Ablation behaviour of C/C–ZrC composites in a solid rocket motor environment
Source abstract
Abstract
Abstract Ablation of C/C–ZrC composites in a solid rocket motor environment was investigated. The chemical compositions of the combustion gases were calculated using the principle of free energy minimisation. The chemical thermodynamics of the products of the reactions between the combustion gases and ZrC were studied using the FactSage software. The results show that H 2 O, CO 2 , and OH are the main oxidising species that consume ZrC/carbon, and the oxidation of ZrC reduces carbon consumption. In addition, melting and evaporation of ZrO 2 absorb heat from the combustion gases, relieving the erosive attack on carbon. The ablation of C/C–ZrC composites is controlled by both thermal chemical ablation and mechanical breakage. The cone-shaped fibres and shell-shaped, honeycomb matrix are attributed to thermal chemical ablation, whereas the carbon fragments result from mechanical breakage.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Energetic Materials and Combustion · Rocket and propulsion systems research · Thermal and Kinetic Analysis
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
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