Conceptual Design of a Three-stage Rocket to Tansport a Load of 200 kg to a Low Orbit

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. keywords: Cohete, empuje, motor cohete, órbita baja de la Tierra (LEO), propelente.