Abstract
Hypersonic vehicles structures suffer complex combined loadings generally. For the thin-walled structures and thermal protection systems of the aircraft, high temperature and intensity acoustic loadings are the significant factors that leading to their break. The object of this paper is typical simply supported titanium alloy plate, the finite element method was adopted to calculate the critical thermal buckling temperature the ordinal coupling method and Newmark method were adopted to calculate the thermal- acoustic dynamic response. Based on the FEM analysis, the power spectrum densities (PSD) of center point was presented. Research results show that the thermal buckling of the typical simply supported titanium alloy plate occurs easily because of the low critical thermal buckling temperature, dynamic response of the thermal buckled plate suffering acoustic loads performs strong nonlinear characteristics and complex forms of exercise.
Highlights
With the fast development of aviation technology, advanced aircraft structures are exposed to combined loading environments, including mechanical, thermal, and acoustic loadings, such as thin-walled structures and thermal protection systems of aircraft, they suffer both high intensity acoustic loading and aerodynamic loading, while they are exposed to thermal environment [1]
The dynamic response research of the aircraft under the combined loads has become essential for the aircraft structure design
The dynamic response research of the aircraft structures developed with advances in aviation technology
Summary
With the fast development of aviation technology, advanced aircraft structures are exposed to combined loading environments, including mechanical, thermal, and acoustic loadings, such as thin-walled structures and thermal protection systems of aircraft, they suffer both high intensity acoustic loading and aerodynamic loading, while they are exposed to thermal environment [1]. Chen and Mei, et al [3], analyzed dynamic response of the beams underling thermalacoustic loadings using FEM and Newmark method; Ng, et al [4,5], derived the single-mode equations using the Von Karman equation and Galerkin method, they analyzed the nonlinear response of the flat and bent plates underling thermal-acoustic loadings by relatively experiment, including the basic dynamic response features and the snap-through motions; Vaicaitis, et al [6], analyzed the nonlinear response of the aircraft structure under random load using Montecarlo method In this paperthe object is typical supported titanium alloy plate of the aircraft structure. A preliminary discussion on the thermal-acoustic response mechanism is analyzed to provide reference for the acoustic fatigue test and structure design of the aircraft in thermal-acoustic environment
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
