Abstract
In this paper, an analytical method is proposed to directly obtain the aeroelastic time domain response of the elastic boundary panel. Based on a modified Fourier series method (MFSM), the vibration analysis of elastic boundary panels is carried out, after the dynamics equation of the panel is obtained. Then, the vibrational functions are combined with the supersonic piston theory to establish the aeroelastic equation. The aeroelastic time domain response of the panel is obtained to analyze the flutter speed of the panel more intuitively. Finally, the flutter speeds of panels with different length-width ratios, thicknesses, and elastic boundary conditions are discussed in detail.
Highlights
Hypersonic aircraft has gradually become a new-generation aircraft developed by various countries
The aerodynamic model is based on the second-order piston theory which can be expressed as follows: p = 1 + κ vz + κ κ + 1 vz where p∞, a∞, and κ are constants, indicating the atmospheric pressure of the incoming flow, the speed of sound of the incoming flow, and the specific heat capacity ratio, respectively
An analytical method based on the modified Fourier series method (MFSM) is proposed to obtain the aeroelastic time domain response of the elastic boundary panel
Summary
Hypersonic aircraft has gradually become a new-generation aircraft developed by various countries. The MFSM has been applied to solve many problems of plates with elastic boundary restraints, such as free vibration of two elastically coupled rectangular plates [22], modal analysis of general plate structures [23], and modeling analysis of elastically restrained panel [24]. This method is used well in triangular plates [25], blades [26], circular plates [27], confocal annular elliptic plates [28], and so on. An analytical method is proposed to obtain the aerodynamic elastic response of the elastic boundary panel in time domain directly, so as to study the flutter problem more intuitively
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.
