Controle por modos deslizantes de quadcóptero com carga suspensa por cabo para trajetórias baseadas na propriedade de planicidade diferencial do sistema e input shaping

• Ano de defesa: 2019
• Autor(a) principal: Araújo, Mateus Amarante
• Tipo de documento: Dissertação
• Tipo de acesso: Acesso aberto
• Idioma: por
• Instituição de defesa: Universidade Federal de Uberlândia; Brasil; Programa de Pós-graduação em Engenharia Mecânica
• Palavras-chave em Português: Controle por modos deslizantes; Sliding mode control; Sistemas diferencialmente planos; Differentially flat systems; Moldagem de entrada; Input shaping; Sistemas sub-atuados; Underactuated systems; Transporte de carga aéreo; Aerial load transportation; Engenharia mecânica; CNPQ::ENGENHARIAS::ENGENHARIA MECANICA; CNPQ::ENGENHARIAS::ENGENHARIA AEROESPACIAL::DINAMICA DE VOO::ESTABILIDADE E CONTROLE; CNPQ::OUTROS::ENGENHARIA MECATRONICA
• Link de acesso: https://repositorio.ufu.br/handle/123456789/29031; http://doi.org/10.14393/ufu.di.2019.2548

In the context of high demand for autonomous aircrafts in cargo transport applications, this work presents a motion control and trajectory generation solution for a system composed of a quadrotor with a cable-suspended load that aims to control the aircraft position and reduce the load swing. First, the dynamic model of the system is derived using the Newton-Euler and Euler-Lagrange methods and divided into two parts: a fully actuated subsystem associated with the robot altitude and yaw angle, and an underactuated subsystem associated with the other state variables of the quadrotor. Each subsystem is controlled by a sliding mode controller which is proved to be stable in Lyapunov's sense for the task of driving the system to the sliding surfaces and staying on them. It is demonstrated by the Routh-Hurwitz stability criterion that the sliding surfaces associated with the underactuated subsystem are locally stable given some constraint rules obtained for the control parameters that make the tuning process easier. Finally, a new trajectory generation structure is proposed to suppress the load balance which consists on build a polynomial trajectory for the load, apply input shaping on it and compute the desired state of the aircraft by making use of the differential flatness property of the system. The controller is tested together with the designed trajectory generator in simulation for a point-to-point trajectory and for different durations. The controller is effective in controlling the aircraft state even when no filter is applied to the input reference and the trajectory generator greatly reduces the load swing. However, the aircraft trajectory obtained by the differentially flat model becomes prohibitive for the controller when the reference speed and acceleration reach certain limits for which the alternative solution of only applying input shaping to the aircraft trajectory presents moderate performance.