Plume-Surface Interaction (PSI) between lander engine plumes and landing area regolith poses risks to the landers and space exploration missions through view obscuration and high-energy ejecta impacts from eroded particle clouds and vehicle tilting from plume-induced craters. To address these risks, NASA MSFC Fluid Dynamics Branch (ER42) has developed a cascade of predictive simulation capabilities for PSI, including the recent development of a hybrid CFD/engineering model tool that allows for rapid PSI simulations with a descending/ascending vehicle and an eroding surface. The development of this fully-coupled, moving body/eroding surface simulation capability is detailed along with a demonstration of the tool’s capabilities on the Apollo 12 Lunar Module landing. Predictions of eroded mass flow rates as a function of time are verified against Apollo 12 flight data, from which the developed, viscous erosion model has been calibrated.
A Hybrid CFD/Engineering Model Tool for Lunar Lander Surface Erosion Prediction
ASCE Earth & Space 2024 ; 2024 ; Miami, FL, US
Aufsatz (Konferenz)
Keine Angabe
Englisch
Common Lunar Lander (CLL) Engineering Study Results
NTRS | 1991
|Common Lunar Lander (CLL) Engineering Study Results
NTIS | 1991
|ASCE | 2008
|AIAA | 2008
|