CHAMBER OF LIQUID PROPELLANT LOW-THRUST ROCKET ENGINE

摘要

FIELD: rocket engineering. SUBSTANCE: proposed chamber contains combustion chamber with nozzle and mixing head housing with fitted on coaxial centrifugal injectors. Spaces of injectors are connected with manifolds of corresponding components of propellant. Manifold of outer injectors communicates with jet injectors uniformly spaced over circumference. Tangential channel feeding propellant components into swirl chambers of outer and inner injectors are made in form of slots in flat ring plates installed in planes perpendicular to axes of swirl chamber. Manifold of inner injectors is coupled by thermal bridge with space of combustion chamber. EFFECT: improved preparation of propellant, simplified design and process of manufacture of chamber for liquid-propellant low-thrust engine. 4 cl, 3 dwg