<p>This study proposes an integrated analytical–numerical and experimental framework for active vibration control and optimized flutter suppression in missile tail structures, utilizing distributed piezoelectric layers and advanced particle swarm optimization (PSO). The methodology was applied to the NAL-16 missile tail, where simultaneous geometric tailoring and multi-modal (displacement, velocity, acceleration) feedback control parameters were optimized. Results show a significant increase in critical flutter Mach number from 2.3 (uncontrolled) to 3.7 (controlled), constituting a 60% improvement over the baseline. In addition, a 30% expansion in the dynamic stability range and a 30% reduction in structural weight were achieved without compromising stability or natural frequencies. The optimized system further offered a 12% enhancement in the fundamental natural frequency and the highest reported damping ratios (up to 4.5%) compared to leading references. Experimental validation and quantitative comparison with recent laboratory results confirm the accuracy and practical applicability of the proposed approach, especially for intelligent actuator placement near the free edge of the tail. These outcomes demonstrate the superiority of the integrated optimization–control methodology, setting a new benchmark for the design, stability, and efficiency of next-generation smart missile control surfaces. The findings have significant implications for the advancement of robust, lightweight, and adaptable aerospace components.</p>