This paper presents the design of an attitude controller for a magnetically actuated nanosatellite. The goal of this attitude control system is to be able to dump excess kinetic rotational energy as well as to point to a rotating frame with an accuracy of five degrees on each axis. From the options considered, a locally asymptotically stable PD type controller is chosen as the best solution to the local attitude control pointing problem. This design choice is verified via simulation which includes actuator constraints, environmental disturbance torques due to drag, solar radiation, residual dipoles and gravity, and satellite models from the cubesat Delfi-n3Xt.
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