The exploration of the Jovian system, particularly its icy moons, has become a central theme in contemporary planetary science. This trend is driven by flagship missions such as ESA's JUICE and NASA's Europa Clipper. Building upon these initiatives, future mission concepts increasingly envision Multi-Moon Orbiters (MMOs).  These spacecraft would execute successive transfers between satellites, such as a transition from a Ganymede orbit to a Europa orbit. However, the design of such inter-moon trajectories poses a substantial astrodynamics challenge, which traditional methodologies struggle to address efficiently. High-thrust transfers, such as patched-conic Hohmann transfers, require prohibitive Delta-V budgets. Conversely, Low-Energy Transfers (LETs) utilizing invariant manifolds within the Circular Restricted Three-Body Problem (CR3BP) offer high fuel efficiency but often suffer from excessively long flight times because of the chaotic nature of ballistic capture. This paper proposes a novel trajectory design framework that resolves this dichotomy by integrating phase space lobe dynamics with impulsive maneuvers within a coupled dynamical model.
   The proposed framework models the transfer from Ganymede to Europa using two coupled Planar Circular Restricted Three-Body Problems (PCR3BPs): the Jupiter-Ganymede system and the Jupiter-Europa system. Although the Jacobi constants in both systems can be iteratively tuned to compatible levels, a feasible connection also requires verifying the geometric alignment of the relevant phase-space structures. To address this problem, we formulate the trajectory design as a patched dynamical problem using an intermediate Poincaré section situated between the orbits of the two moons. This section serves as a diagnostic interface that visualizes the phase-space topology and identifies whether the unstable manifold of the departure system intersects the stable manifold of the arrival system. The transition between the two dynamical regimes is then facilitated by identifying these intersections and applying an impulsive maneuver to correct the discontinuity in the velocity vector.
   A key innovation of this research is the use of lobe structures arising from resonant dynamics. This contrasts with the traditional approach, which relies primarily on Lyapunov orbits. Standard tube dynamics relies on invariant manifolds associated with L_1, L₂ Lyapunov orbits, but these structures often lack the granularity required for precise optimization. Relying solely on Lyapunov manifolds hides finer transport mechanisms and makes it difficult to distinguish between fast and slow pathways. To overcome this limitation, we use a multi-manifold approach that incorporates invariant manifolds associated with multiple   resonant orbits. Unlike the uniform manifolds of Lyapunov orbits, these resonant manifolds form distinct geometric lobes on the Poincaré section. These lobes directly govern the transport characteristics of the phase space. By analyzing the collection of resonant lobes, we categorize available pathways according to their resonance ratios and identify the precise locations at which transfers should occur. This enables the identification of precise jump locations required to access specific resonance-assisted transport channels. Consequently, we can design impulsive maneuvers that target a specific p:q resonant manifold, allowing for the deterministic selection of a trajectory with the desired transit duration and geometry.
   Furthermore, the synthesis of the transfer maneuver is guided directly by the identified lobe geometry. After isolating the fast-exit and fast-entry lobes on the Poincaré section, we compute the optimal Delta-V vector required to bridge the corresponding velocity states. Unlike traditional optimization methods that rely on global Delta-V searches, our approach computes the maneuver specifically at the phase-space coordinates where the relevant transport channels intersect. This ensures the spacecraft is injected into a deterministic pathway with guaranteed transit characteristics.
   In conclusion, this research provides a systematic solution to the trade-off between transfer time and fuel consumption in MMO mission design. By leveraging the natural transport channels elucidated by lobe dynamics, the proposed method circumvents the prolonged capture phases typical of traditional low-energy transfers. At the same time, using the manifold structure as a dynamical backbone reduces the deterministic Delta-V required compared with classical high-thrust approaches. Overall, the framework demonstrates that chaotic dynamics can be controlled effectively to achieve both Delta-V efficiency and time-efficient operations in the Jovian system.