FIELD: rocketry. SUBSTANCE: wall of proposed exit nozzle contains great number of cooling channels 5 arranged close to each other and passing mainly from inlet end of exit nozzle to its outlet end. Proposed method of designing of nozzle includes mounting of outer wall 3 in preset position around inner wall 2, forming of great number of spacing elements 4 and arranging them between said outer wall 3 and said inner wall 2 and connecting spacing elements 4 between outer wall and inner wall, thus forming cooling channels 5. Connections are made by laser welding with formation of welds 9 of such form at which said welds in cross section of wall are mainly T-shaped, with form 10 rounded off in direction of inner side of cooling channels 5. EFFECT: provision of improved method of manufacture of exit nozzle, reduced weight, cut down expenses in manufacture and optimum cooling characteristics. 7 cl, 5 dwg
