HEAT GENERATING TRANSFER ORBIT SHIELD

A system and apparatus are provided for preventing heat loss in a spacecraft during the upper stage launch phase and transfer orbit. A thermal control panel can be provided that can be positioned adjacent to exposed areas of radiator panels on the spacecraft in a collapsed configuration. The outer surface of the panel can have a high absorptivity, and the inner surface can have a high emissivity. During upper stage launch phase and transfer orbit, the panel can tend to emit heat toward the radiator panels on an inboard side of the spacecraft, thus reducing heat loss from the radiator panels to reduce the need for onboard electronic heaters and thereby preserve battery power for other onboard systems.