Membrane wing aerodynamics for micro air vehicles

Lian, Yongsheng; Shyy, Wei; Viieru, Dragos; Zhang, Baoning

doi:10.1016/s0376-0421(03)00076-9

Cited by 184 publications

(91 citation statements)

References 92 publications

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“…Proper-Orthogonal-Decomposition (POD) has previously successfully been applied to the flow field around membrane wings (Schmit et al, 2003;Lian et al, 2003) as well as membrane dynamics (Stanford et al, 2010;Buoso and Palacios, 2015;Shi et al, 2013). The complexity of membrane-vibrations requires a technique which is capable to identify and quantify twodimensional spatial structures in membrane-oscillations.…”

Section: Decomposition Of Membrane Dynamicsmentioning

confidence: 99%

“…Membrane wings combine vehicle agility, enlarged maximum stall angle, extended maximum lift and smooth gust reaction (Ifju et al, 2002;Stanford et al, 2014;Shyy et al, 1999;Lian et al, 2003). The main source of their benefits is suggested to rely on their inherent membrane oscillations which can energize the weak boundary layer to enforce longer flow attachment (Rojratsirikul et al, 2010).…”

Section: Introductionmentioning

confidence: 99%

“…In addition, membrane vibrations are found to enhance leading edge vortex shedding, forming large vortices that can significantly contribute to the total lift enhancement at high incidence. The key to understanding the aeromechanics of flexible membrane wings is to understand the coupling effects between flow, membrane and force dynamics (Bleischwitz et al, 2014;Lian et al, 2003). At low to moderate angles-of-attack, the dynamics of membrane wings come at a price.…”

Section: Introductionmentioning

confidence: 99%

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Aeromechanics of membrane and rigid wings in and out of ground-effect at moderate Reynolds numbers

Bleischwitz

Kat

Ganapathisubramani

2016

Journal of Fluids and Structures

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Wind tunnel experiments are conducted using membrane wings and rigid flat-plates in ground-effect at a moderate Reynolds number of Re = 56,000 with ground clearances from 1% to 200% chord length measured from their trailing-edge. A six-axis load-cell captures time-resolved forces and moment while time-resolved stereo digital image correlation (DIC) measurements are performed to capture membrane motions. The lift and drag coefficients of the rigid wing in ground-effect follow well-established trends while the membrane wing appears to exhibit improved coefficients and efficiency (compared to the rigid wing) when in ground-effect. Proper orthogonal decomposition (POD) is applied to study the spatiotemporal structure of membrane vibrations. With increasing angles-ofattack and/or decreasing heights above ground, mode shapes of membrane deformation are dominated by large-scale fluctuations that have a smaller number of local extrema along the chord. Ground-effect induces modifications to the membrane deformation, which appear to be similar to the modifications induced by increasing angles-of-attack in free-flight. At high angles-of-attack in free-flight or at moderate angles in ground-effect, two POD modes of membrane fluctuations are found to be sufficient to capture 90% of all membrane deformations. Under these conditions, a membrane deformation with maximum camber near the trailing edge of the membrane wing is found to correlate with high lift, low drag and a nose down pitching moment. The extrema in membrane deformations and lift and drag forces occur simultaneously, while there is a time-lag between the deformation and the pitching moment.

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Section: Decomposition Of Membrane Dynamicsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Aeromechanics of membrane and rigid wings in and out of ground-effect at moderate Reynolds numbers

Bleischwitz

Kat

Ganapathisubramani

2016

Journal of Fluids and Structures

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“…The system can then be co-simulated by separately computing the deformation of the wing and the velocity/pressure fields of the airflow and then coupling them (Fig. 1c) in an appropriate manner [14]. In the context of this paper, simulation of a system refers to the approximation of the solution by numerical integration of the equations, i.e., the approximation of the state vector at discrete time steps.…”

Section: Simulation and Co-simulationmentioning

confidence: 99%

Can complex systems really be simulated?

Kalmár‐Nagy¹,

Stanciulescu²

2014

Applied Mathematics and Computation

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The simulation of complex systems is important in many fields of science and in real-world applications. Such systems are composed of many interacting subsystems. There might exist different software packages for simulating the individual subsystems and co-simulation refers to the simultaneous execution of multiple interacting subsystem simulators. Simulation or co-simulation, if not designed properly, can return misleading numerical solutions (unstable numerical solutions for what is in fact a stable system or vice versa). To understand the cause of these numerical artifacts, we first propose a simple mathematical model for co-simulation, and then construct stability charts. These charts shed light on transitions between stable and unstable behaviour in co-simulation. Our goal is to understand the stability properties of the simulated and co-simulated representation of the continuous system. We will achieve this goal by expressing the trace and determinant of the discretized system in terms of the trace and determinant of the continuous system to establish stability criteria.

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“…Aerodynamic forces and moments change substantially with variations in flight conditions and we need databases for low-Re aerodynamic coefficients and stability derivatives. Some numerical and experimental studies on aerodynamic characteristics have been performed for fixedwing, [3][4][5] flexible-wing, [6][7][8] and flapping-wing MAVs. 3,9) Additionally, to achieve autonomous flight control, an understanding of flight dynamic characteristics is very significant.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Modeling and Analysis of Fixed-Wing Micro Air Vehicle

Kuo¹,

Soong

Chang

2010

Trans. Japan Soc. Aero. S Sci.

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This paper describes the dynamic modeling and analysis of a fixed-wing micro air vehicle (MAV). A nonlinear model for the MAV motion with six degrees of freedom is formulated first. Next, an extended version of the linear-time-invariant model for the MAV is derived by applying small perturbation theory and linearizing around an equilibrium flight condition. This ad hoc extended model for the MAV retains more terms that are generally neglected in mathematic models of conventional airplanes. To explore the stability and control characteristics, the aerodynamic derivatives required by dynamic modeling are evaluated using low-Reynolds-number wind tunnel testing data and some theoretical/empirical formulas. A fixed-wing MAV with a 15-cm wingspan successfully flown in 2002 is used as a baseline prototype for dynamic modeling and analysis. The longitudinal and lateral dynamic responses of the MAV under various conditions are demonstrated. The performance of the present extended MAV model is investigated by comparing the flight dynamics for different models. The simulation results show that the proposed extended model is consistent with the nonlinear dynamics model for a wider range of flight conditions. The present analysis may aid a better understanding of flight characteristics as well as design and analysis of MAV systems.

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Membrane wing aerodynamics for micro air vehicles

Cited by 184 publications

References 92 publications

Aeromechanics of membrane and rigid wings in and out of ground-effect at moderate Reynolds numbers

Aeromechanics of membrane and rigid wings in and out of ground-effect at moderate Reynolds numbers

Can complex systems really be simulated?

Dynamic Modeling and Analysis of Fixed-Wing Micro Air Vehicle

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