ELECTRIC THERMAL MICRO ENGINE Russian patent published in 2012 - IPC F02K9/68 

FIELD: space-rocket technology.

SUBSTANCE: invention refers to space machinery, particularly to small weight satellite's propulsion systems. The micro engine contains cylindrical gas passage equipped with gas fuel input system and with two cylindrical flanges. These flanges are mounted on its external part with the shift from its ends. Micro engine is mounted inside of cylinder barrel with a cylinder shoulder near the bottom. A free end of the gas passage abuts to the bottom of cylindrical barrel. Length of micro drive is chose due to the sink of opposite cylindrical flange against the opened barrel's end. Electric heat elements are mounted between the cylindrical flanges outside the gas passage. The inner diameter of barrel is equal to the gas passage's cylindrical flanges outer diameter. Also the micro engine includes a barrel section which contacts barrel's cylindrical shoulder by inner diameter and its opened end by bottom's inner surface. The aperture for Laval nozzle is performed in the bottom and connected to the gas passage. Also the section bottom is performed with overhanded inner tapped cylindrical flange and with the shoulder. Laval nozzle is profiled and the nozzle cone end contacts with the cone surface that is performed on the gas passage's end. Section's cylindrical shoulders and Laval nozzles are connected with welding.

EFFECT: increasing of effectiveness of micro engine by volume impulse enlargement and construction simplification.

1 dwg, 11 dwg