Super Pressure Balloons (SPBs) for atmospheric exploration of planetary bodies offer a unique capability for long-duration in-situ studies. The design requirements that drive the trade-off between the SPB diameter and film thickness are Float Altitude (FA) in m, Launch Altitude (LA) in m, Rate of Ascent/Descent ( \(\mathbf {V_z}\) ) in m/s, and Payload-System Mass Ratio (PSMR). This paper discusses a novel Constraint-Driven design methodology specifically tailored for planetary SPBs. The methodology integrates an iterative sizing procedure with a comprehensive constraint analysis to systematically generate feasible design points that satisfy the mission requirements. The approach was successfully applied to develop preliminary design parameters for atmospheric exploration missions to Venus, Mars, and Titan, confirming the engineering feasibility for all three targets. Furthermore, the design methodology is validated against historical data from the VEGA Balloon missions on Venus. For Mars and Titan, the methodology is benchmarked against conceptual studies from established literature.
