Effect of Aerodynamic Heating on Deformation of Composite Cylindrical Panels in a Gas Flow

Victor Birman; Charles W. Bert; Isaac Elishakoff

doi:10.1016/0263-8223(90)90034-C

Effect of Aerodynamic Heating on Deformation of Composite Cylindrical Panels in a Gas Flow

Victor Birman
, Charles W. Bert
, Isaac Elishakoff

Mechanical and Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

Abstract

In this paper, motions of composite cylindrical panels in a gas flow are considered. It is shown that the main factor contributing to large static deformations is a nonuniform aerodynamic heating, while aerodynamic pressure is of secondary importance, at high Mach number. It was found that the main factor resulting in the increase of deformations is the nonuniform distribution of temperature along the curved edges. Deformations decrease rapidly in shallower panels. Nonuniformly heated panels become unstable at the values of axial compressive load, which are much smaller than the static buckling value calculated in the absence of heating. The condition of panel flutter of nonuniformly heated composite panels in a gas flow is also formulated. © 1990.

Original language	American English
Journal	Composite Structures
DOIs	https://doi.org/10.1016/0263-8223(90)90034-C
State	Published - Jan 1 1990

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Aerospace Engineering
Mechanical Engineering

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https://doi.org/10.1016/0263-8223(90)90034-C

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title = "Effect of Aerodynamic Heating on Deformation of Composite Cylindrical Panels in a Gas Flow",

abstract = " In this paper, motions of composite cylindrical panels in a gas flow are considered. It is shown that the main factor contributing to large static deformations is a nonuniform aerodynamic heating, while aerodynamic pressure is of secondary importance, at high Mach number. It was found that the main factor resulting in the increase of deformations is the nonuniform distribution of temperature along the curved edges. Deformations decrease rapidly in shallower panels. Nonuniformly heated panels become unstable at the values of axial compressive load, which are much smaller than the static buckling value calculated in the absence of heating. The condition of panel flutter of nonuniformly heated composite panels in a gas flow is also formulated. {\textcopyright} 1990.",

author = "Victor Birman and Bert, \{Charles W.\} and Isaac Elishakoff",

year = "1990",

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doi = "10.1016/0263-8223(90)90034-C",

language = "American English",

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AU - Birman, Victor

AU - Bert, Charles W.

AU - Elishakoff, Isaac

PY - 1990/1/1

Y1 - 1990/1/1

N2 - In this paper, motions of composite cylindrical panels in a gas flow are considered. It is shown that the main factor contributing to large static deformations is a nonuniform aerodynamic heating, while aerodynamic pressure is of secondary importance, at high Mach number. It was found that the main factor resulting in the increase of deformations is the nonuniform distribution of temperature along the curved edges. Deformations decrease rapidly in shallower panels. Nonuniformly heated panels become unstable at the values of axial compressive load, which are much smaller than the static buckling value calculated in the absence of heating. The condition of panel flutter of nonuniformly heated composite panels in a gas flow is also formulated. © 1990.

AB - In this paper, motions of composite cylindrical panels in a gas flow are considered. It is shown that the main factor contributing to large static deformations is a nonuniform aerodynamic heating, while aerodynamic pressure is of secondary importance, at high Mach number. It was found that the main factor resulting in the increase of deformations is the nonuniform distribution of temperature along the curved edges. Deformations decrease rapidly in shallower panels. Nonuniformly heated panels become unstable at the values of axial compressive load, which are much smaller than the static buckling value calculated in the absence of heating. The condition of panel flutter of nonuniformly heated composite panels in a gas flow is also formulated. © 1990.

UR - https://scholarsmine.mst.edu/mec_aereng_facwork/1478

UR - https://doi.org/10.1016/0263-8223(90)90034-C

U2 - 10.1016/0263-8223(90)90034-C

DO - 10.1016/0263-8223(90)90034-C

M3 - Article

JO - Composite Structures

JF - Composite Structures

ER -

Effect of Aerodynamic Heating on Deformation of Composite Cylindrical Panels in a Gas Flow

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