发明名称 SANDWICH PANEL FOR SATELLITE STRUCTURE
摘要 PROBLEM TO BE SOLVED: To efficiently emit heat generated in a high heating apparatus by adhering an artificial isotropic laminate, as a heat sink, which has thermal conductivity higher than a specific value and has high thermal conductivity carbon fiber as reinforcements, to a sandwich panel that has complex material having carbon fiber as reinforcements as a surface skin material. SOLUTION: This sandwich panel comprises an aluminum honey-comb core 2, an adhesive 3 of a surface skin material 7 with the aluminum honey-comb core 2, the surface skin material 7 made of complex material having carbon fiber as reinforcements, a heat sink 9 that is mounted with a high heating apparatus 5 and is formed from an artificial isotropic laminate having carbon fiber as reinforcements, and an adhesive 10 of the heat sink 9 and the surface skin material 7. By using high thermal conductivity carbon fiber whose thermal conductivity is higher than 600 W/m.k, isotropically laminated laminate is substantially equal to that of aluminum alloy. Since coefficient of thermal expansion of this heat sink 9 is close to coefficient of thermal expansion of the surface skin material 7, stress by the thermal expansion hardly occurs and construction adhesive with high strength can be used.
申请公布号 JP2000085697(A) 申请公布日期 2000.03.28
申请号 JP19980264448 申请日期 1998.09.18
申请人 MITSUBISHI ELECTRIC CORP 发明人 SHIGEMASA HIROYUKI
分类号 B64G1/50;B64G1/66;(IPC1-7):B64G1/50 主分类号 B64G1/50
代理机构 代理人
主权项
地址