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  • 1
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    Galanin neurons in the medial preoptic area govern parental behaviour (2014)
    Nature Publishing Group (NPG)
    Details
    Publication Date: 2014-05-16
    Description: Mice display robust, stereotyped behaviours towards pups: virgin males typically attack pups, whereas virgin females and sexually experienced males and females display parental care. Here we show that virgin males genetically impaired in vomeronasal sensing do not attack pups and are parental. Furthermore, we uncover a subset of galanin-expressing neurons in the medial preoptic area (MPOA) that are specifically activated during male and female parenting, and a different subpopulation that is activated during mating. Genetic ablation of MPOA galanin neurons results in marked impairment of parental responses in males and females and affects male mating. Optogenetic activation of these neurons in virgin males suppresses inter-male and pup-directed aggression and induces pup grooming. Thus, MPOA galanin neurons emerge as an essential regulatory node of male and female parenting behaviour and other social responses. These results provide an entry point to a circuit-level dissection of parental behaviour and its modulation by social experience.〈br /〉〈br /〉〈a href="https://www.ncbi.nlm.nih.gov/pmc/articles/PMC4105201/" target="_blank"〉〈img src="https://static.pubmed.gov/portal/portal3rc.fcgi/4089621/img/3977009" border="0"〉〈/a〉   〈a href="https://www.ncbi.nlm.nih.gov/pmc/articles/PMC4105201/" target="_blank"〉This paper as free author manuscript - peer-reviewed and accepted for publication〈/a〉〈br /〉〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Wu, Zheng -- Autry, Anita E -- Bergan, Joseph F -- Watabe-Uchida, Mitsuko -- Dulac, Catherine G -- F32 DC010089/DC/NIDCD NIH HHS/ -- R01 DC003903/DC/NIDCD NIH HHS/ -- R01 DC009019/DC/NIDCD NIH HHS/ -- R01 DC013087/DC/NIDCD NIH HHS/ -- Howard Hughes Medical Institute/ -- England -- Nature. 2014 May 15;509(7500):325-30. doi: 10.1038/nature13307.〈br /〉〈span class="detail_caption"〉Author address: 〈/span〉Howard Hughes Medical Institute, Department of Molecular and Cellular Biology, Center for Brain Science, Harvard University, Cambridge, Massachusetts 02138, USA. ; Department of Molecular and Cellular Biology, Center for Brain Science, Harvard University, Cambridge, Massachusetts 02138, USA.〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/24828191" target="_blank"〉PubMed〈/a〉
    Keywords: Aggression/physiology ; Animals ; Copulation ; Female ; Galanin/deficiency/genetics/*metabolism ; Grooming/physiology ; Male ; Maternal Behavior/*physiology ; Mice ; Neurons/*metabolism ; Optogenetics ; Paternal Behavior/*physiology ; Pheromones/analysis ; Preoptic Area/*cytology/metabolism ; TRPC Cation Channels/deficiency/genetics ; Vomeronasal Organ/physiology
    Print ISSN: 0028-0836
    Electronic ISSN: 1476-4687
    Topics: Biology , Chemistry and Pharmacology , Medicine , Natural Sciences in General , Physics
    Published by Nature Publishing Group (NPG)
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  • 2
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    Nonlinear Analysis and Post-Test Correlation for a Curved PRSEUS Panel (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept, developed by The Boeing Company, has been extensively studied as part of the National Aeronautics and Space Administration's (NASA s) Environmentally Responsible Aviation (ERA) Program. The PRSEUS concept provides a light-weight alternative to aluminum or traditional composite design concepts and is applicable to traditional-shaped fuselage barrels and wings, as well as advanced configurations such as a hybrid wing body or truss braced wings. Therefore, NASA, the Federal Aviation Administration (FAA) and The Boeing Company partnered in an effort to assess the performance and damage arrestments capabilities of a PRSEUS concept panel using a full-scale curved panel in the FAA Full-Scale Aircraft Structural Test Evaluation and Research (FASTER) facility. Testing was conducted in the FASTER facility by subjecting the panel to axial tension loads applied to the ends of the panel, internal pressure, and combined axial tension and internal pressure loadings. Additionally, reactive hoop loads were applied to the skin and frames of the panel along its edges. The panel successfully supported the required design loads in the pristine condition and with a severed stiffener. The panel also demonstrated that the PRSEUS concept could arrest the progression of damage including crack arrestment and crack turning. This paper presents the nonlinear post-test analysis and correlation with test results for the curved PRSEUS panel. It is shown that nonlinear analysis can accurately calculate the behavior of a PRSEUS panel under tension, pressure and combined loading conditions.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2013-1736 , NF1676L-15294 , 54th AIAA/ASME/ASCE/AHS/ASC, Structures, Structural Dynamics, and Materials Conference; Apr 08, 2013 - Apr 11, 2013; Boston, MA; United States
    Format: application/pdf
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  • 3
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    Full-Scale Test and Analysis Results of a PRSEUS Fuselage Panel to Assess Damage Containment Features (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Integrally stitched composite technology is an area that shows promise in enhancing the structural integrity of aircraft and aerospace structures. The most recent generation of this technology is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept. The goal of the PRSEUS concept relevant to this test is to provide damage containment capability for composite structures while reducing overall structural weight. The National Aeronautics and Space Administration (NASA), the Federal Aviation Administration (FAA), and The Boeing Company have partnered in an effort to assess the damage containment features of a full-scale curved PRSEUS panel using the FAA Full-Scale Aircraft Structural Test Evaluation and Research (FASTER) facility. A single PRSEUS test panel was subjected to axial tension, internal pressure, and combined axial tension and internal pressure loads. The test results showed excellent performance of the PRSEUS concept. No growth of Barely Visible Impact Damage (BVID) was observed after ultimate loads were applied. With a two-bay notch severing the central stringer, damage was contained within the two-bay region well above the required limit load conditions. Catastrophic failure was well above the ultimate load level. Information describing the test panel and procedure has been previously presented, so this paper focuses on the experimental procedure, test results, nondestructive inspection results, and preliminary test and analysis correlation.
    Keywords: Aircraft Design, Testing and Performance
    Type: NF1676L-14599 , 2012 Aircraft Airworthiness and Sustainment Conference; Apr 02, 2012 - Apr 05, 2012; Baltimore, MD; United States
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  • 4
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    Assessment of Damage Containment Features of a Full-Scale PRSEUS Fuselage Panel Through Test and Teardown (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An area that shows promise in enhancing structural integrity of aircraft and aerospace structures is the integrally stitched composite technology. The most recent generation of this technology is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept developed by Boeing Research and Technology and the National Aeronautics and Space Administration. A joint test program on the assessment of damage containment capabilities of the PRSEUS concept for curved fuselage structures was conducted recently at the Federal Aviation Administration William J. Hughes Technical Center. The panel was subjected to axial tension, internal pressure, and combined axial tension and internal pressure load conditions up to fracture, with a through-the-thickness, two-bay notch severing the central stiffener. For the purpose of future progressive failure analysis development and verification, extensive post failure nondestructive and teardown inspections were conducted. Detailed inspections were performed directly ahead of the notch tip where stable damage progression was observed. These examinations showed: 1) extensive delaminations developed ahead of the notch tip, 2) the extent and location of damage, 3) the typical damage mechanisms observed in composites, and 4) the role of stitching and warp-knitting in the failure mechanisms. The objective of this paper is to provide a summary of results from these posttest inspections.
    Keywords: Aircraft Design, Testing and Performance
    Type: NF1676L-14533 , 2012 American Society for Composites 27th Technical Conference; Oct 01, 2012 - Oct 03, 2012; Arlington, TX; United States|15th US-Japan Conference on Composite Materials; Oct 01, 2012 - Oct 03, 2012; Arlington, TX; United States
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  • 5
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    Full-Scale Test and Analysis of a PRSEUS Fuselage Panel to Assess Damage-Containment Features (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Stitched composite technology has the potential to substantially decrease structural weight through enhanced damage containment capabilities. The most recent generation of stitched composite technology, the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept, has been shown to successfully arrest damage at the sub-component level through tension testing of a three stringer panel with damage in the form of a two-bay notch. In a joint effort undertaken by the National Aeronautics and Space Administration (NASA), the Federal Aviation Administration (FAA), and the Boeing Company, further studies are being conducted to characterize the damage containment features of the PRSEUS concept. A full-scale residual strength test will be performed on a fuselage panel to determine if the load capacity will meet strength, deformation, and damage tolerance requirements. A curved panel was designed, fabricated, and prepared for residual strength testing. A pre-test Finite Element Model (FEM) was developed using design allowables from previous test programs to predict test panel deformation characteristics and margins of safety. Three phases of testing with increasing damage severity include: (1) as manufactured; (2) barely visible impact damage (BVID) and visible impact damage (VID); and (3) discrete source damage (DSD) where the panel will be loaded to catastrophic failure. This paper presents the background information, test plan, and experimental procedure. This paper is the first of several future articles reporting the test preparations, results, and analysis conducted in the test program.
    Keywords: Aircraft Design, Testing and Performance
    Type: NF1676L-11521 , 2011 Aircraft Airworthiness and Sustainment (AAS) Conference; Apr 18, 2011 - Apr 21, 2011; San Diego, CA; United States
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