FIELD: engines and pumps.
SUBSTANCE: low-thrust rocket engine chamber comprises combustion chamber with nozzle and mixing head, prechamber with igniter, and fuel components feed pipelines. Mixing head comprises fuel and oxidiser feed pipelines communicated with components feed pipelines. Oxidiser feed pipeline comprises axial channel making a nozzle with its one end communicated with oxidiser feed pipeline. Axial channel wall has one or several radial bores to communicated with prechamber cavity and tails in auger to crease oxidiser swirled flow into combustion chamber. Fuel feed line comprises radial channel changing into annular manifold communicated via tangential channels with annular intermediate chamber arranged outside of axial channel communicates, on one side, with combustion chamber and, on opposite side, with, at least, one lengthwise channel provided with baffle. Axial channel making a nozzle communicating intermediate chamber with combustion chamber may be restricted by annular ledge made on outer wall of said axial channel.
EFFECT: reliable repeated start of engine at minimised engine weight.
