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2004
Conference Paper
Titel
Numerical study of hypervelocity space debris impacts on CFRP/al honeycomb spacecraft structures
Abstract
Recent advances in numerical modeling techniques ([1],[2],[3],[4]) have allowed improved descriptions of the phenomenology (shock propagation, fragmentation, detached spall) of hypervelocity impact on complex composite targets. As the use of CFRP Aluminum honeycomb structures rapidly increases in space applications, the risk of this structure type to the M/OD environment must be assessed. It is expected that the non-homogenous nature of a honeycomb sandwich panel will significantly affect structural performance during hypervelocity impact if the projectile is small relative to the honeycomb cell size. Risk assessment of a spacecraft structure requires extensive experimental testing. Alternatively a preliminary numerical study can be utilized to identify key areas of interest and reduce the required magnitude of the experimental campaign. The results of a predictive numerical study presented in this paper found that hydrocode simulations using SPH discretisation and mode rn composite material models [1] are able to reproduce the phenomenology of the physical material in hypervelocity impact tests for velocities above 3 km/s. Quantitative reproduction of experimental results is still dependant on availability of precise material data. Within the known limitations of predictive capabilities it was determined that the honeycomb core impact location has a weak effect on the ballistic limit of the structure and total spall mass. However, dispersion of detached spall clouds and the affected area of spacecraft interior are strongly influenced by the impact location relative to the honeycomb microstructure.