Predicting the Rupture of a COPV Impacted by a High-Speed Orbital Debris Particle: Including the Effects of Temperature and COPV Contents
Publication: Journal of Aerospace Engineering
Volume 34, Issue 3
Abstract
A main design consideration for spacecraft destined to operate in the meteoroid or orbital debris (MOD) environment is the prevention of possible damage that might occur following an MOD impact. Risk assessments that are performed during spacecraft design typically consider what might happen following an onorbit MOD impact. In order to perform such an assessment, a variety of response prediction equations are required, including equations that predict whether a structural element, such as a pressure vessel or fuel tank, is perforated or ruptured by an MOD impact. In this paper, we bring together the datasets from room temperature gas-filled and cryogenic liquid-filled pressure vessel testing programs to develop a single equation that predicts whether tank rupture will occur following a high-speed impact. A comparison with test results shows that the equation developed correctly predicts the rupture/nonrupture responses of the pressure vessels considered in this study. This new rupture limit equation (RLE) can now predict whether or not a composite overwrapped pressure vessel (COPV) would rupture under a much wider range of temperatures, constructions, and COPV contents.
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Data Availability Statement
All data, models, and code generated or used during the study appear in the published article.
Acknowledgments
The author gratefully acknowledges the support provided by the NASA Engineering Safety Center and the NASA White Sands Test Facility for performing the impact tests that generated the data used in this study.
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Published In
Journal of Aerospace Engineering
Volume 34 • Issue 3 • May 2021
Copyright
© 2021 American Society of Civil Engineers.
History
Received: Sep 1, 2020
Accepted: Oct 28, 2020
Published online: Feb 4, 2021
Published in print: May 1, 2021
Discussion open until: Jul 4, 2021
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