Nacelle acoustic liner, crucial for noise reduction in modern civil high-bypass-ratio turbofan engines, has suffered numerous structural strength failures in harsh conditions. Similar to aircraft honeycomb sandwich structures, it consists of a perforated plate, honeycomb and backplate. An initial equivalent modeling approach, homogenizing the orthotropic properties of the perforated plate and honeycomb core, reduces finite element model degrees of freedom and boosts efficiency. However, it shows poor stress/strain prediction accuracy (only 10% of actual values). This paper proposes a novel vibration analysis strategy combining global equivalent modeling with local refined modeling via sub-modeling, ensuring both local accuracy and overall efficiency, with an error within 10%.