The temperature dependence of oxidation behavior for the graphite IG-11, used in the HTR-
10, was investigated by thermogravimetric analysis in the temperature range of 400–1200° …

The modelling of ablation of carbon/carbon (C/C) composites utilized as rocket engine hot
parts is addressed under the angle of the competition between bulk transport of reactants …

GRAPHITE and carbon–carbon composites, which have excellent thermophysical properties
as well as low densities, are widely used as materials for rocket-nozzle inserts. The hostile …

Ablative materials are commonly used to protect the nozzle metallic housing and to provide
the internal contour to expand the exhaust gases in both solid and hybrid rockets. Because …

In order to enhance energy characteristics of propellants in hybrid rocket motors, aluminum
particles are added into the solid fuel. However, these particles may lead to nozzle …

THE erosion of rocket-nozzle materials during motor firings continues to be one of the major
hindrances in the advancement of solid-rocket propulsion. A noneroding nozzle is desired …

The erosion of the nozzle throat can represent one of the major limitations against the future
widespread use of hybrid rocket engines (HREs) in the space industry. In fact, nozzle …

This paper focuses on investigating ablation characteristics of different nozzle materials in
hybrid rocket motors by firing tests and numerical simulations. Hybrid rocket nozzles with …

Nozzle throat erosion in hybrid rocket engines is generally more emphasized than in solid
rockets due to a greater concentration of oxidizing species in the combustion products …

The interaction between a chemically reactive boundary layer and an ablative material is
one of the most challenging phenomena to model when predicting the heat load during …