Abstract
Sandwich panels are widely used in the design of unmanned satellites and in addition to having a structural function, can often serve as orbital debris shielding. In this application, sandwich panels with open-cell foam cores have a significant advantage, enabling intensive interaction between the impactor fragments and the foam ligaments which enhances the fragments’ breakdown and reduces their damaging potential. Modeling of this process requires an explicit meso-scale representation of the core material. In this study, realistic geometry models were obtained for 10 ppi and 20 ppi 8% aluminum open-cell foams using X-ray Computed Tomography imaging. They were then converted into meshless simulation models and used in modeling of 6.9 km/s particles impact on foam core sandwich panels. Results of the numerical simulations were compared with experimental data reported by NASA in terms of the panels’ core and rear facesheet damage.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
