Simulation of the erosion behaviour of a rocket on a lunar landing pad
- Paper number
IAC-24,D3,2B,9,x85201
- Author
Mrs. Marianne Eckel, TU Braunschweig, Germany
- Coauthor
Mr. Jannis Petersen, Technische Universität Dresden (DTU), Germany
- Coauthor
Ms. Lisa Windisch, Technische Universität Braunschweig, Germany
- Coauthor
Mr. Martin Propst, TU Dresden, Germany
- Coauthor
Mr. Theodor Heutling, Technische Universität Dresden (DTU), Germany
- Coauthor
Dr. Christian Bach, Technische Universität Dresden (DTU), Germany
- Coauthor
Mr. Julian Baasch, Technical University of Berlin, Germany
- Coauthor
Mr. Stefan Linke, Technische Universität Braunschweig, Institute of Space Systems, Germany
- Coauthor
Prof. Enrico Stoll, TU Berlin, Germany
- Coauthor
Dr. Advenit Makaya, European Space Agency (ESA), The Netherlands
- Coauthor
Dr. Jeroen Van den Eynde, ESTEC, European Space Agency, The Netherlands
- Coauthor
Prof. Carsten Schilde, Technische Universität Braunschweig, Germany
- Coauthor
Mr. Tobias Lamping, Technical University of Braunschweig, Germany
- Coauthor
Mr. Bradley Craig, University of Glasgow, United Kingdom
- Coauthor
Mr. Senthilkumar Subramanian, University of Glasgow, United Kingdom
- Coauthor
Prof.Dr. Konstantinos Kontis, School of Engineering, University of Glasgow, United Kingdom
- Year
2024
- Abstract
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, it is essential to minimize potentially harmful dust emissions caused by a rocket plume interacting with the lunar surface. For this, a furnace-sintered lunar landing pad (LLP) could be used. Due to the extreme conditions on the lunar surface (e.g. vacuum and low gravity) and limited amount of data, the experimental characterization 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 modeled using bonds based on an elastic beam model. A heat transfer model is included to simulate the fracture behavior of sinter bridges caused by mechanical stress and temperature. To calibrate the numerical model, a combination of continuum methods such as bending and shearing tests, and interparticle techniques like nanoindentation, are employed. The calibration process involves adjusting parameters such as Young's modulus, shear modulus, radius and maximum bond length to best match the experimental results. 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 indicate that the particle erosion rate is affected by the porosity of the LLP, as well as its thermal conductivity and thermal capacity. Additionally, the erosion rate is influenced by the position under the rocket, its altitude and the heat flux onto the LLP.
- Abstract document
- Manuscript document
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