Abstract: In order to measure the structural dynamic responses in the powered-flight phase and the micro vibration characteristics of the spacecraft structural slab in the orbital injection phase with high precision, a novel MEMS vibration response testing system is designed. In view of the strong vibration shock and the wide spectrum of the vibration signal in the powered-flight phase, as well as the small amplitudes and low-frequency of the vibration signal in the orbital injection phase, an integrated design composed of a high-capacity piezoelectric accelerometer, a domestic MEMS accelerometer and a MEMS gyroscope is implemented, which can synthetically measure the structural dynamic responses and the micro vibration characteristics. The vibration response analyses both in the time domain and the frequency domain for the spacecraft motion, show that the system work normally with complete and effective measurement data of adequate accuracy, satisfactory for the related requirements. Besides, the system is already technically-mature to become a product for further applications.