propulsion of future spacecraft. One potential device for deploying and supporting very large solar sails is the CoilAble boom made by ATK Space Systems - Goleta (formally AEC-Able Engineering). CoilAble's have a long and reliable track record in space. KaZaK Composites is a major developer and supplier of pultruded composite structural members used in CoilAble booms. For solar sail applications, it is important to develop advanced technologies that create the lightest possible booms. KaZaK is already pultruding advanced solar sail test hardware made with IM-9 carbon fiber as a first step toward improving solar sails. This SBIR proposal will identify a replacement for the recently out-of-production IM-9 baseline carbon fiber, and pursue three additional lines of investigation aimed at creating significant improvements in next generation solar sail structures. Specifically, we will investigate methods for making 1) near-zero CTE pultruded members of unlimited length via materials hybridization, 2) very lightweight tubular structures, with and without cores, to reduce the weight of solar sail longerons, and 3) passively damped structures achieved by additives to the matrix of pultruded composite sail materials. Mast structural elements made with least one and possibly several of these technologies will be prototyped and tested in Phase I.

Summary

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We propose to develop a Multi-Element Lean Direct Injection, ME-LDI, Combustion concept with the following innovative features: 1. Independent, mini burning zones created by containing the flame in a cylinder downstream of each fuel injector/swirler element in a multiple fuel injector array, see figure 1. The independent burning zones will enable fuel staging the fuel injectors (turning off fuel to selected fuel injectors) to cover the operating cycle, such that at each point of the operating cycle the combustor will have high combustion efficiency (>99%) and low NOx emissions. At high power conditions the combustion efficiency should be greater than 99.9%. 2. A low flow number, "Butterfly" fuel injector will be incorporated into ME-LDI that is low cost and simple to manufacture but a highly effective atomizer. The term "Butterfly" derives from the butterfly shape of the spray. The shape of the spray is formed by two diametrically opposed slots cut through a closed end fuel tube, see figure 2. The fuel flow through each slot forms a fan spray. The slot width can be varied to control drop-sizes within the spray.

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The key innovation proposed in this effort is the development of a model composition toolkit that will enable NASA Airspace Concept Evaluation System (ACES) users to design and compose agents, activities, and models to meet specific design requirements. Our technical approach builds on recent advances in formal agent specification, role composition and model composers. The toolkit will allow end-users to use a graphical editor and templates/property sheets to load, create, configure and interconnect agents, activities and domain models.. In addition to composing agent and models, a key feature provided by this toolkit is a family of "physical language specific adaptors" that will allow users to import domain models written Matlab<SUP>REG</SUP>. The toolkit will also provide capabilities to export ACED LDC data to tools such as Matlab for post analysis and graphing. The primary focus of the Phase I effort will focus on demonstrating the feasibility and capability of this toolkit for the ACES Terminal Area Plant. We propose to demonstrate this capability by developing showing how an end-user, not experienced with Java, can easily add a C2 agent to perform runway balancing and replace the current timer-based Terminal Area Link transit models with 4-D trajectory models.

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The objective of the proposed program is to develop lightweight and highly elastic electrically conducting interconnects and strain sensor arrays for next generation adaptive aerospace vehicles and structures. The systems-level problem this would solve is the inability of currently available materials to undergo the large strains and displacements associated with shape changes of morphing structures. NanoSonic will demonstrate the feasibility of the Metal RubberTM family of freestanding nanocomposite materials to serve as 1) electrically conductive, low modulus electrodes for large displacement mechanical actuators required to affect large shape changes, and 2) an integrated network of strain sensors to allow mapping of strain and determination of shape in adaptive structural components. Metal Rubber<SUP>TM</SUP> is fabricated via layer-by-layer, molecular self-assembly, which enables thickness and placement control over multiple molecular constituents for true nanostructured multifunctionality. As an electrode material, new, ultra-low modulus Metal Rubber<SUP>TM</SUP> can be strained to 1000% elongation while remaining electrically conductive; it returns to its original shape and nominal conductivity when released. As a strain sensor, strains up to 1000% have been measured in very highly flexible structures. During Phase I the feasibility of using such electrodes and strain sensors would be demonstrated in cooperation with a large aerospace company.

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The program aims to demonstrate a new genre of all-magnetic logic circuits which are radiation-tolerant and capable of reliable operation in extreme environmental conditions including low temperatures and wide temperature swings. The circuits are based on tunneling magnetoresistive technology, and are expected to have a greater single-event latchup immunity than semiconductor-based CMOS logic. Recent breakthroughs in magnetic tunnel junction technology have resulted in magnetoresistive responses in excess of 200%. With these developments adequate current gain may now be realized to implement practical multi-stage logic circuits. This work will seek to prove novel gate designs and explore the magnetic thin-film tunneling structures necessary to realize them.

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Long duration spaceflight and exploration missions will require complex operations and demanding tasks. Success will therefore depend on the knowledge and flexibility of the crew and the critical tools at their disposal. The purpose of this Phase II project is to develop a software tool that combines intelligent tutoring (or logic) with highly interactive 3D simulation software to create an on-demand situational training and operations support system. The platform will include a user interface that allows subject matter experts ? not programmers - to author the logic and intelligent portion of each simulation in a non-programming environment for more cost effective training systems development. The project includes the creation of two new application program interfaces (API) an XML schema and several new Java functions to allow for communication between the logic engine software and the 3D scene. A menu-driven authoring interface will then be created. The feasibility of the system was determined in the Phase I project, and demonstrated with a 3D simulated NASA EVA decontamination trainer. For Phase II, a prototype of the system will be created for a current NASA scenario-based training system to test the commercial-readiness of the authoring tool.

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Future NASA planetary exploration missions require secondary (rechargeable) batteries that can operate at extreme temperatures (-60<SUP>o</SUP>C to 60<SUP>o</SUP>C) yet deliver high specific energies (> 180 W7hr/kg) and long cycle life (>2,000 cycles). Functional organic materials are a promising technology for use as the cathode in Li-Ion batteries due to their high specific energy density. It is also expected that the use of polymeric cathodes instead of lithium metal oxides will make Li-Ion batteries thinner, lighter and less environmentally hazardous. This Phase I proposal is based on demonstrating the feasibility of fully packaged Li-Ion batteries that have a superior specific energy (>200 W7hr/kg) through the use of novel polymeric cathodes (composite conducting polymer/disulfide materials) when coupled with room temperature ionic liquid (RTIL) electrolyte. Compared to traditional organic electrolyte systems (e.g. (e.g. lithium salts dissolved in alkyl carbonates), RTIL electrolytes have favorable electrochemical windows (> 5 V) and high ionic conductivity over a wide range of temperatures from ?60?C to 250?C and are known to prolong the lifetime of conducting polymer electrochemical devices. Besides these highly desirable characteristics for use in these novel Li-ion batteries, RTILs have inherent safety characteristics by virtue of their thermal stability, non-flammability, non-volatility and low heat of reaction with active materials.

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In this SBIR effort, Los Gatos Research (LGR) proposes to develop a suite of laser-based diagnostics for the study of reactive and non-reactive hypersonic flows. These sensors will include both in situ and line-of-sight measurements of several critical parameters including gas temperature, velocity, and composition. Both established near-infrared and emerging mid-infrared laser sources will be utilized to make highly-accurate measurements via tunable diode laser absorption spectrometry. The SBIR instrument will be the first system capable of providing real-time, rapid quantification of these important combustion parameters in NASA's hypersonic wind tunnels. Such quantification is essential to the development of improved reactive CFD models and subsequent hypersonic propulsion systems for future aerospace vehicles.

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MagiQ proposes to develop a compact tunable high-efficiency low-power-consumption entangled photon source. The source, based on inter-Fabry-Perot-cavity Spontaneous Parametric Down Conversion (SPDC) of pump light in periodically polled non-linear waveguides (PPLN or PPKTP) is expected to provide high spectral density flux of entangled photon pairs. The output wavelength will be within the C-band (1529 to 1563 nm) permitting usage of plethora of components developed for classical communication links. The Fabry-Perot setup will provide for the narrow frequency output ? an attractive feature for low power communications in presence of the ambient light. Waveguide-based inter-cavity SPDC is the main proposed innovation. The entangled output wavelength tuning will be achieved by changing the wavelength of the pump light. The wavelength agility will facilitate device usage in the reconfigurable communications links ? a feature that can be very important in the planetary exploration systems involving small robotic explorers. Breadboard demonstration of the time-bin entanglement setup will be completed during Phase I of the project; delivery of a fully functional device producing both, time-bin and polarization entanglement is expected at the end of Phase II.

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ZONA Technology, Inc. (ZONA) proposes a R&D effort to develop a Unified Nonlinear Flight Dynamics and Aeroelastic Simulator (UNFDAS) Tool that will combine proven simulation and visualization techniques to accurately match in-flight recorded dynamic behavior of an air vehicle. ZONA proposes to develop the UNFDAS Tool through a blend of state-of-the-art aerodynamic model updating and control-oriented techniques. It blends mathematically sound flight dynamics and aeroelastic modeling approaches with CFD, wind-tunnel or flight-test data. The end product is a nonlinear dynamic tool capable of simulating the key aeroelastic coupling mechanism between structural modes and unsteady aerodynamic effects with classical rigid-body dynamics. Feasibility studies are proposed to validate the UNFDAS Tool using a suite of actual data from flying qualities and flutter flight tests. This enabling technology will be invaluable to the flight test community by accurately simulating the air vehicle responses to different input commands, and then identifying the critical flying conditions before actual flights are performed. Marketing the resulting software package will be simplified by taking advantage of ZONA's current extensive customer list. ZONA Technology's reputation and track record in supporting the aerospace industry and government with ZONA codes can assure the success of the commercialization plan.

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To enhance aerodynamic design capabilities, Desktop Aeronautics proposes to combine a new sweep/taper integrated-boundary-layer (IBL) code that includes transition prediction with a Cartesian Euler solver developed at NASA. This combined solver will play an important role in the preliminary design of both conventional and unconventional aerospace vehicles traveling at subsonic, transonic, and supersonic speeds. Complex aircraft configurations may be easily analyzed with the practically automated surface intersection and Cartesian mesh generation of the Euler solver. The proposed design-oriented approach to transition prediction will permit rapid assessment of aircraft that exploit natural laminar flow to reduce drag. To facilitate design and numerical optimization using the new aerodynamic analysis, a parameterized geometry engine that can quickly model complex aircraft configurations will be interfaced with the Euler/IBL solver. Desktop Aeronautics will also develop a set of optimization tools well-suited to use with the geometry engine and aerodynamic analysis. This set of tools will permit aerodynamic shape optimization and multidisciplinary design at earlier stages in the vehicle development process.

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In response to NASA's need to develop advanced nanostructured thermolectric materials, UTRON is proposing an innovative high pressure powder consolidation manufacturing to fabricate near net shape and net shape thermolectric components with improved densification and properties than possible conventional powder metallurgical methods. Potential candidate materials such as Tellurides, TAGs and SiGe micro/nano composites will be developed at high compaction pressures (150 tsi) using select geometries/shapes and optimized disk samples will be characterized for geometrical, shrinkage, mechanical, microstructure/microchemistry and thermolectric properties. The proposed work has been planned in close subcontract/collaboration with Teledyne and Auburn University-Space Research Institute. Other advanced nanocomposite alloys and scaling up to fabricate complex geometries will be done in Phase II.

Summary

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Rotor blades adapted for vibration control have the added benefit of extended blade and rotor life, as well as improved passenger comfort. Approaches that have been explored for on-blade active control or individual blade control include control surface actuation, such as trailing edge flaps, and integrated blade manipulation, such as controllable twist. For retro-fit and upgrade purposes, the advanced rotor system needs an actuation scheme with appropriate force, deflection, and bandwidth, without detrimentally increasing on-blade mass. Research in this area has been conducted with potential solutions employing various conventional active material actuator configurations, but these systems have typically suffered from inherent disadvantages. Due to these limitations, Techno-Sciences, Inc. proposes the use of pneumatic artificial muscles to actuate a trailing edge flap device for management of rotorcraft vibration. The proposed actuators are constructed of passive materials that are very mass efficient and low cost, while maintaining adequate force, stroke, and bandwidth. Oriented along the blade span and located within the airfoil contour near the blade root, the antagonistic configuration of actuators offers bi-directional flap deflection and operation under a low centrifugal field. A lightweight mechanism accompanies the actuators, running along the span, to transfer and tailor the mechanical work from the actuators to the span station of the flap. The proposed research plan will work to properly size and scale the actuators and mechanism for the desired response, and construct a prototype device that demonstrates the feasibility of the concept on the bench-top and in a rotating environment at full-scale loading.

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The severity of the lunar dust problems encountered during the Apollo missions were consistently underestimated by ground tests, illustrating the need to develop significantly better lunar dust simulants and simulation facilities. ORBITEC proposes to develop a family of High-Fidelity Lunar Dust Simulants that will better match the unique properties of lunar dust than existing simulants (such as JSC-1AF). Current lunar dust simulants do not have enough of the very fine particles, and they lack the agglutinitic glass and complex surface textures that dominate lunar dust. The proposed family of High-Fidelity Lunar Dust Simulants will approximate the size, morphology, composition, and other important properties of lunar dust. High-Fidelity Lunar Dust Simulants are required to physically evaluate the effects of lunar dust on the operation of all Exploration Surface Systems and to verify the effectiveness of dust mitigation strategies and technologies. The proposed Phase 1 effort will define requirements, develop, characterize, and deliver a sample of a prototype lunar dust simulant to NASA (TRL 4). The Phase 2 effort will refine the production process to create a large quantity of lunar dust simulant that will be characterized and delivered to NASA (TRL 6).

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Gases trapped in the propellant feed lines of space-based rocket engines due to cryogenic propellant boil-off or pressurant ingestion can result in poor combustion efficiencies, combustion instabilities, or long startup transients. To assist NASA in the use of the high performing liquid oxygen propellant combinations in space engines, IN Space proposes to investigate the feasibility of an innovative swirl injector design for liquid oxygen and hydrocarbon propellants to achieve high combustion efficiencies, stable operation, and short and smooth startup transients despite potential two-phase oxidizer flow. Additionally anticipated benefits of the injector include low inert mass and low manufacturing costs. IN Space plans to carry out the feasibility assessment of the injector design by conducting broad parametric test fire evaluations of a notional LOX/hydrocarbon workhorse thruster based on present NASA needs to assess the effects of several design considerations on the combustion efficiency, static combustion stability, and startup transient duration performance merits. A preliminary flightweight injector design will also be generated in order to compare the estimated injector mass with similar injector designs.

Summary

Description

Lithium-ion (Li-ion) batteries are attractive candidates for use as power sources in aerospace applications because they have high specific energy, energy density and long cycle life. However, conventional Li-ion batteries experience loss of capacity and increased impedance and poor cycle life when they are charged/discharged at high rates over C-rate. These problems are magnified at low temperature operation. The limitations in the high rate capability of Li-ion batteries are mainly caused by slow solid-state diffusion of Li+ within the electrode materials Yardney/Lithion Inc., the world leader in cutting edge Li-ion battery technology proposes to investigate new non-toxic nano-engineered electrodes that significantly shortens the Li+ diffusion length within the electrode materials and increases the rate capability of Li-ion batteries. The goal of this Phase II project is to manufacture rapid recharge Li-ion battery for aerospace application. Yardney will manufacture 5 prototype cells capable of recharge at less than 15 min at room temperature. During the phase I we found that the nanoengineered anode showed excellent rate capabilities compared to planar electrode. Nanoarchitectured current collector provides higher safety due to large surface area contact with the active material and that acts as heat sink in high rate applications and also lower impedance.

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We propose new concepts for developing components for high performance space based Lidar systems. While it is generally recognized that photonic crystal fiber technology can extend the performance range of fiber laser based sources these fibers are considered by many to be incompatible with complementary component technology such as fused couplers and pump combiners. Integration of these fibers into real systems for deployment either in space or terrestrial systems is hindered by the very structure which brings the advantage in effective area and nonlinearity mitigation. The problem is related to the air holes which provide guidance for both pump and signal. Our proposal centers not on developing sophisticated new component manufacturing techniques but rather on modifying the micro-structured gain fiber itself to retain the desirable advantages while eliminating the problems associated with component development. This can be achieved by use of only refractive index micro-structuring to create an all-solid structure with index control an order of magnitude better than direct deposition techniques. In the phase I program we will demonstrate an all solid micro-structured gain fiber with effective area >5005m2, as well as showing the feasibility of fabricating compatible tap couplers and pump combiners.

Summary

Description

NASA has determined that it requires extremely durable, high-performance, low cost engines to meet future multi-use in-space, non-toxic, cryogenic propulsion requirements such as orbit transfer, descent, ascent and pulsing attitude control. Transpiration-cooling technology has long been considered a candidate for long-life thrust chambers but has never been deployed on a domestic rocket engine. In this program WASK Engineering, Inc. proposes to design, fabricate and hot-fire test a 100 lbf reaction control engine (RCEs) with transpiration-cooled thrust chambers and novel injector design. This effort will build on the technology demonstrations achieved on our Phase I program. These new transpiration-cooled O2/CH4 RCEs will be tested in existing atmospheric (non-vacuum) test facilities on an existing and operational test stand. Test results will be used to anchor and refine existing transpiration cooling thermal/performance analysis models. Ultimately, results of this Phase II program will lead to a durable, low cost, non-toxic RCE technology capable of using in situ propellant combinations, particularly oxygen/methane that will have higher performance than current toxic, expensive, storable hypergolic RCE designs using rhenium-based thrust chamber technology.

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Purpose of this effort was to offer a novel solution to the pressing need for radiation tolerant memory for the demanding satellite and space probe worldwide community. The effort included radiation testing of the Ferro Electric Random Access (FRAM) memory developed under NASA/JPL contract NNG04CA25C, and the design of stacked versions resulting in up to 16Mb of storage in a footprint smaller than a standard TSOP. The work done resulted in a number of tested samples of 2Mb FRAM die fabricated using the 0.35 um process at Fujitsu, and designed by Cellis Semiconductor. The packaged parts were electrically tested then subjected to radiation testing. The enclosed radiation test program conducted and the successful results are contained herein. For higher density configurations, a preliminary design of stacks in 2, 4, and 8 high die was done using our 5Z Ball Stack<SUP>REG</SUP> technology, offering a total of up to 16Mb of addressable memory.

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The need for higher performance fiber optic telecommunications receivers has provided the impetus for substantial progress during the last decade in the understanding and performance of InP-based linear mode avalanche photodiodes (APDs) for the wavelength range from 1.0 to 1.7 um. However, these advances have not been paralleled in the performance and availability of single photon avalanche diodes (SPADs) based on similar design and materials platforms. Moreover, the vast majority of the activity in this field has been focused on optimizing devices for telecommunications wavelengths in the vicinity of 1550 nm, and there has been very little work on devices for use at 1064 nm. For this SBIR program, we propose to apply innovative design concepts for the development of high performance SPADs optimized for 1064 nm applications. In particular, we will implement a novel bandgap engineering approach to tailor the SPAD avalanche gain properties to realize higher single photon detection efficiency while maintaining the very low dark count rates that are made possible by optimizing the absorption region design for the detection of 1064 nm photons. We will also apply design concepts that we have innovated during the course of developing state-of-the-art 1550 nm SPADs that involve optimization of the device electric profile for photon counting as well as epitaxial layer compositions. These efforts will culminate in 1064 nm large area detectors (with active area diameters up to 500 um) that demonstrate feasibility in meeting SPAD performance targets including 50% detection efficiency, bandwidth of 500 MHz, saturation levels of 50 Mcounts/s, and non-gated operation.

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The NLNS software developed in phase I is a robust and user-friendly environment that NASA researchers can use to customize the latest HHT technologies for their applications in astrophysics, earth sciences, and exploration. The proposed technology includes the latest discoveries and inventions not available in the state-of-the-art. Its taxonomy includes gravitational sensors and sources, expert systems, portable data analysis tools, software development environments, and software tools for distributed analysis and simulation. The Hilbert-Huang Transform (HHT) and related analysis technologies were successful in detecting non-linear and transient LISA-signal components of very small magnitude with respect to the signal noise. Other types of NLNS analyses will include de-noising (filtering), spectral analysis, reconstruction, and registration, potentially extended to two-dimensional data. The proposed research and development team has participated in the latest cycle of technology development related to the HHT at the theoretical, implementation, and application levels. Not only will the creation of the proposed software contribute to the detection of gravitational wave signals (for both LIGO and LISA data) or understanding patterns of climate change temperature records from ice cores or monitoring structural dynamics, but also in other non-linear and non-stationary applications within and outside NASA's mission.

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Advanced Situation Awareness Technologies (ASAT) will facilitate exploration of the moon surface, and other planetary bodies. This powerful technology will also find application in the commercial sector, particularly submersible vehicle operation. ASAT will fuse video and other sensor technologies, with geographic databases to maximize vehicle operator situation awareness, and enhance the navigation state of the guidance and control system. During previous research and development activities RIS invented a method to use video camera data to enhance vehicle attitude estimation from gyroscopic inertial navigation systems. In non-earth environments, the absence of a strong reference field increases the problem of INS drift, and decreases operator situation awareness as a consequence. RIS will develope technology which enhances navigation and situation awareness in these challenging environments.

Summary

Description

Future missions to investigate the structure and evolution of the universe require highly efficient, low-temperature cryocoolers for low-noise detector systems. We propose to develop a highly efficient low-cost regenerator for regenerative cryocoolers with cooling temperatures in the range of 15 K and below. The proposed regenerator uses an innovative non-rare-earth material to achieve a volumetric specific heat of about 0.65 to 0.31 J/cm3-K at temperatures of 15 to 4.2 K. The large heat capacity will substantially reduce the thermal swing during periodic heat transfer and therefore improve the efficiency of low-temperature regenerative cryocoolers. The regenerator will be lightweight and easy to fabricate. In Phase I we will optimize the regenerator for a specific cooling application. We will use the resulting design and model to show that a regenerative cryocooler can achieve a very high efficiency. In Phase II we will build a prototype regenerator, measure its key performance parameters, and integrate it with an existing cryocooler to demonstrate its high thermal effectiveness.

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The proposed Plasma Air Decontamination System (PADS) is a trace contaminant control device based on non-thermal atmospheric-pressure plasma technology. Compared to the Trace Contaminant Control System (TCCS) and the Vapor Phase Catalytic Ammonia Removal system (VPCAR), this novel technology operates at ambient temperature and atmospheric pressure, requires less energy, has no moving parts, and requires no consumables. The non-thermal plasma has been proven successful in decomposing various volatile organic carbons (VOCs) found in spacecraft environments. The prototype PADS reactor developed in Phase I has also demonstrated successful removal of ammonia and selected VOCs (e.g., methane, acetone, methylene chloride, and ethylbenzene) in air. The Phase II effort will further optimize this technology and improve its efficiency. It will be designed to interface with both TCCS and VPCAR. Its incorporation would eliminate the high-temperature catalytic reactors in the two systems, and facilitate a decrease in size or total elimination of the intensive resupply of activated carbon for adsorbent beds. This would result in significant savings in launch mass and cost for long duration missions and a reduction in power requirements. It also has great potential to be scaled to various applications and/or incorporated into other life support systems for streamlined air purification.

Summary

Description

This project consists in developing a Vibrating Powder Handling System for planetary X-Ray Diffraction instruments. The principle of this novel sample handling technique relies on vibrations generated in a sample holder to create movements in the powdered sample. The major benefit over conventional sample handling techniques is the possibility to characterize materials with grain-sizes up to two orders of magnitude larger, with no degradation in the data quality. It allows existing planetary sample-preparation systems such as rock crushers and drills to be used in place of fine-grinding mills normally required for quality XRD analysis. A secondary benefit is that it offers a simple means of loading and removal of samples, with potentially no moving parts. This research will answer a critical need for sample handling devices for conducting definitive mineralogical analyses in the Solar System. The Phase 2 effort will focus on addressing key technical issues in the development of a miniature Vibrating Powder Handling System. This work will lead to a brassboard prototype that can be remotely operated and interfaced to a planetary XRD instrument.