Design and conception of a trailing edge morphing wing concept with bistable composite skin

2020 ◽  
Author(s):  
Aghna Mukherjee ◽  
Deepak Kumar ◽  
Shaikh F. Ali ◽  
Arunachalakasi Arockiarajan
Keyword(s):  
Morphing Wing ◽  
Trailing Edge

scholarly journals Design And Experimental Studies Of Flexible Trailing Edge For Variable Camber Morphing Wing

2021 ◽  
Author(s):  
Ahmad T. Kalaji
Keyword(s):  
Experimental Data ◽  
Carbon Fiber ◽  
Deflection Angle ◽  
Experimental Studies ◽  
Morphing Wing ◽  
Trailing Edge ◽  
Wing Section ◽  
Rigid Constraint ◽  
The Difference

This thesis presents a flexible trailing edge mechanism capable of undergoing a change in camber for a wing section. The mechanism takes advantage of a rigid constraint between the ends of two flexible carbon fiber panels, which produces a deflection when there is a difference in length between the two panels. A prototype was designed and built and experimental data was collected for the deformation of the panels for different values of lengths and analyzed to find a function to describe the coefficients which form the polynomials describing the shape for each of the panels, based on the difference in length value. Deflection and deflection angle results were used to develop a controller which will calculate the required change in length based on a deflection or angle and a bottom panel length input.

Analysis and optimization of morphing wing aerodynamics

2019 ◽  
Vol 91 (3) ◽  
pp. 538-546 ◽  
Author(s):  
Witold Artur Klimczyk ◽  
Zdobyslaw Jan Goraj
Keyword(s):  
Optimal Solution ◽  
Design Sensitivity ◽  
Substantial Improvement ◽  
Surface Model ◽  
Morphing Wing ◽  
Trailing Edge ◽  
Significant Information ◽  
Content Type ◽  
Additional Information ◽  
Wing Optimization

PurposeThe purpose of this paper is to present a method for analysis and optimization of morphing wing. Moreover, a numerical advantage of morphing airfoil wing, typically assessed in simplified two-dimensional analysis is found using higher fidelity methods.Design/methodology/approachBecause of multi-point nature of morphing wing optimization, an approach for optimization by analysis is presented. Starting from naïve parametrization, multi-fidelity aerodynamic data are used to construct response surface model. From the model, many significant information are extracted related to parameters effect on objective; hence, design sensitivity and, ultimately, optimal solution can be found.FindingsThe method was tested on benchmark problem, with some easy-to-predict results. All of them were confirmed, along with additional information on morphing trailing edge wings. It was found that wing with morphing trailing edge has around 10 per cent lower drag for the same lift requirement when compared to conventional design.Practical implicationsIt is demonstrated that providing a smooth surface on wing gives substantial improvement in multi-purpose aircrafts. Details on how this is achieved are described. The metodology and results presented in current paper can be used in further development of morphing wing.Originality/valueMost of literature describing morphing airfoil design, optimization or calculations, performs only 2D analysis. Furthermore, the comparison is often based on low-fidelity aerodynamic models. This paper uses 3D, multi-fidelity aerodynamic models. The results confirm that this approach reveals information unavailable with simplified models.

Aero-servo-elastic design of a morphing wing trailing edge system for enhanced cruise performance

2019 ◽  
Vol 86 ◽  
pp. 215-235 ◽  
Author(s):  
Maurizio Arena ◽  
Antonio Concilio ◽  
Rosario Pecora
Keyword(s):  
Morphing Wing ◽  
Trailing Edge ◽  
Elastic Design

Multi-fidelity Aeroelastic Simulation of a Morphing Wing Trailing Edge

2021 ◽  
Author(s):  
Kensuke Soneda ◽  
Tomohiro Yokozeki ◽  
Taro Imamura ◽  
Natsuki Tsushima
Keyword(s):  
Morphing Wing ◽  
Trailing Edge

scholarly journals AERODYNAMIC CHARACTERISTIC OF THE ACTIVE COMPLIANT TRAILING EDGE CONCEPT

2016 ◽  
Vol 42 ◽  
pp. 1660173
Author(s):  
RUI NIE ◽  
JINHAO QIU ◽  
HONGLI JI ◽  
DAWEI LI
Keyword(s):  
Flow Separation ◽  
Aerodynamic Characteristic ◽  
High Strength ◽  
Aerodynamic Characteristics ◽  
Structure Design ◽  
Field Analysis ◽  
Design Parameters ◽  
Morphing Wing ◽  
Trailing Edge ◽  
Noise Characteristics

This paper introduces a novel Morphing Wing structure known as the Active Compliant Trailing Edge (ACTE). ACTE structures are designed using the concept of “distributed compliance” and wing skins of ACTE are fabricated from high-strength fiberglass composites laminates. Through the relative sliding between upper and lower wing skins which are connected by a linear guide pairs, the wing is able to achieve a large continuous deformation. In order to present an investigation about aerodynamics and noise characteristics of ACTE, a series of 2D airfoil analyses are established. The aerodynamic characteristics between ACTE and conventional deflection airfoil are analyzed and compared, and the impacts of different ACTE structure design parameters on aerodynamic characteristics are discussed. The airfoils mentioned above include two types (NACA0012 and NACA64A005.92). The computing results demonstrate that: compared with the conventional plane flap airfoil, the morphing wing using ACTE structures has the capability to improve aerodynamic characteristic and flow separation characteristic. In order to study the noise level of ACTE, flow field analysis using LES model is done to provide noise source data, and then the FW-H method is used to get the far field noise levels. The simulation results show that: compared with the conventional flap/aileron airfoil, the ACTE configuration is better to suppress the flow separation and lower the overall sound pressure level.

Unsteady aerodynamic characteristics of a morphing wing

2018 ◽  
Vol 91 (1) ◽  
pp. 1-9 ◽  
Author(s):  
Jinwu Xiang ◽  
Kai Liu ◽  
Daochun Li ◽  
Chunxiao Cheng ◽  
Enlai Sha
Keyword(s):  
Lift Coefficient ◽  
Angle Of Attack ◽  
Large Angle ◽  
Unsteady Aerodynamics ◽  
Aerodynamic Characteristics ◽  
Static Case ◽  
Morphing Wing ◽  
Trailing Edge ◽  
Content Type ◽  
Unsteady Aerodynamic

Purpose The purpose of this paper is to investigate the unsteady aerodynamic characteristics in the deflection process of a morphing wing with flexible trailing edge, which is based on time-accurate solutions. The dynamic effect of deflection process on the aerodynamics of morphing wing was studied. Design/methodology/approach The computational fluid dynamic method and dynamic mesh combined with user-defined functions were used to simulate the continuous morphing of the flexible trailing edge. The steady aerodynamic characteristics of the morphing deflection and the conventional deflection were studied first. Then, the unsteady aerodynamic characteristics of the morphing wing were investigated as the trailing edge deflects at different rates. Findings The numerical results show that the transient lift coefficient in the deflection process is higher than that of the static case one in large angle of attack. The larger the deflection frequency is, the higher the transient lift coefficient will become. However, the situations are contrary in a small angle of attack. The periodic morphing of the trailing edge with small amplitude and high frequency can increase the lift coefficient after the stall angle. Practical implications The investigation can afford accurate aerodynamic information for the design of aircraft with the morphing wing technology, which has significant advantages in aerodynamic efficiency and control performance. Originality/value The dynamic effects of the deflection process of the morphing trailing edge on aerodynamics were studied. Furthermore, time-accurate solutions can fully explore the unsteady aerodynamics and pressure distribution of the morphing wing.

scholarly journals Synthesis, Analysis, and Design of a Novel Mechanism for the Trailing Edge of a Morphing Wing

Aerospace ◽  
2018 ◽  
Vol 5 (4) ◽  
pp. 127 ◽  
Author(s):  
Harun Levent Şahin ◽  
Yavuz Yaman
Keyword(s):  
Dynamic Force ◽  
Morphing Wing ◽  
Trailing Edge ◽  
Aerodynamic Efficiency ◽  
Structural Mechanism ◽  
Analysis And Design ◽  
Design Error ◽  
Morphing Wings ◽  
Wing Skin ◽  
Four Bar Linkage

In the design and analysis of morphing wings, several sciences need to be integrated. This article tries to answer the question, “What is the most appropriate actuation mechanism to morph the wing profile?” by introducing the synthesis, analysis, and design of a novel scissor-structural mechanism (SSM) for the trailing edge of a morphing wing. The SSM, which is deployable, is created via a combination of various scissor-like elements (SLEs). In order to provide mobility requirements, a four-bar linkage (FBL) is assembled with the proposed SSM. The SSM is designed with a novel kinematic synthesis concept, so it follows the airfoil camber with minimum design error. In this concept, assuming a fully-compliant wing skin, various types of SLEs are assembled together, and emergent SSM provide the desired airfoil geometries. In order to provide the required aerodynamic efficiency of newly-created airfoil geometries and obtain pressure distribution over the airfoil, two-dimensional (2D) aerodynamic analyses have been conducted. The analyses show similar aerodynamic behavior with the desired NACA airfoils. By assigning the approximate link masses and mass centers, the dynamic force analysis of the mechanism has also been performed, and the required torque to drive the newly-developed SSM is estimated as feasible.

scholarly journals Implementation of a Hybrid Electro-Active Actuated Morphing Wing in Wind Tunnel

2017 ◽  
Vol 260 ◽  
pp. 85-91 ◽  
Author(s):  
Gurvan Jodin ◽  
Johannes Scheller ◽  
Eric Duhayon ◽  
Jean François Rouchon ◽  
Marianna Braza
Keyword(s):  
Wind Tunnel ◽  
Shape Memory ◽  
Low Frequency ◽  
Aerodynamic Performance ◽  
Point Of View ◽  
Morphing Wing ◽  
Wind Tunnel Experiments ◽  
Trailing Edge ◽  
Actuation System ◽  
Hybrid Actuation

Amongst current aircraft research topics, morphing wing is of great interest for improving the aerodynamic performance. A morphing wing prototype has been designed for wind tunnel experiments. The rear part of the wing - corresponding to the retracted flap - is actuated via a hybrid actuation system using both low frequency camber control and a high frequency vibrating trailing edge. The camber is modified via surface embedded shape memory alloys. The trailing edge vibrates thanks to piezoelectric macro-fiber composites. The actuated camber, amplitude and frequency ranges are characterized. To accurately control the camber, six independent shape memory alloy wires are controlled through nested closed-loops. A significant reduction in power consumption is possible via this control strategy. The effects on flow via morphing have been measured during wind tunnel experiments. This low scale mock-up aims to demonstrate the hybrid morphing concept, according to actuator capabilities point of view as well as aerodynamic performance.

scholarly journals Design And Aerodynamic Analysis Of Compliant Mechanism Based Morphing Wings

2021 ◽  
Author(s):  
Stephen D. Sharp
Keyword(s):  
Flow Separation ◽  
Compliant Mechanism ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Discrete Control ◽  
Morphing Wing ◽  
Trailing Edge ◽  
Morphing Wings ◽  
Drag Ratio ◽  
Lift To Drag Ratio

Aircraft today use discrete control surface, typically mounted using pin and sliding joints. These designs can lead to high part-count assemblies and backlash within the assemblies that require lubrication and frequent maintenance. These wing designs also feature fixed dimensions and do not allow for geometry changes mid-flight. These limitations lead to a compromised design that must work relatively well in all situations. This causes inefficiencies in all stages of flight. The Wright brothers, who achieved the first successful powered flight did not use these techniques. Instead they used a system on cables to apply tension and bend the wings to changes their angle of attack. They called this technique wing warping. As aviation advanced it quickly moved from the wing-warping technique towards the discrete element control surfaces. However, there is renewed interest in techniques such as wing warping as the idea of morphing wings becomes more prevalent in aerospace research. Morphing wings would allow for changing major characteristics, such as camber, span, sweep, etc. of the wing mid-flight and allow for continuous optimization through all stages of its mission. The design covered in this thesis was centered around camber morphing of the wing in flight. Biomimicry played a large role in the design, with research into the skeletal systems of birds and fish used to dictate the rib structures. This bio-inspired path led to the use of compliant mechanisms for the ribs. This choice allowed for a low part-count and zero-backlash design that would require no maintenance and have a very long service life due to an extremely low amount of fatigue. Several design iterations were tested with different common desktop 3-D printing materials. The final rib design was made of PETG and whose compliant shape was directly inspired by the skeletal structure of the spine of a fish. The design proved to be extremely reliable and robust. Skin design has long been one of the biggest hurdles of morphing wing design. Most research reviewed in this paper used an elastomer style skin that was pre-stretched to reduce buckling under compression. Through testing it was found that this method is difficult and unreliable to maintain a smooth and continuous surface. Even when pre-stretching, the elastomer would fatigue and buckle under compression. The final design was a PETG panel with a web and flange that would interact with the rib structure and was able to translate chordwise along the rib as the wing altered its camber. The skin had built-in flexures to reduce bending actuation forces. The wing also featured a rigid leading-edge skin panel with which the other skin panels would be able to slide under to maintain skin coverage under both extension and compression of the wing surfaces. This however led to aerodynamic problems that were discovered in the CFD analysis. The wing was prepared for CFD using finite element analysis to produced morphed wing bodies for a 0, 10, 20, and 30-degree trailing edge deflection angles. A model was also produced of the same base airfoil (NACA 0018) with a hinged flap of 30% chord length deflected by the same amount to serve as a performance benchmark for the morphing wing. The main criteria used to evaluate the performance were the lift, drag, and lift-to-drag ratios. For the 0⁰ tests, the morphing wing had up to almost 29% higher drag at high speeds. The results showed that the 10⁰ deflection tests found up to a 115% increase in lift over the hinged flap design and a lift-to-drag ratio of up to 161% higher for the morphing wing. The 20⁰ and 30⁰ tests saw the lift advantage of the morphing wing decrease but on average across all tests, the morphing wing had a lift coefficient higher than the hinged flap by 43%. Additionally, for the large deflection tests the hinged flap had up to a 60.5% advantage in lift-to-drag ratio. The computational fluid dynamic analysis showed that due to the larger effective angle of attack and the step-down in the skin of the morphing wing, at larger deflection angles the flow would separate much earlier along the chord. Therefore, based on the analysis, the morphing wing would create a substantial performance and efficiency gains when wing trailing edge deflection was kept below 20⁰. This meant it would be suitable for stages of flight such as takeoff and climb. Planned future work aims to reduce the 0⁰ drag of the morphing wing as well as the early flow separation at high angles of deflection. It is assumed, that by scaling up the wing, the proportion of the step size will decrease dramatically and as a result would improve the flow characteristics. Additionally, the placement and rotational limits of the flexures can be tested further to optimize the morphed shape to reduce the severity of the adverse pressure gradient along the upper surface when in high deflection states. With continued work on improving the flow separation, this design proves promising for even high-deflection cases. Overall the V4 rib design and the accompanying compliant skin panel design were very successful for their initial tests.

scholarly journals Design And Aerodynamic Analysis Of Compliant Mechanism Based Morphing Wings

2021 ◽  
Author(s):  
Stephen D. Sharp
Keyword(s):  
Flow Separation ◽  
Compliant Mechanism ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Discrete Control ◽  
Morphing Wing ◽  
Trailing Edge ◽  
Morphing Wings ◽  
Drag Ratio ◽  
Lift To Drag Ratio

Aircraft today use discrete control surface, typically mounted using pin and sliding joints. These designs can lead to high part-count assemblies and backlash within the assemblies that require lubrication and frequent maintenance. These wing designs also feature fixed dimensions and do not allow for geometry changes mid-flight. These limitations lead to a compromised design that must work relatively well in all situations. This causes inefficiencies in all stages of flight. The Wright brothers, who achieved the first successful powered flight did not use these techniques. Instead they used a system on cables to apply tension and bend the wings to changes their angle of attack. They called this technique wing warping. As aviation advanced it quickly moved from the wing-warping technique towards the discrete element control surfaces. However, there is renewed interest in techniques such as wing warping as the idea of morphing wings becomes more prevalent in aerospace research. Morphing wings would allow for changing major characteristics, such as camber, span, sweep, etc. of the wing mid-flight and allow for continuous optimization through all stages of its mission. The design covered in this thesis was centered around camber morphing of the wing in flight. Biomimicry played a large role in the design, with research into the skeletal systems of birds and fish used to dictate the rib structures. This bio-inspired path led to the use of compliant mechanisms for the ribs. This choice allowed for a low part-count and zero-backlash design that would require no maintenance and have a very long service life due to an extremely low amount of fatigue. Several design iterations were tested with different common desktop 3-D printing materials. The final rib design was made of PETG and whose compliant shape was directly inspired by the skeletal structure of the spine of a fish. The design proved to be extremely reliable and robust. Skin design has long been one of the biggest hurdles of morphing wing design. Most research reviewed in this paper used an elastomer style skin that was pre-stretched to reduce buckling under compression. Through testing it was found that this method is difficult and unreliable to maintain a smooth and continuous surface. Even when pre-stretching, the elastomer would fatigue and buckle under compression. The final design was a PETG panel with a web and flange that would interact with the rib structure and was able to translate chordwise along the rib as the wing altered its camber. The skin had built-in flexures to reduce bending actuation forces. The wing also featured a rigid leading-edge skin panel with which the other skin panels would be able to slide under to maintain skin coverage under both extension and compression of the wing surfaces. This however led to aerodynamic problems that were discovered in the CFD analysis. The wing was prepared for CFD using finite element analysis to produced morphed wing bodies for a 0, 10, 20, and 30-degree trailing edge deflection angles. A model was also produced of the same base airfoil (NACA 0018) with a hinged flap of 30% chord length deflected by the same amount to serve as a performance benchmark for the morphing wing. The main criteria used to evaluate the performance were the lift, drag, and lift-to-drag ratios. For the 0⁰ tests, the morphing wing had up to almost 29% higher drag at high speeds. The results showed that the 10⁰ deflection tests found up to a 115% increase in lift over the hinged flap design and a lift-to-drag ratio of up to 161% higher for the morphing wing. The 20⁰ and 30⁰ tests saw the lift advantage of the morphing wing decrease but on average across all tests, the morphing wing had a lift coefficient higher than the hinged flap by 43%. Additionally, for the large deflection tests the hinged flap had up to a 60.5% advantage in lift-to-drag ratio. The computational fluid dynamic analysis showed that due to the larger effective angle of attack and the step-down in the skin of the morphing wing, at larger deflection angles the flow would separate much earlier along the chord. Therefore, based on the analysis, the morphing wing would create a substantial performance and efficiency gains when wing trailing edge deflection was kept below 20⁰. This meant it would be suitable for stages of flight such as takeoff and climb. Planned future work aims to reduce the 0⁰ drag of the morphing wing as well as the early flow separation at high angles of deflection. It is assumed, that by scaling up the wing, the proportion of the step size will decrease dramatically and as a result would improve the flow characteristics. Additionally, the placement and rotational limits of the flexures can be tested further to optimize the morphed shape to reduce the severity of the adverse pressure gradient along the upper surface when in high deflection states. With continued work on improving the flow separation, this design proves promising for even high-deflection cases. Overall the V4 rib design and the accompanying compliant skin panel design were very successful for their initial tests.

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