Применение микрогибридных гетерогенных конденсированных систем для повышения энергетики ракетных двигателей

Abstract

The paper considers heterogeneous condensed systems which potentially make it possible to use highly efficient oxidizers in their composition, including those liquid. The existing technologies are unable to include them in composition of the solid rocket propellants. Placing oxidizers such as nitrogen dioxide and tetranitromethane in hermetically sealed combustible polymer capsules connected by physical or chemical means allows creating a microhybrid rocket engine. Studies based on analyzing characteristics of similar systems and thermodynamic calculations demonstrate that such systems are potentially able to ensure mechanical strength required for the rocket engine functioning, sufficient speed, combustion static stability and chemical compatibility of components, as well as power at the level of liquid high-boiling fuel vapors, while maintaining advantages of the solid fuel engines. Considering their initial higher safety in production and operation, as well as the ability to be produced by modern technologies, microhybrid rocket engines appear to be promising area of further research.