Installation of a radiation-cooled nozzle of a carbon-carnonic composite material to the combustion chamber of main engine 11Д58МРБ ДМ-SL

A. V. Mezhevov; Межевов А. В.; V. I. Skoromnov; Скоромнов В. И.; A. V. Kozlov; Козлов А. В.; N. N. Tupitsin; Тупицын Н. Н.; V. G. Khaskekov; Хаспеков В. Г.

doi:10.18287/2541-7533-2006-0-2-2(10)-260-264

Installation of a radiation-cooled nozzle of a carbon-carnonic composite material to the combustion chamber of main engine 11Д58МРБ ДМ-SL

Authors: Mezhevov A.V.¹, Skoromnov V.I.¹, Kozlov A.V.¹, Tupitsin N.N.¹, Khaskekov V.G.¹
Affiliations:
1. S.P. Korolev Rocket and Space Corporation Energia, Korolev, Moscow region
Issue: Vol 5, No 2-2 (2006): Special Issue
Pages: 260-264
Section: TECHNICAL SCIENCES
URL: https://journals.ssau.ru/vestnik/article/view/420
DOI: https://doi.org/10.18287/2541-7533-2006-0-2-2(10)-260-264
ID: 420

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Abstract

A radiation cooling nozzle of a carbon-carbonic composite material is installed on main engine 11Д58М, which is used on the Upper Stage DM-SL as a part of the Zenit-3SL LV in the Sea Launch project. The specific impulse of the engine increased by 4 s through an increase of the nozzle geometric expansion ratio. The results of flight tests show a good convergence with design-theoretical and experimental data.