Simulation of orbital debris impact on the Space Shuttle wing leading edge

A series of three dimensional hypervelocity impact simulations has been performed to study the effects of orbital debris impact on the Space Shuttle wing leading edge. The simulations employed an improved hybrid particle-finite element method and an orthotropic elastic-plastic material model recentl...

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Bibliographic Details
Published in:International journal of impact engineering 2006-12, Vol.33 (1), p.231-243
Main Authors: Fahrenthold, Eric P., Hernandez, Roque J.
Format: Article
Language:English
Subjects:
Exact sciences and technology
Fracture mechanics (crack, fatigue, damage...)
Fundamental areas of phenomenology (including applications)
Impact simulation
Inelasticity (thermoplasticity, viscoplasticity...)
Measurement and testing methods
Physics
Reinforced carbon–carbon
Solid mechanics
Structural and continuum mechanics
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Summary:A series of three dimensional hypervelocity impact simulations has been performed to study the effects of orbital debris impact on the Space Shuttle wing leading edge. The simulations employed an improved hybrid particle-finite element method and an orthotropic elastic-plastic material model recently developed for reinforced carbon–carbon. The simulation results are consistent with the available experimental data, and suggest the use of momentum scaling to estimate damage effects for impact conditions outside the range of current light gas gun technology. Projectile shape and orientation effects appear to be modest for flat plate projectiles at impact velocities above the ballistic limit.
ISSN:0734-743X
1879-3509
DOI:10.1016/j.ijimpeng.2006.09.080