Aerodynamic calculation of unmanned aircraft

Figat, Marcin; Goetzendorf‐Grabowski, Tomasz; Goraj, Zdobysław

doi:10.1108/00022660510628453

Cited by 18 publications

(15 citation statements)

References 4 publications

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“…The complex aerodynamic calculations were made using experience from previous projects 10 and the same panel code, 9 which was used for basic computations. Figure 8 presents the mesh prepared for numerical computation and exemplary pressure distribution.…”

Section: Aerodynamic Designmentioning

confidence: 99%

Design of UAV for photogrammetric mission in Antarctic area

Goetzendorf‐Grabowski

Rodzewicz

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The history of UAVs is relatively long and many such vehicles are in service for different tasks. They can be used even in environments inhospitable for humans, e.g. because of extreme temperature. Moreover, they can perform a task that is difficult or impossible for a manned aircraft because of its size and usually relatively high airspeed. The photogrammetric tasks belong to this group, especially if we need to take high-resolution pictures during low level flight. The advantages of a small UAV for such mission are more evident if we want to investigate the natural environment, where the wild animals are. The paper presents the small UAV designed for a special task, which is counting of the penguins in Antarctica. Inhabited area, extreme weather conditions, the fearfulness of penguins and the goal of the mission put up certain requirements for the UAV. It had to be a reliable, stable platform, which is able to carry photogrammetric equipment and to perform precise flight to cover all investigated areas. The presented UAV was used on such missions in Antarctica in 2014 and 2015. All mentioned tasks were successfully accomplished.

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Section: Aerodynamic Designmentioning

confidence: 99%

Design of UAV for photogrammetric mission in Antarctic area

Goetzendorf‐Grabowski

Rodzewicz

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The numerical computation was made by the MGAERO 21 package, tested within the previous projects 22 and by the Ansys Fluent. First method is multigrid method which solved the Euler equation.…”

Section: Aerodynamic Analysis and Optimizationmentioning

confidence: 99%

Lightweight unmanned aerial vehicle for emergency medical service – Synthesis of the layout

Goetzendorf‐Grabowski

Tarnowski

Figat

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The article presents the innovative unmanned aerial vehicle project for emergency medical services. Designed unmanned aerial vehicle combines vertical takeoff and landing characteristics with fast forward flight capability that are vital to perform such an emergency medical mission. The main purpose of the designed unmanned aerial vehicle is to deliver the necessary medical package to the place where access is difficult, and estimated arrival time of conventional ambulance is too long. The cost of the support of such unmanned aerial vehicle could be significantly lower than in case of medical helicopter, which is not necessary in some cases. Designed unmanned aerial vehicle can also be used for fast delivery of essential medical substances (e.g. blood). The selection of configuration was the first and crucial step of the design. After analysis of many different copter configurations, together with selected crash reports analysis, the coaxial quadcopter configuration crossed with conventional airplane was selected. All power units for VTOL capability are electric, and they are doubled for redundancy purposes, with maximum T/W ratio about 2.0. Such configuration allows to sustain a stable flight (vertical phases) in case of one motor failure. Two versions of the vehicle are designed: fully electric (power units for the forward flight and vertical takeoff and landing are electric) and mixed where forward flight unit is a small piston engine. The final layout was the result of conceptual investigation and preliminary research, MDO and trade-off analysis, where as many aspects as possible were considered. The main problem was to meet the vertical takeoff and landing capabilities, relatively long range and endurance, expected payload (3 kg) and the requirement not to exceed 25 kg of maximum take-off weight. Paper presents the design process from initial requirement to the final configuration accepted to be manufactured.

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“…The aerodynamic model of the aircraft was developed based on aerodynamic properties captured using analytical and numerical methods [16], [17]. For numerical analyses [18] (figure 4) MGAERO software was used.…”

Section: Nonlinear Equations Of the Aircraft Motionmentioning

confidence: 99%

An Unmanned Aircraft Model for Control System Reconfiguration Analysis and Synthesis

Żugaj

Bibik

Figat

2017

Transactions on Aerospace Research

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Reliability of unmanned aircraft is a decisive factor for conducting air tasks in a controlled airspace. One of the means of improving unmanned aircraft reliability is reconfiguration of the control system, which will allow to maintain control over the aircraft despite an occurring failure. The control system is reconfigured by using still operational control surfaces to compensate for failure consequences and to control the damaged aircraft. Development of effective reconfiguration algorithms involves utilization of a non-linear model of unmanned aircraft dynamics, in which each control surface deflection can be controlled independently. The paper describes a non-linear model of a small unmanned aircraft with decoupled control surfaces. The paper discusses aircraft flight dynamics equations and estimated equations for controllability derivatives for each control surface, the results of comparison tests of the model and actual aircraft as well as the structure of the simulation model. The developed unmanned aircraft model may be used in development and in optimization of control algorithms for aircraft with damaged control systems as well as to test the impact of failures on dynamic properties of the aircraft.

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Aerodynamic calculation of unmanned aircraft

Cited by 18 publications

References 4 publications

Design of UAV for photogrammetric mission in Antarctic area

Design of UAV for photogrammetric mission in Antarctic area

Lightweight unmanned aerial vehicle for emergency medical service – Synthesis of the layout

An Unmanned Aircraft Model for Control System Reconfiguration Analysis and Synthesis

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