FIELD: space engineering.
SUBSTANCE: invention relates to liquid-propellant thrusters designed to control spacecraft and organization of mixing and combustion of liquid self-ignition components of propellant in low thrust engines (less than 3 N). Proposed chamber of thruster consists of mixing head body with channels to deliver components of propellant, coaxial two-component member installed in body and communicating with said channels, and combustion chamber. According to invention, two-component mixing member is made in form of two coaxial capillary tubes, at least one of tubes being made of plastically deformable material. End face part of outer tube can project into combustion chamber axially relative to inner tube, and outlet section of outer tube can be made narrowing. End pieces with holes of required section coaxial to tubes can be installed in outlet sections of capillary tubes.
EFFECT: provision of higher degree of liquid-phase mixing of oxidizer and propellant and uniform distribution of ratio of fuel components over section of combustion chamber, increased economy of engine.
6 cl, 3 dwg
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