Mechanical-impulse detumble dynamics and perforation energy model for the detumble and capture of tumbling space debris

The proliferation of space activity has significantly increased orbital debris, with rapid-tumbling targets posing a major challenge for active debris removal (ADR). Traditional ADR methods typically separate detumbling and capture phases, leading to increased mission complexity. While mechanical-impulse methods have been proposed to reduce angular momentum via projectile impacts, they risk projectile rebound and secondary debris generation. This study proposes an optimized solution: to the approach by equipping the projectile with harpoon-like penetrating heads, barbs and tethers. Upon impact, the projectile embeds in the target, preventing ricochet, enabling simultaneous detumbling and capture in a single engagement. This work focuses on modeling the impact dynamics and perforation energetics to predict post-impact angular velocity reduction. Specifically, we develop (1) a dynamic equilibrium formulation for predicting post-impact velocities in normal and oblique collisions; (2) quasi-static analytical perforation-energy models for petaling and plugging failure modes in aluminum honeycomb sandwich panels; and (3) a novel free-spin-target impact test method that emulates in-orbit projectile strikes against spinning debris in a controlled ground environment. Experimental results validate the theoretical predictions and confirm the effectiveness of the proposed system. Tests reveal that flat and v-groove projectiles induce plugging failures, while conical, ogival, and spherical heads favor petaling under low obliquity, transitioning to intermediate modes at steeper angles. The models reliably predict perforation energy and its relationship to angular momentum transfer. This integrated detumble-and-capture concept presents a robust and efficient pathway for future ADR missions targeting non-cooperative, tumbling space debris.