Aerodynamic characteristics of a novel catapult launched morphing tandem-wing unmanned aerial vehicle

Gao, Liang; Li, Changle; Jin, Hongzhe; Zhu, Yanhe; Zhao, Jie; Cai, Hao

doi:10.1177/1687814017692290

Cited by 22 publications

(8 citation statements)

References 27 publications

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“…Most recently, CFD method has also been used by Gao and colleagues to investigate the unsteady aerodynamic characteristics of a catapult launched morphing tandem-wing UAV. 29 Results demonstrated that the deformation rate had significant influence on the aerodynamic coefficients and the hinge moments of both lifting surfaces; additionally, the rapider deformation rate caused higher variable quantity of the unsteady aerodynamic characteristics. Compared with CFD methods, theoretical calculations with higher efficiency can also be used to calculate the unsteady aerodynamics in the preliminary design of tandem-wing UAVs.…”

Section: Introductionmentioning

confidence: 93%

Unsteady aerodynamics investigation of deploying tandem-wing with different methods

Cheng

Wang

Shi

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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In the rapidly deploying process of the unmanned aerial vehicle with folding wings, the aerodynamic characteristics could be largely different owing to the effects of deformation rate and the aerodynamic interference. The investigation on the unsteady aerodynamics is of great significance for the stability analysis and control design. The lifting-line method and the vortex-lattice method are improved to calculate the unsteady aerodynamics in the morphing stage. It is validated that the vortex-lattice method predicts the unsteady lift coefficient more appropriately than the lifting-line method. Different tandem wing configurations with deployable wings are simulated with different deformation rates during the morphing stage by the vortex-lattice method. As results indicated, the unsteady lift coefficient and the induced drag of the fore wing rise with the deformation rate increasing, but it is reversed for the hind wing. Additionally, the unsteady lift coefficient of the tandem wing configuration performs well with a larger stagger, a larger magnitude of the gap and a larger wingspan of the fore wing; however, the total induced drag has a larger value for the configuration that the two lifting surfaces with the same wingspans are closer to each other.

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Section: Introductionmentioning

confidence: 93%

Unsteady aerodynamics investigation of deploying tandem-wing with different methods

Cheng

Wang

Shi

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…All chosen drones for comparison are roughly equal in Reynolds number. The first drone chosen is a catapult-launched tandem wing morphing unmanned aerial vehicle [32] (Team 1), the second is a fixed wing micro air vehicle (MAV) [17] (Team 2) and the last drone is a rotating wing micro air vehicle [16] (Team 3). The variation of the drag coefficient as a function of the angle of attack is presented in Figure 19, this figure represents a comparison of the results of the experimental measurements of the drag of the present heliplane and three other unmanned aerial vehicles.…”

Section: Comparisonmentioning

confidence: 99%

Experimental investigation of aerodynamics behavior of a new generic of unmanned air vehicle (heliplane)

Kaddouri

Benlefki

Adjlout

et al. 2022

JMES

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The aeronautics studies and particularly the development of drones represent an important field, in which there is a very large number of research and studies.This article aims to present an experimental aerodynamic study of an autonomous surveillance unmanned aerial vehicle (UAV) that is capable of combining the advantages of both categories, namely the fixed-wing drones and the rotary-wing drones. To achieve this objective, a wind tunnel was used to study the flow around this drone in order to better understand the aerodynamic phenomena and to obtain some initial estimates of the lift, drag and moment coefficients, at three different Reynolds numbers of 4.02×104, 6.03×104 and 8.04×104, and for different angles of attack, from [−45°, +45°] with step of 1°.The experimental results obtained in this work show an casi-symetrical variation bertwen the negatif and positif incidence angles of the lift coeffecient, wiche indicate that the heliplane can fly in an inverted position, whatever the angle of incidence. Moreover, the minimum mean value of drag coeffecient according 1° incidence angle is 0.0478 then the drag due to geometry and pitching moment can never be canceled.

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“…The equations can be linearised under the small disturbance theory and then aerodynamic forces and moments can be described by the Taylor series (Cook, 1997). In the case of unconventional configurations, the problem of estimation of aircraft flight dynamics by solving the eigenvalues problem was considered in Goetzendorf-Grabowski et al (2016), Goraj (2014) and Mieloszyk et al (2020).…”

Section: Introductionmentioning

confidence: 99%

Analysis of longitudinal dynamic stability of tandem wing aircraft

Figat

Kwiek

2023

AEAT

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Purpose Tandem wing aircrafts belong to an unconventional configurations group, and this type of design is characterised by a strong aerodynamic coupling, which results in lower induced drag. The purpose of this paper is to determine whether a certain trend in the wingspan impact on aircraft dynamic stability can be identified. The secondary goal was to compare the response to control of flaps placed on a front and rear wing. Design/methodology/approach The aerodynamic data and control derivatives were obtained from the computational fluid dynamics computations performed by the MGAERO software. The equations of aircraft longitudinal motion in a state space form were used. The equations were built based on the aerodynamic coefficients, stability and control derivatives. The analysis of the dynamic stability was done in the MATLAB by solving the eigenvalue problem. The response to control was computed by the step response method using MATLAB. Findings The results of this study showed that because of a strong aerodynamic coupling, a nonlinear relation between the wing size and aircraft dynamic stability proprieties was observed. In the case of the flap deflection, stronger oscillation was observed for the front flap. Originality/value Results of dynamic stability of aircraft in the tandem wing configuration can be found in the literature, but those studies show outcomes of a single configuration, while this paper presents a comprehensive investigation into the impact of wingspan on aircraft dynamic stability. The results reveal that because of a strong aerodynamic coupling, the relation between the span factor and dynamic stability is nonlinear. Also, it has been demonstrated that the configuration of two wings with the same span is not the optimal one from the aerodynamic point of view.

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Aerodynamic characteristics of a novel catapult launched morphing tandem-wing unmanned aerial vehicle

Cited by 22 publications

References 27 publications

Unsteady aerodynamics investigation of deploying tandem-wing with different methods

Unsteady aerodynamics investigation of deploying tandem-wing with different methods

Experimental investigation of aerodynamics behavior of a new generic of unmanned air vehicle (heliplane)

Analysis of longitudinal dynamic stability of tandem wing aircraft

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