DART project
The DART project that revolves around the design and creation of a solid propellant rocket model. The ultimate goal of the project is to reach 2500m of apogee.
The DART project deals with the development and construction of a model rocket that aims to break the record of 2500m apogee for an amateur carrier, equipped with a solid propellant engine consisting of 65% of KNO3 and 35% of sorbitol, capable of generating up to 1500 [N] with a maximum chamber pressure of 10 [Mpa].
Since the birth of the project in 2017, the changes have been many as the choice to use a modular engine in order to simplify the construction of the propellant and optimize the trend of the thrust. The structure department has therefore sized both the combustion chamber, steel E355 material, and the nozzle, steel AISI-420C material, considering the high pressures and high operating temperatures, through all phases of ignition, speed and shutdown of the engine. The carrier body has been designed so as to be light and durable, using the fiberglass as a material, so as not to create interference to the sensor board.
The studies carried out by the aerodynamics department through the software STAR CCM+ have allowed to study the individual components at different speeds and inclinations in order to evaluate their behavior in all possible cases. The configuration shown has been developed together with the flight mechanics department, which has the lowest possible aerodynamic resistance combined with excellent flight stability. In addition, the simulation of the entire flight, through the Simulink software, allowed us to establish the critical points of the mission.
To date an engine test has been carried out (equipped with a simply converging nozzle) which partially validated the ideal results obtained and showed the problems on which the whole team must work. In October 2021, a second engine test will be carried out (this time with a converging-diverging nozzle) to which modifications have been made in order to meet the required performance levels. With the support of the IT area, we hope to soon be able to achieve the goal of building the rocket model complete with the recovery system and electronics necessary for telemetry, fundamental systems for the success of our launch.
