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Software for Application of HHT Technologies to Time Series Analysis Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:27:16.000ZThe proposed innovation is a robust and user-friendly software environment where NASA researchers can customize the latest HHT technologies for the LISA (and LIGO) application. The proposed technology will include 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 disturbance caused by the passage of a gravitational wave is expected to be very small and will be measured with laser interferometry. The Hilbert-HuangTransform (HHT)and related analysis technologies developed since the original concept has been used successfully in other applications to extract non-linear and transient signal comonents of very small magnitude with respect to the measured signal. 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 data analysis of the gravitational wave signals in the laser interferometry measurements (for both LIGO and LISA data), but also in other applications within and outside NASA's mission.
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Novel Versatile Intelligent Drug Delivery Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:23:14.000ZThis SBIR project will demonstrate and develop a novel micro-pump capable of controlled and selective chemical transport. Phase I will create, characterize, and model a robust and readily fabricated low-power miniaturized pump achieving "forceless" dissolved ion transport compatible with microgravity conditions. The compact technology will be extremely versatile, low-cost, stable, easily tailorable, and readily scaleable to higher fluxes via structure duplication and application in parallel. The device will be physically stable, chemically inert, and pH insensitive while its small dimensions result in lower power consumption and reduced mass. The result will be a more versatile and general pump capable of moving a variety of drugs. Phase I will explore the pump performance, stability, and design optimization using selected ionic compounds as model transport subjects by running designed experiments exploring pump operations as a function of key pump structural and operation variables. This data will determine the controlling variables, their effects on the system performance, and will be utilized with first-principles system physics analysis to develop a pump operation model. This model will allow rapid technology configuration exploration, operation performance refinement, and will provide critical insights into preferred, better optimized, structures to be evaluated during Phase II.
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Stable, Extreme Temperature, High Radiation, Compact. Low Power Clock Oscillator for Space, Geothermal, Down-Hole & other High Reliability Applications Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:30:08.000ZEfficient and stable clock signal generation requirements at extreme temperatures (-180C to +450C)and radiation (>250 Krad TID) are not met with the current solutions.Chronos technology proposes to design and fabricate RTXO as a new, comprehensive and scalable solution that simultaneously addresses the attributes of a reliable clock source in extreme environments. RTXO offers very small form-factor 5X7mm surface mount device utilizing high-Q Quartz material and CMOS/SOI for the extreme cold temperatures of Mars surface up to +110C. For extreme high temperature (to +450C) it uses Silicon Carbide (SiC-4H) semiconductor technology, high quality Gallium Orthophisphate (GaPO4) piezo-electric resonator material in a non-adhesive configured innovative assembly. All the different elements and processes used in the RTXO technology have been investigated in phase I to comply with the intended performance. This includes the individual elements, packaging, interconnecting method and manufacturing processes. RTXO offers standard signal interface, wide operating voltage range, conventional microelectronic packaging, and industry standard and reliable metal to metal as well as glass to metal sealing processes. RTXO delivers its exceptional performance over a wide (application specific) frequency range to 100 MHz from a single supply voltage and requires very low power.
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Vibration-Free Cooling Cycle Pump for Space Vehicles and Habitats Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:26:51.000ZMainstream 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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Robust Optimal Fragmentation and Dispersion of Near-Earth Objects Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:31:30.000Z<p> During the past 2 decades, various concepts for mitigating the impact threats from NEOs have been proposed, but many of these concepts were impractical and not technically credible. In particular, all non-nuclear techniques require mission lead times larger than 10 years. However, for the most probable impact threat with a warning time less than 10 years, the use of high-energy nuclear explosives in space becomes inevitable for proper fragmentation and dispersion of an NEO in a collision course with Earth. However, the existing nuclear subsurface penetrator technology limits the impact velocity to less than 300m/s because higher impact velocities destroy prematurely the detonation electronic equipment. Thus, an innovative space system architecture utilizing high-energy nuclear explosives must be developed for a worst-case intercept mission resulting in relative closing velocities as high as 5-30km/s. An advanced system concept is proposed for nuclear subsurface explosion missions. The concept blends a hypervelocity kinetic-energy impactor with nuclear subsurface explosion, and exploits a 2-body space vehicle consisting of a fore body and an aft body. These 2 spacecraft bodies may be connected by a deployable boom. The fore body provides proper kinetic impact crater conditions for an aft body carrying nuclear explosives to make a deeper penetration into an asteroid body. For such a complex mission architecture design study, non-traditional, multidisciplinary research efforts in the areas of hypervelocity impact dynamics, nuclear explosion modeling, high-temperature thermal shielding, shock-resistant electronic systems, and advanced space system technologies are required. Expanding upon the current research activities, the Iowa State Asteroid Deflection Research Center will develop an innovative, advanced space system architecture that provides the planetary defense capabilities needed to enable a future real space mission more efficient, affordable, and reliable.</p>
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Sanitary Sewer Spills - Strategic KPI
sharefulton.fultoncountyga.gov | Last Updated 2023-01-30T16:55:22.000ZThis measure tracks the number of sanitary sewer overflows reported by Fulton County. This measure currently applies only to the sanitary sewer system operated by Fulton County and does not include the City of Atlanta sewer system. A sanitary sewer overflow is a condition in which untreated sewage is released into the environment. Most overflows in the Fulton County system in recent years have been caused by blockages from debris or grease with roots often being a contributing or primary factor. Other causes have included physical failure of the sewer line and mechanical failure of pumps.
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Compact, Lightweight, Efficient Cooling Pump for Space Suit Life Support Systems Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:21:32.000ZWith the increasing demands placed on extravehicular activity (EVA) for the International Space Station assembly and maintenance, along with planned lunar and Martian missions, the need for increased human productivity and capability becomes ever more critical. This is most readily achieved by reduction in space suit weight and volume, and increased hardware reliability, durability, and operating lifetime. Considerable progress has been made with each successive generation of space suit design; from the Apollo A7L suit, to the current Shuttle Extravehicular Mobile Unit (EMU) suit, and the developmental I-Suit and Mark III suits. However, one area of space suit design which has continued to lag is the fluid pump used to drive the water cooling loop of the Primary Life Support System (PLSS). Conventional electric motor-driven fluid pumps are heavy, bulky, inefficient, and prone to wear. A new pump type is needed. Lynntech proposes to further reduce the size, weight and power consumption of its long-life, low-power, compact, lightweight, efficient electrochemically-driven pumps, which will allow their use in the next generation space suit.
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Additive Manufacturing Technology Development Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:39:10.000Z<p>The 3D Printing In Zero-G (3D Print) technology demonstration project is a proof-of-concept test designed to assess the properties of melt deposition modeling additive manufacturing in the microgravity environment experienced on the International Space Station (ISS). The lessons learned from this technology demonstration will be used for the next generation of melt deposition modeling in the permanent NanoRacks Additive Manufacturing Facility (AMF) as well as for any future additive manufacturing technology NASA plans to use, such as metals or electronics in-space manufacturing, on both the ISS and Deep Space Missions. This demonstration is the first step towards realizing a &ldquo;machine shop&rdquo; in space, a critical enabling component of any Deep Space Mission.</p><p>The 3D Print payload consists of a 3D printer (a two-axis extruder mobility system, a single-axis print tray mobility system, the extruder and accompanying feedstock cartridge, the print tray, Environmental Control Unit (ECU, a prototype for the permanent AMF), an electronics box, and all of the necessary cables and bolts to attach the device to the ISS Microgravity Science Glovebox&nbsp;(MSG) cold plate, MSG laptop computer, and MSG power supply) and all identified spare parts. The 3D Print payload will operate within the MSG. The payload uses extrusion-based additive manufacturing technology to fabricate objects. Additive manufacturing is the process of creating three dimensional objects from a Computer Aided Design (CAD) model where material is deposited layer by layer. The 3D Print payload will extrude a bead of thermo-polymer material from a larger diameter feedstock material. When one layer is complete, the next layer is printed on top and bonded to the lower layer while still molten. This creates an adhesive bond as opposed to a solid material extrusion.</p><p>Performance goals were defined realizing the 3D Print is a technology demonstration. The following is a list of minimum success criteria:<br />1. Successful integration and safe operation in the MSG on the ISS<br />2. Demonstration of extrusion based additive manufacturing using polymeric material<br />3. Successful extrusion and traversing<br />4. Printing of one part while in ISS microgravity<br />5. Mitigation of functional risks for future facilities<br />6. Comparison of ISS printed parts with those printed on Earth (dimensional and strength testing).</p>
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Solid-Solid Vacuum Regolith Heat-Exchanger for Oxygen Production Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:17:45.000ZThis SBIR Phase-1 project will demonstrate the feasibility of using a novel coaxial counterflow solid-solid heat exchanger to recover heat energy from spent regolith at 1050<SUP>o</SUP>C to pre-heat inlet regolith to 750<SUP>o</SUP>C, either continuously, or in 20kg batches. In granular solids the area of contacts between 'touching' grains is quite small. Thus, solid-solid conduction often plays only a minor role in heat transfer through granular solids (i.e., 'effective' conduction), and when an interstitial gas is present, heat transfer occurs primarily via conduction through the gas. If the granular solid is also flowing, then solids convection becomes a significant factor in overall heat transfer and effective 'conduction'. Under vacuum conditions, and at temperatures above 700<SUP>o</SUP>C, radiation will dominate most heat transfer processes; however, solids convection can also play a very significant secondary role. Utilizing judicious placement of radiation baffles, and a novel counterflow configuration, the approach proposed in this SBIR can accomplish the desired heat transfer between spent and fresh regolith with only one moving mechanical part, by making effective use of both radiative heat transfer and solids convection. Discrete-element simulations of regolith flow will be utilized to refine the concept. Utilization of an existing ~1.4 cubic meter partial-vacuum facility at the University of Florida will facilitate construction of feasibility demonstration prototypes during Phase-1 and/or Phase-2. The Phase-1 project will demonstrate the effectiveness of combining solids convection with radiative heat transfer to rapidly transfer heat from 1050C spent material to heat fresh regolith to 750C under vacuum conditions.
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Nano Dust Analyzer Project
data.nasa.gov | Last Updated 2020-01-29T04:54:41.000Z<p> We propose to develop a new highly sensitive instrument to confirm the existence of the so-called nano-dust particles, characterize their impact parameters, and measure their chemical composition. Simultaneous theoretical studies will be used to derive the expected&nbsp; mass and velocity ranges of these putative particles to formulate science and measurement requirements for the future deployment of&nbsp; the proposed Nano-Dust Analyzer (NDA)&nbsp;</p> <p> Early dust instruments onboard Pioneer 8 and 9 and Helios spacecraft detected a flow of submicron sized dust particles coming from the direction of the Sun. These particles originate in the inner solar system from mutual collisions among meteoroids and move on&nbsp; hyperbolic orbits that leave the Solar System under the prevailing radiation pressure force. Later dust instruments with higher&nbsp; sensitivity had to avoid looking toward the Sun because of interference from the solar wind and UV radiation and thus contributed&nbsp; little to the characterization of the dust stream. The one exception is the Ulysses dust detector that observed escaping dust particles&nbsp; high above the solar poles, which confirm the suspicion that charged nanometer sized dust grains are carried to high heliographic&nbsp; latitudes by electromagnetic interactions with the Interplanetary Magnetic Field (IMF). Recently, the STEREO WAVES instruments&nbsp; recorded a large number of intense electric field signals, which were interpreted as impacts from nanometer sized particles striking the&nbsp; spacecraft with velocities of about the solar wind speed. This high flux and strong spatial and/or temporal variations of nanometer&nbsp; sized dust grains at low latitude appears to be uncorrelated with the solar wind properties. This is a mystery as it would require that&nbsp; the total collisional meteoroid debris inside 1 AU is cast in nanometer sized fragments. The observed fluxes of inner-source pickup ions&nbsp; also point to the existence of a much enhanced dust population in the nanometer size range.&nbsp;</p> <p> This new heliospherical phenomenon of nano-dust streams may have consequences throughout the planetary system, but as of yet no dust instrument exists that could be used to shed light on their properties. &nbsp;We propose to develop a dust analyzer capable to detect and&nbsp; analyze these mysterious dust particles coming from the solar direction and to embark upon complementary theoretical studies to&nbsp; understand their characteristics. The instrument is based on the Cassini Dust Analyzer (CDA) that has analyzed the composition of&nbsp; nanometer sized dust particles emanating from the Jovian and Saturnian systems but could not be pointed towards the Sun. By&nbsp; applying technologies implemented in solar wind instruments and coronagraphs a highly sensitive dust analyzer will be developed and&nbsp; tested in the laboratory. The dust analyzer shall be able to characterize impact properties (impact charge and energy distribution of&nbsp; ions from which mass and speed of the impacting grains may be derived) and chemical composition of individual nanometer sized&nbsp; particles while exposed to solar wind and UV radiation. The measurements will enable us to identify the source of the dust by&nbsp; comparing their elemental composition with that of larger micrometeoroid particles of cometary and asteroid origin and will reveal&nbsp; interaction of nano-dust with the interplanetary medium by investigating the relation of the dust flux with solar wind and IMF&nbsp; properties.&nbsp;</p> <p> Complementary theoretically studies will be performed to understand the characteristics of nano-dust particles at 1 AU to answer the&nbsp; following questions:&nbsp; - What is the speed range at which nanometer sized particles impact