Control-oriented modeling of a Skywalker X8 unmanned aerial vehicle
[EN] The utility of unmanned aerial vehicles (UAVs) is evident, as shown by their multiple applications in various fields. Among these, fixed-wing drones are receiving increasing interest due to some of their advantages over the more well-known rotary UAVs, such as that they are faster and more suit...
| Autores: | , , |
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| Formato: | artículo |
| Fecha de publicación: | 2025 |
| País: | España |
| Recursos: | Universitat Politècnica de València (UPV) |
| Repositorio: | RiuNet. Repositorio Institucional de la Universitat Politécnica de Valéncia |
| Idioma: | inglés |
| OAI Identifier: | oai:riunet.upv.es:10251/227712 |
| Acesso em linha: | https://riunet.upv.es/handle/10251/227712 |
| Access Level: | acceso abierto |
| Palavra-chave: | Modelling Simulation Unmanned aerial vehicle (UAV) Fixed-wing Skywalker X8 Modelado Simulación Vehículo aéreo no tripulado (UAV) Ala fija |
| Resumo: | [EN] The utility of unmanned aerial vehicles (UAVs) is evident, as shown by their multiple applications in various fields. Among these, fixed-wing drones are receiving increasing interest due to some of their advantages over the more well-known rotary UAVs, such as that they are faster and more suitable for long-distance flights and for covering large areas, and they are more energy efficient. However, they can be unstable and require robust controllers for their operation. For the design of the control, it is essential to have mathematical and computational models of these complex and non-linear systems. In this work, the development of a dynamic model of a fixed-wing UAV, the Skywalker X8, is presented, as well as its simulation. The non-linear dynamic model obtained describes the behavior of the UAV in a realistic and complete way, taking into account that, as it does not have a tail, the aerodynamic surfaces of the UAV can behave as ailerons (antisymmetric deflection) or as elevators (symmetric deflection). The absence of a tail and the size of the UAV make it possible to separate longitudinal and lateral movements while maintaining their partial coupling. The inputs for the lateral model are the aileron deflection angle and the airspeed, while for the longitudinal model the propulsive force and the elevator deflection angle have been considered as inputs. To validate the UAV model, several simulations of realistic manoeuvres have been carried out. |
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