Design of a Morphing Vehicle

Bye, Derek; McClure, Paul D.

doi:10.2514/6.2007-1728

Cited by 87 publications

(59 citation statements)

References 2 publications

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“…They may at first glance seem highly suited to a span-morphing wingtip: shape memory polymers made by Cornerstone Research Group exhibit an order of magnitude change in modulus and up to 200% strain capability when heated past a transition temperature, yet return to their original modulus upon cooling. There have been attempts to capitalize on the capabilities of SMP skins, such as Lockheed Martin's Z-wing morphing UAV concept (Bye and McClure, 2007) and a reconfigurable segmented variable stiffness skin composed of rigid disks and shape memory polymer proposed by McKnight et al (2010). However, electrical heating of the SMP skin to reach transition temperature proved difficult to implement in the wind tunnel test article and the SMP skin was abandoned as a high-risk option.…”

Section: Introductionmentioning

confidence: 99%

One Dimensional Morphing Structures for Advanced Aircraft

Vocke¹,

Kothera²,

Woods³

et al. 2012

Recent Advances in Aircraft Technology

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Section: Introductionmentioning

confidence: 99%

One Dimensional Morphing Structures for Advanced Aircraft

Vocke¹,

Kothera²,

Woods³

et al. 2012

Recent Advances in Aircraft Technology

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“…Mueller 4 provides an excellent compendium of papers for some of the work done in this area until the beginning of the 21st century. Seigler et al, 5 Sanders et al, 6 Bowman et al, 7 Tidwell et al, 8 Bye and McClure, 9 Abdulrahim and Lind 10 are among several of the papers in the last decade that discuss various aspects of morphing aircraft. Costello and Webb 11 demonstrated that articulated wing MAVs, hinged at the root, could reduce gust sensitivity.…”

Section: Introductionmentioning

confidence: 99%

Control Law Design for Perching an Agile MAV with Articulated Wings

Chakravarthy

Paranjape

Chung

2010

AIAA Atmospheric Flight Mechanics Conference

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This paper explores the use of variable wing dihedral and variable wing twist (in conjunction with a conventional horizontal elevator) to control an aircraft performing a perching maneuver. A choice of controller architecture wherein the dihedral is employed in the forward path and the elevator and twist are employed in the feedback path, is considered. The aircraft is modeled as a multivariable linear time-varying system. A specific perching trajectory is considered; and the open-loop aircraft is longitudinally unstable for a segment of this perching trajectory and lateral-directionally unstable for the entire perching trajectory. A multivariable time-varying controller is designed to efficiently stabilize the aircraft as well as reject longitudinal-lateral-directional wind disturbances, while closely tracking the reference perching trajectory.

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“…In its fully deployed condition the telescopic wing could achieve lift-to-drag ratios as high as 16, which was similar to its solid foam-core wing counterpart. The most dramatic morphing wing involving span change that has been realized as a wind tunnel prototype is the Agile Hunter by Lockheed Martin [7][8][9]. Funded by DARPA within the MAS program, the prototype was based on a military UAV capable of folding the inner sections of the wing near to the fuselage, to reduce the surface area and drag during transonic flight at low altitude (also called a Z-wing).…”

Section: Introductionmentioning

confidence: 99%

Span morphing using the GNATSpar wing

Ajaj

Friswell

Bourchak

et al. 2016

Aerospace Science and Technology

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Rigid wings usually fly at sub-optimal conditions generating unnecessary aerodynamic loses represented in flight time, fuel consumption, and unfavourable operational characteristics. High aspect ratio wings have good range and fuel efficiency, but lack manoeuvrability. On the other hand, low aspect ratio wings fly faster and are more manoeuvrable, but have poor aerodynamic performance. Span morphing technology allows integrating both features in a single wing design and allows continuously adjusting the wingspan to match the instantaneous flight conditions and mission objectives. This paper develops, a novel span morphing concept, the Gear driveN Autonomous Twin Spar (GNATSpar) for a mini-UAV. The GNATSpar can be used to achieve span extensions up to 100% but for demonstration purposes it is used here to achieve span extensions up to 20% to reduce induced drag and increase flight endurance. The GNATSpar is superior to conventional telescopic and articulated structures as it uses the space available in the opposite sides of the wing instead of relying on overlapping structures and bearings. In addition, it has a self-locking actuation mechanism due to the low lead angle of the driving worm gear. Following the preliminary aero-structural sizing of the concept, a physical prototype is developed and tested in the 7 × 5 wind-tunnel at the University of Southampton. Finally, benefits and drawbacks of the design are highlighted and analysed.

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Design of a Morphing Vehicle

Cited by 87 publications

References 2 publications

One Dimensional Morphing Structures for Advanced Aircraft

One Dimensional Morphing Structures for Advanced Aircraft

Control Law Design for Perching an Agile MAV with Articulated Wings

Span morphing using the GNATSpar wing

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