Aeroassist maneuvers offer significant fuel-saving advantages in planetary exploration orbital transfers. Multi-pass aeroassist can enhance maneuverability while reducing thermal protection costs. This paper addresses the minimum-time transfer for multi-pass aeroassisted maneuvers by formulating an optimal control problem with path constraints. Analyzing the characteristics of the minimum-time transfer trajectory yields the conditions necessary for the spacecraft's minimum transfer time. Then, a bisection-based rapid trajectory generation strategy is introduced, iteratively shooting the peak heating rate each pass to precisely activate path constraints, achieving the minimum time of entire maneuver. Simulations quantify the relationship between peak heating rate and atmospheric entry orbit size. Minimum transfer times and passes for varied path constraints were determined via simulation.