Computational and Experimental Investigation of Nozzle Plume Impingement for Detumbling Orbital Debris

Conical cold gas thrusters are characterized for a contactless method to detumble space debris using plume impingement. Vacuum chamber experiments and matching simulations using Computational Fluid Dynamics (for continuum flow within the nozzle) and Direct Simulation Monte Carlo (for rarefied flow inside the vacuum chamber) are performed to infer scaling laws of imparted force on a [Formula: see text] flat plate target as a function of plenum pressure, and the target’s axial and vertical displacement. The increase in vacuum chamber back pressure over time results in plume narrowing and an associated rise in pressure force experienced by the target. The simulations capture the rise and fall of the pressure force on the target in comparison with the experimental results, with the peak force discrepancy recorded to be less than 15% in the majority of cases, validating the reliability of the simulation tools for predicting plume impingement forces at related conditions and larger offset distances in a spacelike environment. The validated simulation tool highlights the challenges and constraints associated with the ground-based testing of orbital plume impingement.