FIELD: space engineering. SUBSTANCE: liquid-propellant thruster has combustion chamber with injector and ignition unit, nozzle, external regenerative cooling passage and cooling component supply cavity which is formed in injector body and is connected with component supply manifold by means of pipe line. Manifold supplying the component to cooling passage is located on supercritical portion of nozzle. Surfaces forming the cooling component cavity are provided with turbulators made in form of transversal rectangular fins. EFFECT: enhanced operational reliability of thruster working on non-hypergolic propellant components at low mass flow rates at simultaneous increase of specific thrust pulse due to operation at more effective propellant component ratio. 2 cl, 2 dwg
