Aerodynamic and stability analysis of personal vehicle in tandem-wing configuration

Goetzendorf‐Grabowski, Tomasz; Figat, Marcin

doi:10.1177/0954410016662077

Cited by 20 publications

(14 citation statements)

References 8 publications

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“…It was at that stage that the authors knew that they were on time with design and manufacturing of the alternative plane for photogrammetry (i.e. PW-ZOOM of tailed configuration and excellent stability, 23,24 further referred to as 'classic' configuration). Moreover, this X-8 baseline configuration was used as a training plane in a short testing campaign before the expedition departed to Antarctica.…”

Section: Light-weight Version Of Tailless Uav -Adaptation Of Skywalkementioning

confidence: 99%

Design and testing of three tailless unmanned aerial vehicle configurations built for surveillance in Antarctic environment

Rodzewicz

Goraj

Tomaszewski

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The tailless fixed-wing aircraft have a very compact design and therefore are very attractive as portable unmanned aerial vehicle (UAV) platforms. There is a special need for using such platforms in case of operations in such backlands as Antarctica, because very often the equipment necessary for preparing improvised airfields near Antarctic scientific bases and organizing the UAV flights must be hand-carried. The main aim of this paper is to present the design activity and testing of a number of UAV configurations to be used for aerial monitoring in Antarctic areas and collecting data of local ecosystems. Two UAV flying-wing platforms-MONICA-1 and MONICA-2-were developed, differing largely with respect to wing-loading and weight-to-power ratios. The lightweight Skywalker X-8 built from the kit and used as a baseline configuration was adapted for special photogrammetric missions. It was found that the main advantage of such light UAV consists in a very simple takeoff system (i.e. bungee), however due to low wing loading a usage of this UAV is limited to the so-called 'weather windows' of relatively low wind, which do not frequently occur in Antarctica. MONICA-1 is much less sensitive to gust but as a heavy platform it is more difficult to handle in harsh Antarctic environment. To be able to operate in much wider range of the wind, vertical gust and heavy turbulence, typical for Antarctic zones, a special UAV platform-called MONICA-2-was designed and manufactured. MONICA-2 platform of higher wing loading is smaller than the X-8 and at the same time is able to carry the same photogrammetry equipment. The effort of designers focused on achieving low sensitivity to gust and turbulence by increasing the critical angle of attack and natural static and dynamic stability in the whole range of operational speeds. The paper contains the selected design details and some observations from the flight tests.

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Section: Light-weight Version Of Tailless Uav -Adaptation Of Skywalkementioning

confidence: 99%

Design and testing of three tailless unmanned aerial vehicle configurations built for surveillance in Antarctic environment

Rodzewicz

Goraj

Tomaszewski

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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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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“…The paper [ 13 ] focuses on the selection and optimization of key parameters of the aircraft fleet used in Small Air Transport. An important feature of the Small Air Transport system is personalization, which is the flexible adaptation of the transport process to the customer’s requirements and capabilities.…”

Section: Introductionmentioning

confidence: 99%

Measurements of Aerodynamic Interference of a Hybrid Aircraft with Multirotor Propulsion

Czyż¹,

Wendeker

2020

Sensors

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This article deals with the phenomenon of aerodynamic interference occurring in the innovative hybrid system of multirotor aircraft propulsion. The approach to aerodynamics requires a determination of the impact of active sources of lift and thrust upon the aircraft aerodynamic characteristics. The hybrid propulsion unit, composed of a conventional multirotor source of thrust as well as lift in the form of the main rotor and a pusher, was equipped with an additional propeller drive unit. The tests were conducted in a continuous-flow low speed wind tunnel with an open measuring space, 1.5 m in diameter and 2.0 m long. Force testing made it possible to develop aerodynamic characteristics as well as defining aerodynamic characteristics and defining the field of speed for the considered design configurations. Our investigations enabled us to analyze the results in terms of a mutual impact of particular components of the research object and the area of impact of active elements present in a common flow.

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Aerodynamic and stability analysis of personal vehicle in tandem-wing configuration

Cited by 20 publications

References 8 publications

Design and testing of three tailless unmanned aerial vehicle configurations built for surveillance in Antarctic environment

Design and testing of three tailless unmanned aerial vehicle configurations built for surveillance in Antarctic environment

An Unmanned Aircraft Model for Control System Reconfiguration Analysis and Synthesis

Measurements of Aerodynamic Interference of a Hybrid Aircraft with Multirotor Propulsion

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