Study on modeling and simulating for spacecraft breakup at hypervelocity impact

In the paper, to the question of spacecraft breakup at hypervelocity impact, the related model is developed to characterize the fragment size distribution. On the foundation of the spacecraft constitution analysis, the basic geometry body is used to depict the spacecraft geometrical shape, and based on the thin plate the spacecraft constitutive model is given. The projectile is equivalent to cylinder with round nose, then its length and velocity degraded model is given. The typical hole diameter models are surveyed and validated, on the basis of the proposed optimal one, the breakup domain producing fragment is modeled. The average fragment size equations are concluded, and the fragment size distribution is modeled as the power law relationship. The simulation case is analyzed, the result indicates that the paper model is effective and flexible, has important engineering reference value.