Spacecraft formation flying is an enabling technology and attractive alternative to single-spacecraft systems. In addition to being reliable and upgradable, spacecraft formations will provide a means of performing a variety of tasks and missions that cannot be performed by a single satellite. Associated with spacecraft formations are a number of new and challenging problems in the area of spacecraft dynamics and control. Active control systems are required to maintain relative configurations to the accuracies demanded by tasks such as high resolution Earth and deep space imaging. In formation missions involving micro-satellites, fuel efficiency is of paramount importance. This study presents a number of control laws well suited to micro-satellite scale formation missions. The control laws are derived using control techniques such as linear quadratic regulator design, feedback linearization and disturbance accommodation to bring fuel requirements into a range feasible for micro-satellite missions. The CanX-4/5 mission, developed by the Space Flight Laboratory at the University of Toronto Institute for Aerospace Studies, is of particular interest. A control law that accommodates propulsion and attitude subsystem limitations associated with the CanX-4/5 system is presented, along with an extensive body of simulation data to aid in the mission design process.