| 摘要 |
A heat dissipating apparatus 10 for use in a spacecraft comprises first and second radiator panels 11a, 11b and one or more heat pipes 14, 15 coupled to the first and second radiator panels 11a, 11b that contain a working fluid. The working fluid may comprise a selected one of: toluene, methanol, butane, water, heptane or pentane. The one or more heat pipes 14, 15 may comprise first and second heat pipe networks 13 including first and second sets of heat pipes arranged as a matrix and which are in thermal communication. The first and second radiator panels 11a, 11b may each comprise inner and outer faceskins 17, 18 wherein the one or more heat pipes 14, 15 are embedded between the inner and outer panel faceskins 17, 18 and a honeycomb core 24 disposed between the inner and outer panel faceskins 17, 18 surround the heat pipes 14, 15. The honeycomb core 24 thermally and structurally bridges the heat pipe networks 13 to the opposing faceskin 17, 18. |
