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infrastructure - The Infrastructure category contains data, from across the Open Data Network™ of publishers, related to infrastructure, streets, 311 data, parking, and construction.

API
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 2015-07-20T05:30:08.000Z
Efficient and stable clock signal generation requirements at extreme temperatures (-180C to +450C)and radiation (&gt;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.
API
Solid-Solid Vacuum Regolith Heat-Exchanger for Oxygen Production Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:17:45.000Z
This 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 1050oC to pre-heat inlet regolith to 750oC, 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 700oC, 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.
API
Compact, Lightweight, Efficient Cooling Pump for Space Suit Life Support Systems Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:21:32.000Z
With 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.
API
An all MMIC Replacement for Gunn Diode Oscillators Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:36:37.000Z
We propose to replace the Gunn Diode Oscillators (GDOs) in NASA?s millimeter- and submillimeter-wave sensing instruments. Our new solution will rely on modern and reliable microwave integrated circuit technology. Specifically our systems will use highly developed microwave oscillators to achieve a low noise and highly stable reference signal in the 10 ? 30 GHz band. Compact amplifiers based on commercial MMIC chips will then increase the signal strength. Finally, our innovative integrated varactor multiplier circuits will be used to increase the frequency to the 60 ? 150 GHz frequency band with high efficiency and minimal added phase noise. With this technology we expect to achieve phase noise and stability comparable to the best Gunn diode oscillators and fundamentally improved output power and frequency agility. The millimeter-wave integrated circuit process and diode technologies are the critical innovative technologies that are required for this research. Through this SBIR project these innovative technologies will be extended to achieve highly compact multipliers for the 60 ? 150 GHz band. These new multipliers will be integrated with highly developed microwave components to achieve a robust and cost efficient replacement for the GDOs presently used in NASA?s Earth Science program.
API
Software for Application of HHT Technologies to Time Series Analysis Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:27:16.000Z
The 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.
API
Novel Versatile Intelligent Drug Delivery Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:23:14.000Z
This 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.
API
Additive Manufacturing Technology Development Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:39:10.000Z
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.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.Performance goals were defined realizing the 3D Print is a technology demonstration. The following is a list of minimum success criteria: 1. Successful integration and safe operation in the MSG on the ISS 2. Demonstration of extrusion based additive manufacturing using polymeric material 3. Successful extrusion and traversing 4. Printing of one part while in ISS microgravity 5. Mitigation of functional risks for future facilities 6. Comparison of ISS printed parts with those printed on Earth (dimensional and strength testing).
API
TRMM Microwave Imager (TMI) Gridded Oceanic Rainfall Product (TRMM Product 3A11) V7
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T04:52:56.000Z
The Tropical Rainfall Measuring Mission (TRMM) is a joint U.S.-Japan satellite mission to monitor tropical and subtropical precipitation and to estimate its associated latent heating. TRMM was successfully launched on November 27, at 4:27 PM (EST) from the Tanegashima Space Center in Japan. The TRMM Microwave Imager (TMI) is a nine-channel passive microwave radiometer, which builds on the heritage of the Special Sensor Microwave/Imager (SSM/I) instrument flown aboard the Defense Meteorological Satellite Program (DMSP) platforms. Microwave radiation is emitted by the Earth's surface and by water droplets within clouds. However, when layers of large ice particles are present in upper cloud regions - a condition highly correlated with heavy rainfall - microwave radiation tends to scatter at frequencies above 19 GHz. The TMI detects radiation at five frequencies chosen to discriminate among these processes, thus revealing the likelihood of rainfall. The key to accurate retrieval of rainfall rates by this method is the deduction of cloud precipitation consistent with the radiation measurement at each frequency. The TMI frequencies are 10.65, 19.35, 37 and 85.5 GHz (dual polarization), and 21 GHz (vertical polarization only). The TMI Gridded Oceanic Rainfall Product, also known as TMI Emission, consists of 5 degree by 5 degree monthly oceanic rainfall maps using TMI Level 1 data as input. Statistics of the monthly rainfall, including number of samples, standard deviation, goodness-of-fit (of the brightness temperature histogram to the lognormal rainfall distribution function) and rainfall probability are also included in the output for each grid box. Spatial coverage is between 40 degrees North and 40 degrees South owing to the 35 degree inclination of the TRMM satellite. TMI brightness temperature histograms at 1 degree intervals are generated based on the 19, 21 and 19-21 GHz combination channels obtained from the Level 1B (calibrated brightness temperature) TMI product. Monthly rainfall indices over the ocean are derived by statistically matching monthly histograms of brightness temperatures with model calculated rainfall Probability Distribution Functions (PDF) using the 19-21 GHz combination data. Retrieved monthly rainfall data must pass a quality test based on the quality of the PDF fit. The data are stored in the Hierarchical Data Format (HDF), which includes both core and product specific metadata applicable to the TMI measurements. A file contains 12 arrays of rainfall data and supporting information each of dimension 72 x 16, with a file size of about 40 KB (uncompressed). The HDF-EOS "grid" structure is used to accommodate the actual geophysical data arrays. There is 1 file of TMI 3A11 data produced per month.
API
Vibration-Free Cooling Cycle Pump for Space Vehicles and Habitats Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:26:51.000Z
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.
API
Robust Optimal Fragmentation and Dispersion of Near-Earth Objects Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:31:30.000Z
 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.