Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
By providing size resolved compositional information, the Aerosol Mass Spectrometer (AMS) has greatly advanced understanding of aircraft particulate matter (PM) emissions. AMS data have been critical to much of our understanding of aircraft PM emissions, but in the past it has had limited utility in probing the smallest (<100 nm) particles in the exhaust. Also, prior to this work the AMS has been able to detect only volatile PM and other instruments have been required to characterize the non-volatile (soot). During Phase I, we: 1) developed an improved computational fluid dynamic (CFD) model to simulate the performance of the AMS for <100 particles; 2) used the CFD model to invent a new AMS technology with improved performance for <100 nm particles; and 3) evaluated a newly developed instrument which combines a laser vaporization system with a standard AMS to provide size resolved mass and composition data for soot. During Phase II we propose: 1) upgrade our CFD modeling capability to three-dimensions to evaluate Brownian motion and the effects of fabrication imperfections; 2) fabricate and test the promising lens geometry invented during Phase I; 3) demonstrate the laser vaporization AMS and improved lens design(s) in the laboratory and in the field.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Satellite observations of the Earth often contain excessive noise and extensive data voids. Aerosol measurements, for instance, are obscured and contaminated by clouds, possible only on the sunlit side of the globe, and difficult over bright land areas. We propose to extend filtering and data assimilation techniques for satellite derived aerosol optical depth based on the wavelet transform. The assimilation system is based on the Model for Atmospheric Transport and Chemistry (MATCH) and include improvements such as the incorporation of satellite observed aerosol size modes and column water vapor. Initially we will focus specifically on aerosol measurements from the Moderate Resolution Imaging Spectroradiometer (MODIS) instruments flying on the Terra and Aqua satellites. The assimilated fields will be tested against surface network observations of aerosol optical depth. We will employ the assimilation assimilation system to produce aerosol datasets for application in Earth radiation budget observations and atmospheric correction methods.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
One of the goals of NASA's Fundamental Aeronautics "Subsonic Fixed Wing" project is to reduce fuel burn by 25% 5% by 2018. This corresponds approximately to an increase in Lift/Drag ratio of the same magnitude. While the improvement in design tools funded by NASA will undoubtedly help attain this goal the innovation proposed here is an addition to this effort. In other words, any improvements in performance due to the innovation should be added to any improvements due to the use of new design tools. The innovation proposed here is a "leading edge wave" in which the leading edge of a wing is described by a high frequency, low amplitude wave, rather than the more conventional straight line. Previous results have indicated that such a leading edge can lead to improvements in Lift/Drag ratio of 15%.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Mechanical and thermal performance of CMC components benefit from low part count, integrally fabricated designs of 3D woven reinforcement. The advantages of these designs include the elimination for the need for post-fabrication mechanical attachment and the higher interlaminar properties offered by the through thickness paths of the fibers within the 3D preform architectures. The specific innovations MR&D is proposing are to improve the preform geometry definition through the use of the Kansas State University digital element approach, improve the material properties calculation module using a modified unit cell algorithm associated with the new geometry, and enhance the code calibration through additional CMC fabrication, imaging and material property testing.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
A versatile self-sustained health management (HM) solution comprising of lightweight, power efficient, portable hardware and highly accurate analytic and reasoning software is the envisioned outcome of this effort. The HM solution will be equipped with customizable feature extraction, fault detection, identification and classification algorithms. A built in powerful reasoner and capability of porting dependency models and user defined analytic algorithms make the solution usable in a variety of HM application. Especially, the solution is suitable for on-component embedding in rotorcraft and fixed wing aircraft. Capability of storing data and HM decisions and communicating with a variety of data/communication bus systems empowers such solutions to function in a collaborative manner and attain vehicle level health management capability. Integration of the dependency models embedded in the individual HM solutions on a vehicle computer, and supplying it with component level observations and the HM outcomes achieves the vehicle level HM. The same reasoning and analytic algorithms can be reused here. Combining the vehicle and system level observation HM outcome and usage information can facilitate fleet level CBM through this effort.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Sample return missions have primary importance in future planetary missions. A basic requirement is that samples be returned in pristine, uncontaminated condition, necessitating development of a canister system capable of maintaining cleanliness and seal integrity through a variety of environments. Such a canister system, the Sealed Planetary Return Canister (SPRC), is proposed. Besides providing a high integrity seal, the canister also incorporates features that for robotic manipulation and to allow the sample to be accessed in a controlled manner upon return to Earth. The SPRC seal system addresses the two most significant concerns for planetary samples ? seal surfaces contaminated by the sample and high pressure due to the phase change of volatiles. The SPRC incorporates a novel sealing system evolved from the only marginally successful Apollo seal approach but with added features to address the difficulties and inconsistencies observed. The indium is contained within a protective barrier to prevent oxidation, and the knife edge is mechanically cleaned during the sealing process. The container body will be configured to accommodate a variety of samples including rock cores, rock fragments, regolith, dust, and frozen soil. Atmospheric samples can also be preserved. The design is readily scalable and adaptable to specific missions.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Long-duration balloon flights are an exciting new area of scientific ballooning, enabled by the development of large super-pressure balloons. As these balloons represent a new form of balloon technology, it follows that there is much to be learned about how these balloons behave in flight. There is a need to collect data on the balloon platform itself in order to better characterize its in-flight behavior. A lightweight suite of sensors will be developed to quantify several variables affecting the balloon. The measurements will include gas temperature inside and outside of the balloon, balloon film strain and temperature, and the aging of the balloon film. Phase I will involve developing a gas temperature sensing approach, a film strain and aging sensing approach, and an alternate approach to film strain and temperature measurements. Taken as a group, the approaches to be investigated are seen as likely to offer promising solutions to those measurement challenges. They will be tested in the laboratory and in a balloon on the ground. The ultimate result of the project will be a sensor suite that allows super-pressure balloon behavior and flights to be accurately modeled.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Continue development of a Compact Transmitter Module (CTM). Modules will be voltage controlled to adjust wavlength using temperature and drive current settings. The electronics will be designed to be space qualifiable. Modules will be designed and manufactured capable of operating at 1.2x 5m and 1.57 5m. Reductions in size, weight and power will be pursued using either small conventional coolers or thin film thermoelectric coolers (nano-coolers) to replace the conventional larger TEC. Weight reductions will be explore by using alternative which are composites of Aluminum Silicon (AlSi) and Aluminum Graphite.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
The proposed innovation is a static, cathode-fed, 2000 psi, balanced-pressure Advanced Cathode Electrolyzer (ACE) based on PEM electrolysis technology. It electrolyzes water vapor supplied to the hydrogen-evolving electrode and eliminates the need to circulate hydrogen and water on the cathode side of the cell. Innovations include the application of Infinity proprietary cell sealing technology to electrolysis to minimize high-pressure seals and the use of innovative passive current-control techniques to eliminate potential hydrogen gas in feedwater chambers. ACE produces hydrogen and oxygen that is free of liquid water droplets without using dynamic product gas/liquid water phase separation and/or other motorized equipment.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
We are proposing to develop high power, high efficiency Ka-band and W-band amplifiers for future NASA missions. The significance of the innovation primarily lies in two areas: better interconnections to available MMIC and extremely low loss power combiner. The approach uses Nuvotronics unique metal micromachining PolyStrataTM process, used to create suspended recta-coax lines, MMIC sockets, and millimeter-wave (MMW) interconnection circuits with low loss, small size/high density, and durability. During this Phase I project, we wil design two circuits at Ka and W-band using commercial of the shelf power amplifer MMICs to achieve the goal of 10 Watts (Ka) and 2 watts (W) output power with 20% efficiency.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Lunar dust has been identified as a significant and present challenge in future exploration missions. Significant development is called for in the area of devices and structures that tolerate or mitigate the presence of lunar dust. Honeybee Robotics seeks to develop a scalable dust-tolerant, autonomous utility connector for lunar surface system applications with a focus on small pressurized rover recharge. Honeybee has heritage in developing mechanisms for extreme, dusty environments. There are many near-term applications of such a connector including: the utility and electrical connections that will be used on the next-generation lunar EVA suit, cryogenic utility connections that will be used to pass liquid hydrogen and liquid oxygen during in-situ resource utilization activities, and high-power electrical connectors capable of thousands of cycles for the Lunar Electric Rover (LER) battery recharge and data transfer functions. The Phase I program has resulted in (1) environmental testing of breadboard lunar dust-tolerant alignment features for autonomous utility connections capable of accommodating 120&#730; angular and 11.5cm lateral approach misalignment; and (2) a conceptual design that integrates the dust-tolerant alignment features with our dust-tolerant electrical connector and mechanical connection mechanisms based on lessons learned during environmental testing of the alignment feature breadboard. In Phase II, Honeybee will develop a prototype autonomous utility connector that integrates the alignment features, mechanical connection mechanism and electrical connection mechanism; testing the prototype in our lunar Dusty environment Simulation Test chamber that is capable of closely reproducing the conditions of the lunar surface. This effort will lead to the development of an autonomous dust-tolerant utility connector to TRL 6 with a focused application to the battery recharge connector for the LER being developed for the Constellation program.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
ORBITEC proposes to develop processes and waste heat recovery techniques to be incorporated into the existing Plastic Melt Waste Compactor (PMWC) to increase efficiency and throughput. The end goal will be to incorporate these processes and techniques into the PMWC system developed by Ames Research Center (ARC). The PMWC has shown to be the best technology for waste management for space applications. It can compress, recover water, and stabilize the waste in one compact system. Even though the PMWC has been built and is being tested by ARC, many technical challenges remain. This Phase I effort is in response to those challenges to increase the PMWC Technology Readiness Level significantly by the end of Phase II. During Phase I much will be done by computational analysis to analyze the best materials to minimize heat losses and how to most effectively add forced air convection to the process. A benchtop simulator will also be developed and tested to more accurately quantify and validate the computational results. Phase II will expand upon these efforts by incorporating the Phase I designs into the current PMWC or by constructing a next generation PMWC, which will have a TRL of 5 or 6.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Robotic sample acquisition is essentially grasping. Multi-finger robot sample grasping devices are controlled to securely pick up samples. Equations have been developed to provide optimal grasps for perfectly modeled objects, but grasping unmodeled objects like a random sample on planetary surfaces is an open research problem. Approaches to grasping unmodeled objects use various sensors, such as cameras, distributed pressure sensors, and strain gages, to characterize the object and the quality of a grasp. That information is then used to initiate or improve the grasp. A major source of difficulty in robotic grasping, therefore, is the sensing of object parameters and grasp quality. Humans combine the high information content of vision, several types of haptic/tactile sensors in the fingers (300 sensors per square centimeter), and a sophisticated learning process to grasp unknown objects. In comparison, current robotic graspers rely on a much more limited set of sensors, particularly for measuring tactile properties. This proposal focuses on an algorithm for improving grasp quality using several types of tactile information as well as the robotic grasper that can provide such information so that remote sample acquisition devices can perform as well as human sample gatherers
Hyperspectral Longwave Infrared Focal Plane Array and Camera Based on Quantum Well Infrared Photodetectors Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
We propose to develop a hyperspectral camera imaging in a large number of sharp hyperspectral bands in the thermal infrared. The camera is particularly suitable for the multispectral thermal infrared (TIR) imager of NASA's HyspIRI Mission. In Phase 1, we successfully developed a crucial camera component: a 640x512 focal plane array (FPA) with 8 - 12 micron broadband longwave infrared spectral response. In Phase 2, we will integrate the FPA with a linear variable filter in a dewar cooler assembly and package the resulting sensor engine with electronics and optics into a camera system. The camera, featuring digital and analog video outputs, will be delivered to NASA at the end of Phase 2 for feasibility testing for the HyspIRI and other NASA missions.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Develop Small Satellite Analysis Laboratory (SatLab): A simulation-of-simulations framework to integrate component and engineering simulations into a single larger simulation capable of full satellite system trade analysis and optimization, in order to reduce the cost and increase the quality of design and development of new small satellites and space vehicles, and test system upgrades and modifications on other space systems.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
High-performance polarimetric and nonpolarimetric sensing is crucial to upcoming NASA missions, including ACE and CLARREO and the multi-agency VIIRS NPP project. The objective of the proposed project is to use single-layer metamaterial metal/dielectric composites to develop multiwavelength polarimetric focal plane arrays (FPAs) that far exceed performance requirements for ACE and CLARREO, while reducing costs through component integration. Phoebus's metamaterial films are an enabling technology and can be used to develop high spectral resolution, low-crosstalk components for other NASA missions, such as GEO-CAPE, as well as transparent metal contacts for high-efficiency sensors and solar cells. Phoebus's metamaterial films can eliminate several problems with current polarimetric detectors, such as diffraction, light scattering, moving parts, and the need to dice/bond components. This project will use recent discoveries in metamaterials research that allow for polarimetric control of the flow and focusing/superbeaming of light, concepts that have been analytically and experimentally verified during Phase I. Phoebus's Phase I results confirmed that its structures will allow for 2500x improvement in polarization extinction ratios - the key performance metric for polarimetric detectors ? compared with currently available polarimetric detectors. Phase I results also confirmed that the relevant structures can be fabricated using routine materials and fabrication techniques in widespread use throughout the semiconductor device industry. In Phase II, Phoebus will focus on improving several performance metrics of its polarizing filter arrays, such as wavelength selectivity and transmissivity, as well as optimizing fabrication processes necessary to produce high aspect ratio light-channeling dielectric apertures.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Center Independent Research & Development Program
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Risks associated with possible medical events during space missions are challenging to identify and manage. Resources must be applied judiciously and risk must not be ignored. NASA's researchers need the capability to identify the risks that arise from the potential medical events, gather all of the published evidence that is available, analyze the probability and severity of the risks, plan to mitigate the risks, investigate the interdependencies between risks and mitigation strategies, track and control the information, and support informed decisions about risks and risk mitigation strategies. S&K Aerospace (SKA) proposes an innovative Web-based system to support the continuous management of medical risk for future space missions. We propose to provide users with the ability to create and maintain a repository of medical risk information, including information about the probability of the risks and the severity of the outcomes. Users will be able to associate outside data with the risk information to support the decisions made regarding the risks. Users will also be able to plan mitigation strategies for the risks, to plan risk mitigation strategies across multiple missions, and to balance the interactions between risk mitigation strategies on a single mission. A continuous risk management system requires that the risks be re-evaluated as contributing factors change, as additional information is learned about the probabilities and consequences of the risks, and simply as time passes.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Development of a static vapor feed electrolyzer utilizing an advanced bipolar plate that produces sub-saturated H2 and O2 is proposed. This novel bipolar design can greatly simplify electrolyzer systems, as it eliminates the need for water/gas phase separation, which is particularly challenging in a zero gravity environment. Maintaining water in the vapor phase greatly reduces membrane swelling which should increase durability. Finally, by keeping water in the vapor phase the MEA is not exposed to ion and other contaminants that are carried by a liquid water stream, further increasing durability and simplifying the system by reducing the need for ultra-pure water. The primary goal of this Phase I program is to demonstrate a high-pressure (1000 psi) static vapor feed electrolyzer and demonstrate that the system can operate without purge of the water feed stream for up to 100 hours.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Modern aircraft (and next generation spacecraft) increasingly rely on composite components due to their excellent specific strength and stiffness, as well as improvements in costs and manufacturing quality. However, life management for composites is in its infancy compared to life management for metal structures. Limitations in the ability of standard nondestructive evaluation (NDE) methods to observe manufacturing quality and in-service damage evolution of composite structures may prevent designers from realizing their full potential. Current NDE practices are incapable of overcoming these limitations. Thus, a new framework and methodology is needed for high resolution imaging and tracking of manufacturing quality and damage evolution. The goal of this program is to enable assessment of the matrix, fiber, and bonding conditions for composites using a combination of detailed physics-based models, high resolution imaging, and controlled loading sources to isolate the composite characteristic of interest. Micromechanical models allow quantitative determination of composite constituent properties. This program focuses on magnetic field sensing (i.e., eddy-current) methods that can be combined with structural analysis to enhance the diagnostic capabilities of these NDE methods. JENTEK and MR&D are well-positioned to deliver this methodology in the form of commercial software and NDE equipment. We will also work with a major aircraft OEM to maintain our focus on practical solutions to high priority needs.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
We propose a 1.5um fiber-optic pulsed coherent lidar as a highly effective sensor sub-system for airborne wake-vortex hazard detection. The proposed design is based on a recently developed platform at Fibertek, for fiber-optic pulsed coherent lidar capable of 6km range, and operating at high pulse rate to give high-resolution spatial map and circulation strength, characteristic of typical wake-vortex signatures. The proposed system uses all COTS 1.5um fiber-optic component technology and COTS high-speed digital electronics, to provide a cost-effective system, that is amenable to rapid transition for field testing and adoption.
Miniaturized, Multi-Analyte Sensor Array for the Automated Monitoring of Major Atmospheric Constituents in Spacecraft Environment Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
The objective of the Phase II SBIR project is to develop a prototype sensor system to detect gaseous analytes in support of the spacecraft environmental monitoring and control system. InnoSense LLC (ISL) has utilized its Chemical Fingerprint?' sensor array fabrication technology in Phase I to establish the feasibility of a miniature device with multi-analyte detection capability. In particular, we have detected oxygen, carbon dioxide and humidity as potential target analytes. The oxygen sensor performed over 3-45% concentrations under a variable pressure of 8-14.7 psia. The Phase I working model could generated discernible signal with 0.1% O2 concentration. Upon fine-tuning the indicators in Phase II, the system performance will be tested with a prototype hardware that will also be developed in Phase II. ISL has received technology endorsement letter from a prime contractor in the NASA application area. ISL has also secured Phase III follow-on funding commitment from a commercialization partner. For assuring success of this project, ISL has assembled a technical team with a cumulative 100 person-years of experience in developing commercially viable sensor systems.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Despite the obvious advantages of millimeter wave technology, a major barrier to expanded use is high assembly costs due to: need for specialized equipments; need for precision impacts on yields; design technologies for manufacturability; and experienced personnel with demonstrated track records. The challenges of this R&D project are to expand and fully develop the Phase 1 technologies for: Methods to use common manufacturing equipment to achieve the high accuracy die placement required for millimeter wave frequencies (+/- 5 micron accuracy) Automation methods and processes to achieving speed and precision for production of low cost modules Modeling to arrive at cost effective trade-offs for achieving customer specifications with minimum capital investment and labor cost As part of the research, NxGen will conduct a demonstration effort utilizing two existing JPL module designs facilitating the collection statistical data both in terms of yields as well as baseline data for cost estimating.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Visualization of turbulence and shock phenomena by schlieren imaging has led to important discoveries in aerodynamics, and there has been much interest in applying schlieren methods for aircraft in flight. The goal of this project is to develop the next generation of Schlieren for Aircraft in Flight (SAF) systems.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Future NASA missions including the Cornell Caltech Atacama Telescope (CCAT) and Global Atmospheric Composition Mission (GACM), require 1 to 4 meter aperture, submillimeter-wavelength, primary reflector (mirror) segments. Astigmatic surface errors in a composite primary reflector and inconsistent radius of curvature in composite reflector segments limit application of composites to instruments. This project proposes to improve upon state-of-the-art passive reflector surface accuracy by characterizing the behavior and properties of actuated, graphite composite reflector laminates and panels that are suitable for space and earth science instruments. Surface error in composite primary reflectors and inconsistent radius of curvature in composite reflector segments currently limit application of composites to submillimeter wavelength primary mirrors. The goal is to minimize surface error including ROC error.