Direct simulation of the fluid-structure interaction of a compliant panel in a hypersonic compression ramp flow

hypersonic, compression ramp, fluid-structure interaction, aerothermoelastic, aeroelasticity, piston theory

Sullivan, Bryson ; Bodony ; Daniel J.

关键词: hypersonic, compression ramp, fluid-structure interaction, aerothermoelastic, aeroelasticity, piston theory;   

Others  :  https://www.ideals.illinois.edu/bitstream/handle/2142/104947/SULLIVAN-THESIS-2019.pdf?sequence=1&isAllowed=y

美国|英语

来源: The Illinois Digital Environment for Access to Learning and Scholarship

【 摘 要 】

Sustained flight at hypersonic speeds presents a challenge to robust vehicle design and control. An extreme aerothermal environment acting on geometrically-thin, multifunctional structures can result in significant static and dynamic structural deformations of the vehicle and its subcomponents. In particular, for a control surface-motivated scenario, the adverse pressure gradient generated by a compression ramp can produce a large region of subsonic, separated flow with the potential to degrade accurate estimation of surface loading by traditional hypersonic aerodynamic methods such as piston theory. The present work details high-fidelity, coupled fluid-thermal-structure interaction (FTSI) simulations of laminar, unsteady 2D flow at Mach 6.04 over a 35-degree compression ramp with an embedded compliant panel. Surface-pressure loading generated by the corner shock wave boundary layer Interaction (SWBLI) is compared between compliant and non-compliant compression ramp configurations, and SWBLI-excited response of the compliant panel is demonstrated. An analytical model based on Rayleigh's method is introduced which, given the maximum amplitude of vibration, predicts the nonlinear frequency of a compliant panel to within an average error of 8.3% over several orders of magnitude in flexural rigidity. Maximum observed heat transfer rates to the panel were diminished for the compliant panel cases relative to the rigid case, believed to be caused by a break-up in structure of the oscillating shear layer due to the motion of the panel. Reduced-order models, such as shock expansion/ local piston theory (SE/LPT), are computed for each panel and were found to perform well with a modification to account the influence of the corner separation region. Reynolds analogy for estimating heat flux was found to work reasonably well for the rigid case, but lost accuracy when applied to the thinnest panels and largest deflections.