This paper presents work on development of tools and modelling techniques for simulation of hypervelocity impact on spacecraft structures using the Lawrence Livermore DYNA3D code. Analyses were performed to evaluate the capability of unmodified DYNA3D to model hypervelocity impact on multiple plate structures. These showed that improvements were required in three main areas: constitutive modelling, the element erosion criterion, and the ability to model the debris cloud formed by thin plate impacts.

The SESAME Equation of State library has been implemented into DYNA3D. The implementation was validated by calculation of the Hugoniot curve for aluminium using DYNA3D results. Good agreement with the expected curve was observed.

To improve the element erosion criterion two different criteria have been implemented and tested. The first is based on total element deformation and results show reasonable agreement with experiment. The second is intended to delete an element when it is numerically inaccurate. Initial results show that fewer elements are eroded than for a element strain criterion.

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