A ballistic limit equation for hypervelocity impacts on composite honeycomb sandwich panel satellite structures

Ryan, S, Schaefer, K, Destefanis, R and Lambert, M 2008, 'A ballistic limit equation for hypervelocity impacts on composite honeycomb sandwich panel satellite structures', Advances in Space Research, vol. 41, no. 7, pp. 1152-1166.


Document type: Journal Article
Collection: Journal Articles

Title A ballistic limit equation for hypervelocity impacts on composite honeycomb sandwich panel satellite structures
Author(s) Ryan, S
Schaefer, K
Destefanis, R
Lambert, M
Year 2008
Journal name Advances in Space Research
Volume number 41
Issue number 7
Start page 1152
End page 1166
Total pages 15
Publisher Elsevier
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.
Keyword(s) Space debris
hypervelocity impact
composites
CFRP
damage laws
ballistic limit equation
DOI - identifier 10.1016/j.asr.2007.02.032
Copyright notice © 2008.
ISSN 0273-1177
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