FIELD: aviation.
SUBSTANCE: invention is related to space-rocket engineering, in particular to thrusters. Thruster chamber working on two-component anergolic gaseous fuel, comprises combustion chamber with nozzle and mixing head, pre-chamber with igniter, pipelines for supply of fuel components, besides mixing head includes a line of oxidiser supply, which represents radial channel connected to supplying pipeline passing in ring collector, communicated with channel-nozzles for supply of oxidiser into combustion chamber and with one or several longitudinal channels for supply of smaller part of oxidiser flow in pre-chamber, a line for fuel supply, which represents radial channel connected to pipeline passing in ring collector, communicated with channel-nozzles for supply of fuel in combustion chamber and channels with intermediate cavity installed on thruster combustion chamber communicated, on one side, with axial channel to pre-chamber, and on the other side communicated by axial channel-nozzle with combustion chamber. According to the second version mixing head includes a line for supply of oxidiser, which represents axial channel-nozzle connected by one end with pipeline of oxidiser supply and by other end communicated with combustion chamber and, by means of one or several radial openings in channel-nozzle wall, with a pre-chamber cavity, a line of fuel supply, which represents radial channel connected to fuel supply pipeline, passing in ring collector communicated to channels-nozzles for supply of fuel to combustion chamber and channels with ring intermediate cavity located on outer side of oxidiser channel-nozzle, which, on one side, is communicated with ring channel-nozzle to combustion chamber, and, on the other side, is communicated with one or several longitudinal channels to pre-chamber.
EFFECT: invention provides for reliable multiple start and operation of thruster at minimum expenses.
5 cl, 3 dwg
