Polymeric Ablative Composite Materials and their Application in the Manufacture of Aerospace Propulsion Components
The development of thermal protection systems and high-temperature composite materials for the manufacture of low-weight propulsion components represents a major challenge for the aerospace industry, especially in the field of rocketry. The rocket combustion chamber and nozzles must be designed to w...
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Universidad Pedagógica y Tecnológica de Colombia
2020
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| Online Access: | https://revistas.uptc.edu.co/index.php/ingenieria/article/view/10662 |
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| author | Robayo-Salazar, Rafael Portocarrero-Hermann, Julián Díaz-Padrón, Ubaldo Patiño-Castrillón, Oscar |
| author_facet | Robayo-Salazar, Rafael Portocarrero-Hermann, Julián Díaz-Padrón, Ubaldo Patiño-Castrillón, Oscar |
| author_sort | Robayo-Salazar, Rafael |
| collection | OJS |
| description | The development of thermal protection systems and high-temperature composite materials for the manufacture of low-weight propulsion components represents a major challenge for the aerospace industry, especially in the field of rocketry. The rocket combustion chamber and nozzles must be designed to withstand operating temperatures above 1600-2000 ° C in a severe ablative environment. This research focuses on obtaining a characterization of ablative composite materials based on a polyester resin matrix (30%) reinforced with particulate materials (fillers) (67%) and short glass fibers (3%), highlighting that the fillers correspond to industrial waste or by-products such as steel slag, aluminum slag, foundry slag and ceramic waste. The composites were physically and mechanically characterized and subjected to an ablative direct flame test (~1600-2000 °C, 120 seconds), reporting thermal insulation levels between 72.6-92.9%, with maximum temperatures on the opposite side of the flame between 141.6-548.8 ° C, and post-ablative weight losses of between 8.5-13.2%. Based on the obtained results, the optimal composites were selected and their application was validated in the manufacture of rocket-type nozzle propulsion components, which were subjected to a real static combustion test, using a solid propellant Candy KNSu type (65 % KNO3-35% Sucrose). The results proved the possibility of obtaining ablative composites and thermal protection systems from available materials and high contents of industrial by-products. These applications are considered important to develop the Colombian aerospace field in the construction of sounding rockets for scientific, technological, and military purposes. |
| format | Online |
| id | oai:oai.revistas.uptc.edu.co:article-10662 |
| institution | Revista Facultad de Ingeniería |
| language | spa |
| publishDate | 2020 |
| publisher | Universidad Pedagógica y Tecnológica de Colombia |
| record_format | ojs |
| spelling | oai:oai.revistas.uptc.edu.co:article-106622022-06-15T15:57:47Z Polymeric Ablative Composite Materials and their Application in the Manufacture of Aerospace Propulsion Components Materiales compuestos ablativos de matriz polimérica y su aplicación en la fabricación de componentes de propulsión aeroespacial Robayo-Salazar, Rafael Portocarrero-Hermann, Julián Díaz-Padrón, Ubaldo Patiño-Castrillón, Oscar ablative materials composite materials propulsion components rocket engine rocket nozzle thermal protection systems materiales compuestos materiales ablativos sistemas de protección térmica motor cohete componentes de propulsión tobera The development of thermal protection systems and high-temperature composite materials for the manufacture of low-weight propulsion components represents a major challenge for the aerospace industry, especially in the field of rocketry. The rocket combustion chamber and nozzles must be designed to withstand operating temperatures above 1600-2000 ° C in a severe ablative environment. This research focuses on obtaining a characterization of ablative composite materials based on a polyester resin matrix (30%) reinforced with particulate materials (fillers) (67%) and short glass fibers (3%), highlighting that the fillers correspond to industrial waste or by-products such as steel slag, aluminum slag, foundry slag and ceramic waste. The composites were physically and mechanically characterized and subjected to an ablative direct flame test (~1600-2000 °C, 120 seconds), reporting thermal insulation levels between 72.6-92.9%, with maximum temperatures on the opposite side of the flame between 141.6-548.8 ° C, and post-ablative weight losses of between 8.5-13.2%. Based on the obtained results, the optimal composites were selected and their application was validated in the manufacture of rocket-type nozzle propulsion components, which were subjected to a real static combustion test, using a solid propellant Candy KNSu type (65 % KNO3-35% Sucrose). The results proved the possibility of obtaining ablative composites and thermal protection systems from available materials and high contents of industrial by-products. These applications are considered important to develop the Colombian aerospace field in the construction of sounding rockets for scientific, technological, and military purposes. El desarrollo de sistemas de protección térmica y materiales compuestos de alta temperatura para la fabricación de componentes de propulsión de bajo peso representa un reto importante para la industria aeroespacial, especialmente en el campo de la cohetería. La cámara de combustión del cohete, propulsores y boquillas deben diseñarse para soportar temperaturas de trabajo superiores a los 1600-2000 °C en un ambiente ablativo severo. Esta investigación se enfoca en la obtención y caracterización de materiales compuestos ablativos basados en una matriz de resina poliéster (30%) reforzada con materiales particulados (fillers) (67%) y fibras cortas de vidrio (3%); destacando que los fillers corresponden a residuos o subproductos industriales tipo escoria siderúrgica, escoria de aluminio, escoria de fundición y residuo cerámico. Los compuestos fueron caracterizados físico-mecánicamente y sometidos a un ensayo ablativo de llama directa (~1600-2000 °C, 120 segundos), reportando niveles de aislamiento térmico de entre 72.6-92.9%, con temperaturas máximas en la cara opuesta a la llama de entre 141.6-548.8 °C, y pérdidas de peso posteriores al ensayo ablativo de entre 8.5-13.2%. Con base en los resultados obtenidos, se eligieron los compuestos óptimos y su aplicación fue validada en la fabricación de componentes de propulsión tipo toberas de motor-cohete, las cuales fueron sometidas a una prueba estática de combustión real utilizando un propelente sólido tipo Candy KNSu (65%KNO3-35%Sucrosa). Los resultados obtenidos demostraron la posibilidad de producir compuestos ablativos y sistemas de protección térmica a partir de materiales de fácil adquisición y altos contenidos de subproductos industriales; aplicaciones que se consideran de suma importancia para desarrollar el campo aeroespacial colombiano en la construcción de cohetes de sondeo con fines científicos, tecnológicos y militares. Universidad Pedagógica y Tecnológica de Colombia 2020-05-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf application/xml https://revistas.uptc.edu.co/index.php/ingenieria/article/view/10662 10.19053/01211129.v29.n54.2020.10662 Revista Facultad de Ingeniería; Vol. 29 No. 54 (2020): Continuos Publication; e10662 Revista Facultad de Ingeniería; Vol. 29 Núm. 54 (2020): Publicación Continua; e10662 2357-5328 0121-1129 spa https://revistas.uptc.edu.co/index.php/ingenieria/article/view/10662/9330 https://revistas.uptc.edu.co/index.php/ingenieria/article/view/10662/9506 Copyright (c) 2020 Rafael Robayo-Salazar; Julián Portocarrero-Hermann; Ubaldo Díaz-Padrón; Oscar Patiño-Castrillón |
| spellingShingle | ablative materials composite materials propulsion components rocket engine rocket nozzle thermal protection systems materiales compuestos materiales ablativos sistemas de protección térmica motor cohete componentes de propulsión tobera Robayo-Salazar, Rafael Portocarrero-Hermann, Julián Díaz-Padrón, Ubaldo Patiño-Castrillón, Oscar Polymeric Ablative Composite Materials and their Application in the Manufacture of Aerospace Propulsion Components |
| title | Polymeric Ablative Composite Materials and their Application in the Manufacture of Aerospace Propulsion Components |
| title_alt | Materiales compuestos ablativos de matriz polimérica y su aplicación en la fabricación de componentes de propulsión aeroespacial |
| title_full | Polymeric Ablative Composite Materials and their Application in the Manufacture of Aerospace Propulsion Components |
| title_fullStr | Polymeric Ablative Composite Materials and their Application in the Manufacture of Aerospace Propulsion Components |
| title_full_unstemmed | Polymeric Ablative Composite Materials and their Application in the Manufacture of Aerospace Propulsion Components |
| title_short | Polymeric Ablative Composite Materials and their Application in the Manufacture of Aerospace Propulsion Components |
| title_sort | polymeric ablative composite materials and their application in the manufacture of aerospace propulsion components |
| topic | ablative materials composite materials propulsion components rocket engine rocket nozzle thermal protection systems materiales compuestos materiales ablativos sistemas de protección térmica motor cohete componentes de propulsión tobera |
| topic_facet | ablative materials composite materials propulsion components rocket engine rocket nozzle thermal protection systems materiales compuestos materiales ablativos sistemas de protección térmica motor cohete componentes de propulsión tobera |
| url | https://revistas.uptc.edu.co/index.php/ingenieria/article/view/10662 |
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