Strength Analysis of Supersonic Rocket Projectile's Tail Based on Fluid-solid-thermal Coupling

Abstract

To evaluate the safety of the rocket tail under supersonic condition, the steady-state flow field of a rocket with different Mach numbers was numerically simutated on the consideration of the ballistic curve. Then the transient heat transfer of the rocket tail in 2 s was calculated. According to the simulation results, the material mechanical property parameters of the tail was adjusted. And the total deformation and equivalent stress of the rocket tail caused by aerodynamic force in different Mach numbers was simulated. The results show that temperature of the leading edge tip is the highest on the whole tail at high Mach number conditions, and the high temperature will transmit into the within rapidly. The higher the flight Mach number is, the higher temperature of the tail is, which leading to the ablation occurs at the leading edge of the tail. Therefore, thermal protection treatment should be considered on the rocket tail under high Mach number condilion since high temperature will degrade the properties of tail's material. Large deformation will occur on the tail and the equivalent stress may exceed allowable value under the combined action of aerodynamic heat and force. The maximum deformation which occurs at the leading edge tip and the maximum equivalent stress which occurs at the tail root near the leading edge, increase with the increase of Mach number.