Un abordaje a los sistemas de propulsión aspirada basada en combustión supersónica “SCRAMJET”

Iván Felipe Rodríguez Barón; Jaime Enrique Orduy Rodríguez; Sergio Nicolás  Pachón Laiton

doi:10.24054/rcta.v3iEspecial.853

Authors

Iván Felipe Rodríguez Barón Fundación Universitaria los Libertadores
Jaime Enrique Orduy Rodríguez Fundación Universitaria los Libertadores
Sergio Nicolás Pachón Laiton Fundación Universitaria los Libertadores

DOI:

https://doi.org/10.24054/rcta.v3iEspecial.853

Keywords:

Air-Breathing, Hypersonic Aerothermodynamics, Mach number, Ramjet, Scramjet

Abstract

Rockets generally carry out Space missionswith approximately 97% to 98% of efficiency. The total weight of a rocket is approximately 95% propulsion system (fuel, oxidant and structure) and 5% payload, for this reason, the operating costs are quite high. Several research centres have been concerned with reducing weight of the propulsion system in terms of fuel and infrastructure. This article reflects a preliminary exploratory analysis of the concepts and characteristics that make up a propulsion system that can optimize fuel requirements and increase efficiency. The present work is divided into four parts, beginning with the introduction including the needs to look for a newtechnology in space missions. The second part deals with relevant historical aspects; in the third part,a description of the operation, the advantages and disadvantages of its implementation is made, finally, a discussion of the feasibility of Scramjet technology.

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