In order to effectively solve the position and attitude interference problem of spacecrafts caused by the vibration of the space solar array sailboard，further improve the flight control stability of satellites and orbiters and their own pointing accuracy （earth and sun orientation），a set of solar array active vibration suppression ground experimental system is designed. The active vibration suppression mechanism of macro fiber composite（MFC）is studied. The optimal bonding area of MFC is determined by the maximum modal strain energy theory. A PID self-tuning controller is designed，and the active vibration suppression experiment of the solar array is carried out to verify the feasibility of the PID self-tuning control algorithm. In the experiment，the vibration suppression in free vibration state，sinusoidal interference and white noise interference are studied respectively. The experimental results show that the free vibration tends to be stable for more than 40 s without active control. After adopting the active control based on PID self-tuning algorithm，the free vibration of the sailboard can be stabilized within 3 s. In addition，the self-excited vibration of the sailboard can be effectively controlled in 3~5 s under the above sinusoidal and random white noise signal interference excitation，and the amplitude of the sailboard stabilized in the balance position before and after active control is reduced from 18 to 3 mm，and the vibration suppression efficiency is up to 6 times. In addition，through the Fourier transform of the time-domain signal，it can be seen from the spectrum curve that the vibration suppression effect is also very significant，the maximum response amplitude is reduced from 24 to 6 mm，and the vibration suppression efficiency can reach 4 times.