A Multi-Fidelity, Multi-Disciplinary Analysis and Optimization Framework for the Design of Morphing UAV Wing

Ciarella, Andrea; Tsotskas, Christos; Hahn, Marco; Werter, Noud; Breuker, Roeland De; Beaverstock, C.S.; Friswell, Michael I.; Yang, Yosheph; Ozgen, Serkan; Antoniadis, Antonios; Drikakis, Dimitris; Tsoutsanis, Panagiotis

doi:10.2514/6.2015-2326

Cited by 8 publications

(4 citation statements)

References 2 publications

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“…However, in the computational framework developed during the CHANGE project, a RANS solver was already made available, so it was used without further effort. Brief explanation regarding the RANS solver used in the CHANGE project can be found in a publication authored by CHANGE project partners (Ciarella et al, 2015). In the publication, a comparison between drag computations of a low-fidelity analysis (using VLM method) and high-fidelity analysis (using RANS solver) is briefly discussed.…”

Section: Aerodynamic Analysesmentioning

confidence: 99%

Structural and aerodynamic analyses of a hybrid trailing edge control surface of a fully morphing wing

Gürses

Tunçöz

Yang

et al. 2016

Journal of Intelligent Material Systems and Structures

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In this article, the design and analysis of a hybrid trailing edge control surface of an unmanned aerial vehicle are presented. The structural design was performed to increase and decrease the camber of the control surface to match selected airfoil profiles. The design was first analyzed with the help of finite element method to assess the morphing capability. The morphed control surface was then analyzed aerodynamically and comparisons with the original target profiles were made. According to the aerodynamic analyses, it was concluded that the control surface can successfully morph into target profiles with very minor changes in the target aerodynamic values while still ensuring the structural integrity and the safety of the control surface.

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Section: Aerodynamic Analysesmentioning

confidence: 99%

Structural and aerodynamic analyses of a hybrid trailing edge control surface of a fully morphing wing

Gürses

Tunçöz

Yang

et al. 2016

Journal of Intelligent Material Systems and Structures

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“…In comparison with standard wing designs, the advantages of morphing wing are numerous. It can help optimize the lift-to-drag ratio of the wing during both high-and low-speed cruise (Jha and Kudva 2004;Coutu et al 2009), improve the maneuverability of the plane , expand the flight envelope (Ciarella et al 2015), reduce parasite drag, reduce vibration and flutter (Wilson 2002;Thill et al 2008;Sabri and Meguid 2011), and gain control of the local aerodynamic condition (Stanewsky 2001).…”

Section: Introductionmentioning

confidence: 99%

Complete morphing wing design using flexible-rib system

Meguid

Wang

2015

Int J Mech Mater Des

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This study is concerned with the complete design, analysis, functional prototyping and flight testing of a novel morphing wing system for use in a relatively small (\10 kg) unmanned aerial vehicles (UAVs). To achieve improved flight performance with limited weight penalty, camber-adjustable morphing wing was designed using flexible servomotor-actuated mechanisms. The current design, which was originally conceptualized by Monner et al. (Smart structures and materials: industrial and commercial applications of smart structures technologies. Proceedings of SPIE 3326, pp 60-70, 1998), ensures that the airfoil shape of the wing is able to continuously morph between the non-cambered and the cambered configurations. The morphing function of the wing is achieved using a flexible-rib system driven by onboard servomotorrocker. This unique design of a flexible-rib assembly enables the airfoil of the wing to be accurately morphed to the target configuration. With the aid of aerodynamic and finite element analyses, the flexible rib assembly performance and structural integrity are evaluated and assessed. The design process was in compliance with aircraft design standards, including the Federal Aviation Regulations-Part 23. The functional prototype of the flexible rib morphingwing enabled UAV was manufactured and assembled and a test plane was ground tested. The success of the entire project, including flight testing of the flexible rib assembly is summarized in this paper.

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“…Much of the research in these programmes was focused on individual non-integrated morphing, actuation, or sensing concepts. These programmes focused on topics such as, but not limited to, morphing using compliant mechanisms [7], span and chord morphing mechanisms [8], or aircraft sensing methods [9]. Only occasionally did hardware demonstrators contain multiple actuation or sensing concepts.…”

Section: Introductionmentioning

confidence: 99%

Overview of the SmartX Wing Technology Integrator

Breuker

Mkhoyan²,

Nazeer³

et al. 2022

Actuators

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This article describes the challenges of integrating smart sensing, actuation, and control concepts into an over-sensed and over-actuated technology integrator. This technology integrator has more control inputs than the expected responses or outputs (over-actuated), and its every state is measured using more than one sensor system (over-sensed). The hardware integration platform is chosen to be a wind tunnel model of a low-speed aircraft wing such that it can be tested in a large university-level wind tunnel. This hardware technology integrator is designed for multiple objectives. The nature of these objectives is aerodynamic, structural, and aeroelastic, or, more specifically; drag reduction, static and dynamics loads control, aeroelastic stability control, and lift control. Enabling technologies, such as morphing, piezoelectric actuation and sensing, and fibre-optic sensing are selected to fulfil the mentioned objectives. The technology integration challenges are morphing, actuation integration, sensor integration, software and data integration, and control system integration. The built demonstrator shows the intended level of technology integration.

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A Multi-Fidelity, Multi-Disciplinary Analysis and Optimization Framework for the Design of Morphing UAV Wing

Cited by 8 publications

References 2 publications

Structural and aerodynamic analyses of a hybrid trailing edge control surface of a fully morphing wing

Structural and aerodynamic analyses of a hybrid trailing edge control surface of a fully morphing wing

Complete morphing wing design using flexible-rib system

Overview of the SmartX Wing Technology Integrator

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