As telescopic wing is a kind of morphing wing, due to the characteristics of the timevarying and flexible body of the structure, its flight performance is influenced by the timevarying transverse vibration in the process of morphing. In this paper, modal experiment and vibration experiment of telescopic wings were completed, where the active wing at different positions and with different velocity is determined by the rotational speed and the direction of the servo motor, and the rational speed and direction is controlled by the PLC control system. On the one hand, modal experiment of active wing in five conditions is carried out using the hammering method, and the initial third order nature frequency and modal shape is obtained. On the other hand, the transverse vibration of active wing in the process of morphing is investigated and collected by the ICP acceleration sensor as well as the LMS data acquisition and analysis system. The relationship between velocity and maximum vibration amplitude, and the relationship between velocity and maximum response frequency are obtained. The analysis results show that the longer the length of active wing is, the lower the nature frequency is. As the velocity is a parametric excitation, when the equivalent excitation of the velocity equals to the specific nature frequency of active wing in specific conditions, the structure resonance occurs. The studies in this paper can provide theoretical basis and technical support in investigating the vibration control and the reasonable velocity of the wing.