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  • Aircraft Design, Testing and Performance  (2)
  • Acute Disease  (1)
  • 2000-2004  (1)
  • 1995-1999  (2)
  • 1
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    Decreased muscarinic receptor binding in the arcuate nucleus in sudden infant death syndrome (1995)
    American Association for the Advancement of Science (AAAS)
    Details
    Publication Date: 1995-09-08
    Description: Muscarinic cholinergic activity in the human arcuate nucleus at the ventral medullary surface is postulated to be involved in cardiopulmonary control. A significant decrease in [3H]quinuclidinyl benzilate binding to muscarinic receptors in the arcuate nucleus is now shown to occur in sudden infant death syndrome (SIDS) infants, compared to infants dying acutely of known causes. In infants with chronic oxygenation abnormalities, binding is low in other nuclei, as well as in the arcuate nucleus. The binding deficit in the arcuate nucleus of SIDS infants might contribute to a failure of responses to cardiopulmonary challenges during sleep.〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Kinney, H C -- Filiano, J J -- Sleeper, L A -- Mandell, F -- Valdes-Dapena, M -- White, W F -- P30-HD18655/HD/NICHD NIH HHS/ -- R01-HD20991/HD/NICHD NIH HHS/ -- New York, N.Y. -- Science. 1995 Sep 8;269(5229):1446-50.〈br /〉〈span class="detail_caption"〉Author address: 〈/span〉Department of Pathology, Children's Hospital, Boston, MA, USA.〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/7660131" target="_blank"〉PubMed〈/a〉
    Keywords: Acute Disease ; Anoxia/metabolism ; Arcuate Nucleus of Hypothalamus/*metabolism ; Autoradiography ; Brain Stem/metabolism ; Chronic Disease ; Humans ; Infant ; Infant, Newborn ; Quinuclidinyl Benzilate/*metabolism ; Receptors, Muscarinic/*metabolism ; Sudden Infant Death/*etiology
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
    Published by American Association for the Advancement of Science (AAAS)
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    PAPER CURRENT
  • 2
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    An Integrated Vehicle Modeling Environment (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes an Integrated Vehicle Modeling Environment for estimating aircraft geometric, inertial, and aerodynamic characteristics, and for interfacing with a high fidelity, workstation based flight simulation architecture. The goals in developing this environment are to aid in the design of next generation intelligent fight control technologies, conduct research in advanced vehicle interface concepts for autonomous and semi-autonomous applications, and provide a value-added capability to the conceptual design and aircraft synthesis process. Results are presented for three aircraft by comparing estimates generated by the Integrated Vehicle Modeling Environment with known characteristics of each vehicle under consideration. The three aircraft are a modified F-15 with moveable canards attached to the airframe, a mid-sized, twin-engine commercial transport concept, and a small, single-engine, uninhabited aerial vehicle. Estimated physical properties and dynamic characteristics are correlated with those known for each aircraft over a large portion of the flight envelope of interest. These results represent the completion of a critical step toward meeting the stated goals for developing this modeling environment.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 99-4106 , AIAA Atmospheric Flight Mechanics Conference; Aug 09, 1999 - Aug 11, 1999; Portland, OR; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aero-Mechanical Design Methodology for Subsonic Civil Transport High-Lift Systems (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: In today's highly competitive and economically driven commercial aviation market, the trend is to make aircraft systems simpler and to shorten their design cycle which reduces recurring, non-recurring and operating costs. One such system is the high-lift system. A methodology has been developed which merges aerodynamic data with kinematic analysis of the trailing-edge flap mechanism with minimum mechanism definition required. This methodology provides quick and accurate aerodynamic performance prediction for a given flap deployment mechanism early on in the high-lift system preliminary design stage. Sample analysis results for four different deployment mechanisms are presented as well as descriptions of the aerodynamic and mechanism data required for evaluation. Extensions to interactive design capabilities are also discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment; 7-1 - 7-12; RTO-MP-35
    Format: text
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    NASA TECHNICAL REPORTS
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