- API data.nasa.gov | Last Updated 2018-07-19T18:16:03.000Z
As the amount of textual information grows explosively in various kinds of business systems, it becomes more and more desirable to analyze both structured data records and unstructured text data simultaneously. Although online analytical processing (OLAP) techniques have been proven very useful for analyzing and mining structured data, they face challenges in handling text data. On the other hand, probabilistic topic models are among the most effective approaches to latent topic analysis and mining on text data. In this paper, we study a new data model called topic cube to combine OLAP with probabilistic topic modeling and enable OLAP on the dimension of text data in a multidimensional text database. Topic cube extends the traditional data cube to cope with a topic hierarchy and stores probabilistic content measures of text documents learned through a probabilistic topic model. To materialize topic cubes efficiently, we propose two heuristic aggregations to speed up the iterative Expectation-Maximization (EM) algorithm for estimating topic models by leveraging the models learned on component data cells to choose a good starting point for iteration. Experimental results show that these heuristic aggregations are much faster than the baseline method of computing each topic cube from scratch. We also discuss some potential uses of topic cube and show sample experimental results.
- API data.nasa.gov | Last Updated 2018-07-19T10:53:04.000Z
<p>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.</p> <p>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.</p><p> </p><p>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.</p><p> </p><p>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.</p><p> </p><p>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.</p>
- API data.nasa.gov | Last Updated 2018-07-19T04:20:35.000Z
NASA's International Halley Watch (IHW) has created a Comet Halley Archive. The collection of data spans the full wavelength range as submitted by scientists to the IHW. The observations belong to one of the following Disciplines: Amateur, Astrometry, Infrared Studies, Large-Scale Phenomena, Meteor Studies, Near-Nucleus Studies, Photometry and Polarimetry, Radio Studies, and Spectroscopy and Spectrophotometry. The data collected by these nine disciplines were augmented by Spacecraft measurements. The data were submitted to IHW, but the evaluation and selection for the Archive has been the primary responsibility of the Discipline Specialist Teams for each network in cooperation with the Lead Center. The Photometry and Polarimetry Network collected 132 observations for the Stokes Parameters Subnetwork. These data cover the date range from 1985 December 30 through 1986 April 16.
A Micro-Cylindrical Ion Trap (Âµ-CIT) Micro-Mass Spectrometer Instrument System (Âµ-MSIS) for NASA Planetary Explorationdata.nasa.gov | Last Updated 2018-08-02T15:25:43.000Z
<p>The goal of this follow-on early stage innovation activity is to advance the development of new, extremely small, low power, and low cost “micro” mass spectrometer instrument systems (μMSIS) through the application of MEMS design and fabrication, and microsystem component integration and packaging, toward deployment on distributed planetary payload platforms. This work attains significant early impact due to our recently-awarded ASTID project (van Amerom et al.), to develop the core chip-based micro cylindrical ion trap (μ-CIT) mass analyzer at GSFC. In particular, this work will enable early, coincident design and development of the critical microsystem integration and packaging that is required to achieve the final level of miniaturization offered by this core μ-CIT technology. We therefore propose to develop a MEMS μMSIS packaging concept that is modular and flexible to further integration of a micro gas chromatograph, micro vacuum chamber and microelectronic components, into a complete instrument system.</p> <p>This activity will significantly increase the fidelity of the miniaturized component packaging of the μ-CIT mass spectrometer assembly. Our design approach emphasizes the smallest feasible footprint, combining MEMS MS component integration, and the use of ultra-high vacuum (UHV) materials. This activity will significantly increase the fidelity of the miniaturized component packaging of the μ-CIT mass spectrometer assembly. Our design approach emphasizes the smallest feasible footprint, combining MEMS MS component integration, and the use of ultra-high vacuum (UHV) materials and techniques for fabrication of the final package. Final package systems designs and component parts have been fabricated using micro fabrication capabilities and MEMS processing. Assembly and integration of the package takes advantage of existing packaging expertise, materials, and tooling. The component packaging system will be evaluated for form, function, outgassing, and vibration here at GSFC.</p>
- API data.nasa.gov | Last Updated 2018-07-19T07:30:17.000Z
Mars planetary surface access is one of NASA's biggest technical challenges involving advanced entry, descent, and landing (EDL) technologies and methods. This NASA Innovative Advanced Concept (NIAC) project intends to solve one of the top challenges for landing large payloads and humans on Mars by using advanced atmospheric In-Situ Resource Utilization (ISRU) methods that have never been tried or studied before. The proposed Mars Molniya Orbit Atmospheric Resource Mining concept mission architecture will make Mars travel routine and affordable for cargo and crew, therefore enabling the expansion of human civilization to Mars.
- API data.nasa.gov | Last Updated 2018-07-19T12:33:59.000Z
M4 Engineering proposes to implement physics-based, multidisciplinary analysis and optimization objects that will be integrated into a Python, open-source framework and used in a wide variety of simulations. The integrated objects will perform discipline-specific analysis across multiple flight regimes at varying levels of fidelity. The process will also deliver system-level, multi-objective optimization. Addressing physics-based, system-level objectives that span more than one discipline will have profound effects on improving decision-making abilities during the conceptual design phase when evaluating advanced technological concepts. In the proposed effort, existing capabilities will be leveraged to create a high fidelity, physics based, multidisciplinary analysis and optimization (MDAO) system. This proposed work will compliment M4 Engineering's expertise in developing modeling and simulation toolsets that solve relevant subsonic, supersonic, and hypersonic demonstration applications.
- API data.nasa.gov | Last Updated 2018-07-19T07:52:35.000Z
<p>This multi-year IRAD proposal, in a strategic partnership with University of Maryland (UMD) and Bowie State University (BSU), creates a collaborative virtual reality (VR) tool for concept design and assembly in VR from a database of pre-defined "parts", enabling engineers and scientists to work in a shared VR environment, as part of a concept design or pre-phase A proposal process. The proposal will define a domain agnostic database for specifying a set of physical, off-the-shelf, plug and play parts with reduced detail shape/CAD files and migrate existing domain-specific GSFC database(s) to this format, to quickly realize a collaborative, model-based VR engineering environment for prototyping, assembly mockup, and visualizations for pre-phase A work.</p><p>This proposal will create a collaborative VR environment for early stage design and assembly of hardware projects from pre-defined, off-the-shelf parts as part of a concept design or pre-phase A proposal process. The project will:</p><ul><li>Create a database of metadata about parts</li><li>Create a collaborative VR environment where users<ul><li>Visualize a complete project design composed of off-the-shelf parts at real-world scales (or user-selected scales) and at any orientation</li><li>View and select off the shelf parts, and drag-and-drop them into a design</li><li>Layout and orient parts including alignment and mounting holes</li><li>Use virtual tools to determine tool paths and whether the model can be assembled in the real world without expensive manufacturing, physical prototypes or 3D printing</li></ul></li><li>Export projects as documents with assembly information and pictures at a level appropriate for pre-phase A proposals</li></ul><p>The VR environment can also help the downstream process with communication and planning between scientists and engineers in the Mission Design Lab (MDL) or for educational outreach. The first year will culminate in an alpha app for mechanical engineers for concept design and assembly mockups.</p>
- API data.nasa.gov | Last Updated 2018-07-20T07:19:34.000Z
We will design and formally verify a VLIW processor that is radiation-hardened, and where the VLIW instructions consist of predicated RISC instructions from the PowerPC 750 Instruction Set Architecture (ISA). The PowerPC 750 ISA is used in the radiation-hardened RAD750 flight-control computer that is utilized in many NASA space missions, including Deep Impact, the Mars Reconnaissance Orbiter, the Mars Rovers, and is planned to be used in the Crew Exploration Vehicle (CEV). The VLIW processor will have reconfigurable functional units and specialized instructions that will be optimized for Software Defined Radio applications. The radiation-hardening will be done at the microarchitectural level with a mechanism that will allow the detection and correction of all timing errors---caused not only by radiation, but also by variations in the voltage, frequency, manufacturing process, and aging of the chip. The binary-code compatibility of the resulting VLIW processors with the PowerPC 750 ISA will allow them to seamlessly execute legacy binary code from previous space missions. We have made critical contributions to the fields of formal verification of complex pipelined microprocessors, and Boolean Satisfiability (SAT), and have developed highly efficient Electronic Design Automation (EDA) tools that we will use.
- API data.nasa.gov | Last Updated 2018-07-19T04:23:25.000Z
NASA's International Halley Watch (IHW) has created a Comet Halley Archive. The collection of data spans the full wavelength range as submitted by scientists to the IHW. The observations belong to one of the following Disciplines: Amateur, Astrometry, Infrared Studies, Large-Scale Phenomena, Meteor Studies, Near-Nucleus Studies, Photometry and Polarimetry, Radio Studies, and Spectroscopy and Spectrophotometry. The data collected by these nine disciplines were augmented by Spacecraft measurements. The data were submitted to IHW, but the evaluation and selection for the Archive has been the primary responsibility of the Discipline Specialist Teams for each network in cooperation with the Lead Center. The Infrared Imaging subnetwork contains 66 images of Halley and 29 images of calibration stars (HD18881, HD3029, HD10560, HD10696, HD12965, BS134, BS923, BS1856, Beta Pegn Rho Ori) for dates spanning 1985 March 11 through 1986 May 23.
Low Cost Automated Manufacture of High Efficiency THINS ZTJ PV Blanket Technology (P-NASA12-007), Phase Idata.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.