Multi-excitation source united controlling test method based on distributed actuation

In view of the questions of high-speed aircraft withstanding complicated vibration environment, their vibration durability could not being plenary examined by existing vibration test technology, a vibration test technique integrating piezoelectric element, vibration table, exciter was proposed, the vibration table and exciter placed on the large-stiffness part of the structure to provide concentration force and piezoelectric elements on the small-stiffness part to provide distributed force. The vibration environment dimension of high-speed aircraft and its influence to the failures of high-speed aircraft were analysed. Based on the research on the material and actuation dimension of the piezoelectric element, the feasibility of piezoelectric element used as the distributed excitation source in vibration test was analysed. Last, a test demonstration system was constituted and a serial of test items were carried out. Using this method, the RMS magnitude of one point on the flexible part of the structure can be controlled to 20.8 g. The rationality and the extensive engineering application potential of this technique are verified by the test results.