Oxygen-methane torch ignition system for aerospace applications
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| Autor principal: | |
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| Data de Publicação: | 2020 |
| Outros Autores: | |
| Formato: | Artigo |
| Idioma: | eng |
| Fonte: | Repositório Institucional da UnB |
| Texto Completo: | https://repositorio.unb.br/handle/10482/43859 https://doi.org/10.3390/aerospace7080114 https://orcid.org/ 0000-0002-2934-1795 https://orcid.org/ 0000-0002-4105-6700 |
Resumo: | A new ignition system, based on a CH4/O2 torch has been developed by the Chemical Propulsion Laboratory of the University of Brasilia. Designed to ignite a hybrid rocket, this device has been improved to be used in testing of solid and liquid ramjet engines under development in our lab. The capability to provide multiple ignitions and to cool-down its combustion chamber walls by using a swirled injection of the oxidizer, along with a very low weight to power ratio, makes this device versatile. The igniter is controlled by a feedback system, developed by our group, which guarantees the possibility of operating in different design conditions enabling, therefore, complete integration with systems of different nature. The main characteristics of the igniter and the design solutions are presented including some considerations about the tests performed to evaluate the quality and performance of the ignition system. |