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Paula Reis da Silva
Departamento de Engenharia Eletrônica e Telecomunicações, Faculdade de Engenharia, Universidade do Estado do Rio de Janeiro (UERJ), Rio de Janeiro, RJ
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Tiago Roux Oliveira
Programa de Pós Graduação em Engenharia Eletrônica, Faculdade de Engenharia, Universidade do Estado do Rio de Janeiro (UERJ), Rio de Janeiro, RJ
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Davi A. Santos
Departamento de Mecatrônica, Instituto Tecnológico de Aeronáutica (ITA), São José dos Campos, SP
Keywords:
attitude control, sliding mode control, experimental rocket
Abstract
This paper addresses the development and results of an attitude control system designed for an experimental rocket, built to have its rotational axes stabilized during the entire rocket’s ascent flight operation. To achieve this, its nonlinear equations of motion were developed, not considering aerodynamics coefficients and mass variation. Therefore, the control law was designed using the sliding mode control for the nonlinear equations, since it is a well- known robust control method. Simulations of the whole system were performed and the results were analyzed taking into account the expected results for the control system. Thus, all the results and knowledge obtained during this project offer an alternative to the most used control systems in real aerospace applications.
