Patent ID: 6511021
Filing Date: 2003-01-28
Classification: B64G

Abstract:
A thermal control system for a spacecraft comprising:a thin film outer layer provided around a main body of the spacecraft, wherein the outer layer includes at least one thermal control flap moveable between an open position and a closed position, and wherein the thermal control flap comprises a portion of the thin film outer layer; a first magnetic field generator located on the thermal control flap of the outer layer, wherein the first magnetic field generator generates a first magnetic field; a second magnetic field generator located on the main body of the spacecraft beneath the thermal control flap, wherein the second magnetic field generator generates a second magnetic field; control circuitry coupled to at least one of the first magnetic field generator and the second magnetic field generator, wherein the control circuitry controls at least one of the first magnetic field and the second magnetic field in response to a temperature condition of the main body of the spacecraft such that the first magnetic field opposes the second magnetic field to open the thermal control flap.