FLANGE OF ROTATING NOZZLE OF ROCKET ENGINE FROM COMPOSITE MATERIALS AND MANUFACTURING METHOD OF ROTATING NOZZLE FLANGE OF ROCKET ENGINE FROM COMPOSITE MATERIALS Russian patent published in 2011 - IPC F02K9/97 B32B3/12 B29C53/56 

FIELD: engines and pumps.

SUBSTANCE: flange of rotating nozzle of rocket engine from composite materials includes mesh housing consisting of diagonal and circumferential ribs made from intersecting harnesses, front, support and rear circular frames. Front and rear frames are arranged inside multi-layer plastic profiles, and support frame is provided with cloths made from composite material, which are located between layers of harnesses. Ribs of housing in the section from front frame to support frame are equipped on the outer side with tight cover with warmth-keeping coating. In support frame there made are axial holes located above intersection of diagonal ribs with front edge located on the edge interfacing with engine flange, after the housing, and with rear edge - inside housing wall dimension with intersection of hole axis and middle cone-shaped surface of mesh wall of the housing inside the frame width. Flange manufacturing method involves installation of multi-layer profiles of rear and front circular frames on cone-shaped mandrel and routing tightly to profiles of separating layer of rubber-like material with provision of diagonal and circular grooves in it and profiles, as well as groove of support frame. Then, winding of harnesses of diagonal and circular ribs and frames is performed by being laid in groove of support frame of cloth, and heat treatment is made. After heat treatment in the front edge of support frame there made are axial holes with penetration of cutting tool in front edge above intersection of diagonal ribs and outlet in rear edge within the cell clearance of mesh structure inside housing wall dimension with intersection by means of axis of the tool of cone-shaped middle surface of the housing wall to the outlet of cutting tool.

EFFECT: inventions allow improving manufacturability and reliability of flange of rotating nozzle of rocket engine and reducing its weight.

11 cl, 12 dwg