Abstract
The objective of this paper is to present a multifidelity approach for estimating recession rate and kinetic energy impact rate on the surface of planetary entry vehicles operating in dusty atmospheric environments at hypersonic speeds. The multifidelity model used a co-Kriging approach that combined a low-fidelity correlation with a correction factor from high-fidelity CFD solutions. The developed multifidelity model enables efficient and accurate exploration of a design space to determine at what conditions encountering dust is most dangerous to TPS survivability. Two sample problems are used to demonstrate the effectiveness of the approach: the Mars 2020 lander and a HIAD-type entry vehicle design space. Converged multifidelity models for the M2020 and HIAD design spaces were able to predict independent sets of high-fidelity test points with 2.83% and 3.84% error, respectively. Additionally, the computational cost of evaluating the converged multifidelity models was approximately 4 orders of magnitude lower than one high-fidelity CFD solution. The converged models were then applied to sets of randomly generated atmospheric ballistic entry trajectories to demonstrate the effectiveness of the multifidelity dust erosion prediction for mission and trajectory analysis.
Recommended Citation
A. Boland et al., "Multifidelity Dust Erosion Analysis of Mars Entry Vehicles," AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025, American Institute of Aeronautics and Astronautics, Jan 2025.
The definitive version is available at https://doi.org/10.2514/6.2025-1138
Department(s)
Mechanical and Aerospace Engineering
Publication Status
Full Access
International Standard Book Number (ISBN)
978-162410723-8
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2025 American Insstitute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 2025
