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This article presents the work made with the solid propellant micro-thrusters in the MIS group (Microsystems and Systems Integration) at LAAS-CNRS (Laboratory for Analysis and Architecture of Systems) located in Toulouse (France). In first place the ignition process and thrust level were characterized, then, in a second part, its applicability over the station keeping of spatial missions was evaluated, specifically missions concerning either individual or a group (constellation) of small satellites (microsatellites, nano-satellites).

Micropropulsión basada en combustible sólido caracterización y aplicación en el control de conservación de órbita en pequeños satélites.