Hybrid particle-finite element simulation of large deformation dynamics in composite materials.

摘要

Space structures such as satellites and the space shuttle are subject to severe damage, due to the impact of space debris and micrometeoroids. In order to prevent such damage, it is necessary to develop advanced spacecraft shield designs. Composite materials and multi-layer geometry shields play an important role in the design of spacecraft protection systems. Adequate material models and efficient numerical methods are needed to simulate hypervelocity impact phenomena in such systems. Recent research has employed numerical simulations to study hypervelocity impact phenomena, because of the high cost of advanced shielding materials, the limitations of experimental capabilities, and recent improvements in numerical methods and computing power. This research has developed an improved hybrid particle-finite element method and new composite material models for the simulation of hypervelocity impact on space structures. An anisotropic rate dependent material model has been developed to model composites, in three dimensional hypervelocity impact applications. A kernel free hybrid particle-finite element method has been formulated, that eliminates the use of density interpolation kernels, simplifying the method and reducing the computational cost of the particle dependent calculations. It has been validated in three dimensional simulations of hypervelocity impact on spacecraft thermal protection materials.