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International Journal of Aerospace Engineering
Volume 2017 (2017), Article ID 1015674, 9 pages
Research Article

Numerical Simulation of Projectile Oblique Impact on Microspacecraft Structure

Hypervelocity Impact Research Center, Harbin Institute of Technology, Harbin 150080, China

Correspondence should be addressed to Runqiang Chi; nc.ude.tih@qrihc

Received 25 October 2016; Revised 25 January 2017; Accepted 20 February 2017; Published 16 April 2017

Academic Editor: Enrico C. Lorenzini

Copyright © 2017 Zhiyuan Zhang et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


In the present study, the microspacecraft bulkhead was reduced to the double honeycomb panel, and the projectile oblique hypervelocity impact on the double honeycomb panel was simulated. The distribution of the debris cloud and the damage of a honeycomb sandwich panel were investigated when the incident angles were set to be 60°, 45°, and 30°. The results showed that as incident angle decreased, the distribution of debris cloud was increased gradually, while the maximum perforation size of the rear face sheet was firstly increased with the decrease of the incident angle and then decreased. On the other hand, the damage area and the damage degree of the front face sheet of the second honeycomb panel layer were increased with the decrease of the incident angle. Finally, the critical angle of front and rear face sheets of the honeycomb sandwich panel was obtained under oblique hypervelocity impact.