A deployable radiator configured to be mounted on a body structure of a satellite, the deployable radiator comprising: - a first radiator panel; a first deployment mechanism to connect the first radiator panel to the body structure of the satellite and to deploy the first radiator panel from a state where the first radiator panel is opposed to a north or south face of the body structure of the satellite; - a second radiator panel stacked with the first radiator panel to be opposed to the north or south face of the body structure of the satellite and sandwiched between the body structure of the satellite and the first radiator panel, in the state where the first radiator panel is opposed to the body structure of the satellite; and - a second deployment mechanism to connect the second radiator panel to the body structure of the satellite and to deploy the second radiator panel in a direction opposite to a deployment direction of the first radiator panel from a state where the second radiator panel is opposed to the north or south face of the body structure of the satellite, - wherein in the first radiator panel, an outer layer surface that is the opposite surface of a first opposed surface opposed to the north or south face of the body structure of the satellite is a thermally insulated surface and the first opposed surface is a heat removal surface, and - wherein in the second radiator panel, a second opposed surface opposed to the north or south face of the body structure of the satellite and the opposite surface of the second opposed surface are heat removal surfaces, wherein the thermal insulation is a multi-layer insulation, which is attached to the outermost layer surface of the radiator panels on the side opposite to the north or south side of the body structure of the satellite, with respect to the radiator panels stacked up at a time of the stowed state, so that an amount of heat removal becomes substantially zero. - a first radiator panel; a first deployment mechanism to connect the first radiator panel to the body structure of the satellite and to deploy the first radiator panel from a state where the first radiator panel is opposed to a north or south face of the body structure of the satellite; - a second radiator panel stacked with the first radiator panel to be opposed to the north or south face of the body structure of the satellite and sandwiched between the body structure of the satellite and the first radiator panel, in the state where the first radiator panel is opposed to the body structure of the satellite; and - a second deployment mechanism to connect the second radiator panel to the body structure of the satellite and to deploy the second radiator panel in a direction opposite to a deployment direction of the first radiator panel from a state where the second radiator panel is opposed to the north or south face of the body structure of the satellite, - wherein in the first radiator panel, an outer layer surface that is the opposite surface of a first opposed surface opposed to the north or south face of the body structure of the satellite is a thermally insulated surface and the first opposed surface is a heat removal surface, and - wherein in the second radiator panel, a second opposed surface opposed to the north or south face of the body structure of the satellite and the opposite surface of the second opposed surface are heat removal surfaces, wherein the thermal insulation is a multi-layer insulation, which is attached to the outermost layer surface of the radiator panels on the side opposite to the north or south side of the body structure of the satellite, with respect to the radiator panels stacked up at a time of the stowed state, so that an amount of heat removal becomes substantially zero.