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  • 1
    Electronic Resource
    Electronic Resource
    Regulation of lysyl oxidase and cyclooxygenase expression in human lung fibroblasts: interactions among TGF-β, IL-1β, and prostaglandin E (1996)
    New York, N.Y. : Wiley-Blackwell
    Journal of Cellular Biochemistry 62 (1996), S. 411-417 
    Details
    ISSN: 0730-2312
    Keywords: lysyl oxidase ; cyclooxygenase ; transforming growth factor-β ; prostaglandin ; interleukin-1β ; Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Chemistry and Pharmacology , Medicine
    Notes: Prostaglandin E2, transforming growth factor-β and interleukin-1β variably regulate the expression of cyclooxygenase 1, cyclooxygenase 2, and lysyl oxidase in IMR90, human embryo lung fibroblasts. Prostaglandin E2 at 100 nM upregulates cyclooxygenase 1 mRNA by approximately three-fold while it downregulates lysyl oxidase mRNA levels. Notably, prostaglandin E2 suppresses the enhancing effect of TGF-β on basal levels of lysyl oxidase mRNA. These changes in steady state mRNA levels reflect transcriptional level control, at least in part. Corresponding changes are seen in the protein levels of lysyl oxidase, cyclooxygenase 1 and cyclooxygenase 2 and in catalytic activities of these enzymes, including net prostaglandin E2 synthesis. Cyclooxygenase 2 mRNA(t1 2, 30 min) is considerably less stable than that of cyclooxygenase 1 (t1 2, 4h) while lysyl oxidase mRNA is unusually stable (t1 2 〉 14h). Taken together with the differing kinetics with which these genes respond to perturbation by these cytokines, the present results suggest a coordinated, autocrine-like mechanism of regulation of cyclooxygenase 1 and cyclooxygenase 2 and further point to the potential of their metabolic product, prostaglandin E2, to suppress the expression of lysyl oxidase in the inflammatory response to injury. © 1996 Wiley-Liss, Inc.
    Additional Material: 6 Ill.
    Type of Medium: Electronic Resource
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    Paper (German National Licenses)
  • 2
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    Proposal and Development of a High Voltage Variable Frequency Alternating Current Power System for Hybrid Electric Aircraft (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The development of ultra-efficient commercial vehicles and the transition to low-carbon emission propulsion are seen as strategic thrust paths within NASA Aeronautics. A critical enabler to these paths comes in the form of hybrid electric propulsion systems. For megawatt-class systems, the best power system topology for these hybrid electric propulsion systems is debatable. Current proposals within NASA and the Aero community suggest using a combination of alternating current (AC) and direct current (DC) for power generation, transmission, and distribution. This paper proposes an alternative to the current thought model through the use of a primarily high voltage AC power system, supported by the Convergent Aeronautics Solutions (CAS) Project. This system relies heavily on the use of doubly-fed induction machines (DFIMs), which provide high power densities, minimal power conversion, and variable speed operation. The paper presents background on the activity along with the system architecture, development status, and preliminary results.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN46211 , Incorporating Strathclyde Fault Management Technology; Aug 22, 2017; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aqueous, QUick-Charging Battery Integration For Electric Flight Research (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: AQUIFER establishes technical feasibility of an early-stage technology, a high-energy density, aqueous-based, flow battery, resulting in a near-term increase of 1.7 times range over an all-electric battery, while retiring fire and explosion hazards associated with lithium-based chemistries. The Nano-electrofuel (NEF) flow battery will be integrated with a rim-driven motor (RDM) as a multi-functional design to eliminate conductive EMI and weight from long cable runs, and provide liquid cooling from the aqueous fuel. When successful, the technology provides an improved safety energy storage solution for emission-free electric propulsion in commercial aviation.
    Keywords: Electronics and Electrical Engineering
    Type: AFRC-E-DAA-TN60723 , Annual Convergent Aeronautics Solutions (CAS) Showcase; Sep 18, 2018 - Sep 20, 2018; Moffett Field, CA; United States
    Format: application/pdf
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  • 4
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    Control Demonstration of Multiple Doubly-Fed Induction Motors for Hybrid Electric Propulsion (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Convergent Aeronautics Solutions (CAS) High Voltage-Hybrid Electric Propulsion (HVHEP) task was formulated to support the move into future hybrid-electric aircraft. The goal of this project is to develop a new AC power architecture to support the needs of higher efficiency and lower emissions. This proposed architecture will adopt the use of the doubly-fed induction machine (DFIM) for propulsor drive motor application.The Convergent Aeronautics Solutions (CAS) High Voltage-Hybrid Electric Propulsion (HVHEP) task was formulated to support the move into future hybrid-electric aircraft. The goal of this project is to develop a new AC power architecture to support the needs of higher efficiency and lower emissions. This proposed architecture will adopt the use of the doubly-fed induction machine (DFIM) for propulsor drive motor application. DFIMs are attractive for several reasons, including but not limited to the ability to self-start, ability to operate sub- and super-synchronously, and requiring only fractionally rated power converters on a per-unit basis depending on the required range of operation. The focus of this paper is based specifically on the presentation and analysis of a novel strategy which allows for independent operation of each of the aforementioned doubly-fed induction motors. This strategy includes synchronization, soft-start, and closed loop speed control of each motor as a means of controlling output thrust; be it concurrently or differentially. The demonstration of this strategy has recently been proven out on a low power test bed using fractional horsepower machines. Simulation and hardware test results are presented in the paper.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN43482 , AIAA/SAE/ASEE Joint Propulsion Conference; Jul 10, 2017 - Jul 12, 2017; Atlanta, GA; United States
    Format: application/pdf
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  • 5
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    Proposal and Development of a High Voltage Variable Frequency Alternating Current Power System for Hybrid Electric Aircraft (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The development of ultra-efficient commercial vehicles and the transition to low-carbon emission propulsion are seen as thrust paths within NASA Aeronautics. A critical enabler to these paths comes in the form of hybrid-electric propulsion systems. For megawatt-class systems, the best power system topology for these hybrid-electric propulsion systems is debatable. Current proposals within NASA and the Aero community suggest using a combination of AC and DC for power transmission. This paper proposes an alternative to the current thought model through the use of a primarily high voltage AC power generation, transmission, and distribution systems, supported by the Convergent Aeronautics Solutions (CAS) Project. This system relies heavily on the use of dual-fed induction machines, which provide high power densities, minimal power conversion, and variable speed operation. The paper presents background on the project along with the system architecture, development status and preliminary results.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN33090 , AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Jul 25, 2016 - Jul 27, 2016; Salt Lake City, UT; United States
    Format: application/pdf
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  • 6
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    Status of Electrical Actuator Applications (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An ever increasing number of actuation functions historically performed by hydraulics or pneumatics are being accomplished by electric actuation. If 'end to end' systems are considered, electric actuators (EA's) are potentially lighter and more efficient. In general, system redundancies may be more easily implemented and operationally monitored. Typically, electrical components exhibit longer mean times to failure and projected lifetime costs of EA's are potentially much lower than those of other options. EA's have certain characteristics which must be considered in their application. The actual mechanical loadings must be established, for the more easily controlled EA may be operated much closer to its full capabilities. At higher rates of motion, EA's are operating as constant power devices. Therefore, it may be possible to start a movement that can not be stopped. The incorporation of high power electronics into remote locations introduces new concerns of EMI and thermal control. It is the management of these and other characteristics that forms the engineering design challenges. Work is currently in progress on EA's for aircraft and expendable launch vehicles. These applications span from ten to 40+ horsepower. The systematics and status of these actuators will be reported along with current technical trends in this area.
    Keywords: Electronics and Electrical Engineering
    Type: NASA-TM-107319 , NAS 1.15:107319 , E-10416 , Intersociety Energy Conversion Engineering Conference; Aug 11, 1996 - Aug 16, 1996; Washington, DC; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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