The solar wing is a vital energy component of spacecraft. It often faces challenges from vibrations and deformations during orbit, impacting spacecraft pointing accuracy and operational performance. To address these issues, a novel actuation method based on embedded piezoelectric actuator (EPA) is proposed in this study, which overcomes the technical difficulties of large additional mass and volume, and low control effectiveness. Firstly, a sandwich stacked EPA is meticulously designed and embedded into the connecting rod based on comprehensive analysis. Secondly, a novel modeling using the transfer matrix method improves the computational accuracy and the evaluation efficiency. Finally, a prototype of the EPA is fabricated, and the measurement system is constructed. The correctness of the modeling and the feasibility of the design are verified by case studies. The applications of the EPA for active vibration control are verified by additional case studies of the connecting rod and the scaled solar wing prototype, respectively. The results reveal the amplitude reduction rates at the natural frequency are 97.36% and 97.48% in the XOZ plane and YOZ plane, respectively, with residual disturbances limited to only 0.03 mm. The exemplary outcomes solidify the exceptional performance of the proposed embedded piezoelectric actuation method for the active vibration control of solar wings. This novel method holds great promise for enhancing spacecraft stability and performance.