Several initiatives, such as NASA's Artemis and ESA's Argonaut missions, are ongoing to bring recurrent cargo and crew to the Moon. To establish infrastructure on the lunar surface, minimising potentially harmful dust emissions caused by a rocket plume interacting with the lunar surface is essential. A furnace-sintered lunar landing pad (LLP) could be used for this. Due to the extreme conditions on the lunar surface (e.g. vacuum and low gravity) and limited data, the experimental characterisation of the erosion of the LLP is challenging. Numerical simulations are a valuable tool for this, as they allow rapid parameter changes. In this study, a simulation model was built to describe the erosion caused by a rocket's plume using the Discrete Element Method (DEM). Particle sizes similar to those found on the Moon, ranging from 55 to 550 μm, were selected. Sintered structures are modelled using bonds based on an elastic beam model. A heat transfer model is included to simulate the fracture behaviour of sinter bridges caused by mechanical stress and temperature. Shear force and surface heat flux, calculated from a macroscale Computational Fluid Dynamics (CFD) simulation, are applied to the top surface of the LLP. The erosion rate is calculated by evaluating the movement of particles over time. The simulation results indicated that the landing pad is capable of withstanding the shear forces that are applied to it, thus preventing erosion. Instead, the landing pad was observed to undergo a process of fluidisation as it was heated by the rocket plume, resulting in the material flowing.