▎ 摘　　要

NOVELTY - The device has a heat conduction film (2) whose end is mounted on insulating material (1). The insulating material is pasted on a backside of a fixed solar wing (6) of a spacecraft that needs heat dissipation. Another end of the heat conduction film is mounted on a side of the spacecraft main body that is not directly irradiated by the sun. A secondary surface mirror (3) is mounted on the heat-conducting film. A heat dissipation device is provided with a load-bearing portion (4). A cooling device is provided with a multi-layer insulation assembly (5). The multi-layer heat insulation assembly is installed between the heat conduction film and the spacecraft main body, where thickness of the polyimide film is 20 microns. The secondary surface mirror is formed as F46 silver plating secondary surface mirror. The graphene film is formed as multi-layer composite graphene film. A bearing piece is formed as a carbon nanometre copper foil. USE - Radiating device for fixing solar wing of spacecraft. ADVANTAGE - The radiating device cools down the fixed solar wing through the flexible graphene film under the premise of not changing the structure design of the body, which can satisfy the temperature index requirements after the number of fixed solar wing cloth pieces is reduced, and allow the solar wing to output voltage satisfy specific requirements. DESCRIPTION OF DRAWING(S) - The drawing shows a schematic view of a radiating device. (Drawing includes non-English language text). 1Insulating material 2Heat conduction film 3Secondary surface mirror 4Load-bearing portion 5Multi-layer insulation assembly 6Fixed solar wing