Effect of honeycomb core under hypervelocity impact: numerical simulation and engineering model. (2017)

• Record Type: Journal Article
• Authors: Chen, Hong; Francesconi, Alessandro; Liu, Sen; Lan, Shengwei
• Is Part Of: Procedia engineering. Volume 204(2017)
• Page Start: 83
• Page End: 91
• Publication Date: 2017
• Subjects: Honeycomb core -- Hypervelocity impact -- Numerical simulation -- Engineering model; Engineering -- Congresses; Engineering -- Periodicals; Engineering; Conference proceedings; Periodicals; 620.005
• DOI: 10.1016/j.proeng.2017.09.759
• Languages: English
• ISSNs: 1877-7058

Abstract

Abstract: Honeycomb sandwich panels (HC/SP) are the most common used structures for space vehicle. Under the threat of meteoroid and space debris, the distribution of the fragments produced in a hypervelocity impact event on HC/SP is critical to the vulnerability assessment of space vehicle. CISAS developed an engineering model to describe fragments clouds propagating inside spacecraft in consequence of space debris impact on HC/SP. In this model, the effect of the honeycomb core was modeled by an empirical corrective factor, which was not related to the physical of the impact. To improve this model, a new model to describe the effect of the honeycomb core was developed. In the new model, the honeycomb core was equaled to multi-parallel thin plates, which can represent the discontinuity of honeycomb core without complex boundary. Based on the knowledge of hypervelocity impact on a simple thin plate and approximation supported by numerical simulation results, the model was deduced. The coefficient of the model was fitted by the numerical simulation results.