Modeling and Simulation of an Octorotor UAV with Manipulator Arm
Edmundo Javier Ollervides-Vazquez,
Pablo A. Tellez-Belkotosky,
Victor Santibañez,
Erik G. Rojo-Rodriguez,
Luis A. Reyes-Osorio,
Octavio Garcia-Salazar
Affiliations
Edmundo Javier Ollervides-Vazquez
Aerospace Engineering Research and Innovation Center, Faculty of Mechanical and Electrical Engineering, Autonomous University of Nuevo Leon, Apodaca 66616, Nuevo Leon, Mexico
Pablo A. Tellez-Belkotosky
Aerospace Engineering Research and Innovation Center, Faculty of Mechanical and Electrical Engineering, Autonomous University of Nuevo Leon, Apodaca 66616, Nuevo Leon, Mexico
Victor Santibañez
Technological Institute of La Laguna-TecNM, Torreon 27000, Coahuila, Mexico
Erik G. Rojo-Rodriguez
Aerospace Engineering Research and Innovation Center, Faculty of Mechanical and Electrical Engineering, Autonomous University of Nuevo Leon, Apodaca 66616, Nuevo Leon, Mexico
Luis A. Reyes-Osorio
Aerospace Engineering Research and Innovation Center, Faculty of Mechanical and Electrical Engineering, Autonomous University of Nuevo Leon, Apodaca 66616, Nuevo Leon, Mexico
Octavio Garcia-Salazar
Aerospace Engineering Research and Innovation Center, Faculty of Mechanical and Electrical Engineering, Autonomous University of Nuevo Leon, Apodaca 66616, Nuevo Leon, Mexico
In this paper, the conceptual design, modeling, and simulation are proposed for an octorotor UAV with a manipulator arm. The conceptual design of the octorotor UAV with a manipulator arm is developed, and for the study and analysis, the design is implemented and validated in Matlab (Simulink-SimMechanics) software. The kinematics and dynamics models of the octorotor UAV with a manipulator arm are obtained using the classical Denavit–Hartenberg convention and the recursive Newton–Euler method, respectively. In this sense, a cascade PID controller for the attitude and navigation of the UAV and a simple PID controller for the manipulator arm are proposed and simulated in a closed-loop system in order to highlight the performance of the proposed design. Finally, simulations show the feasibility and behavior of the mathematical model and the flight controller in a closed-loop system.