The application of concurrent engineering approach to the design of a large flexible space structure is discussed. A full system model using bond graphs incorporating orbital and ballistic dynamics, controls, optics, and vibrational analyses is developed. Design of experiment techniques is used to analyze the entire system and determine the optimum set of design parameters. The objective of the design effort involved the simultaneous design of the control algorithm, structural characteristics, and optical geometry. The system size and mass were limited by current space shuttle capabilities. The satellite was required to track the missile plume of an ICBM with minimum line-of-site error and transmit the position data to earth.