In this approach, the controller gain can be calculated using the dynamic parameters in the transfer function model and the desired characteristic equation. Gain tuning for the PID controller is accomplished using the pole placement technique. The fixed-wing UAV model is created using the Plane Maker software and is based on existing geometry and propulsion data from the literature. This research focuses on developing an automatic flight control system for a fixed-wing unmanned aerial vehicle (UAV) using a software-in-the-loop method in which the PID controller is implemented in National Instruments LabVIEW software and the flight dynamics of the fixed-wing UAV are simulated using the X-Plane flight simulator. Results show a reliable system mass estimation similar to the results obtained with other known methods and also providing the weight for each component individually. The whole system can now be sized more in detail during the preliminary design process, which allows to have a more reliable estimation and to perform systems installation analysis. The main advantage of this new methodology is that all the components and actuators can be properly sized instead of just having overall system results. A surrogate model for the hinge moment estimation is also proposed and used. The objective of this paper is to propose a new methodology for flight control system sizing, including mass and power estimation. Detailed information about the airfoil, wing surfaces, control surfaces, and actuators is needed but yet not known on early design phases. Hinge moments are difficult to estimate on the early stages of the design process due to the large number of required input. Hinge moments need to be estimated so that the actuators can be properly sized and their effects on the overall aircraft design are measured. This fact becomes even more important when developing more-electric aircraft. Actuator sizing is the key when comparing different flight control system architectures. Control surfaces include the ailerons, rudder, elevator, flaps, slats, and spoilers, and they are moved by electric or hydraulic actuators. These moments need to be estimated in order to properly size the aircraft actuators. As a result, hinge moments are generated. Flight control surfaces guarantee a safe and precise control of the aircraft.
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