Optimization of aerodynamic efficiency for twist morphing MAV wing

Ismail, N. I.; Zulkifli, Abdul Halim; Abdullah, M. Z.; Basri, M. Hisyam; Abdullah, Norazharuddin Shah

doi:10.1016/j.cja.2014.04.017

Cited by 20 publications

(21 citation statements)

References 21 publications

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“…Based on previous study shown in references [9], [10], this malevolent performance is partially contributed by the enlargement of tip vortex structure induced by TM wing. Larger tip vortex structure contributed into higher induce drag component in which consequently contributed into higher drag performance [11].…”

Section: Drag Coefficient Resultsmentioning

confidence: 99%

“…The twist morphing, membrane and rigid MAV wing are modeled based on previous research done at the University of Teknologi MARA [9], [10]. Due to symmetrical wing condition, all wing model are simplified into half wing.…”

Section: Mav Wing Model and Boundary Conditionsmentioning

confidence: 99%

“…The thickness for wing skeleton and membrane skins is constantly at 1.0mm. The material for wing structure and membrane skin is set to be Perspex [10] and silicone rubber [10], respectively. The detail structure of each wing can be found in [9] and represented in Fig.…”

Section: D2me 2016mentioning

confidence: 99%

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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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Section: Drag Coefficient Resultsmentioning

confidence: 99%

Section: Mav Wing Model and Boundary Conditionsmentioning

confidence: 99%

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Drag Performance of Twist Morphing MAV Wing

et al. 2016

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“…Biomimetic design incorporates feasible biological science (with reverse engineering concept) of a certain mechanism into a technology field. Flapping [2] and morphing [3] wing concepts are some examples of biologically-inspired designs, which have already been successfully implemented on MAV platform by previous researchers [4]. Natural flyers have fully manipulated their multi-hinged skeleton, flexible skin and their naturally distributed compliance wings for flight manoeuvres.…”

Section: Introductionmentioning

confidence: 99%

Lift distribution of washout twist morphing MAV wing

Ismail

Yusoff

Sharudin

et al. 2018

IJET

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Micro Air Vehicle, or also commonly known as MAV, is a miniature aircraft that has been gaining interest in the industry. MAV is defined as a flying platform with 15cm wingspan and operates at a speed of around 10m/s. Recently, MAV has been exposed with the latest development and link towards the biologically-inspired designs such as morphing wing. Twist morphing wing is one of the latest MAV wing design developments. The application of Twist Morphing (TM) on MAV wing has been previously known to produce better aerodynamic performance. Previous study in washin TM wing has shown a promising possibility of generating higher lift force. Despite the benevolent performance exhibited by the washin TM wing, the lift distribution for the washout type of TM MAV is relatively unknown and still open to be explored. This is probably due to the lack of experimental test rig to produce the washout twist morphing motion on the MAV wing. Therefore, this research aims to produce a special test rig for washout TM wing that is compatible for wind tunnel experimental testing. By using the special test rig, the experimental investigation on the lift performance of washout TM MAV wing can be done. Based on the wing deformation results, it clearly shows that the proposed test rig is capable to produce up to 19.5mm tip deflection at the morphing point, which is also resulting in a significant morphing motion. Higher morphing force induces larger morphing motion. Based on the lift distribution results, they show that the morphing motion has significantly affected the overall lift distribution on the MAV wing. The morphing motion on TM wing has produced at least 17.6% and 5.33% lower CL and CLmax magnitude, respectively, with the membrane wing especially at the pre-stall region. However, the TM wing is still able to maintain the stall angle similar to the baseline wing at αstall= 31°. By maintaining high αstall value with lower CL and CLmax magnitude, TM wing produces more agility for the MAV maneuverability that will be useful for indoor mission or obstacle avoidance flight.

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“…Due to the MAV characteristics, it has numerous potential applications for both military and civilian [2]. Based on the previous study, MAV can be categorized according to 5 basic types known as flapping, fixed, membrane flexible, rotary and morphing [3]as shown in Figure 1. At maximal dimension of 15 cm and nominal flight speeds of around 10 m/s [4], MAVs can perform missions such as environmental monitoring, surveillance, and assessment in hostile situations.…”

Section: Introductionmentioning

confidence: 99%

The Influence of Hoop Diameter on Aerodynamic Performance of O-Ring Paper Plane

Ismail

Sharudin

Talib

et al. 2018

IOP Conf. Ser.: Mater. Sci. Eng.

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Abstract. The O-ring paper plane can be categorized as one of the Micro Air Vehicle (MAV) based on their characteristics and size. However, the aerodynamics performance of the O-ring paper plane was not fully discovered by previous researchers due to its aerodynamics complexity and various hoop diameters. Thus, the objective of this research is to study the influence of hoop diameters towards the aerodynamics performance of O-ring paper plane. In this works, three types of O-ring paper plane known as Design 1, 2 and 3 with different hoop diameter were initially developed by using the ANSYS-Design Modeler. All the design was analyzed based on aerodynamic simulations works executed on ANSYS-CFX solver. The results suggested that Design 3 (with larger hoop size) produced better C L , C Lmax and AoA stall magnitude compared to other design. In fact, O-ring paper plane with larger hoop size configurations showed potential in providing at least 5.2% and 5.9% better performance in stability (ΔC M /ΔC L ) and aerodynamic efficiency (C L /C Dmax ), respectively. Despite the advantages found in lift performances, however, O-ring paper plane with larger hoop size configurations slightly suffered from larger drag increment (C Dincrement ) compared to smaller hoop size configurations. Based on these results, it can be presumed that O-Ring paper plane with larger hoop sizes contributed into better lift, stability and aerodynamic efficiency performances but slightly suffered from larger drag penalty.

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Optimization of aerodynamic efficiency for twist morphing MAV wing

Cited by 20 publications

References 21 publications

Drag Performance of Twist Morphing MAV Wing

Drag Performance of Twist Morphing MAV Wing

Lift distribution of washout twist morphing MAV wing

The Influence of Hoop Diameter on Aerodynamic Performance of O-Ring Paper Plane

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