Abstract: The explosion breakup debris distribution of the cylindrically simulated satellite with thin-walled aluminum alloy is researched by the sandpit retrievable experiment and theoretical analysis. The experimental results show that the explosion breakup behavior of simulated satellite is significantly influenced by the wall thickness and the residual propellant mass. The amount of explosion breakup debris increases with the decrease in wall thickness and the increase in residual propellant mass. Moreover, the explosion breakup debris mass shows a wide range from less than 0.2 g particles to more than 100 g irregular debris. By incorporating the experimental results into the covered explosive explosion breakup model and simulated satellite low intensity explosion breakup model, respectively, both the amount and mass distribution models of simulated satellite explosion breakup debris are presented, contributing to the assessment of satellite breakup debris distribution characteristics in accident.

Key words: spacecraft structure and design, space debris, simulated satellite, debris distribution, explosion breakup