Fluid/Structure-Interaction Analysis of the Fish-Bone-Active-Camber Morphing Concept

Woods, Benjamin K.S.; Dayyani, Iman; Friswell, Michael I.

doi:10.2514/1.c032725

Cited by 62 publications

(43 citation statements)

References 17 publications

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“…The initial study here will show how the BTNS mechanism can be applied for energy balancing in a morphing application, as most morphing applications require external actuation, and many have high internal structural loads to overcome, for example [27]. A recently introduced active camber concept known as the fish bone active camber (FishBAC) mechanism is considered as the load in this paper [28,29]. In this case, both the aerodynamic load and the elastic deformation of the structure were considered and the analytical formulation was derived from Euler-Bernoulli beam theory.…”

Section: Case Study: Morphing Wing Section and Optimisationmentioning

confidence: 99%

“…Figure 14 shows the predicted shapes of the morphed profiles for the range of the tendon pulley rotation angles studied, along with a schematic representation of the spine bending displacement. This structural model is analytical and derived from Euler-Bernoulli beam theory, and the torque produced by the pulley rotation is assumed to induce a moment on the FishBAC [28]. The required moment to actuate the active camber is provided by a rotary actuator, which can be solved by prescribing the tendon spooling pulley rotation angle, as shown in Fig.…”

Section: Case Study: Morphing Wing Section and Optimisationmentioning

confidence: 99%

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Bidirectional torsional negative stiffness mechanism for energy balancing systems

Zhang

Shaw

Amoozgar

et al. 2019

Mechanism and Machine Theory

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A new concept of an integrated bidirectional torsional negative stiffness mechanism is introduced which allows for passive energy balancing of mechanical systems by reducing actuation requirements and improving energy efficiency. This novel design is a modular device, is bidirectional and is easily integrated and customised for different applications. The energy balance concept is achieved by employing a negative stiffness system to couple with a positive stiffness system of the mechanical system to create a zero stiffness system which can be driven with lower energy requirements. The bidirectional torsional negative stiffness mechanism proposed here uses a series of pre-compressed springs around a bidirectional torque shaft to convert decreasing force in the springs into increasing torque output through geometric reconfiguration to generate the negative stiffness characteristic. The kinematics of the negative stiffness mechanism were derived and a physical model was assembled from LEGO ® components for validation. An analytical model was developed for prediction and the numerical results showed that a satisfactory performance can be generated to match the torque requirements. An experimental demonstrator was then built and tested to verify the predictions from the analysis. To show the impact of the energy balancing concept on actuator efficiency, a representative case study is made of a tendon-driven morphing active camber mechanism. The performance of the optimised bidirectional negative stiffness device is investigated to shows an improvement by the kinematics tailoring.

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Section: Case Study: Morphing Wing Section and Optimisationmentioning

confidence: 99%

Section: Case Study: Morphing Wing Section and Optimisationmentioning

confidence: 99%

Bidirectional torsional negative stiffness mechanism for energy balancing systems

Zhang

Shaw

Amoozgar

et al. 2019

Mechanism and Machine Theory

Self Cite

View full text Add to dashboard Cite

show abstract

“…The additional structure may increase the weight and negate any aerodynamic improvements being realised for mission efficiency. Cross-sectional parameters, such as camber [15][16][17], can be used to improve flight efficiency through improving the spanwise lift distribution. Modifications to the wing cross-section require potentially fewer structural compromises and less added mass than planform changes, but possibly offer only marginal gains in efficiency when compared to span morphing.…”

Section: Introductionmentioning

confidence: 99%

Performance Comparison between Optimised Camber and Span for a Morphing Wing

et al. 2015

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Morphing technology offers a strategy to modify the wing geometry, and the wing planform and cross-sectional parameters can be optimised to the flight conditions. This paper presents an investigation into the effect of span and camber morphing on the mission performance of a 25-kg UAV, with a straight, rectangular, unswept wing. The wing is optimised over two velocities for various fixed wing and morphing wing strategies, where the objective is to maximise aerodynamic efficiency or range. The investigation analyses the effect of the low and high speed velocity selected, the weighting of the low and high velocity on the computation of the mission parameter, the maximum allowable span retraction and the weight penalty on the mission performance. Models that represent the adaptive aspect ratio (AdAR) span morphing concept and the fish bone active camber (FishBAC) camber morphing concept are used to investigate the effect on the wing parameters. The results indicate that generally morphing for both span and camber, the aerodynamic efficiency is maximised for a 30%-70% to 40%-60% weighting between the low and high speed flight conditions, respectively. The span morphing strategy with optimised fixed camber at the root can deliver up to 25% improvement in the aerodynamic efficiency over a fixed camber and span, for an allowable 50% retraction with a velocity range of 50-115 kph. Reducing the allowable retraction to 25% reduces the improvement to 8%-10% for a 50%-50% mission weighting. Camber morphing offers a maximum of 4.5% improvement approximately for a velocity range of 50-90 kph. Improvements in the efficiency achieved through camber Aerospace 2015, 2 525 morphing are more sensitive to the velocity range in the mission, generally decreasing rapidly by reducing or increasing the velocity range, where span morphing appears more robust for an increase in velocity range beyond the optimum. However, where span morphing requires considerable modification to the planform, the camber change required for optimum performance is only a 5% trailing edge tip deflection relative to cross-sectional chord length. Span morphing, at the optimal mission velocity range, with 25% allowable retraction, can allow up to a 12% increase in mass before no performance advantage is observed, where the camber morphing only allows up to 3%. This provides the designer with a mass budget that must be achieved for morphing to be viable to increase the mission performance.

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“…In this section, a static aeroelastic analysis procedure is developed using an aerodynamic routine Xfoil, a two-dimensional viscous panel model which has been widely used for aerofoil design and fluid/structure coupling analysis (Woods et al, 2015;Daynes and Weaver 2012b). In the aero-structural design optimization procedures, aerodynamic loads are calculated and transferred to the structural model noting that different ways have been used in the literature (De Gaspari et al, 2011):…”

Section: Static Aeroelastic Analysismentioning

confidence: 99%

Design and mechanical testing of a variable stiffness morphing trailing edge flap

Azarpeyvand²

2017

Journal of Intelligent Material Systems and Structures

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Morphing structures that are both light-weight and conformal to the aerofoil are currently being considered as promising candidates for the next generation of aircraft high-lift systems. Utilizing spatially variable stiffness materials in morphing structures leads to a possible reduction in the actuation energy requirement and also enables geometric control over the deformed shape of the morphing structure, resulting in enhanced aerodynamic and aeroacoustic performance. In this study, a design optimization methodology has been developed to identify the required material stiffness variations of a morphing structure for target optimal deformed shapes. In the optimization scheme, a layer-wise sandwich beam model is used to predict the structural behaviour of the flap with a specific material stiffness variation. Two-dimensional fluid/structure static aeroelastic interaction analysis is performed in the design optimization. Finite element analysis and mechanical tests were also carried out for a chosen optimization result to study the actuation requirements and the capability of control over the deformed shape of the morphing trailing edge. Numerical and experimental results confirm the feasibility of the proposed optimization methodology for identifying the required stiffness variation in the core and also ways of using rapid prototyped honeycomb core to realize the honeycomb core stiffness variations are discussed.

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Fluid/Structure-Interaction Analysis of the Fish-Bone-Active-Camber Morphing Concept

Cited by 62 publications

References 17 publications

Bidirectional torsional negative stiffness mechanism for energy balancing systems

Bidirectional torsional negative stiffness mechanism for energy balancing systems

Performance Comparison between Optimised Camber and Span for a Morphing Wing

Design and mechanical testing of a variable stiffness morphing trailing edge flap

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