Performing co-ordinated turns with articulated wing-tips as multi-axis control effectors

Bourdin, P.; Gatto, A.; Friswell, Michael I.

doi:10.1017/s0001924000003511

Cited by 19 publications

(10 citation statements)

References 14 publications

(21 reference statements)

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“…The ten initial position error vector is [5,15,5]m. The desired trajectory include two manoeuvres: the first is a straight line level flight, and the second is a helix climbing path defined as d / dt P d = [8Cos(0·1) Cos(0·2t), 8Cos(0·1) Sin(0·2t), −8Sin(0·1)].…”

Section: Simulation Resultsmentioning

confidence: 99%

“…A.C. Hurst et al presented an adaptive aircraft with morphing control input that allows it to land through a perching manoeuvre (14) . P. Bourdin et al presented a novel method for the control of aircraft by using articulated split wing-tips (15) . J.J. Henry explored the idea of aircraft roll control through asymmetric variable span morphing (16) .…”

Section: Introductionmentioning

confidence: 99%

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Multi-body dynamic modelling and flight control for an asymmetric variable sweep morphing UAV

Tong¹,

2014

Aeronaut. j. (1968)

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In this paper, the multi-body dynamic model of an asymmetric variable sweep wing morphing UAV is built based on Kane's method. This model describes the UAV's transient behaviour during morphing process and the dynamic characteristic of the variable sweep wings. An integrated design of trajectory tracking control via constrained backstepping method is presented then. The idea of aircraft roll control through asymmetric wing sweep angle changes rather than traditional aileron is explored and used in the flight control design. The control of variable sweep wings is designed as well based on the presented dynamic model. Command filters are used in the backstepping design procedure to accommodate magnitude, rate and bandwidth constraints on virtual states and actuator signals. Stability of the closed-loop system can be proved in the sense of Lyapunov. Simulation of tracking a desired trajectory which contains two manoeuvres demonstrates the feasibility of the proposed protocol and the morphing wing roll controller.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multi-body dynamic modelling and flight control for an asymmetric variable sweep morphing UAV

Tong¹,

2014

Aeronaut. j. (1968)

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“…Unmanned aerial vehicles (UAVs) have been widely developed and used for various tasks such as disaster assessment [1], airway transportation [2], military aerial vehicles [3], surveillance [4], and logistics [5]. The UAVs are classified into three main categories: fixed wing UAV [6], [7], vertical take-off and landing (VTOL) UAV [8], and hybrid UAV [9], [10]. The fixed wing UAVs have been studied as a classic type of air vehicle.…”

Section: Introductionmentioning

confidence: 99%

Tri-Copter UAV With Individually Tilted Main Wings for Flight Maneuvers

2020

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A tri-copter unmanned aerial vehicle (UAV) with individually tilted main wings for various flight maneuvers is presented. In contrast to conventional tilt wing UAVs, thrust vectoring and control of the directions of main wing surfaces are attained by tilting main wings individually. Such individually tilted main wings allow more efficient maneuvers of the UAV. Even though the UAV is a tri-copter, it can compensate the reaction torque created by the tail motor by the individual control of the main wings. Few publications have appeared in the literature, dealing with tri-copter UAV with individually tilted main wings. Dynamic model of the UAV is established via the Newton-Euler formulation and effect of individual wing control is examined. The PID controller and PI controller for control of flight maneuvers are implemented and used for simulations and experiments. Results of simulations and experiments are presented for validation of flight performance of the UAV, including the roll rate 80% larger than that of the conventional UAV with ailerons as control surfaces.

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“…Other morphing concepts include variations on wing geometric parameters as wing twist [17,18] or continuously change the shape of wingtips [19] or winglets [20], usually for stability and maneuverability improvement. Studies on compliant structures for morphing have also been performed [21][22][23].…”

Section: Introductionmentioning

confidence: 99%

Energy Efficiency Studies of A Morphing Unmanned Aircraft

A¹

2013

J Aeronaut Aerospace Eng

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In this paper an analytical model is used for the development of the controls for the optimal longitudinal performances of two small UAV aircraft which differ exclusively on the wing: an optimum Fixed Wing (FWA) and a telescopic and camber varying Morphing Wing (MWA). The aerodynamic data of the two wings is based on previous coupled FEM-CFD work. Both static and dynamic formulations for the longitudinal control are presented and applied to the two aircrafts. The static results show that the MWA has an extended operational range when compared to the FWA with the exception of the rate of climb which is slightly penalized. The dynamic results include the analysis of 128 different missions which include climb-cruise missions and descent missions. The dynamic formulation shows very satisfactory results in optimal control calculation for trajectory tracking. Energy actuation estimates based on the optimal control obtained for the missions are calculated and total mission energy consumption estimates comparisons are presented. The actuation energy estimates show that actuation energy is two orders of magnitude inferior to the engine output.

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Performing co-ordinated turns with articulated wing-tips as multi-axis control effectors

Cited by 19 publications

References 14 publications

Multi-body dynamic modelling and flight control for an asymmetric variable sweep morphing UAV

Multi-body dynamic modelling and flight control for an asymmetric variable sweep morphing UAV

Tri-Copter UAV With Individually Tilted Main Wings for Flight Maneuvers

Energy Efficiency Studies of A Morphing Unmanned Aircraft

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