Flight Characteristics of Shaping the Membrane Wing of a Micro Air Vehicle

Abdulrahim, Mujahid; Garcia, Helen; Lind, Rick

doi:10.2514/1.4782

Cited by 112 publications

(67 citation statements)

References 15 publications

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“…MAVs should work in places and situations where larger vehicles could not exit including both military and civilian sectors. They are also considered an ideal platform for the morphing demonstration as they require quite small power, whereas the benefit is quite large, besides, the ability to use flexible structures, yet strong enough to support the wing loading (2)(3)(4) . These flexible structures could allow different control concepts, hence provide efficient control surfaces that would improve the MAV's agility and maintain smooth flight.…”

Section: Introductionmentioning

confidence: 99%

“…Their development, design, analysis, and modelling including shape, aerodynamics, structures and control aspects have always presented a big challenge. However, many unique designs have been designed, built and flown recently (1)(2)(3)(4) . MAVs should work in places and situations where larger vehicles could not exit including both military and civilian sectors.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic shape optimisation, wind tunnel measurements and CFD analysis of a MAV wing

Nabawy

Elnomrossy

Abdelrahman

et al. 2012

Aeronaut. j. (1968)

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The aerodynamic shape optimisation of a micro air vehicle (MAV) wing is performed to obtain the basic wing geometrical characteristics which produce the maximum range and endurance requirements. Multhopp's method based on Prandtl's classical lifting line theory is used for the determination of the spanwise load distribution required during the optimisation process. The obtained lift and drag characteristics are used for the derivation of the range and endurance equations of an electrically driven micro air vehicle. The optimisation process is based on the modified feasible directions gradient based optimisation algorithm. Results are validated using wind tunnel measurements showing very good agreement. Results are also compared with solutions to the Navier-Stokes equations obtained with ANSYS-CFX finite elements using different turbulence models. These include the k-ε and the shear stress transport (SST) models as well as the Reynolds stress model.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Aerodynamic shape optimisation, wind tunnel measurements and CFD analysis of a MAV wing

Nabawy

Elnomrossy

Abdelrahman

et al. 2012

Aeronaut. j. (1968)

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show abstract

“…With dimension lesser than 15cm, MAV is seen as small scale aircraft that can also fly at low-speed with Reynolds number regime between 10 4 -10 5 . In order to improve the MAV performance, the biological inspired MAV design such as morphing wing is seen as a new potential to be explored [1]. Most of these biological designs are inspired from flying characteristics of airborne mammals, birds [2] and insects [3].…”

Section: Introductionmentioning

confidence: 99%

Drag Performance of Twist Morphing MAV Wing

et al. 2016

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Abstract.Morphing wing is one of latest evolution found on MAV wing. However, due to few design problems such as limited MAV wing size and complicated morphing mechanism, the understanding of its aerodynamic behaviour was not fully explored. In fact, the basic drag distribution induced by a morphing MAV wing is still remained unknown. Thus, present work is carried out to compare the drag performance between a twist morphing wing with membrane and rigid MAV wing design. A quasi-static aeroelastic analysis by using the Ansys-Fluid Structure Interaction (FSI) method is utilized in current works to predict the drag performance a twist morphing MAV wing design. Based on the drag pattern study, the results exhibits that the morphing wing has a partial similarities in overall drag pattern with the baseline (membrane and rigid) wing. However, based CD analysis, it shows that TM wing induced higher CD magnitude (between 25% to 82% higher) than to the baseline wing. In fact, TM wing also induced the largest CD increment (about 20% to 27%) among the wings. The visualization on vortex structure revealed that TM wing also produce larger tip vortex structure (compared to baseline wings) which presume to promote higher induce drag component and subsequently induce its higher CD performance.

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“…Boothe 13) modeled the flight dynamics of a MAV with a morphing wing using a linear input varying system. Abdulrahim et al 14) performed a linear analysis of the flight dynamics of a MAV with a membrane wing. Kuo et al 15) and Chang et al 16) performed an analysis based on a general linear time-invariant (LTI) model to investigate the influences of component allocation and control surface Ó 2010 The Japan Society for Aeronautical and Space Sciences performance on the longitudinal and lateral-directional stability characteristics of a fixed-wing MAV, showing a discrepancy between nonlinear and LTI models.…”

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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Flight Characteristics of Shaping the Membrane Wing of a Micro Air Vehicle

Cited by 112 publications

References 15 publications

Aerodynamic shape optimisation, wind tunnel measurements and CFD analysis of a MAV wing

Aerodynamic shape optimisation, wind tunnel measurements and CFD analysis of a MAV wing

Drag Performance of Twist Morphing MAV Wing

Dynamic Modeling and Analysis of Fixed-Wing Micro Air Vehicle

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