Extending the Applicability of Thermal Protection System Ballistic Limit Equations Beyond the Testable Regime

Author

William P. Schonberg, Missouri University of Science and TechnologyFollow
Michael D. Squire

Abstract

Spacecraft use thermal insulation in their design, which is usually placed on their exterior. As such, it is susceptible to high-speed impacts by meteoroids and orbital debris, which can damage it to a point where the protection it offers is below acceptable limits. It is important to be able to characterize expected levels of damage stemming from such high-speed impacts. In this paper, we extend the applicability of a previously developed ballistic limit equation (BLE) for one such thermal insulation material using the results of a series of Smooth Particle Hydrodynamics Code (SPHC) impact simulations at velocities in excess of 10 km/s. When the predictions of the updated and expanded BLE were compared against the results of the SPHC runs, the predictions were seen to be consistent with the data regarding whether or not a particular impact might or might not result in the perforation of the underlying substructure upon to which the thermal insulation was attached.

Recommended Citation

W. P. Schonberg and M. D. Squire, "Extending the Applicability of Thermal Protection System Ballistic Limit Equations Beyond the Testable Regime," Proceedings of the 17th Hypervelocity Impact Symposium Hvis 2024, article no. v001t08a001, American Society of Mechanical Engineers, Jan 2025.

The definitive version is available at https://doi.org/10.1115/HVIS2024-007

Department(s)

Civil, Architectural and Environmental Engineering

Publication Status

Free Access

Comments

NASA Engineering and Safety Center, Grant None

International Standard Book Number (ISBN)

978-079188872-8

Document Type

Article - Conference proceedings

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 2025 American Society of Mechanical Engineers, All rights reserved.

Publication Date

01 Jan 2025