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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.142 SNIP: 0.16 CiteScore™: 0.29

ISSN Print: 2150-766X
ISSN Online: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2018023565
pages 165-174

HIGH-TEMPERATURE COATING: HYBRID ROCKET MOTOR THERMAL PROTECTION CASE HISTORY

Marcela Galizia Domingues
ITA – Instituto Tecnológico de Aeronáutica, Departamento de Química, Praça Marechal Eduardo Gomes, 50 - Vila das Acácias, São José dos Campos - SP, 12228-900, Brazil
José Atílio Fritz Fidel Rocco
ITA – Instituto Tecnológico de Aeronáutica, Departamento de Química, Praça Marechal Eduardo Gomes, 50 - Vila das Acácias, São José dos Campos - SP, 12228-900, Brazil

ABSTRACT

Most of the coatings available on the market do not meet the protection requirements of high temperatures and oxidation of metallic surfaces exposed to chemically aggressive environments at high temperatures. Thus, the development of an inorganic base coating (potassium silicate) was proposed in the form of an aqueous solution for application in hybrid rocket motor metallic components. This coating distinguishes itself from others by supporting extreme operating conditions of operation without degrading or losing its original characteristics, thus forming a glassy film which anchors in/on the surface of the substrate in which it is applied, i.e., becoming a superficial layer. The investigation of the applicability of a high-temperature coating was studied in adverse conditions, as in the case of a hybrid rocket motor; different components of the engine have received the coating application. Once coated, the components were assembled as a hybrid engine and subjected to firing tests. The results were very promising, since the coating could reduce the erosion in the throat of the nozzle by 50%, improving the hybrid rocket motor operation time at temperatures around 2.000 Celsius.


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