Simulación de una computadora de vuelo para el control de un cohete sonda

Abstract

The present degree work seeks to complement the project that is being carried out by the RESEARCH SEED of the LOS LIBERTADORES UNIVERSITY FOUNDATION in its area of ​​Rocket, therefore it has as main objective to perform the simulation of the operating parameters of a flight computer that It will have the purpose of determining the actions necessary for the total control of a rocket probe, for this the parameters that affect the flight path were determined, which served to develop a simulation that determines the rocket's flight dynamics, involving the atmospheric model, gravitational, aerodynamic and dynamic that make up the final code. Then the basic principle of accelerometers and the mathematical development that governs and determines its operation are shown, thus establishing the output parameters that this device will have at the time of being implemented in the flight computer. With the principle of operation and the parameters established by the manufacturer, it is determined that the device is the optimum for the study in the present grade work, this being the model of Analog Devices ADXL 377 given its characteristics. When determining this, the implementation was carried out of the Simulink model of the ADXL 311 accelerometer provided by the manufacturer, to understand the behavior of the accelerometer and thus make the necessary modifications to obtain the ADXL377 accelerometer model that is the one selected for the project. Subsequently, the accelerometer model and the flight dynamics of the rocket are coupled, thus obtaining the necessary data to establish the design and programming parameters of the Accelerometer and the Microcontroller. Finally, the conceptual and preliminary design of all the parts necessary for the construction of the avionics rack and its location to optimize its operation is carried out.