A ballistic limit equation for hypervelocity impacts on composite honeycomb sandwich panel satellite structures |
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Authors: | S Ryan F Schaefer R Destefanis M Lambert |
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Institution: | 1. Fraunhofer-Institut für Kurzzeitdynamik, Ernst-Mach-Institut (EMI), Eckerstr. 4, D-79014 Freiburg, Germany;2. School of Aerospace, Mechanical & Manufacturing Engineering, RMIT University, GPO Box 2476V, Melbourne, Australia;3. Alcatel Alenia Space, Str. Antica di Collegno 253, 10146 Turin, Italy;4. ESA-ESTEC, Postbus 299, NL-2200 AG Noordwijk, The Netherlands |
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Abstract: | During a recent experimental test campaign performed in the framework of ESA Contract 16721, the ballistic performance of multiple satellite-representative Carbon Fibre Reinforced Plastic (CFRP)/Aluminium honeycomb sandwich panel structural configurations (GOCE, Radarsat-2, Herschel/Planck, BeppoSax) was investigated using the two-stage light-gas guns at EMI. The experimental results were used to develop and validate a new empirical Ballistic Limit Equation (BLE), which was derived from an existing Whipple-shield BLE. This new BLE provided a good level of accuracy in predicting the ballistic performance of stand-alone sandwich panel structures. Additionally, the equation is capable of predicting the ballistic limit of a thin Al plate located at a standoff behind the sandwich panel structure. This thin plate is the representative of internal satellite systems, e.g. an Al electronic box cover, a wall of a metallic vessel, etc. Good agreement was achieved with both the experimental test campaign results and additional test data from the literature for the vast majority of set-ups investigated. For some experiments, the ballistic limit was conservatively predicted, a result attributed to shortcomings in correctly accounting for the presence of high surface density multi-layer insulation on the outer facesheet. Four existing BLEs commonly applied for application with stand-alone sandwich panels were reviewed using the new impact test data. It was found that a number of these common approaches provided non-conservative predictions for sandwich panels with CFRP facesheets. |
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Keywords: | Space debris Hypervelocity impact Composites CFRP Damage laws Ballistic limit equation |
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