@Article{OspinaContrerasRold:2020:CoDeTh,
author = "Ospina Contreras, Daimer and Roldan Torres, Luis Carlos",
affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and
{Universidad San Buenaventura}",
title = "Conceptual design of a three-stage rocket to transport a load of
200kg to a loworbit",
journal = "Tecciencia",
year = "2020",
volume = "15",
number = "29",
pages = "1--8",
keywords = "Rocket, rocket engine, low earth orbit, propellant.",
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 flight path of a three-stage rocket
with solid propellants, proceed to select the propellant mixture
that meets the design requirements and path raised flight, 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 flight 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.",
doi = "10.18180/tecciencia.2020.29.1",
url = "http://dx.doi.org/10.18180/tecciencia.2020.29.1",
language = "en",
urlaccessdate = "2024, Apr. 20"
}