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Application of Formal Optimization Techniques in Thermal/structural Design of a Heat-pipe-cooled Panel for a Hypersonic Vehicle

Application of Formal Optimization Techniques in Thermal/structural Design of a Heat-pipe-cooled Panel for a Hypersonic Vehicle PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

Book Description


Application of Formal Optimization Techniques in Thermal/structural Design of a Heat-pipe-cooled Panel for a Hypersonic Vehicle

Application of Formal Optimization Techniques in Thermal/structural Design of a Heat-pipe-cooled Panel for a Hypersonic Vehicle PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

Book Description


Application of Formal Optimization Techniques in Thermal/Structural Design of a Heat-Pipe-Cooled Panel for a Hypersonic Vehicle

Application of Formal Optimization Techniques in Thermal/Structural Design of a Heat-Pipe-Cooled Panel for a Hypersonic Vehicle PDF Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725985414
Category :
Languages : en
Pages : 32

Book Description
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...

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