Methodology for Estimation of Shock Wave and Acoustic Loading of a Designed Rocket Block Equipped with an Aerospike Engine at the Landing Stage

The paper considers a methodology for assessing the shock wave and acoustic loading of the elements of the rocket block body of an ultralight partially reusable launch vehicle during landing, taking into account the dynamics of movement. Using the ANSYS Fluent software package and broadband noise method, a mathematical model was formed to estimate the motion of the computation domain boundary, gas outflow adjusted for compressibility of turbulent viscosity, and acoustic power distribution over the surface of the vehicle. The values of acoustic power on the vehicle surface at the moment of landing as well as the static pressure distribution over the surface of the tail compartment protective shield over the landing time were determined. Directions for improving the accuracy of the methodology were identified.