| 摘要 |
FIELD: rocketry, applicable for rocket systems with oxygen-hydrogen-fuelled engines. ^ SUBSTANCE: the oxygen-hydrogen-fuelled engine installation has a body, combustion chamber coupled to a nozzle for exit of gases, a microporous structure is positioned in the combustion chamber, the structure is made of hollow microspheres and/or sealed hollow capillaries, a portion of which is filled with oxygen, and the other-with hydrogen. The microspheres and the capillaries may by made of combustible polymeric material. The capillaries may wound on an extension positioned along the installation axis. The microporous structure may be made of capillaries wound on an extension and located in the portion of the combustion chamber adjoining the engine body, and of microsphere filling the central portion of the chamber. The microporous structure may be made of capillaries located along the installation axis in the portion of the combustion chamber adjoining the engine body, and of microspheres filling the central portion of the chamber. Besides, the microporous structure may be made of microspheres perforated by capillaries. ^ EFFECT: reduced overall dimensions of the engine installation, enhanced explosion proofness. ^ 12 cl, 5 tbl |
