FIELD: engines and pumps.
SUBSTANCE: rocket engine comprises housing, propellant with blind channel, nozzle partially recessed in housing and annular igniter. The nozzle is provided with connection frame and structural elements with heat-protection coating. Note here that nozzle recessed part has heat-protection collar. Igniter case is secured to nozzle recessed part and has discharge holes, some of them directed to propellant blind channel and located on igniter case end side. Nozzle recessed part outer surface is shaped to cylinder. Heat protection of structural elements make igniter case fitted to rest upon joint frame and coupled with recessed part over cylindrical surface. Heat-protection collar is coupled with igniter case end.
EFFECT: decreased weight and overall dimensions.
4 cl, 1 dwg
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