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  • Aircraft Design, Testing and Performance  (3)
  • Acute Disease  (1)
  • 2000-2004  (1)
  • 1995-1999  (2)
  • 1960-1964  (1)
  • 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
  • 4
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    Experimental Research on 4-Duct Tandem VTOL Aircraft Configurations (1962)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents a brief summary of several wind-tunnel investigations conducted at the Langley Research Center of the NASA to study the aerodynamic and stability and control characteristics of several VTOL aircraft configurations powered by four tilting ducted propellers arranged in tandem pairs. Specifically the two rear ducts could be mounted close alongside the upper rear portion of the fuselage with small wing panels attached to the outboard side of the ducts or could be mounted outboard on the tips of a small wing located high on the rear portion of the fuselage. The two front ducts were always mounted close inboard on the forward part of the fuselage and could be mounted either in a high or low position on the fuselage. The results of the investigation indicated that aircraft of this type could have acceptable aerodynamic and static longitudinal and lateral stability and control characteristics in both transition and normal cruise flight except for the possible qualification that the lateral force due to sideslip is abnormally high and might cause the aircraft to be too sensitive to side gusts.
    Keywords: Aircraft Design, Testing and Performance
    Type: Annual Forum of the American Helicopter Society; May 03, 1962 - May 05, 1962; Washington, D.C.; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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