Summary

Description

Recent advances in ontology development support a rich description of entities that are modeled within a domain and how these entities relate to each other. However, even with ontology information, interoperability of a (sub-) system with other systems remains a serious issue. Interoperability issues may arise when two sub-systems that had not been designed as a unit must now work together. Interoperability issues also arise when extensions to a sub-system result in conflicts with the remainder of the system. In this work, we target (sub-) systems pertinent to advanced life support that are developed using software agent technology. Our innovation is to develop an ontology-aware meta-model to support designers and developers in exposing the information that must be captured in order to achieve the goal of 'designing for interoperability, extensibility, and re-use'. Additionally, the meta-model will be integrated into the agent-oriented software engineering (AOSE) design process. Even beyond development of the meta-model and methodology for coupling into the design process, we propose to develop tool support so that the meta-model can be easily utilized within the design process. The success of this innovative meta-model, process, and tool, will support agent-based software re-use and rapid, trouble-free integration of upgraded sub-system components.

Summary

Description

Every day, turbulence has an adverse effect on aircraft operations and capacity of the NAS, costing the airline industry at least $100 million annually in operational inefficiencies, unscheduled maintenance, and injuries. A contributor to these costs is that controllers' and dispatchers' current tactical knowledge of turbulence hazards relies heavily on verbal pilot reports of turbulence, which are often inconsistent, late, and subjective. AeroTech will develop a turbulence hazard decision support tool (TurbDST) that will enhance controllers' and dispatchers' situational awareness of the location and severity of turbulence; by providing real-time quantitative turbulence information down-linked from aircraft. TurbDST will enhance tactical and strategic decision making with regard to airspace usage and aircraft routing by enabling users to predict the effect of the reported/detected turbulence on aircraft whose route may take them through that location. With enhanced turbulence knowledge, collaboration with pilots regarding route changes can be improved and cost savings to the airlines can be gained through more efficient and safer aircraft routing. Phase I will prove technical feasibility of integrating the turbulence information and will develop, using controller and dispatcher inputs, CONOPS and requirements for the TurbDST. By Phase III, a meaningful controller/dispatcher TurbDST will be developed, tested, and evaluated.

Summary

Description

We propose to develop a novel thermal interface material (TIM) that is based on an array of vertical carbon nanotubes (CNTs) for high heat flux applications. For high precision, spaceborne lasers and other high power devices critical to NASA's Science Mission Directorate, heat flux levels are projected to reach 100 W/cm2. The state-of-the-art in space-compatible thermal interface materials (TIMs) is limited to a maximum achievable thermal conductance of approximately 5 W/cm2<SUP>o</SUP>C. Preliminary testing of our innovative TIM approach has demonstrated thermal conductance values of 33 W/cm2<SUP>o</SUP>C, a nearly seven-fold increase. For an incident heat flux of 100 W/cm2, this corresponds to a temperature drop of only 3<SUP>o</SUP>C, compared with 20<SUP>o</SUP>C for current technology. Thus, the use of our innovative CNT-based TIM will enable increased reliability, decreased size, and increased performance of spaceborne thermal management systems for the SMD.

Summary

Description

Future long-duration manned space flights will rely upon onboard production facilities to grow and produce food throughout the mission. Because the lives of the mission participants will depend upon successful agricultural and horticultural practices, it is imperative to provide them with sophisticated diagnostic tools with which to assure success. Continuous real-time monitoring of gaseous species in the ambient environment is required. There are several gases vital to this application including ethylene, oxygen, and carbon dioxide. Vista Photonics proposes to develop a rugged, real-time, 15 parts-per-billion (ppb) gaseous ethylene analyzer, ultimately compatible with space flight. The sensor technology developed on this project will be further capable of high-performance detection of additional trace gases including moisture and plant respiratory oxygen and carbon dioxide.

Summary

Description

Metis Design Corporation (MDC) proposes the development of a strain-based power replenishment technology to harvest energy for recharging remote sensors. MDC has been working to development of a structural health monitoring (SHM) device, which essentially evolves the embedding of sets of sensors into a structure to allow continuous remote monitoring. MDC's work is aimed at developing a robust infrastructure package to support a variety of sensor types and detection methods for aerospace structures. Components have been developed to acquire data, excite transducers, store and wirelessly transmit data, as well as a thin-film battery and packaging to protect the electronics from moisture, EMI and impact. During the course of this SBIR, MDC will work to develop a power replenishment patch that uses piezoelectric technology coupled with an innovative circuit design to "top-off" SHM system batteries. These thin patches would be intimately bonded to the structure in order to harvest strain energy to recharge a thin-film Lithium battery slowly over time. This concept is unique since it takes advantage of the low duty cycle of SHM electronics, instead of attempting to harvest energy for continuous system operation. MDC will demonstrate the ability to performing structural integrity testing using only harvested power.

Summary

Description

Precise location information is critical for crewmembers for safe EVA Moon and Mars exploration. Current inertial navigation systems are too bulky, fragile, and expensive for this purpose and therefore cannot meet NASA requirements. To address these requirements, Physical Optics Corporation (POC) proposes a novel Time and Relative Distance Inertial Navigation System (TARDIS), a compact, cost-effective solution providing EVA crewmembers and monitoring personnel with location and orientation to home base. With this information, TARDIS will generate a 3D navigation track of the astronaut's movement, which the astronaut can compare to a preplanned path, as well as key reference points, such as the base camp, rover, and destination. TARDIS builds on POC's smart inertial sensor cluster technology, integrating compact dedicated microprocessors with inertial microelectromechanical systems in a purely digital six-degree-of-freedom inertial navigation system in an extremely small volume. This is coupled with a Kalman filter for optimal position estimation. Spatial operator analysis (SOA) derives the relative orientation of an EVA crewmember's arms and legs to specify current activity (bending, walking, sitting, climbing). In Phase I POC will prove the concept by demonstrating a scaled-down working model with a limited number of sensors. In Phase II POC will demonstrate a complete working prototype.

Summary

Description

This proposed SBIR Phase I addresses the development of catalysts and technology for the ignition of advanced monopropellants consisting of mixtures of hydroxylammonium nitrate (HAN) and a combustible component. The catalysts will possess intrinsic activity for ignition and will also possess requisite thermal stability and erosion resistance. Minimal delay times will be achieved by the catalyst composition and enhanced surface area, which will accelerate rate limiting steps of ignition. Phase I will consist of the synthesis and physical characterization of catalysts, evaluation of catalyst activity, initial optimization of composition and preparation of catalysts, and testing in a combustion chamber. In Phase II, the preferred catalyst(s) will be optimized, synthesized in larger quantities, and subjected to more rigorous and extensive testing in a device. The goal of the proposed program will be to develop a catalyst exhibiting a low ignition temperature, but also possessing the favorable attributes described above. Successful development of such catalyst technology will lead to applications in a number of propulsion-related devices.

Summary

Description

CFD codes used to simulate upper stage expander cycle engines are not adequately mature to support design efforts. Rapid and accurate simulations require more versatile grid frameworks to handle complex geometries of multi-element injector configurations. Turbulence models require upgrades to better predict fuel/air mixing with swirl and to predict heat flux. The innovation proposed initiates work towards developing a mature, high-fidelity simulation tool. Geometry complexity and numerical accuracy problems are addressed via a multi-element UNS grid adaptation strategy that builds upon techniques developed for valving problems and scramjet injectors. Turbulent mixing and heat transfer are upgraded by including PDE's that solve for temperature and species variance (yielding local values of Prandtl and Schmidt number), as well as swirl corrections. Finally generalized preconditioning that accounts for stiffness resulting from a large range of Mach numbers, and generalized thermodynamic formulations for real fluids will be matured to yield robust numerics with improved solution convergence. The tools and technology to be developed here would directly impact design efforts for future long duration lunar and Mars missions that require more durable long-life, light weight system components, and address methodology to operate with novel hydrocarbon fuels that may be harvested in-situ.

Summary

Description

To address NASA needs for quiet crew volumes in a space habitat, Physical Optics Corporation (POC) proposes to develop a new Adaptive Intelligent Ventilation Noise Control (AIVNC) system to reduce acoustic noise and vibration inside the crew living quarters. The proposed AIVNC is based on multifrequency active patches as a thin-skin-type actuator inside the ventilation system, and an intelligent adapting module instantly and continuously suppresses broadband noise in crew rest areas. The AIVNC active adapting module provides actuation signals to the multifrequency active patches by means of real-time intelligent adaptation to time-varying noise sources. The AIVNC multiple-modal actuation array targeting different frequency ranges enables users to perform fast active adaptation for acoustic noise suppression in a space habitat with an easy retrofit capability. In Phase I POC will demonstrate both the feasibility of AIVNC by testing active actuation patches, and an intelligent adapting model including an optimized system configuration and methodology. In Phase II POC plans to implement AIVNC into a fast, compact, standalone board with a complete actuator subsystem for precise acoustical control.

Summary

Description

NASA is seeking a high performance thermal insulation material for cryogenic applications in space launch development. Many of the components in cryogenic distribution systems at the launch site can be complex and require an insulation that can be formed to irregular shapes to minimize heat leak. Aerogel beads are configurable to virtually any shape and offer a lightweight insulation solution with substantial improvements over conventional insulations. Success in the commercialization of high performance insulating aerogel beads has relied on the effectiveness of converting loose beads into functional insulation components. This type of insulation component requires reasonable mechanical strength and should be able to withstand a certain degree of compression, tensile, and flexural loads. Aspen Aerogels' solution entails the use of mechanically resistant aerogel beads and a binder that does not penetrate the surface of the beads. Preliminary investigation into composite development in the Phase I effort has resulted in a net shape insulation component having excellent thermal and mechanical properties. This type of insulation component is able to fill areas that are currently inaccessible with existing insulation products. A high-performance thermal insulation composite, such as that described in this proposal, will have a significant impact in insulation technology advancement.

Summary

Description

The Integrated Mars In-Situ Propellant Production System (IMISPPS) is an end-to-end system that will produce rocket propellant on Mars from CO2 in the Martian atmosphere. The IMISPPS conducts both the Reverse Water Gas Shift (RWGS) and Sabatier (S/RWGS) reactions in a single reactor to produce a useful high-specific impulse fuel (methane plus carbon monoxide) and water, which is condensed and electrolyzed to produce oxygen and hydrogen. The hydrogen is recycled back to the S/RWGS reactor to react with fresh Martian CO2 to produce more fuel, while the oxygen is stored to provide oxidizer. Some of the carbon monoxide is removed by cryogenic separation to increase propellant specific impulse. The IMISPPS system produces the correct amount of oxygen to burn the methane produced, almost doubling the leverage of a Sabatier/Electrolysis system alone.

Summary

Description

A robotic sample management device and system for the exposure of biological and material specimens to heavy ion beams of the NASA Space Radiation Laboratory (NSRL) and other irradiation venues is proposed by SHOT, Inc. Full and efficient utilization of NSRL requires the automation of precise sample positioning and sample exchange that is otherwise performed manually at the cost of hours of beam time and risk of personnel. The device and system will consist of a multiplicity of sample holders providing an environmentally controlled enclosure. Samples to be irradiated will be translated into the ion beam, one at a time, within the controlled environment. Samples to be accommodated include, but are not limited to, cell cultures, small animal (flies, worms, fish) cultures, mice, rats and small samples of shielding or electronic materials. Operating software will be compatible with that in use at the irradiation venues, specifically NSRL, and will be used to establish environmental control settings, to record environmental conditions, and to control and record the insertion of samples into the ion beam. Three objectives will be met in Phase I research: (1) user requirements and engineering requirements will be established in detail, (2) a preliminary design including assembly and component 3-D renderings will be completed, and (3) this design will be subjected to design review by internal and external advisers and potential users. An optional objective, if matching funding is available from the State of Indiana, is the production and testing of a Specimen Holder Assembly prototype. Phase II research will consist of (1) finalizing requirements and design documents for official preliminary review, (2) building and testing prototypes of components for final overall design approval, and (3) assembling and testing a first system at SHOT and assembling, installing and testing a final product at NSRL and placing it into use for the benefit of the user community.

Summary

Description

The PI has developed a miniature time-of-flight mass spectrometer (TOF-MS), which can be op-timized for space and extraterrestrial applications, by using a revolutionary ion-focusing scheme. The instrument is optimized for a matrix assisted laser desorption/ionization ion source. The design is compact and the device that will be built under a Phase II grant will have a mass of less than 1 kg, a volume of less than one liter and draw approximately 3.5 Watts, exclusive of vac-uum generation, laser and sample-handling equipment. The proposed device will include a sam-ple-handling component, which will slightly increase the mass, volume and power requirements. Although there are several miniature TOF-MS systems currently available (NASA has a design available for licensing) the proposed innovation will out-perform all of the miniature designs currently available by 1 to 2 orders of magnitude (resolution and sensitivity) and has mass resolution comparable to current full-size research instruments. For commercial applications where volume, mass and power requirements are not so stringent, a device that performs better than current full-sized instruments can be designed.

Summary

Description

Latest advances in semiconductor optoelectronics makes it possible to develop compact light weight robust sources of coherent optical pulses, demanded for numerous applications such as lidars. Recent improvements in heterostructure growth and processing technology, as well as new approaches in waveguide design make it possible to integrate single frequency laser diode, saturable absorber, and semiconductor amplifier in one compact device with high wallplug efficiency and long lifetime. In this Phase I project we will design a prototype device, fabricate it and study its basic parameters.

Summary

Description

This proposed Small Business Innovative Research (SBIR) Phase I addresses development of a compact reformer system based on a cyclic partial oxidation (POx) technology for the purpose of generating hydrogen for fuel cell systems. The need for improved reformers arises from: 1) the tendency of hydrocarbon fuels to deposit carbon on surfaces; 2) requirement of large quantities of steam; 3) a massive and voluminous fuel desulfurization stage; 4) substantial size and power consumption requirements; and 5) the lack of efficient, robust, and compact hydrogen separation technology. These issues will be addressed by employment of a fixed bed cyclic redox system utilizing a metal oxide oxygen carrier for partial oxidation of fuel. The reformer will consist of a small heated bed of sulfur tolerant partial oxidation catalyst and will operate by alternate exposure to air and vaporized fuel. Carbon deposition and steam requirements and, possibly, the need for a prereformer will be reduced or eliminated by this cyclic mode. This cyclic operation will also eliminate the need for an expensive air separation unit or for H2/N2 separation. Phase I will consist of identification of catalysts, testing under cyclic conditions with real fuel, and integration of reformer and hydrogen separation modules. On the basis of Phase I data, a prototype system will be designed, fabricated, and tested during Phase II.

Summary

Description

Diagnostic and prognostic algorithms for many aircraft subsystems are steadily maturing. Unfortunately there is little experience integrating these technologies into a complete and practical on-board prognosis system, and integration often proceeds in an ad-hoc manner. Sentient Corporation proposes to develop a general-purpose architecture and set of reusable algorithms for integrating diagnostics and predictive models into an efficient and highly accurate prognostic system. The architecture is based on a flexible and powerful model updating algorithm that provides optimal fusion of diagnostics with model-based state indications and minimization of uncertainty in remaining life predictions. This project will focus on development of several key features of that algorithm, including automatic recognition of a failure that is not progressing according to the physical model, and practical considerations for on-board use such as minimizing computational and memory requirements. By the end of Phase II, Sentient will demonstrate a working prototype of an on-board prognostic system developed using the proposed architecture and tools. This demonstration will use diagnostic and model algorithms developed under the DARPA Prognosis Program, and will be compared to a large set of fault data for turbine engine and subscale bearings.

Summary

Description

Spire Corporation is developing a key component for thermophotovoltaic (TPV) power technology for deep space missions. We are developing InGaAs monolithically interconnected modules (MIMs) that convert thermal photons from the ~1100C General Purpose Heat Source (GPHS) into electrical power. The innovation is that these MIMs are designed to operate at higher cell temperatures (150C) and be more radiation-hard than current MIMs to better match the cell environment on missions. In Phase 1, we developed a model that predicts an optimum InGaAs bandgap (adjustable during epigrowth) for the operating temperature and 1100C blackbody GPHS spectrum of ~0.7eV, made sample devices, and tested temperature coefficients to confirm the model and measured data agree (e.g. model predicts ?1.7mV/C for Voc vs. ?1.8mV/C for data). In Phase 2, we will perform five iterations of a model, design, epitaxially grow, process, and test cycle. Data from each cycle will be used to improve the next design. Testing will include both radiation, temperature stability and accelerated life testing. Before program completion, we will survey NASA and commercial space power contractors for needs and make samples of the best design to distribute among space power contractors as a step toward generating interest and commercial sales.

Summary

Description

To address the NASA need for a miniature pressure-leak sensor, Physical Optics Corporation (POC) proposes to develop a new Microelectromechanical System-based Internally Unpowered Sensor (MEMIUS). Fabrication of MEMIUS involves integration of a small MEMS piezoresistive sensor with proprietary miniature electronics and a novel wireless power transfer mechanism for device power-up and data read-out for a miniature footprint (2 cm x 2 cm x 1 cm, < 20 g weight). MEMIUS can be applied to both nonshielding and metal alloy shielding containers by utilizing inductive coupling with a small, efficient antenna, or a dual-band sensor antenna mounted on metal with a feed-through capacitor. MEMIUS represents an accurate pressure-leak sensor (~0.01 mbar) with no-battery on board electronics. It operates at low-temperatures with remote and efficient wireless power transfer capabilities at variable distances (1-10 m). These specifications are critical to the NASA search for an extremely rugged power efficient pressure sensor less than 5 cu. cm operating from -70 deg. C to +20 deg. C. The proposed MEMIUS thus solves the problems of weight, size, power efficiency, shielding, and electro-magnetic interference. The Phase I effort will demonstrate MEMIUS feasibility, and confirm its ruggedness and sensitivity. In Phase II POC will develop an advanced MEMIUS prototype.

Summary

Description

Recent work has developed a number of architectures and algorithms for accurately estimating spacecraft and formation states. The estimation accuracy achievable during spacecraft operation depends not only on the algorithm, but also on its implementation. Typically, the algorithm will be implemented on a real-time multi-tasking processor that allocates on-board computational resources to multiple tasks and functions according to some scheduling policy. The processor's task scheduler may induce delays that were unaccounted for at design-time and may sometimes preempt estimation tasks in favor of other tasks. Hence, estimation accuracy and in general the performance of any embedded algorithm can be significantly lower than expected during execution. The goal of this project is to develop distributed spacecraft state estimation algorithms that account for real-time multi-tasking processor and other implementation related resource constraints. We bring together modeling techniques from multi-class queuing, well-known Kalman filtering techniques and recent advances in embedded systems to develop an innovative co-design framework for the design of embedded state estimation algorithms and software. During the proposed effort, we will design, implement and evaluate estimation algorithms on a network of real-time processors or hardware emulations of processors on-board formation spacecraft.

Summary

Description

High temperature permanent magnet materials play an important role in NASA's space missions in electric propulsion, energy generation and storage and other applications. We propose to devise accelerated testing methods to test and predict the service life of SmCo based ultra high temperature permanent magnets in a high vacuum environment at high temperatures in excess of 400 degrees C. The proposed research will enable designers to appropriately design and use high temperature permanent magnets to optimize their performance. The proposed efforts will measure outgassing rates through total mass loss methods based on ASTM standards at temperatures from 300 to 700 degrees C at vacuum levels of 10 exp-5 Torr or higher. The microstructure and chemical composition variations at the near-interface region after exposure to high vacuum and high temperatures will be analyzed with scanning electron microscopy and auger electron spectroscopy or energy dispersive X-ray spectroscopy. Magnetic properties will be measured and modeled with finite element analysis. These methods will enable prediction of reliability and performance of high temperature magnets over long space missions through short-term test methods.

Summary

Description

This Phase II program builds from the successful Phase I efforts to demonstrate that Quantum Logic Devices' nanoelectronic platform for biological detection could detect binding of Epo, TNF-alpha, IL-6, and IGF-1 in saline and serum without labels. The creation of an electronic "direct detection" platform for proteomics, enables rapid point of care monitoring of metabolic analytes in microgravity. This Phase II proposal will build working prototypes based on PDA-style electronic data capture with disposable assay cartridges for the analytes demonstrated in Phase I.

Summary

Description

Previous high temperature magnetic bearings employed electromagnets only. The work proposed in this SBIR program seeks to utilize High Temperature Permanent Magnets (HTPM) developed by EEC. This will improve efficiency since the majority of the static load on any bearing can be suspended by the magnetic field of the HTPM. The end product will be a high speed/high temperature/high load test platform for the future development of bearing, motor, generator, and seal components. This capability will be of special benefit to the aerospace and process machinery industries. In addition the component demonstrations from this SBIR will provide designers with the confidence needed to integrate similar components in their high performance machinery.

Summary

Description

nLight developed high-power, high-efficiency laser diodes emitting at 1907nm for the pumping of solid-state lasers during the Phase I. The innovation brought to bear at 19-xxnm wavelengths nLight's design knowledge and experience from its highly successful 9xx-nm and 14xx-nm, high-efficiency and high-power laser diode programs. The expected performance for the laser at the conclusion of the phase I was 25% electrical-to-optical (E/O) conversion efficiency and 18 W continuous-wave power (CW) - both measured at 15C. The program was highly successful in achieving performance of 25W and 23% efficiency at 20C (5C warmer than projection). 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. This work can readily be extended to 18xx-nm and 20xx-nm with comparable performance for application to the pumping of other solid-state lasers.

Summary

Description

Dust, especially lunar dust, has been identified as a significant and present challenge in future exploration missions. In addition to posing contamination and health risks for human explorers, the interlocking, angular nature of lunar dust and its broad grain size distribution make it particularly detrimental to mechanisms with which it may come into contact. All Apollo lunar missions experienced some degree of equipment failure due to dust, and it appears that dust accumulation on exposed material is unavoidable and difficult to reverse. However, experience also indicates that material selection, location, and crew action can mitigate the detrimental effects of dust. It remains the case that significant development is called for in the area of devices and structures that tolerate or mitigate the presence of lunar dust. Thus, Honeybee Robotics proposes to develop both active and passive methods for tolerating and mitigating dust accumulation on reusable connection mechanism interfaces. Techniques such as baffles, brushes, and fluid-washing will be explored more thoroughly as they relate to mechanical connections. Dust-tolerant connection strategies will be an enabling step for much of the technology that Honeybee is currently developing for lunar drilling and sample and instrument manipulation in particular, and as a necessary precursor to interfaces for transferring electricity, fluids, and other utilities in general.

Summary

Description

SciberQuest, Inc. proposes to develop a state-of-the-art data mining engine that extends the functionality of Virtual Observatories (VO) from data portal to science analysis resource. Our solution consists of two integrated products, IDDat and RemoteMiner: (1) IDDat is an advanced grid-based computing infrastructure which acts as an add-on to VOs and supports processing and remote data analysis of widely distributed data in space sciences. IDDat middleware design is such as to reduce undue network traffic on the VO. (2) RemoteMiner is a novel data mining engine that connects to the VO via the IDDat. It supports multi-users, has autonomous operation for automated systematic identification while enabling the advanced users to do their own mining and can be used by data centers for pre-mining. In addition, our data mining algorithms have reverse engineering capabilities which enable analytical derivation of models from time series data. These innovations will significantly enhance the science return from NASA missions by providing data centers and individual researchers alike an unprecedented capability to mine vast quantities of data. Phase II work will encompass the building of a full commercial product with associated production quality technical and user documentation.