Development of modelling design tool for harpoon for active space debris removal

The level of debris in Earth orbit presents an increasing risk. Active removal, involving capture and deorbit larger items, has been identified as important controlling future population growth. One concept for capturing is a harpoon, with low post-penetration residual velocity being key design requirement. Aluminium sandwich panels are common structural components on typical spacecraft consequently probable target structure. An ideal harpooning event characterised complete penetration the panel harpoon (post penetration) velocity. This paper development numerical modelling tool active orbital removal. ability to predict ballistic limit aluminium honeycomb core representative large satellite element primary requirement tool. approach was validated against experimental results from normal oblique impact tests performed ogive flat nose projectiles over range between 50 m/s 120 m/s. based explicit finite method, using commercial LS-DYNA code. failure criterion used approximate material damage failure. Sensitivity studies were investigate influence model features projectile exit strongest face sheet projectile-panel friction model. exist velocities observed experiments select final parameters used. use deletion that incorporated stress triaxiality improved agreement plate deformation behaviour results. For projectile, agreed well angles considered. overestimated In case this due model's inability crushing ahead projectile.