Abstract
This paper offers a new set of 'generic', data-Based hole size and crank length prediction models for spherical orbital debris particles impacting multi-plate targets at velocities up to ~12 km/s. the equations are applicable to a wide variety of spacecraft target configurations, but are limited to hole sizes above, but relatively near, the ballistic limit of the impacting particles. Additional work is underway to expand these models to diameters farther above the ballistic limit for the described shield types.
Recommended Citation
J. E. Williamsen and W. P. Schonberg, "An Improved Prediction Model for Spacecraft Damage Following Orbital Debris Impact," 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference 2012, American Institute of Aeronautics and Astronautics, Jan 2012.
The definitive version is available at https://doi.org/10.2514/6.2012-1507
Department(s)
Civil, Architectural and Environmental Engineering
Publication Status
Full Access
International Standard Book Number (ISBN)
978-160086937-2
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2024 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 2012
