Design and Thermomechanical Evaluation of Polymer Matrix Ablative Composite Materials for Rocket Motor Nozzles
| dc.creator | Candela-Rengifo, Valentina | |
| dc.creator | Robayo-Salazar, Rafael | |
| dc.creator | Portocarrero Hermann, Julián | |
| dc.creator | Rojas, Gustavo Adolfo | |
| dc.creator | Salgado Díaz, Jonathan | |
| dc.date | 2025-11-19 | |
| dc.description | Rocket propulsion systems require materials with high thermal resistance and low density for rocket-motor nozzles, where polymeric ablative composite materials (PACM) emerge as a low-cost alternative. This research aimed to design and characterize polymer matrix ablative composite materials (PACM) based on a polyester resin modified with ceramic particulates (refractory brick and quartz) and synthetic fibers (glass and carbon). The methodology included physical tests (density), mechanical tests (compression, tensile, flexural, and impact strength), thermal tests (thermogravimetric analysis, thermal conductivity, and direct flame resistance), and scanning electron microscopy. The results highlighted that PACMs exhibit densities ranging from 1.22 to 1.67g/cm³ and thermal insulation values between 83% and 90% when exposed to a propane gas flame at 1600–2000°C for 120 seconds, a condition simulating the combustion of a sounding rocket motor during a low-altitude flight. Additionally, thermo-mechanical simulation using Ansys software demonstrated that the designed PACMs can withstand the thermal conditions experienced during rocket motor combustion. However, for nozzles with a 7 mm thick ablative zone, an external carbon fiber reinforcement of 2.5 mm thickness is required to endure the mechanical stresses generated by the high exhaust pressure. In conclusion, PACMs can be employed in the manufacturing of propulsion components such as nozzles using readily available materials, which are also lighter than conventional refractory metals and superalloys, thereby contributing to the development of experimental rocketry missions in emerging countries such as Colombia. | en-US |
| dc.description | Los sistemas de propulsión de cohetes demandan materiales con alta resistencia térmica y baja densidad para las toberas de motor cohete, donde los materiales compuestos ablativos de matriz polimérica (PACM, por sus siglas en inglés) surgen como alternativa de bajo costo. Esta investigación tuvo como objetivo el diseño y caracterización de PACM basados en una resina poliéster modificada con particulados cerámicos (ladrillo refractario y cuarzo) y fibras sintéticas (de vidrio y de carbono). La metodología empleada incluyó la realización de ensayos físicos (densidad), mecánicos (resistencia a la compresión, tracción, flexión e impacto), térmicos (análisis termogravimétrico, conductividad térmica y resistencia a la llama directa) y microestructurales (microscopía electrónica de barrido). Entre los resultados obtenidos se destacó que los PACM poseen densidades de entre 1,22–1,67 g/cm3 y valores de aislamiento térmico de entre 83–90 % cuando son sometidos a la incidencia de una llama de gas propano de 1600–2000°C durante 120 s; condición que simula la combustión de un motor de cohete tipo sonda durante un vuelo de baja altura. Complementariamente, a partir de una simulación termomecánica en el software Ansys se logró establecer que los PACM diseñados soportan las condiciones térmicas a las cuales son sometidos durante la combustión del motor cohete. Sin embargo, para toberas con zona ablativa de 7 mm de espesor es necesario emplear un revestimiento (refuerzo) exterior de fibra de carbono de 2,5 mm de espesor para soportar los esfuerzos mecánicos generados por la alta presión de salida de los gases de combustión. Finalmente, se concluye que los PACM pueden ser utilizados para la manufactura de componentes de propulsión tipo toberas con materiales de fácil adquisición e inclusive más livianos que los convencionales (metales refractarios y superaleaciones), lo que contribuiría al desarrollo de misiones de cohetería experimental en países emergentes como Colombia. | es-ES |
| dc.format | application/pdf | |
| dc.format | text/xml | |
| dc.format | application/epub+zip | |
| dc.format | text/html | |
| dc.identifier | https://revistas.itm.edu.co/index.php/tecnologicas/article/view/3318 | |
| dc.identifier | 10.22430/22565337.3318 | |
| dc.language | spa | |
| dc.publisher | Instituto Tecnológico Metropolitano (ITM) | en-US |
| dc.relation | https://revistas.itm.edu.co/index.php/tecnologicas/article/view/3318/3811 | |
| dc.relation | https://revistas.itm.edu.co/index.php/tecnologicas/article/view/3318/3901 | |
| dc.relation | https://revistas.itm.edu.co/index.php/tecnologicas/article/view/3318/3902 | |
| dc.relation | https://revistas.itm.edu.co/index.php/tecnologicas/article/view/3318/4012 | |
| dc.relation | https://revistas.itm.edu.co/index.php/tecnologicas/article/view/3318/4094 | |
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| dc.rights | Copyright (c) 2025 TecnoLógicas | en-US |
| dc.rights | https://creativecommons.org/licenses/by-nc-sa/4.0 | en-US |
| dc.source | TecnoLógicas; Vol. 28 No. 64 (2025); e3318 | en-US |
| dc.source | TecnoLógicas; Vol. 28 Núm. 64 (2025); e3318 | es-ES |
| dc.source | 2256-5337 | |
| dc.source | 0123-7799 | |
| dc.subject | ciencia y tecnología de materiales | es-ES |
| dc.subject | cohetes, materiales aeroespaciales | es-ES |
| dc.subject | materiales compuestos | es-ES |
| dc.subject | propulsión aeroespacial | es-ES |
| dc.subject | materials science and technology | en-US |
| dc.subject | rockets | en-US |
| dc.subject | aerospace materials | en-US |
| dc.subject | composite materials | en-US |
| dc.subject | aerospace propulsion | en-US |
| dc.title | Design and Thermomechanical Evaluation of Polymer Matrix Ablative Composite Materials for Rocket Motor Nozzles | en-US |
| dc.title | Diseño y evaluación termomecánica de materiales compuestos ablativos de matriz polimérica para toberas de motor cohete | es-ES |
| dc.type | info:eu-repo/semantics/article | |
| dc.type | info:eu-repo/semantics/publishedVersion | |
| dc.type | Research Papers | en-US |
| dc.type | Artículos de investigación | es-ES |
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