Performance analysis of mini-propellers based on FlightGear

This paper presents a performance analysis of three mini-propellers based on the FlightGear flight simulator. Although a basic propeller analysis has to be performed before the use of FlightGear, for a complex and more practical performance analysis, it is advantageous to use a propeller model in cooperation with a particular aircraft model. This approach may determine whether the propeller has sufficient quality in respect of aircraft requirements. In the first section, the software used for the analysis is illustrated. Then, the parameters of the analyzed mini-propellers and the tested UAV are described. Finally, the main section shows and discusses the results of the performance analysis of the mini-propellers. © 2016 Author(s)

Conceptual design and control of twin-propeller tail-sitter mini-UAV: Conceptual study of V-TS mini-UAV

This paper describes progress made on the design and analysis of a twin-propeller tail-sitter mini-UAV (named V-TS). Since the V-TS mini-UAV is a combination of airplanes and copters, high energy efficiency during the forward flight and VTOL capability in the hover flight are achieved. However, this configuration also brings new challenges and difficulties, especially in the case of control. Free software which was used in the design process is presented and described. AVIGLE Demonstrator is analyzed in SU2 to verify correct settings of the aerodynamic analysis. Furthermore, 3D model of the V-TS mini-UAV with the Y-tail configuration and its basic geometrical parameters are shown. The results prove that it is aerodynamically efficient for our purpose. In addition, probably all control modes, transitional flight phases, and difficulties which appear in the control of the twin-propeller tail-sitter mini-UAV are defined and solutions are proposed. The transitional flight phases are determined as a combination of the control modes and sub-modes. © 2019, Deutsches Zentrum für Luft- und Raumfahrt e.V

Application for calculation of mean aerodynamic chord of arbitrary wing planform

This paper presents an application for the calculation of the mean aerodynamic chord (MAC) of an arbitrary wing planform. The MAC is most often used in the aerodynamic and stability analysis. The calculation uses a method where the MAC is defined by an array of chords. The MAC of each chord is computed as separated trapezoidal wing and then, the final MAC is calculated. This approach may find the accurate solution of complicated wing planforms, including elliptical, in the regime of low subsonic speeds. The first section describes the MAC and essential equations used for the computation. Finally, the application and two various examples of calculation are illustrated and discussed. © 2016 Author(s)

Control system designer for JSBsiM with algorithm of automatic Ziegler-Nichols sustained-oscillation method

In this paper, the algorithm of the automatic Ziegler-Nichols sustained oscillation method is described. The algorithm is used as the essential way of PID setting in the Control System Designer for JSBSim. The algorithm is tested during a control system design of the wing leveler, and its sufficient functionality is proved. The first section introduces the Ziegler-Nichols method itself, and the description of the Control System Designer for JSBSim follows. The main section shows the algorithm which can perform the method automatically. The last section illustrates the experiment with the successful PID adjustment. © 2020 American Institute of Physics Inc.. All rights reserved.Department of Computer and Communication Systems of Tomas Bata Universit

Comparison of open-source CFD software for aerodynamic analysis of mini-UAV

The objective of this paper is to compare opensource CFD (Computational Fluid Dynamics) software for the aerodynamic analysis of a mini-UAV (Unmanned Aerial Vehicle). When low cost analysis is necessary, open-source applications seem to be the best choice; however, the quality of the open-source software may vary. Hence, this paper includes leading candidate open-source CFD software-SU2, OpenFOAM, and Code-Saturne. PyFR and HiFiLES will be analyzed in future work. The first part of this paper shows the geometry of two mini-UAVs used for the aerodynamic analysis. In the second section, the free software is summarized and described, including the open-source CFD applications. Although this analysis is focused on small subsonic UAVs, the software can also be applicable to other categories of aircraft (e.g., gliders, large supersonic airplanes, and MAVs); however, accuracy may be different from this research. Finally, the results of the aerodynamic analysis are recorded, evaluated, and discussed. © 2015 IEEE.Free software 2 mini-UAVs analyzed in 3 CFD applications-SU2 • ROE (Roe's Approximate Riemann Solver) • JST (Jameson-Schmidt-Turkel)-OpenFOAM-Code-Saturne Results-SAGITTA with and without Boundary Layer-AVIGLE without Boundary Layer © 2015 IEEE

JSBSim library for flight dynamics modelling of a mini-UAV

This paper presents using of JSBSim library for flight dynamics modelling of a mini-UAV (Unmanned Aerial Vehicle). The first part of the paper is about general information of UAVs and about the fundamentals of airplane flight mechanics, forces, moments, and the main components of typical aircraft. The main section briefly describes a flight dynamics model and summarizes the information about JSBSim library. Then, a way of using the library for the modelling of a mini-UAV is shown. A basic script for lifting and stabilization of the UAV has been developed and described. Finally, the results of JSBSim test are discussed

FlightGear application for flight simulation of a mini-UAV

This paper presents using of FlightGear application for flight simulation of a mini-UAV (Unmanned Aerial Vehicle). The first part of the paper is about general information of UAVs and about the fundamentals of airplane flight mechanics. The main section summarizes the information about FlightGear application and describes a way of using the application to simulate a mini-UAV. The process of altitude change by using autopilot has been simulated. In the created simulation, three stage cascade controller was used for an altitude control. Heading was controlled by 2 stage cascade PID (Proportional-Integral-Derivative) controller. An automatic throttle system was applied for a velocity control. The setting of all controllers is included in the description of the simulation. Finally, the results of FlightGear simulation are discussed

A survey of free software for the design, analysis, modelling, and simulation of an unmanned aerial vehicle

The objective of this paper is to analyze free software for the design, analysis, modelling, and simulation of an unmanned aerial vehicle (UAV). Free software is the best choice when the reduction of production costs is necessary; nevertheless, the quality of free software may vary. This paper probably does not include all of the free software, but tries to describe or mention at least the most interesting programs. The first part of this paper summarizes the essential knowledge about UAVs, including the fundamentals of flight mechanics and aerodynamics, and the structure of a UAV system. The second section generally explains the modelling and simulation of a UAV. In the main section, more than 50 free programs for the design, analysis, modelling, and simulation of a UAV are described. Although the selection of the free software has been focused on small subsonic UAVs, the software can also be used for other categories of aircraft in some cases; e.g. for MAVs and large gliders. The applications with an historical importance are also included. Finally, the results of the analysis are evaluated and discussed—a block diagram of the free software is presented, possible connections between the programs are outlined, and future improvements of the free software are suggested. © 2015, CIMNE, Barcelona, Spain.Internal Grant Agency of Tomas Bata University in Zlin [IGA/FAI/2015/001, IGA/FAI/2014/006

Development of control system designer for JSBSim FDM

In this paper, an application for the control system design of JSBSim autopilot is described and its function is demonstrated. The program facilitates the whole process, from creation, through adjustment, to simulation. The results show that the application and the used method are sufficiently functional. The first section introduces the autopilot and script definition in JSBSim flight dynamics model (FDM). The main section shows the control system designer and an example, conditions and results of a simulation process. © 2018 Author(s).IGA/CebiaTech/2017/001; IGA/CebiaTech/2016/002; MSMT-7778/2014, MŠMT, Ministerstvo Školství, Mládeže a Tělovýchovy; LO1303, MŠMT, Ministerstvo Školství, Mládeže a TělovýchovyMinistry of Education, Youth and Sports of the Czech Republic within the National Sustainability Programme [LO1303 (MSMT-7778/2014)]; Internal Grant Agency of Tomas Bata University [IGA/CebiaTech/2017/001, IGA/CebiaTech/2016/002

Airfoil geometry converter: From Selig and Lednicer to GEO and mesh formats

In this paper, a utility for the conversion of the airfoil geometry is described and its function is demonstrated. The utility can convert a Selig, Lednicer, or VSP airfoil file to the universal GEO format, and then it may mesh the geometry for a following CFD analysis. The first section lists the formats which may be used for the storage of airfoil data and for meshing. The main section introduces the utility, briefly describes the code, and shows an example of use. © 2017 Author(s).Ministry of Education, Youth and Sports of the Czech Republic within the National Sustainability Programme [LO1303 (MSMT-7778/2014)]; Internal Grant Agency of Tomas Bata University [IGA/CebiaTech/2016/002, IGA/FAI/2015/001