Hall effect thrusters are used for space propulsion. The energy deposition on the inner surfaces of Hall effect thruster is analysed. Using a PIC MC 1D-3V model, the ion and electron exchanges of energy by bombardments are estimated in presence of a potential sheath near the surfaces and an electron secondary emission. Morever, simple expressions are deduced from the classic theory of non collisional potential sheath but without electron secondary emssion. A 3D ray-tracing method to determine the radiation energy deposition on the wall from visible and VUV optical ranges is presented. Key words: satellite, propulsion, Hall effect thrusters, plasma propulsion.

Авиационно-космическая техника и технология [Текст] : Научно-технический журнал // Авиационно-космическая техника и технология - Х. : Нац. аэрокосм. ун-т им. Н. Е. Жуковского "Харьк. авиац. ин-т". — Х. : Нац. аэрокосмический ун-т "ХАИ", 2012.

• УДК // Електричні ракетні двигуни. Плазмові, магнітогідродинамічні двигуни