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To meet the design challenges of tomorrow, NASA and industry require advancements in the state-of-the-art for physics-based design and analysis frameworks. In particular, NASA needs the ability to make more use of physics-based models earlier in the design process. This will allow engineers to more accurately capture the complex coupling between engineering disciplines and to more accurately simulate the complex behavior of novel design configurations. Key technical barriers include long execution times, model and data complexity, and geometry management. In the Phase II project, Phoenix Integration will expand on the successful Phase I prototypes to develop new technologies and user interfaces that will help overcome these barriers. This project will focus on (1) the development of a flexible capability for implementing Multi-Disciplinary Analysis and Optimization (MDAO) strategies (such as multi-fidelity) in ModelCenter, (2) the creation of a flexible geometry visualization and monitoring capability for high-fidelity system models, and (3) the extension of Phoenix Integration's "Plug-In" infrastructure to better support a wide range of high-fidelity analysis and geometry management tools (CAD/CAE tools, meshing tools, mesh morphing tools). These technologies will combine with other NASA funded technologies to create a robust physics-based design and analysis framework for designing next generation air vehicles.

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We propose that the Membrane Aperture Shell Technology (MAST) approach be expanded with a specific focus on space exploration orbiting comm network RF aperture applications. The approach is based on a proven combination of 1) thin film materials with space heritage, 2) inherent low areal density (40 to 200 g/m2), 3) structural shell stiffness provided through the induction of permanent curvature, 4) sufficiently low surface roughness and thickness variation (verging on optical grade), and global figure to satisfy all RF wavelength operations, 5) proven RF reflectivity, 6) compact stack or roll stowage, 7) robust passive self deployment with stowed strain energy, and when needed, 8) compatibility with boundary control/adjustment to provide initial phasing, rigid body fine pointing and environmental disturbance effect rejection. Recent advances in shell fabrication technology enable easily scaleable aperture systems based on hexagons segments. By optimizing local segment figure and alignment large scale on axis (or even off axis) parabolas can be adequately approximated. In the PI we will demonstrate fabrication of suitable hexagon shaped segments, determine optimal system architectures, confirm RF performance, numerically show sufficient stiffness in the face of environmental and launch loads, review figure mitigation and control techniques. This prepares the way for a detailed PII focused on demonstrating performance in realistic environments (TRL 6), a key step in any realistic commercialization plan for space hardware.

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Manned planetary exploration has become re-invigorated, thanks to President Bush's recent call for a lunar base to be established within two decades and manned landing on Mars sometime after 2030. Such exciting explorations will demand innovative technologies for the next round of manned exploration of space. One such technology that is desired to be advanced is LIDAR ? the LIght Detection And Ranging, for which SMI and Cornell University jointly proposed to develop a 1 x 10 electrically switched silicon nano-optic switch/multiplexer for use with high power lasers in LIDAR systems, especially the fiber-based fixed-array laser transmitter for use in NASA planetary explorations. Specifically, we have invented a few approaches to minimize optical absorption and optical loss in silicon nano-photonics and extend the applicability of silicon from infrared into visible and near-infrared spectrum with wavelengths shorter than 1100nm. These methods will serve as the groundwork for striding progress in Phase II. The prototype 1x16 photonic switch array will have < 10 nano-second switching time, < 3dB optical loss, complete temperature stabilization circuit, electronics driver circuits, and can transmit greater than 200 micro-Joules transmission over 5 nano-second pulse at 10 kHz repetition rate for LIDAR applications.

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NASA will return to the IIS by 2014 and the moon by 2020. To accomplish these missions, NASA will exploit to the maximum degree possible the Apollo architecture and especially the lessons learned and technological advances that have occurred over the intervening 40 years in building robust, cost effective, efficient, and, partly reusable launch, lander, explorer, and resupply vehicles. In support of this effort, Technology Assessment & Transfer (TA&T) proposes to develop a magnesium metal matrix composite (MMC) for use as aerospace structural members. This material exhibits three times the specific stiffness of the best aluminum-lithium alloys and two times that of PMCs. TA&T will demonstrate the feasibility and practicality of a low temperature method for achieving high loading of ceramic particles in a magnesium matrix that will enable a cast or extruded structural material of non-uniform cross-section exhibiting the unusual combination of light weight, high specific stiffness and strength, radiation shielding, and low cost. The MMC will be protected from corrosion by a unique thin film coating designed specifically to prevent corrosion of aluminum and magnesium alloys.

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MetroLaser proposes to design and develop an innovative narrowband tunable IR filter based on the properties of a one-dimensional photonic crystal structure with a resonant cavity. Such a structure can exhibit an ultra-narrow, high-throughput band in the middle of a wide low-transmission stop-band. During Phase I, we will demonstrate experimentally the proof-of-concept for the proposed filter with sub-angstrom bandpass and a tuning range of at least 10 cm-1 in the spectral region around 10 um. We will complete modeling of the functional characteristics, based on the specific features of photonic crystal structures with a resonant cavity, and develop a strategy for building a prototype of the instrument. Fine-tuning of the filter will be accomplished by varying the optical cavity length. The proposed filter is expected to have an acceptance angle of at least 1 degree and an aperture of about 1 inch. During Phase II, the compact prototype module will be demonstrated with an expected tunability range of 10 cm-1 and a bandpass range of 0.1 cm-1. A compact, rugged, monolithic filter architecture will allow this instrument to be incorporated in air- or space-based platforms and provide stable performance in harsh operating environments.

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Microcosm will build on the Phase I X-ray pulsar-based navigation and timing (XNAV) feasibility assessment to develop a detailed XNAV simulation capability to evaluate navigation performance for specific missions of interest, and create an XNAV flight software experiment ready to integrate on an appropriate near-term flight demonstration mission in Phase III. Phase I demonstrated achievable XNAV accuracy, developed a preliminary source catalog, constructed an XNAV error budget, and laid out potential implementation options for XNAV, focusing on an Earth-Sun L2 Lagrange point mission. Brighter, less stable, non-traditional X-ray sources were also considered for possible XNAV application with promising initial results, especially for formation flying applications. Taking advantage of concurrent XNAV efforts at DARPA to the maximum extent possible, Phase II will develop and validate XNAV algorithms via a simulation which will be targeted for integration with Goddard Space Flight Center's GPS Enhanced Onboard Navigation System (GEONS) software. The error budget will be developed in more detail to support the algorithm and simulation work. XNAV holds great potential for NASA as an enabling technology for fully autonomous interplanetary navigation and could provide a significant mission enhancement as an adjunct to the Deep Space Network (DSN) and ground based navigation.

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This Phase I NASA SBIR Proposal seeks to demonstrate a new zero-erosion ablative thermal protection system (TPS) technology that is based upon an ultra-high temperature (UHT) ceramic fiber pre-form / organic ablative matrix composite structure. In this TPS material concept, the "char" phase is pre-engineered UHT zirconium carbide (Zr(O)C) ceramic fiber pre-forms, which have dual functions of high compressive strength of ligaments and non-recession of fiber components after matrix ablation. To increase the pre-form ligament strength and stiffness, Zr(O)C fiber reinforcements will be combined with the high-modulus carbon fibers. MG's ablative TPS are designed to retain their shape in extreme environments, thereby reducing the thickness requirement and lowering the TPS total mass, which will be crucial at high re-entry velocity. MG's new ablator slowly absorbs high levels of energy when ablated at higher temperatures. The ablative carbonaceous phase has been identified by the use of a melamine-formaldehyde and/or polyethylene polymer resin. This selection was based upon its high heat of volatilization and decomposition. At the completion of the Phase I and Phase II program, MG will have fabricated a high specific strength C-Zr(O)C / C-ablator and have demonstrated an completely integrated 5'x5' size TPS with attachment features, operational at > 6000oF.

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In Phase I, the research team formed by APEI, Inc. and University of Arkansas proved the feasibility of developing ultra-wide temperature (-230 <!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Strict//EN" "http://www.w3.org/TR/xhtml1/DTD/xhtml1-strict.dtd"> <sup>o</sup> C to +130 <sup>o</sup> C) motor drives utilizing silicon-germanium (SiGe) asynchronous logic digital control electronics by the successful design, simulation and layout of an insensitive-delay asynchronous microcontroller. The microcontroller incorporates asynchronous-to-synchronous and synchronous-to-asynchronous interfaces (wrappers) using an IBM SiGe 5AM process. The complete asynchronous microcontroller was successfully simulated using temperature calibrated models to -230 C. Electronic components needed in the development of the DC-motor power stage were first characterized down to -184 C and then a complete 20W DC-motor drive power stage was successfully demonstrated while operating at cryogenic temperatures and driving a Maxon RE 25 permanent magnet DC-motor at full power (This motor is currently used on the Mars Spirit and Opportunity rovers). Ultra-wide temperature power electronics system will have a profound impact on deep space exploration craft enabling greater mobility and mission lifetime. The use of ultra-wide temperature power electronics will allow increased payload capacity of Lunar and Mars exploratory craft, while improving reliability through reduced system level complexity. The goal of this Small Business Innovation Research Phase II project is to deliver, to NASA JPL, a complete DC-motor drive that is fully functional over the entire temperature range required for lunar and Martian extreme environment exploratory robotic missions (-230 C to +130 C). This cryogenic DC-motor drive will encompass a SiGe-based 8051-compatible delay-insensitive asynchronous microcontroller with significantly enhanced capabilities for the advanced control of the DC-motor drive.

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Pentalim Inc. is developing a new sensor for the measurement of chemiluninescence of air breathing engine combustion. The sensor will be wireless and incorporate optical power scavenging technology that will increase its effective transmission range. The sensor will also incorporate Silicon Carbide electronic materials to enable in situ monitoring of combustion. This sensor will be applicable to both future propulsion systems as well as legacy and helicopter engines and will enable improved combustion instability, pattern factor and emissions control.

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Mainstream Engineering Corporation completed the design of a high-speed pump for International Space Station (ISS) Environmental Control and Life Support Systems and future spacecraft and extraterrestrial outpost applications. Specifications for this pump were derived from an existing pump currently operating as part of the thermal control loop on the ISS. The design includes magnetic bearings so that a vibration-reducing control algorithm can be implemented. A digital controller was designed, which measured and reduced vibration-causing fluctuations in shaft displacement due to rotor unbalance in multiple axes. The controller was tested over an operating speed range of 600 to 7200 rpm with excellent results. The controller reduced mean shaft displacement by 71% over the entire operating range, and reduced it by more than 80% at higher operating speeds where synchronous vibration was dominant. In Phase II the magnetic bearing equipped cooling loop pump designed in Phase I will be fabricated and tested. Mainstream will demonstrate the added efficiency, reliability, and low vibration of the system as compared with the existing pump. The pump assembly will undergo vibration characterization testing with support from Marshall Space Flight Center.

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An innovative microwave system is proposed for the continuous production of medical grade water. This system will utilize direct absorption of microwave radiation to rapidly heat potable water well above normal autoclave conditions, achieving equivalent microbial lethality in much shorter times. High thermal efficiencies will be gained by placement of the microwave antennae directly in the flowing water stream allowing very efficient volumetric coupling of microwaves. The sterilized water stream will then pass through a regenerable endotoxin filter to achieve water for injection (WFI) purity standards. This filter will remove endotoxins by selective adsorption. The combined system will enable the energy efficient and practical production of WFI aboard spacecraft or planetary habitats under microgravity or hypogravity conditions with a low equivalent system mass (ESM). In the Phase I research, sterilization chambers and endotoxin filters will be designed, assembled, and tested. The Phase II program will deliver a fully instrumented, computer-controlled system with a low ESM whose performance is well documented. This technology will form the basis for multiple applications in commercial sterilization markets.

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This proposal addresses the need for a real-time Prognostics and Health Management (PHM) system to identify anomalous states in digital electronic systems used in spaceflight applications and recommend corrective actions. We identify promising host platforms for implementation of PHM and consider strategies for identifying faults at the board level. Models for each approach are developed for further study of the effectiveness in identifying faults, estimating system states, and identifying anomalous states. Each method is then ranked with respect to prognostic fault coverage (state-awareness), missed alarms, and false alarms. Finally, a strategy is developed to optimally and dynamically reconfigure or recover the digital system based on current or predicted system status given by the prognostic/reasoner approach and board topology. By responding to a need for greater health awareness in complex on-board digital systems, the technology developed in this project will improve safety and effectiveness of future spaceflight missions, and improve serviceability and availability throughout the system lifecycle.

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Honeybee Robotics proposes to: ?Derive and document the functional and technical requirements for Aerobot surface sampling and sample handling across a range of aerial platforms, mission applications and exploration targets, like Mars and Titan. ?Create a preliminary design for a tether or boom deployed, reusable, low mass & volume surface and subsurface sample acquisition and handling system that can acquire ice and icy regolith samples and perform automated sample transfer. We will focus on designs relevant to environments and sample types on Mars and Titan. ?Demonstrate proof-of-concept, subsystem-level hardware that can acquire a subsurface ice or icy regolith sample deployed from a platform capable of simulating the horizontal and vertical motion of an Aerobot vehicle. The proposed innovations primary significance would be to: ?Provide mission planners with the performance specifications, necessary accommodations, concept of operations and the functional requirement information needed to develop new concepts and exploration applications for Aerobot platforms that have sampling and handling capabilities. ?Identify and address the critical challenges surrounding tether or boom deployed, very low-preload sampling systems targeted toward consolidated materials (e.g. ice or rock). ?Test and characterize the effectiveness of a variety of sample methods, relevant to Aerobot platforms, to acquire ice cores, chips, icy regolith and even liquid samples with integrity and volatiles retained. ?Demonstrate sampling at a safe distance and in a safe manner from the aerial platform. ?Demonstrate, with analysis and hardware, the basic feasibility of an Aerobot sampling and handling system. ?Provide requirement information and test data about an existing system, Honeybee's Touch and Go Sample System (TGSS), capability to acquire ice, icy regolith and even liquid samples from a platform with both horizontal and vertical motion during sampling operations.

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One of NASA's primary goals for the next decade is the design, development and launch of a spacecraft aimed at the in-situ exploration of the deep atmosphere and surface of Venus. The success of this mis-sion, called VISE (Venus In-Situ Explorer), is reliant on the development of effective thermal insulation solutions capable of protecting spacecraft for extended periods of time from the extreme heat and pressure associated with the lower atmosphere of Venus. Materials intended for exterior application must also be inert towards the sulfuric, hydrochloric and hydrofluoric acid present. Aspen Aerogels, Inc. proposes to develop a revolutionary aerogel composite intended to provide unprecedented thermal and chemical pro-tection to a Venus spacecraft. This unique material is expected to be thermally stable to 2000oC under inert conditions, enabling the possibility for use as a high-temperature heat shield in a Venus deceleration module. This flexible and conformable material will also find use as a thin lightweight thermal protection solution for a Venus pressure vessel. The remarkable thermal properties and ultra low density will afford a significant mass savings over conventional MLI insulation, increasing the operation lifetime and volume of the scientific payload significantly. These materials will also be inert towards the corrosive environ-ment of the Venus atmosphere at high temperatures and pressures, allowing these materials to be utilized in both exterior and interior applications.

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This SBIR Phase I proposal addresses the need for explosion proof, sensitive and reliable hydrogen sensors for NASA and commercial hydrogen fuel systems. It also addresses the need for multiple sensing points with minimum tank or bulkhead feedthroughs. The proposed innovations will increase the response speed of reported hydrogen sensors by a factor of 5 and the sensitivity by a factor of 10. In the Phase I feasibility work, it is proposed to demonstrate these attributes for single sensors. In Phase II, the multiplexing, detection reliability and special packaging necessary to make the sensors practical for NASA and other applications will be demonstrated in preparation for commercialization in Phase III.

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Supercomputing plays a major role in many areas of science and engineering, and it has had tremendous impact for decades in areas such as aerospace, defense, energy, finance, and telecommunications?to name just a few. Supercomputing enables many of our most important high-tech tools, and nowhere is it more important than at NASA, where attaining increased computing speed and performance at lower costs are constant objectives. The goal of this multi-phase SBIR project is exactly that?to develop, validate, and commercialize next-generation supercomputing capabilities that provide NASA and other government/commercial users with massive increases in speed at minimal cost and with reduced energy requirements and significant "footprint" efficiency. In Phase I of this NASA SBIR project, Accelogic successfully demonstrated the feasibility of developing the world's first reconfigurable computing linear equation (banded) solver for large-scale computing problems?such as those seen in aerospace applications?with greatly increased speed using an FPGA chip. The speed attained was equivalent to 240 CPU's per FPGA chip for banded systems?which represents nearly a 60x computing speedup (surpassing the 50x Phase I target). Accelogic's Phase I success sets the stage for a Phase II effort focused on prototyping/validating an initial supercomputing acceleration product. The Phase II technical goal is to demonstrate the potential for 1,000x speedup. During Phase I, Accelogic has proven it is ideally positioned to capitalize upon recent advances in reconfigurable computing?many of which were attained by Accelogic's own experts. Applications for the products targeted by this project include many that are of interest to NASA, DOD, DOE, and many commercial entities. Based on Phase I results and the clear commercial potential, Accelogic has obtained interest/commitment letters from well-established commercial vendors and key NASA contractors, including Silicon Graphics.

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Our objective is to develop a compact scanning Fabry-Perot spectrometer, for satellite far-infrared astronomy and Earth remote sensing, that operates at wavelengths of 100 ?m and longer, with a resolving power of 10,000 and free spectral range of ~50 cm-1. The novelty of this innovation lies in obtaining this very large free spectral range simultaneously with a resolution equivalent to the state of the art for laboratory far-infrared spectrophotometers in a volume less than a liter and directly suitable for airborne and satellite instrumentation. The critical innovation lies in providing far-infrared Fabry-Perot mirrors of >99.99% reflectance to enable unprecedented system finesse. This mirror development and proof testing, and a systems analysis of an F-P spectrometer subsystem for satellite and aerial imaging are the subject of Phase I; Phase II includes design, fabrication and testing of the miniature spectrometer.

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This SBIR phase II project proposes a single frequency high energy fiber laser system for coherent Lidar systems for remote sensing. Current state-of-art technologies can not provide all features of high energy and efficiency, compactness, narrow linewidth, super frequency and power stability, low noise, and high extinction ratio at the same time. PolarOnyx proposes, for the first time, a high energy (1 mJ) single frequency (< 1 KHz) fiber laser transmitter to meet with the requirement of solicitation. It is a specialty fiber based MOPA operating at 1550 nm. PolarOnyx proposes a revolutionary approach to fundamentally resolve the issues of nonlinear effects by employing our patent pending proprietary technologies in fiber lasers. Our unique spectral shaping techniques enable us to reduce the SBS and ASE noise significantly in the amplifier for commercially available EYDFs and to reuse the residual pump to further increase the efficiency. These will make the fiber laser transmitter system superior in terms of wall plug efficiency (over 30%), energy(1 mJ), noise, size, and cost. In Phase I, we have demonstrated all major functions of the proposed idea and shown a practical energy scaling capability in proof of the concept. A prototype of 1 mJ level fiber laser will be delivered at the end of Phase II.

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Durable, creep-resistant ceramic composites are necessary to meet the increased operating temperatures targeted for advanced turbine engines. Higher operating temperatures result in improved performance, fuel savings (higher efficiency) and reduced pollution. Silicon melt infiltrated ceramic composites have been identified as having a 2400F maximum use temperature, which does not take advantage of the highest temperature capability of the newest generation of near stoichiometric SiC fibers. Conversely ceramic composites containing a SiC matrix derived from chemical vapor infiltration have sufficient stability to take full advantage of the creep resistance of the fibers. For many applications, no existing matrix system for SiC-reinforced composites has sufficient through-thickness thermal conductivity at elevated temperatures to result in low thermally induced stresses; such that longer service life at higher temperatures can be achieved. This Phase I work will demonstrate a higher temperature melt infiltrated matrix that is stable to 2950F, and thus allows the full temperature capability of the latest generation SiC fiber reinforcements to be used. This higher temperature capability is combined with a significantly higher predicted elevated temperature thermal conductivity for the ceramic composite, which will reduce the thermally induced stresses on the material that often dominate the stress state on the material. The Phase I effort will produce ceramic composites with this higher temperature melt infiltrated matrix and perform both thermal and mechanical property evaluations at ambient and elevated temperatures to demonstrate the benefits of the system.

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In Phase Sunpower looked at Thermoacoustic Stirling Heat Engines (TASHEs). These ranged from a TASHE which was sized for the heat from a single General Purpose Heat Source (GPHS), to a larger unit sized for a Venus mission. We also looked at different types of cooler to produce both electrical power and sensor cooling for the Venus application. Computer projected performance and layout drawing were created for all the machines investigated. In Phase II we plan to fabricate, test, and develop the single-GPHS sized coaxial. TASHE designed in Phase I.

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High performance silicone coatings are desired for flexible fabrics used in several space and consumer applications. For instance, the total weight of silicone coatings that are used on Mars Exploration Rovers (MER) airbags can be reduced by improving their thermal stability and mechanical properties. The proposed program focuses on developing advanced silicone coatings by working with a manufacturer of coated and laminated fabrics for industrial and general-purpose applications. In Phase I, we will develop coating formulations, deposit coatings on a few different types of fabrics, and characterize the coatings for various properties that are required for airbag applications. Additionally, plans for commercialization and scale-up will be developed during Phase I for implementation in Phase II, so that the product can be manufactured and marketed in Phase III.

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The Small Business Innovative Research Phase II proposal seeks to develop a dual channel, compact mid-infrared laser spectrometer for planetary atmosphere exploration. The device will be capable of measuring numerous trace gases at 3.3 and 4.6 um without the need for cryogens. By using novel, fiber-coupled, solid state lasers, performance will be improved over traditional tunable diode laser sensors with a simplified operation that is rugged and low power.

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Honeybee Robotics proposes to build upon technology we have previously developed with Goddard Space Flight Center and redesign specifically for the lunar environment a "gear bearing" transmission. We intend to bring this technology to a higher Technology Readiness Level (TRL) for the number of applications imagined for future missions to the lunar poles requiring motors and drive trains ranging from mobility systems, in situ resource utilization (ISRU) machinery, and robotic systems mechanisms. The advantages of this design lend themselves well to spaceflight mechanisms in general and specifically to the extreme conditions at the lunar poles. The high gear reductions possible within a single stage, coupled with the already compact size make gear bearing transmissions ideal for spaceflight hardware where size and weight are at a premium. The relative simplicity, the elimination of traditional bearings in the transmission, and the avoidance of sliding friction altogether have significant advantages in cryogenic and hard vacuum environments where material and lubricant selection are limited.

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Triton Systems, Inc. (Triton) proposes to develop a cost-effective manufacturing approach to fabricate combustion chambers for a rocket technology demonstrator engine. The proposed manufacturing process combines Triton's success in fabricating high strength, ductile, discontinuous fiber reinforced aluminum (FRA) composites and rapid prototyping techniques used in the aluminum casting industry. The ability to insert Triton's FRA technology into boost and orbit transfer components supports critical propulsion goals by improving the thrust-to-weight ratio and reducing hardware costs. Significant weight savings will be achieved with Triton's lightweight FRA technology compared to the current nickel superalloy. Hardware costs savings are anticipated with the use of a proven, affordable and high quality casting process to fabricate FRA materials. An added benefit is the ability to incorporate design changes for improved efficiency and/or research and development efforts.

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Computer codes such as MCNPX now have the capability to transport most high energy particle types (34 particle types now supported in MCNPX) with energies extending into the teravolt energy range. The efficient use of these types of Monte Carlo tools is very important for modeling the effects of space radiation on humans, spacecraft and equipment. This proposal would develop a graphical user interface for high energy multi-particle transport. With this innovation, users of the MCNPX code would have access to a powerful graphical user interface for efficient creation and interrogation of their input files, which would significantly reduce the amount of time required to create and debug input files.