![]() ![]() ![]() Int J 3D Print Technol Digit Ind 6(1):83–101. Saracyakupoglu T, Delibas HD, Özcelik AD (2022) An experimental determination and numerical analysis of a loiter munition unmanned aerial vehicle system. (2020) Design and analysis of concept unmanned aerial vehicle. Sadraey MH (2016) Aircraft design: a system engineering approachĭemir R. Raymer D (2018) Aircraft design: a conceptual approach, Sixth Edition. Loitering Munitions: High Precision Systems. Gettinger D (2017) Loitering munitions in focus. ![]() This study carries a great deal of significance for the stability and especially control design engineers working in the domain of UAV design as it presents simple method for developing a complete 6-degree-of-freedom(6-DOF) FDM.Īileron deflection angle \(\delta _\textrm\) Furthermore, the designed control surfaces satisfy the critical requirements and are able to adequately follow and react to the input commands. The results indicate only a minor discrepancy between the stability results both the tools, with the overall aircraft being statically, and dynamically stable. Subsequently, the control integrated dynamics model is subjected to control input testing to evaluate the stability and control capabilities. In this paper, a strategy for computing the stability parameters of a small-scale loitering unmanned aerial vehicle (UAV) with a selected wing span employing two different stability analysis tools is presented, followed by the implementation of a sizing methodology for control surface sizing, which were selected as ailerons and ruddervators. Developing a suitable flight dynamics model (FDM) by assessing the stability and controllability characteristics of the aircraft is essential during the conceptual and preliminary design phase, as it enables us to proceed with further analysis of loads endured and maneuverability aspects. ![]()
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