@article{daSilvaMotaHinckelRoccoetal., author = {da Silva Mota, Fabio Antonio and Hinckel, Jose Nivaldo and Rocco, Evandro Marconi and Schlingloff, Hanfried}, title = {Modeling and Analysis of a LOX/Ethanol Liquid Rocket Engine}, series = {Journal of Aerospace Technology and Management}, volume = {10}, journal = {Journal of Aerospace Technology and Management}, publisher = {Inst Aeronautica \& Espaco-IAE}, doi = {10.5028/jatm.v10.914}, abstract = {This work studies the performance and dry mass of the under development LOX/Ethanol L75 liquid rocket engine. To this end, an object-oriented program written in C++ was developed. The program is intended to be versatile and easily extensible in order to analyze different configurations of liquid rocket engines. The UML (Unified Modeling Language) tool is used to model the architecture of the codes. UML diagrams help to visualize the code structure and the communication between objects, enabling a high degree of abstraction. The cryogenics Vulcain and HM7B engines power cycles along with the staged-combustion SSME engine perform the verification of the codes. Finally, the influence of changes in design parameters on the performance and dry mass of the L75 rocket engine is analyzed.}, language = {en} } @article{daSilvaMotaHinckelRoccoetal., author = {da Silva Mota, Fabio Antonio and Hinckel, Jose Nivaldo and Rocco, Evandro Marconi and Schlingloff, Hanfried}, title = {Trajectory Optimization of Launch Vehicles Using Object-oriented Programming}, series = {Journal of aerospace technology and management}, volume = {10}, journal = {Journal of aerospace technology and management}, publisher = {Institute of Aeronautics and Space}, doi = {10.5028/jatm.v10.948}, abstract = {The aim of this study is to model launch vehicles with focus on 3-DOF trajectory optimization using a modular approach. Despite the large number of operational launch vehicles, they usually consist of basic components and subsystems. In other words, a launch vehicle is an assembly of stages, which in turn is divided into propellant system and engine, and the engine is an assembly of basic components such as pumps, turbines, combustion chamber, and nozzle. To allow future extension and reuse of the codes, a modular structure using object-oriented programming is used. Two formulations of state equations of the trajectory and two optimization methods are described. The launch vehicle performance will be measured by payload mass for a given mission. The simulations of the VLS-1, Ariane 5 and VLS-Alfa were performed and showed good agreement with the literature.}, language = {en} }