NASA and ESA are working on returning humans to the moon through initiatives such as the Artemis mission and Argonaut Lander of the ESA. To establish lunar surface infrastructure, it is crucial to minimise dust emissions generated by the rocket plume. The aim of this study is to develop a computational model investigating the interaction between the plume and a sintered landing surface. Understanding the erosion process of a sintered landing pad is essential to ascertain how long the lunar landing pad can withstand the stress of the rocket. Current models only demonstrate the interaction between the plume and the surface of a loose layer of regolith, using different concepts in the simulation. The proposed model utilises a multiscale approach, covering both macroscale and microscale to overcome computational limitations. In the macroscale, the rocket plume is calculated using computational fluid dynamics (CFD), while the microscale considers the coupling of CFD and the discrete element method (DEM). Therefore, compressible CFD-DEM coupling is utilised together with a heat transfer model between particles and fluid. Bonded, monodisperse particles with a diameter of 100 μm are considered for describing the sintered landing pad. An interface between different scales is represented by interpolating CFD data from the macroscale rocket simulation to the microscale erosion simulation. The main structure and boundary conditions, as well as an analysis of the impact of different discretisation schemes on the mass flow imbalances are presented in this paper. A first-order time discretisation scheme with a second-order space discretisation scheme leads to the lowest mass imbalance. The primary outcome is that the erosion is contingent upon the melting temperature of the lunar landing pad and the heat flux into the pad.