Thermal-stress response of hypersonic rudder to laser irradiation

A static aero elastic model of hypersonic aircraft under laser irradiation was built based on computational fluid dynamics (CFD) and computational structural dynamics coupling numerical computational methodology. The flow was governed by 3-D Reynolds averaged Navier-Stokes equations. To split the viscosity flux and the convective flux of the NS equations, the second order central scheme and the AUSM+up scheme were adopted respectively. With the implicit Gauss-Seidel scheme, the code was advanced in time. The Menter SST turbulence model was used for turbulence simulations. The model was proofread with the experiment data from von Karman Institute hypersonic wind tunnel. Hypersonic aircraft wing under laser irradiation was simulated with this model. The results indicated that the energy addition could reduce the Youngs modulus of hypersonic rudder. Hypersonic aircraft may prang due to the destroy of the rudder.