| 摘要 |
A thermal control system controls spacecraft's internal temperature without significantly increasing the mass of the spacecraft, thereby lowering launch expenses and allowing for the utilization of additional space and/or instrumentation on the spacecraft. The thermal control system incorporates at least one thermal control flap including a first magnetic field generator located thereon. A second magnetic field generator is located beneath the thermal control flap. A current regulation device is coupled to at least one of the first magnetic field generator and the second magnetic field generator. The first magnetic field generator generates a magnetic field that opposes a magnetic field generated by the second magnetic field generator causing the control flap to open and change the thermal reflective characteristics of the spacecraft.
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