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finance - The Finance category contains data, from across the Open Data Network™ of publishers, related to finance, government spending, salaries, budgets, revenues, and taxes.

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Propellant Flow Actuated Piezoelectric Rocket Engine Igniter, Phase II
data.nasa.gov | Last Updated 2018-07-19T09:03:13.000Z
Under a Phase 1 effort, IES successfully developed and demonstrated a spark ignition concept where propellant flow drives a very simple fluid mechanical oscillator to excite a piezoelectric crystal. The Phase 1 effort exceeded expectations, with the device demonstrating reliable ignition of both hydrogen and propane fuels, and achieving in excess of 1 million impact cycles (40,000 start cycles) during fatigue testing without measureable degradation. Several spin-off concepts were also identified that provide additional options for improving spark ignition system design. For Phase 2, IES proposes an accelerated, 18 month effort to refine design concepts and analysis tools, and then develop specific ignition system designs for two customer applications, with the intention of having these ignition systems demonstrated in engine ground testing during Phase 2 and ready to start flight qualification immediately following the Phase 2 effort. Both customers (United Launch Alliance and Pratt Whitney Rocketdyne) have expressed interest and commitment in participating in the Phase 2 activity, making engines and facilities available for development testing, and integrating any resulting viable products into their flight engines. The ULA application is a new gaseous bipropellant H2/O2 attitude control thruster, for which the piezoelectric igniter is ideal as a simple, direct ignition source. The PWR application is for an evolved RL-10 study currently underway, for which the piezoelectric system might be scaled up or used as a pilot igniter for a torch, or make use of another spin-off concept that was identified during the Phase 1 effort. The timing of this Phase 2 effort coincides perfectly with near term needs of both these customers, as well as for other small engine applications in work to replace catalytic hydrazine engines with bi-propellant engines that will require a simple and reliable ignition source.
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EPOXI 103P/HARTLEY2 ENCOUNTER - MRI CALIBRATED IMAGES V1.0
data.nasa.gov | Last Updated 2018-07-19T02:46:12.000Z
This dataset contains calibrated images of comet 103/P Hartley 2 acquired by the Medium Resolution Visible CCD (MRI) from 05 September through 26 November 2010 during the Hartley 2 encounter phase of the EPOXI mission. Clear-filter and CN images of the comet were acquired throughout this phase; OH, C2, and dust continuum images were only acquired for several days spanning closest approach.
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Lightweight and Compace Multifunction Computer-Controlled Strength and Aerobic Training Device, Phase I
data.nasa.gov | Last Updated 2018-07-19T09:03:34.000Z
TDA Research proposes to develop a computer-controlled lightweight and compact device for aerobic and resistive training (DART) to counteract muscular atrophy and bone loss and to improve the overall wellness of astronauts operating in microgravity. The DART will be able to provide resistive loads up to 350 lbf and will accurately simulate the load profile of a mass in a 1-g environment. It will also be capable of applying custom load profiles such as eccentric overloading. In aerobic training mode, the DART will simulate the loads of a rowing machine with loads up to 175. The system will computer-controlled and can automatically calibrate to a user's range of motion. The total weight of the device will be less than 20 lbs and have a compact form factor to enable integration into a small crew module. By using a regenerative energy recovery system, the average power consumption of the DART will be less than 100 W during an exercise session. TDA is able to build on previous experience building exercise equipment for NASA and develop the DART in a short timeframe. TDA will prove the feasibility of providing effective aerobic and resistive training with a single device that is lightweight and compact in Phase I. At the end of Phase I a prototype will be delivered to NASA for evaluation. In Phase II we will advance the technology and provide the second generation prototype to NASA for testing on the International Space Station.
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Inflatable Air Beam Standard Interface Connector
data.nasa.gov | Last Updated 2018-07-19T10:53:04.000Z
The project will develop a system of 3D-printed connectors that can be used as a kit of parts to connect inflatable air beams to form a variety of spacecraft interior outfitting components.  Examples of inflatable IVA structures that can be assembled include crew quarters, waste & hygiene compartment, crew medical restraint system, splints, science payload racks, stowage and other equipment racks, science glove box, recreational devices, other portable devices, work surfaces and other workstations, support braces, other secondary structures, etc.  This inflatable technology can enable such hardware to be packaged in much smaller volumes for delivery in logistics flights or potentially to be integrated within inflatable spacecraft, increasing trade space options.  Crew can also reconfigure spacecraft in-flight, using the ability to 3D-print custom connectors to redesign living spaces or create entirely new interior architectures to respond to mission developments or psychosocial needs. The Habitabiltiy Design Center has already prototyped scale models of inflatable crew stations and initial prototypes of a standard interface connector.  These connectors have demonstrated basic capability, but are too large relative to the airbeams for pracitcal use.  We have a notional reduced size connector and will use this concept as a starting point, to fabricate and test under operational inflation pressures.  Pending initial success, we will fabricate various connectors to provide several linear and angled connections.  This will form the basic building block for assembly of a variety of crew stations and support hardware. This research addresses HAT Needs Numbers 12.1.a and 12.1.b and provides steps towards several HAT-specified performance targets:  Bladder Material Selection: The potentially frequent cycles of inflation and deflation experienced by IVA inflatable structures will require bladder material and seal interfaces capable of resisting puncture, tear, flex cracking, or other damage due to folding, handling, or stowage temperatures.  Predictive Modeling of Deployment Dynamics: Inflation or deflation may involve imparted torques and loads that require IVA inflatable structures to be anchored to the spacecraft secondary structure prior to the initiation of inflation or deflation.  Lightweight Structures and Materials Optimization to Realize Structural System Dry Mass Savings (Minimum of 20-25%) and Operational Cost Savings: The inflatable air beam and connector technology offers significant dry mass savings over traditional IVA structural materials.  Structural mass savings for an individual crew quarters is expected to be in excess of 75% over ISS crew quarters. The intended product deliverable of this activity includes three airbeams of at least 12-inch length and no less than one each of the following: 90-degree connector, 45-degree connector, 180-degree connector, 90-degree five-airbeam connector, 60-degree three-airbeam connector.  Additionally, a test report and CAD models for each connector will constitute deliverables of this activity. Upon completion of this initial ICA effort, we will be able to demonstrate use of the airbeams in conjunction with existing Logistics to Living Modified Cargo Transfer Bags (MCTBs) to demonstrate deployable partitions as an initial example case.  This demonistration will be helpful in explaining the potential for continued investment to reduce both mass and habitability risks.  We will continue to pursue research funding for further development and will also pursue options to directly engage exploration programs to generate solutions for their specific mission architectures.
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A Ferroelectric Semiconductor Absorber for Surpassing the Shockley-Queisser Limit, Phase I
data.nasa.gov | Last Updated 2018-07-19T07:45:37.000Z
Physical Sciences Inc. (PSI) proposes to develop new solar cells based on a ferroelectric semiconductor absorber material that can yield a 30% increase in efficiency and a 20% increase in specific power compared with current triple-junction III-V cells. These gains will be realized by exploiting a unique charge separation mechanism in ferroelectrics that enables open-circuit voltages many times the band gap, leading to maximum power conversion efficiencies exceeding the conventional Shockley-Queisser limit (33%). PSI and team members will create photovoltaic cells based on Earth-abundant SnS stabilized in a ferroelectric state by epitaxial strain engineering. By combining above-gap cell voltages with the high absorption coefficient (<1 x 105 cm-1 at 500 nm), low density (5.22 g/cm3), and ideal band gap (1.1 eV) of SnS, a mass-specific power density of 120 kW/kg (mass of absorber material, 1 um absorber thickness) is projected. In addition, a maximum cell efficiency of >45% is anticipated to be achievable. Importantly, these cells will also offer improved radiation resistance due to the reduced carrier diffusion lengths required by the unique ferroelectric charge separation mechanism. During Phase I, PSI, guided by first-principles calculations conducted by the PARADIM Center at Cornell University, will demonstrate room-temperature ferroelectric ordering in SnS through epitaxial strain engineering. During Phase II, PSI and Lawrence Berkeley National Laboratory will demonstrate the potential of the proposed absorber by achieving above-band gap open-circuit voltages in prototype cells. During a Phase III effort, the efficiency of these cells will be increased to a target value of 45% through reduction of intrinsic defects, leading to substantial improvements in cell size, weight, and power output.
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High Temperature Multimode Harvester for Wireless Strain Applications, Phase I
data.nasa.gov | Last Updated 2018-07-19T07:55:56.000Z
Monitoring of structural strain is a well-established method for assessing the fatigue life and operational loads of aerospace vessels, aircraft, bridges, and other load-bearing structures. Information from extensive instrumentation using 100's to 1000's of strain gages can be fed into a condition based maintenance (CBM) algorithm to improve structural health assessments, detect damage, and lower maintenance costs. Current methods for measuring strain are too cumbersome, bulky, and costly to be practical for a large scale dense network of strain sensors. Furthermore, existing piezoelectric-based vibrational energy harvesters are built around general purpose components designed for operation in low-temperature application spaces. To realize pervasive structural health monitoring across a wide range of thermal and vibrational environments, a low cost, minimally intrusive, low maintenance, and reliable technology is needed. Cutting edge microelectromechanical systems (MEMS) sensors for measurements of strain, acceleration, pressure, acoustic emission, and temperature are becoming increasingly available for use in CBM and structural health monitoring (SHM). While these sensors offer a promising future for wireless sensing networks (WSN), implementation for CBM remains cumbersome due to the lack of versatile, cost-effective powering solutions. Wiring external power to sensors is an unattractive solution given the required installation overhead and associated maintenance costs. Battery powered solutions are unreliable and battery maintenance for a dense network of thousands of sensor nodes is not practical. For this STTR effort, Prime Photonics proposes to team with Virginia Tech to develop a multimode vibrational-thermal harvester with effective energy capture and efficient conversion.
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Low Cost Automated Manufacture of High Efficiency THINS ZTJ PV Blanket Technology (P-NASA12-007), Phase I
data.nasa.gov | Last Updated 2018-07-19T09:38:25.000Z
NASA needs lower cost solar arrays with high performance for a variety of missions. While high efficiency, space-qualified solar cells are in themselves costly, > $250/Watt, there is considerable additional cost associated with the parts and labor needed to integrate the Photovoltaic Assembly. The standard approach has evolved with only minor changes, sacrificing cost because of risk aversion. Integration cost can be as much as double the bare cell cost  i.e. >$500/watt. Dramatic cost savings can be realized through manufacturing engineering of more efficient automated assembly processes. If the design of the Photovoltaic Assembly could be modified to be compatible with conventional and automatable electronic assembly and terrestrial solar panel assembly approaches, there could be considerable cost savings. There are many additional benefits with automation which include higher quality and consistency. This can reduce failures, increase production throughput, speed turnaround, and improve overall reliability. Cost and quality improvements can be realized on both thin and rigid arrays, increasing current capabilities, and enabling future high power missions. The benefits of automation are enhanced by the need for high power generation in support of energy intensive space missions. A 300kW array at $500/W would cost $150M just for the solar cell integrated array panels. A $150/W cell integration cost reduction would translate into savings of $45M, before considering the immediate and substantial benefits in consistency, reliability, and schedule. The Phase I effort demonstrates feasibility of a low cost array using an automated and integrated manufacturing approach, performed on an automation friendly solar cell, verified with environmental testing, and is used to predict array cost for a high power mission. Meeting these technical objectives will demonstrate reduced cost and justify a Phase II SBIR program preparing for a flight experiment.
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EIGHT COLOR ASTEROID SURVEY PRIMARY DATA V1.0
data.nasa.gov | Last Updated 2018-07-19T07:02:30.000Z
The eight color asteroid survey provides reflection spectra for minor planets using eight filter passbands. This dataset includes the primary data obtained for 589 minor planets. The mean values for each minor planet included in the survey, the response curves for the filters, and the values determined for standard stars, are included in other related datasets. The wavelength range covered is from .33 to 1.04 micrometers.
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EPOXI EARTH OBS - HRIV CALIBRATED IMAGES V2.0
data.nasa.gov | Last Updated 2018-07-19T03:28:23.000Z
This data set contains calibrated, narrow band filter images (350-950 nm) of Earth acquired by the Deep Impact High Resolution Visible CCD (HRIV) during the EPOCh and Cruise 2 phases of the EPOXI mission. Five sets of observations were acquired on 18-19 March, 28-29 May and 04-05 June 2008 and on 27-28 March and 04-05 October 2009 to characterize Earth as an analog for extrasolar planets. Each observing period lasted approximately 24 hours. HRIV images were acquired once per hour with the filters centered on 350, 750 and 950 nm, whereas the 450-, 550-, 650-, and 850-nm data were taken every 15 minutes. During the observing period in May 2008, the Moon transited across Earth as seen from the spacecraft. On 27 September 2009 during the first attempt of an Earth south polar observation, only seven HRIV frames were acquired before fault protection turned that instrument off; the full sequence was successfully rerun on 04-05 October 2009. Version 2.0 includes the application of a horizontal destriping process and revised electronic crosstalk calibration files.
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The GlideSonde: A Lifting Body Guided Dropsonde, Phase I
data.nasa.gov | Last Updated 2018-07-19T16:15:59.000Z
Dropsondes are one of the primary in-situ measurement tools available to research aircraft and Unmanned Aerial Vehicles (UAVs). Unlike sensors mounted on aircraft, dropsondes allow a vertical profile of the atmosphere to be taken below the aircraft. A guided dropsonde which could glide away from the launch aircraft will allow profiles to be taken away from the aircraft flight path, and would offer aircraft the ability to deploy dropsondes into dangerous environments, such as thunderstorms and volcanic plumes, where few aircraft are able to safely venture. Anasphere, Inc., in cooperation with Vanilla Aircraft, Inc., proposes to develop a guided dropsonde to meet this need. This dropsonde will be designed as a lifting body. It will build upon an existing miniature dropsonde developed by Anasphere, have essentially no moving parts, retain the ability to return wind profiles along with accurate meteorological data, and have sufficient speed to penetrate moderate headwinds. Phase I work will include designing and prototyping the aerodynamic form, integrating essential guidance electronics, and conducting extensive glide tests. Phase II work will include the integration of complete sensor, guidance, and communications payloads, refinement of the aerodynamic form, and extensive live flight tests from high altitude.