Experimental investigation on dynamic response of aircraft panels excited by high-intensity acoustic loads in thermal environment

13th International Conference on Motion and Vibration Control; 12th International Conference on Recent Advances in Structural Dynamics

Wu, Z.Q.^1 ; Li, H.B.^1 ; Zhang, W.^1 ; Cheng, H.^1 ; Kong, F.J.^1 ; Liu, B.R.^1

Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing

100076, China^1

关键词: Acceleration response;    Acoustic environment;    Composite specimens;    Experimental investigations;    Root mean square values;    Sound pressure level;    Thermal environment;    Thermal Protection System;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/744/1/012092/pdf
DOI  :  10.1088/1742-6596/744/1/012092

来源: IOP

【 摘 要 】

Metallic and composite panels are the major components for thermal protection system of aircraft vehicles, which are exposed to a severe combination of aerodynamic, thermal and acoustic environments during hypersonic flights. A thermal-acoustic testing apparatus which simulates thermal and acoustic loads was used to validate the integrity and the reliability of these panels. Metallic and ceramic matrix composite flat panels were designed. Dynamic response tests of these panels were carried out using the thermal acoustic apparatus. The temperature of the metallic specimen was up to 400 °C, and the temperature of the composite specimen was up to 600 °C. Moreover, the acoustic load was over 160 dB. Acceleration responses of these testing panels were measured using high temperature instruments during the testing process. Results show that the acceleration root mean square values are dominated by sound pressure level of acoustic loads. Compared with testing data in room environment, the peaks of the acceleration dynamic response shifts obviously to the high frequency in thermal environment.