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AssigneeOffice National d'Etudes et de Recherches Aerospatiales
InventorsVictor DESANGLES, Denis PACKAN, Simon PETERSCHMITT, Julien JARRIGE, Paul-Quentin ELIAS
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The invention relates to a satellite thruster that employs electron cyclotron resonance and a magnetic nozzle, that extends at least partially along a longitudinal axis (X), and that includes an external conductor and an ionization chamber, the external conductor and the ionization chamber extending longitudinally along this axis, the external conductor bounding the ionization chamber transversely, and the ionization chamber comprising a circular transverse aperture having a diameter D, characterized in that it further comprises a screen coaxial with the longitudinal axis (X), having a maximum transverse dimension D′ such that the ratio of D′ divided by D is between 3 and 15, said screen including a portion made of dielectric material and/or a portion made of electrically conductive material.
A satellite thruster with electron cyclotron resonance and magnetic nozzle, extending at least partially along a longitudinal axis, comprising an outer conductor and an ionization chamber, the outer conductor and the ionization chamber extending longitudinally along this axis, the outer conductor transversely delimiting the ionization chamber, the ionization chamber including a circular transverse opening including a diameter D, wherein the thruster further includes a screen coaxial to the longitudinal axis, including a maximum transverse dimension D′ such that the ratio of D′ divided by D is between 3 and 15, said screen including a part made of dielectric material and a part made of electrically conductive material, the part made of dielectric material covering the part made of conductive material, or said screen being entirely made of dielectric material.
Dependencies are inferred from the claim text.