http://swrc.ontoware.org/ontology#InProceedings
Minimization of unsteady thermal deformation by using laminated structures under the stress restrictions
en
thermal deformation
laminated beam
thermal stress
composite material
temperature distribution
interlaminar stress
thermal expansion
modulus of elasticity
thermal conductivity
spacecraft construction material
aerospace environment
朝野 裕樹
仮屋崎 剛大
室園 昌彦
Asano Yuki
Kariyazaki Takehiro
Murozono Masahiko
宇宙航空研究開発機構
Japan Aerospace Exploration Agency (JAXA)
JAXA Special Publication: Proceedings of Lectures and Workshop International: Recent Advances in Multidisciplinary Technology and Modeling
JAXA-SP-07-008E
142-149
2008-02-29
Laminated beam structures are designed in order to minimize thermal deformations in steady or unsteady temperature field. To suppress thermal deformation, composite materials that has negative longitudinal coefficient of thermal expansion are layered with material that has positive Coefficient of Thermal Expansion (CTE). Assuming steady temperature fields, beam with no strain at central axis and no curvature can be designed. In unsteady temperature fields, it is possible to suppress thermal deformations while lowering thermal stresses. If it takes a long time until the temperature distribution get steady, the beam should be designed with considering unsteady temperature distributions because the beam that was designed with considering only steady temperature distribution could have large thermal deformations in its transitional period. For suppressing thermal deformations, interlaminar shearing stress, and interlaminar moment, materials with large Young's Modulus, CTE, and thermal conductivity are effective to use for low temperature side, oppositely, materials with small Young's Modulus, CTE, and thermal conductivity are effective to use for high temperature side.
1349-113X
AA11984031
資料番号: AA0063824014
レポート番号: JAXA-SP-07-008E