Optimization of a launch vehicle can be specified in terms of many different variables. In the case of a heavy-lift vehicle, the objective is often to minimize the weight of the vehicle on the launchpad. Minimization of this particular variable is essential for designing efficient vehicle capable of bringing specified payloads to orbit. In this paper we discusses a process used to achieve a minimum gross liftoff weight for a vehicle with a flexible payload capability that utilizes pre-existing or near-term propulsion systems. Determining the optimized configuration is accomplished with a combination of brute force methods and with mathematical and visual data organization. Through the variation of five different independent variables, millions of trajectories are simulated for different vehicle configurations to provide the necessary data. Organization of this data presents the means to identify and locate the configurations that meet the performance constraints and minimize overall system mass.
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