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In this study, an automated formation control system for an aircraft formation comprised of one lead and multiple wing aircraft is analyzed. Second- order models of the C-130 aircraft are developed in order to accurately model the flying qualities of large aircraft. This automated formation control system is capable of controlling the C-130 aircraft in maneuvering formation flight, thus reducing the wing's pilot workload. During formation flight, the wing aircraft continuously measures the lead aircraft's relative position with an ideal on-board position sensor. This information, in addition to Proportional Plus Integral feedback control, is used to maintain the aircraft in formation. The control of each wing aircraft is assumed to be independent of other wing aircraft. Other than for nominal formation separation commands, no continuous communication is assumed between the formation aircraft. An analytical analysis of the formation control problem reveals that integral control is needed to achieve zero steady state error in the separation distances (after a formation maneuver is executed). This conclusion is confirmed using computer simulations. An analytical method of selecting the Proportional Plus Integral parameters is developed by identifying the dominant system dynamics and residues of the step response. In an attempt to reduce the fuel consumption of the wing aircraft during formation heading change maneuvers, an alternate control system is designed to conserve the energy of the wing. The resulting automated formation control system effectively maintains the formation of aircraft through a combination of velocity, heading, and altitude changes. These is zero steady state error for all maneuvers and separation distance change responses....Flight control, Automated, Formation, C-130.