The high cycle vibration fatigue test for titanium alloy hollow structure is proposed. The critical location can be defined based on numerical analysis and experimental testing. Closed loop control of testing system is realized by using resonance resides method. The test method is validated by hollow plate specimen testing. The results show that the proposing test method can accurately determine the critical location of the structure. And the stress and amplitude conform to the linear rules under the test condition. Also

sine reside control mode can conduct the closed loop control of continuous testing. The research will bring lots of benefits

including improving the accuracy of the test on titanium hollow structure

effectively cutting the high cycle fatigue period. It is of great significance on improving the level of safety and reliability of aviation as well as aerospace vehicles.