• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.170-176
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• 2004

In this study, the relay driver circuit which controls the spacecraft configuration change are implemented and validated. First of all, the specification of the relay driver circuit is defined, and then its circuit meeting the specification defined is designed. In order to verify the design of the relay driver circuit, its circuit was simulated, and then it's confirmed that the relay pulse current and voltage level defined in the specification are obtained, and the results obtained through the functional test of the relay driver circuit are compared and well matched with the simulation results. Also the worst case analysis for confirming the stable operation of the relay driver circuit under the tolerance of each component is performed.