A study was conducted to demonstrate parametric analysis of single-stage earth-departure-stage in-orbit refueling. It explored possibilities associated with different on-orbit refueling strategies while evaluating associated performance benefits. This goal was achieved through a first-order parametric analysis of on-orbit refueling of single-stage Earth departure stages. The analysis derived non-dimensional parameters for payload growth rates and packaging ratios, which made the framework suitable to be used to any reference payload mass size of interest and allowed consideration of a variety of classes of launch vehicles. Investigations revealed that payload growth rate achieved was a function of the chosen refueling strategy. The isomass constraint enabled comparison of payload growth rates between different refueling strategies.