1. Diseño Conceptual de un Cohete de Tres Etapas Para Transportar Una Carga Útil De 200 kg A Una Órbita Baja.
- Author
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Ospina Contreras, Daimer and Roldán Torres, Luis Carlos
- Subjects
- *
LAUNCH vehicles (Astronautics) , *HEAT of combustion , *ROCKET fuel , *COMBUSTION chambers , *CONCEPTUAL design , *SPECIFIC heat - Abstract
This article presents the conceptual design of a three-stage rocket to carry 200 kg payload to low Earth orbits (by the acronym LEO). From a case study of the fight path of a three-stage rocket with solid propellants, proceed to select the propellant mixture that meets the design requirements and path raised fight, taking into account that it can produce nationwide. The propellant thermochemical behavior is obtained with CPROPEP software. Knowing the values of pressure, temperature and specific heat ratio in the combustion chamber proceeds to design rocket engines to ensure total velocity change in the system equivalent to those obtained in the analysis of the fight path. With the design of the propulsion duct materials that withstand the thermal loads and pressure, to give way to structural design giving an approximation of carrier rocket are chosen. [ABSTRACT FROM AUTHOR]
- Published
- 2020
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