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Application Of Formal Optimization Techniques In Thermal Structural Design Of A Heat Pipe Cooled Panel For A Hypersonic Vehicle
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781725985414 Total Pages :32 pages Book Rating :4.9/5 (854 download)
Book Synopsis Application of Formal Optimization Techniques in Thermal/Structural Design of a Heat-Pipe-Cooled Panel for a Hypersonic Vehicle by : National Aeronautics and Space Administration (NASA)
Download or read book Application of Formal Optimization Techniques in Thermal/Structural Design of a Heat-Pipe-Cooled Panel for a Hypersonic Vehicle written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-22 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Nonlinear mathematical programming methods are used to design a radiantly cooled and heat-pipe-cooled panel for a Mach 6.7 transport. The cooled portion of the panel is a hybrid heat-pipe/actively cooled design which uses heat pipes to transport the absorbed heat to the ends of the panel where it is removed by active cooling. The panels are optimized for minimum mass and to satisfy a set of heat-pipe, structural, geometric, and minimum-gage constraints. Two panel concepts are investigated: cylindrical heat pipes embedded in a honeycomb core and an integrated design which uses a web-core heat-pipe sandwich concept. The latter was lighter and resulted in a design which was less than 10 percent heavier than an all actively cooled concept. The heat-pipe concept, however, is redundant and can sustain a single-point failure, whereas the actively cooled concept cannot. An additional study was performed to determine the optimum number of coolant manifolds per panel for a minimum-mass design. Camarda, Charles J. and Riley, Michael F. Langley Research Center NASA-TM-89131, L-16134, NAS 1.15:89131 RTOP 505-62-81-05...
Book Synopsis Application of Formal Optimization Techniques in Thermal/structural Design of a Heat-pipe-cooled Panel for a Hypersonic Vehicle by :
Download or read book Application of Formal Optimization Techniques in Thermal/structural Design of a Heat-pipe-cooled Panel for a Hypersonic Vehicle written by and published by . This book was released on 1987 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 308 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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Download or read book Aeronautical Engineering written by and published by . This book was released on 1991 with total page 568 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Download or read book NASA SP. written by and published by . This book was released on 1990 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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Book Synopsis Actively Cooled Plate Fin Sandwich Structural Panels for Hypersonic Aircraft by : L. M. Smith
Download or read book Actively Cooled Plate Fin Sandwich Structural Panels for Hypersonic Aircraft written by L. M. Smith and published by . This book was released on 1979 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt: An unshielded actively cooled structural panel was designed for application to a hypersonic aircraft. The design was an all aluminum stringer-stiffened platefin sandwich structure which used a 60/40 mixture of ethylene glycol/water as the coolant. Eight small test specimens of the basic platefin sandwich concept and three fatigue specimens from critical areas of the panel design was fabricated and tested (at room temperature). A test panel representative of all features of the panel design was fabricated and tested to determine the combined thermal/mechanical performance and structural integrity of the system. The overall findings are that; (1) the stringer-stiffened platefin sandwich actively cooling concept results in a low mass design that is an excellent contender for application to a hypersonic vehicle, and (2) the fabrication processes are state of the art but new or modified facilities are required to support full scale panel fabrication.
Book Synopsis Thermal Design for Areas of Interference Heating on Actively Cooled Hypersonic Aircraft by : R. L. Herring
Download or read book Thermal Design for Areas of Interference Heating on Actively Cooled Hypersonic Aircraft written by R. L. Herring and published by . This book was released on 1978 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt: Numerous actively cooled panel design alternatives for application in regions on high speed aircraft that are subject to interference heating effects were studied. Candidate design concepts were evaluated using mass, producibility, reliability and inspectability/maintainability as figures of merit. Three design approaches were identified as superior within certain regimes of the matrix of design heating conditions considered. Only minor modifications to basic actively cooled panel design are required to withstand minor interference heating effects. Designs incorporating internally finned coolant tubes to augment heat transfer are recommended for moderate design heating conditions. At severe heating conditions, an insulated panel concept is required.
Book Synopsis Review of Convectively Cooled Structures for Hypersonic Flight by :
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Book Synopsis Design and Fabrication of a Stringer Stiffened Discrete Tube Actively Cooled Panel for a Hypersonic Aircraft by : Frank M. Anthony
Download or read book Design and Fabrication of a Stringer Stiffened Discrete Tube Actively Cooled Panel for a Hypersonic Aircraft written by Frank M. Anthony and published by . This book was released on 1981 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 0.61 x 1.22 m (2 x 4 ft) test panel was fabricated and delivered to the Langley Research Center for assessment of the thermal and structural features of the optimized panel design. The panel concept incorporated an aluminum alloy surface panel actively cooled by a network of discrete, parallel, redundant, counterflow passage interconnected with appropriate manifolding, and assembled by adhesive bonding. The cooled skin was stiffened with a mechanically fastened conventional substructure of stringers and frames. A 40 water/60 glycol solution was the coolant. Low pressure leak testing, radiography, holography and infrared scanning were applied at various stages of fabrication to assess integrity and uniformity. By nondestructively inspecting selected specimens which were subsequently tested to destruction, it was possible to refine inspection standards as applied to this cooled panel design.
Book Synopsis Closed Form Equations for the Preliminary Design of a Heat-Pipe-Cooled Leading Edge by :
Download or read book Closed Form Equations for the Preliminary Design of a Heat-Pipe-Cooled Leading Edge written by and published by . This book was released on 1998 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
