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| Nonlinear Vibration Response Characteristics of Stiffened Panel Structure of High Speed Aircraft under Thermoacoustic Load |
| Received:August 08, 2024 Revised:August 27, 2024 |
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| DOI：10.7643/issn.1672-9242.2024.09.008 |
| KeyWord:high speed aircraft stiffened panel thermoacoustic load nonlinear vibration thermal buckling thin-walled structure |
| Author | Institution |
| ZHOU Xiaotian |
Key Laboratory of Advanced Measurement and Test Technique for Aviation Propulsion System, School of Aero Engine, Shenyang Aerospace University, Shenyang , China |
| SHA Yundong |
Key Laboratory of Advanced Measurement and Test Technique for Aviation Propulsion System, School of Aero Engine, Shenyang Aerospace University, Shenyang , China |
| YANG Yanze |
Key Laboratory of Advanced Measurement and Test Technique for Aviation Propulsion System, School of Aero Engine, Shenyang Aerospace University, Shenyang , China |
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| Abstract: |
| The work aims to study the large deflection nonlinear vibration response of stiffened panel structure of high speed aircraft exhaust duct under thermoacoustic load. Based on the large deflection motion governing equation of thin-wall structures, the nonlinear response simulation of a stiffened panel structure under thermoacoustic load was carried out. The motion equation of the stiffened panel structure was given, the critical temperature of thermal buckling was analyzed, and the nonlinear vibration response characteristics of the stiffened panel structure under different loads were calculated by numerical simulation according to the finite element method. The consistency of the modal frequency was reflected in the results. The response changes of the panel structure with multiple parameters such as structure, temperature and sound pressure level were calculated. The reinforcement increased the fundamental frequency and decreased the response of the panel structure. Before buckling, the fundamental frequency of the structure decreased with the increase of temperature, and the lowest frequency was near the critical temperature. The fundamental frequency of the structure increased with the increase of temperature after buckling. The fundamental frequency amplitude increased first and then decreased during the temperature rise. For every 6 dB increase of sound pressure level, the equivalent stress increased by an average of 1.98 times, which verified the nonlinear characteristics of response. The parameters of structure, temperature and sound pressure level have great influence on the nonlinear vibration response of the stiffened thin-walled structure. The stiffened thin-wall structure changes from the pre-buckling stable state to the in-buckling unstable state and then to the post-buckling stable state gradually during the temperature rise. The work in this paper can provide reference for the calculation and analysis of nonlinear vibration response characteristics of other thin-walled structures, especially stiffened panel structures. |
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