Advancements in the XONE Rocket
All calculations are referential, obtained in ideal conditions used for the simulation of rocket engines. The engine was designed to work at the atmospheric level, with an escape pressure of 0.101 Mpa. The weight of the engine stage was also idealized, with a constant thrust, which does not occur under real conditions. Thus, some modifications were then made to all calculations.
The eXperimental engine ONE (XONE) was designed to produce an increment in speed of 1.1 km/s, required for the lunar module breaking of the Alicanto Team.
The engine will have two stages:
The first stage will be built as a prototype made of steel ASIS 316L, which has a high safety factor. We intend to use the experience learned in the creation of high gamma engines, validating the theoretical model and modifying possible design errors.
In this first stage, 2 types of propellants will be used. Due to the availability, ease of use and availability of information, an ammonium perchlorate based propellant with an isp of 160 was chosen. This selection was followed by a modification of the nozzle in order to adapt it to tests with the propellant, thus reaching an isp of 160.
After the validation of the theoretical model and the experimental data, we will proceed with the second stage. We will build a carbon fiber combustion chamber using the filament winding process, which will allow a decrease in weight of about 80% in relation with the first prototype.
The actual engine design