Europa's proximity to Jupiter creates a hostile dynamic environment for a spacecraft with limited control authority as is typical with low-thrust missions. The unstable third-body effects are magnified near the polar inclinations where science orbits reside, and plane changes deep within Europa's gravity well are fuel and time expensive. Therefore, designing capture trajectories directly to highly inclined states is desirable but challenging because of the pronounced instability and lack of thrust authority. The approach outlined here confronts this problem by using dynamical systems theory and an extensive preexisting database of restricted three-body problem periodic orbits. The stable manifolds of unstable periodic orbits are used to attract a spacecraft towards Europa. By selecting an appropriate periodic orbit, a mission designer can control important characteristics of the captured state including stability, minimum altitudes, characteristic inclinations, and characteristic radii, among others. Several free parameters are adjusted in the nontrivial mapping from the simplified to a more realistic model until a satisfactory ephemeris capture is found. Although the final capture trajectory is ballistic by design, low thrust is used to target the state that leads to the capture orbit, control the spacecraft after arriving on the unstable quasi-periodic orbit, and begin the spiral down towards the science orbit. Despite the limited control authority and the highly unstable dynamical environment, the method provides structure to the design process and enables the systematic targeting of ephemeris model capture state characteristics.