THERMAL PROTECTION SOLUTION FOR SOLID FUEL ROCKET ENGINES

Abstract

This paper presents a new approach to the thermal protection of solid-fuel rocket engines. The method of thermal protection using coatings not only reduces the risk of damage to the engine casing but also increases the engine’s efficiency in working. Parameters such as thrust and the mass per square meter of the engine casing are used to compare the differences between engines with and without thermal protection coating. Numerical calculation applied to the cruise engine of the rocket 9M39. Calculation results show that the thickness of the thermal protective coating and the thickness of the combustion chamber have been optimized regarding rocket weight. The survey results showed that the mass per square meter of the engine casing decreased by 2.5 times, and the engine’s impulse total increased by 1.13% when using the thermal protective coating. These results are used as data to develop methods to improve the performance of solid propellant rocket engines.