Novel Morphing Wing Design Using Antagonistic Shape Memory Alloy Actuation

2010 ◽  
Author(s):  
A. Y. N. Sofla ◽  
S. A. Meguid ◽  
K. T. Tan
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Unmanned Aerial Vehicle ◽  
Wing Design ◽  
Morphing Wing ◽  
Aerial Vehicle ◽  
Wing Box

A wing shear concept is adopted here to design and fabricate morphing wing for an unmanned aerial vehicle. The concept uses a parallelogram wing-box that consists of several composite rib shells that are hinged to two active spars. Antagonistic shape memory actuation is used to flex the spars and consequently shape morph the wing between straight and curved shapes.

Optimal Flight Planning for a Z-Shaped Morphing-Wing Solar-Powered Unmanned Aerial Vehicle

2018 ◽  
Vol 41 (2) ◽  
pp. 497-505 ◽  
Author(s):  
Mingjian Wu ◽  
Tianhang Xiao ◽  
Haisong Ang ◽  
Hongda Li
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Morphing Wing ◽  
Flight Planning ◽  
Aerial Vehicle ◽  
Solar Powered

Experimental study of a bio-inspired robotic morphing wing mechanism actuated by shape memory alloy wires

Mechatronics ◽  
2014 ◽  
Vol 24 (8) ◽  
pp. 1231-1241 ◽  
Author(s):  
Hamid Basaeri ◽  
Aghil Yousefi-Koma ◽  
Mohammad Reza Zakerzadeh ◽  
Seyed Saeid Mohtasebi
Keyword(s):  
Experimental Study ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Morphing Wing

scholarly journals Conceptual Design of Flapping Wing Using Shape Memory Alloy Actuator for Micro Unmanned Aerial Vehicle

2014 ◽  
Vol 629 ◽  
pp. 152-157
Author(s):  
Navanitha Marimuthu ◽  
Ermira Junita Abdullah ◽  
Dayang L.A. Majid ◽  
Fairuz I. Romli
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Conceptual Design ◽  
Smart Materials ◽  
Operating Cost ◽  
Flapping Wing ◽  
Complex Environments ◽  
Reduce Operating Cost ◽  
Air Vehicle ◽  
Aerial Vehicle

Micro Air Vehicle (MAV) has the capability to fly autonomously in complex environments which enables human to conduct surveillance in areas which are deemed too dangerous or in confined spaces that does not allow human entry. Research and development of MAVs aim to reduce their size further, thus novel techniques need to be explored in order to achieve this objective while still maintaining the MAVs’ current performance. In this paper, a conceptual design of an MAV with a main drive system using shape memory alloy (SMA) actuator to provide the flapping motion is proposed. SMA is considered superior to other smart materials due to its efficiency and large energy storage capacity. By incorporating SMA in the flapping wing MAV, it will provide users the flexibility to add more payloads by reducing bulky cables or reduce operating cost by using less fuel. However, there are some drawbacks in using SMAs such as nonlinear response of the strain to input current and hysteresis characteristic as a result of which their control is inaccurate and complicated.

A computational fluid dynamics investigation of subsonic wing designs for unmanned aerial vehicle application

2019 ◽  
Vol 233 (15) ◽  
pp. 5543-5552
Author(s):  
Z Siddiqi ◽  
JW Lee
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Aspect Ratio ◽  
Unmanned Aerial Vehicle ◽  
Wing Design ◽  
Ansys Fluent ◽  
High Lift ◽  
Aerial Vehicle ◽  
Computational Fluid Dynamics Simulations ◽  
Dynamics Simulations

The wing of an unmanned aerial vehicle, RQ-7 Shadow, is modified to study the changes in the aerodynamics of the wing. The main focus is to investigate the effects of changing the components of wing design when the aircraft climbs and accelerates. These component modifications included changing the airfoil, planform, aspect ratio, and adding a winglet. Another objective is to study the efficacy of employing high-lift airfoils like the EPPLER 559 for subsonic unmanned aerial vehicle applications. For this, five wing designs are considered in this paper. Computational fluid dynamics simulations using ANSYS FLUENT® are conducted for each wing design. The C L /C D ratios for all the wings are calculated at increasing angles of attack (simulating Climbing) and increasing speed (simulating Acceleration). Compared to the NACA 4415 airfoil, which is utilized by the RQ-7 Shadow, the EPPLER 559 provides an increase in lift at the low angles of attack, but yields less of these benefits as the angle of attack increases. The tapered planform significantly reduces the high drag associated with the EPPLER 559 airfoil. The generation of higher lift forces with lower drag is further achieved by increasing the aspect ratio and through the addition of a winglet. When compared to the NACA 4415 airfoil, it is concluded that the EPPLER 559 airfoil is a viable candidate for subsonic unmanned aerial vehicle applications only when the components of wing design are altered. The performance of the wings that employ the EPPLER 559 airfoil improves when the planform is changed from rectangular to tapered, when the aspect ratio is increased and when a winglet is added.

Design of Shape Memory Alloy Actuators for Morphing Laminar Wing With Flexible Extrados

2009 ◽  
Vol 131 (9) ◽  
Author(s):  
Thomas Georges ◽  
Vladimir Brailovski ◽  
Emeric Morellon ◽  
Daniel Coutu ◽  
Patrick Terriault
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Design Methodology ◽  
Laminated Composite ◽  
Morphing Wing ◽  
Active Structure ◽  
Sma Actuators ◽  
Force Displacement ◽  
Cruise Flight ◽  
Novel Design

An active structure of a morphing wing designed for subsonic cruise flight conditions is composed of three principal subsystems: (1) flexible extrados, (2) rigid intrados, and (3) an actuator group located inside the wing box. The four-ply laminated composite flexible extrados is powered by two individually controlled shape memory alloy (SMA) actuators. Fulfilling the requirements imposed by the morphing wing application to the force-displacement characteristics of the actuators, a novel design methodology to determine the geometry of the SMA active elements and their adequate assembly conditions is presented. This methodology uses the results of the constrained recovery testing of the selected SMA. Using a prototype of the morphing laminar wing powered by SMA actuators, the design approach proposed in this study is experimentally validated.

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