The present technology pertains to a
system for optimizing space logistics for multi-part space missions. Space logistics are optimized by selecting a combination of space vehicles and space maneuvers performed by those space vehicles that maximize the destination
mass while simultaneously minimizing the initial
mass, as well as minimize mission
delta-v and costs. This optimization can be performed using an objective function as a weighted combination of the destination
mass and the corresponding initial mass. This optimization can be subject to various constraints, including
system compatibility, operational feasibility, lower and upper bounds for the variables,
mass balance at each node, inflow-outflow relationship,
rocket capacity constraints, and non-negativity applied to the flow.