Огневые испытания материалов сопла ракетного двигателя

Л.М. Мустафа; М.Р. Нургужин; М.С. Джаникеев; И.К. Аблакатов; Б.М. Байсериков; А.Д. Байгонов; Б.С. Медянова; Р.Ш. Жунусов; Г. Партизан

doi:10.18321/cpc23(4)481-49

Authors

L.M. Mustafa National Center for Space Research and Technology, Shevchenko St., 15, Almaty, Kazakhstan
M.R. Nurguzhin National Center for Space Research and Technology, Shevchenko St., 15, Almaty, Kazakhstan
M.S. Dzhanikeyev National Center for Space Research and Technology, Shevchenko St., 15, Almaty, Kazakhstan
I.K. Ablakatov National Center for Space Research and Technology, Shevchenko St., 15, Almaty, Kazakhstan
B.M. Baiserikov National Center for Space Research and Technology, Shevchenko St., 15, Almaty, Kazakhstan
A.D. Baigonov National Center for Space Research and Technology, Shevchenko St., 15, Almaty, Kazakhstan
B.S. Medyanova National Center for Space Research and Technology, Shevchenko St., 15, Almaty, Kazakhstan
R.Sh. Zhunusov National Center for Space Research and Technology, Shevchenko St., 15, Almaty, Kazakhstan
G. Partizan National Center for Space Research and Technology, Shevchenko St., 15, Almaty, Kazakhstan

DOI:

https://doi.org/10.18321/cpc23(4)481-49

Keywords:

rocket engine, nozzle body, insert, thermal insulation, materials, steel, textolite, graphite

Abstract

This article presents the results of research on materials used in the nozzle section of a rocket engine. The study analyzed the properties of high-strength metal alloys, heat-resistant, and thermal insulation materials. A review of materials proposed for use in nozzle constructions was conducted. Three different materials were selected for experimental studies: structural steel 30KhGSA, textolite (grade A), and pressed graphite. To assess the thermal and erosion resistance of these materials, fire tests were conducted on a 70 mm caliber engine test stand. As a result of the tests, the level of erosion wear was determined in different nozzle zones: the converging section, the throat, and the diverging section. Changes in the geometric dimensions (diameter and angles) of nozzle components were monitored. The graphite material demonstrated the highest thermal and erosion resistance in the throat region. While steel materials are effective in terms of mechanical strength, and textolite is suitable as a thermal insulator, it was found to be significantly worn under high temperatures. Overall, the results of the conducted research can serve as a scientific and practical basis for designing and selecting materials for rocket engine nozzle blocks. The work provides recommendations for the proper selection of materials for small- and medium-caliber solid-fuel rocket engines.

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