MANUFACTURING METHOD OF THE MORPHING WING STRUCTURE FOR UAV BY CFRP WITH APPLYING THE ELECTROFORMED RESIN MOLDING METHOD

2021 ◽  
Author(s):  
KAZUAKI KATAGIRI ◽  
CHOONG SIK PARK ◽  
SHIMPEI YAMAGUCHI ◽  
SONOMI KAWAKITA ◽  
KIM DAEKWI ◽  
...  
Keyword(s):  
Carbon Fiber ◽  
Flight Control ◽  
Lattice Structure ◽  
Polymer Particle ◽  
Morphing Wing ◽  
Aircraft Wing ◽  
Manufacturing Method ◽  
Morphing Wings ◽  
Wing Structure ◽  
Sufficient Strength

Aircraft flight control usually requires driving flaps and ailerons. However, the air drags increase significantly due to the corners of flaps and aileron. Especially, the gap between mother wing and flap / aileron causes a drag increase. Therefore, studies are being conducted on morphing wings that smoothly and greatly deform the wing surface. For aircraft wing, it is needless to say that strength is important to sustain lift and drag for the aircraft during the flight. For morphing wings, in addition, actuators must be mounted inside the wing to enable the morphing deformation. Moreover, for the aircraft wing, weight is quite important. Therefore, carbon fiber reinforced plastic (CFRP) is currently most suitable for aircraft wing structural materials. However, it is difficult to mold CFRP so that it has sufficient strength and can be morphed. In this study, by using CFRP, the morphing wing structure was prototyped with targeting a small unmanned aerial vehicle (UAV) weighing 3 kg. The CFRP lattice structure that enables morphing deformation was designed and manufactured by applying the electrodeposition resin molding (ERM) method which was developed by the authors. In the ERM method, firstly, the carbon fiber was fixed with a jig according to the designed morphing wing structure, and immersed in the electrodeposition solution. Secondly, the epoxy polymer particle in the solution were electrophoresed and impregnated between carbon fibers. After thermal curing, the morphing wing structure was fabricated. Further, the loading-unloading torsion and bending tests of the morphing wing structure were carried out. Smooth morphing deformation and sufficient strength were confirmed.

Numerical study of geometric morphing wings of the 1303 UCAV

2021 ◽  
pp. 1-17
Author(s):  
B. Nugroho ◽  
J. Brett ◽  
B.T. Bleckly ◽  
R.C. Chin
Keyword(s):  
Flight Control ◽  
Numerical Study ◽  
Aerodynamic Characteristics ◽  
Morphing Wing ◽  
Rolling Moment ◽  
Wide Range ◽  
Morphing Wings ◽  
Wing Geometry ◽  
Lift And Drag ◽  
Wing Morphing

ABSTRACT Unmanned Combat Aerial Vehicles (UCAVs) are believed by many to be the future of aerial strike/reconnaissance capability. This belief led to the design of the UCAV 1303 by Boeing Phantom Works and the US Airforce Lab in the late 1990s. Because UCAV 1303 is expected to take on a wide range of mission roles that are risky for human pilots, it needs to be highly adaptable. Geometric morphing can provide such adaptability and allow the UCAV 1303 to optimise its physical feature mid-flight to increase the lift-to-drag ratio, manoeuvrability, cruise distance, flight control, etc. This capability is extremely beneficial since it will enable the UCAV to reconcile conflicting mission requirements (e.g. loiter and dash within the same mission). In this study, we conduct several modifications to the wing geometry of UCAV 1303 via Computational Fluid Dynamics (CFD) to analyse its aerodynamic characteristics produced by a range of different wing geometric morphs. Here we look into two specific geometric morphing wings: linear twists on one of the wings and linear twists at both wings (wash-in and washout). A baseline CFD of the UCAV 1303 without any wing morphing is validated against published wind tunnel data, before proceeding to simulate morphing wing configurations. The results show that geometric morphing wing influences the UCAV-1303 aerodynamic characteristics significantly, improving the coefficient of lift and drag, pitching moment and rolling moment.

scholarly journals Ground Structures-Based Topology Optimization of a Morphing Wing Using a Metaheuristic Algorithm

Metals ◽  
2021 ◽  
Vol 11 (8) ◽  
pp. 1311
Author(s):  
Seksan Winyangkul ◽  
Kittinan Wansaseub ◽  
Suwin Sleesongsom ◽  
Natee Panagant ◽  
Sumit Kumar ◽  
...  
Keyword(s):  
Topology Optimization ◽  
Optimization Problems ◽  
Future Research ◽  
Structural Constraints ◽  
Metaheuristic Algorithm ◽  
Morphing Wing ◽  
Aircraft Wing ◽  
Multi Objective ◽  
Wing Structures ◽  
Wing Structure

This paper presents multi-objective topology and sizing optimization of a morphing wing structure. The purpose of this paper is to design a new aircraft wing structure with a tapered shape for ribs, spars, and skins including a torsion beam for external actuating torques, which is anticipated to modify the aeroelastic characteristic of the aircraft wing using multi-objective optimization. Two multi-objective topology optimization problems are proposed employing ground element structures with high- and low-grid resolutions. The design problem is to minimize mass, maximize difference of lift effectiveness, and maximize the buckling factor of an aircraft wing subject to aeroelastic and structural constraints including lift effectiveness, critical speed, and buckling factors. The design variables include aircraft wing structure dimensions and thickness distribution. The proposed optimization problems are solved by an efficient multi-objective metaheuristic algorithm while the results are compared and discussed. The Pareto optimal fronts obtained for all tests were compared based on a hypervolume metric. The objective function values for Case I and Case II at 10 selected optimal solutions exhibit a range of structural mass as 115.3216–411.6250 kg, 125.0137–440.5869 kg, lift effectiveness as 1.0514–1.1451, 1.0834–1.1639 and bucking factor as 38.895–1133.1864 Hz, 158.1264–1844.4355 Hz, respectively. The best results reveal unconventional aircraft wing structures that can be manufactured using additive manufacturing. This research is expected to serve as a foundation for future research into multi-objective topology optimization of morphing wing structures based on the ground element framework.

Design of morphing wing with surface discontinuity

2018 ◽  
Vol 232 (14) ◽  
pp. 2638-2650 ◽  
Author(s):  
Andrzej Tarnowski ◽  
Tomasz Goetzendorf-Grabowski
Keyword(s):  
Shape Change ◽  
Aerodynamic Characteristics ◽  
Morphing Wing ◽  
Aircraft Wing ◽  
Current State ◽  
The Subject ◽  
Wing Structure ◽  
Surface Discontinuity ◽  
Wing Morphing ◽  
Optimal Adaptation

Aircraft wing morphing or radical shape change in flight has long been the subject of inquisitive research around the world. It happens because morphing ensures optimal adaptation to any flight conditions such as take-off, cruise, landing and other manoeuvres. The current state of material engineering is not yet in a position to provide adequate technologies to achieve such significant changes in the wing’s shape as morphing requires, though interesting progress can be observed. This article presents a new concept of the wing morphing, which potentially circumvents problems related to the elastic deformation of the wing structure. The first part of this article presents the principle of the operation and capabilities of the morphing wing, while the second part focuses on preparation for investigation of its numerical aerodynamic characteristics as groundwork to wind tunnel research.

scholarly journals Design and experimental structural analysis of a solar powered aircraft wing structure

2021 ◽  
Vol 1057 (1) ◽  
pp. 012027
Author(s):  
Govindu Sandhya ◽  
Vemireddy Sri Rishitha ◽  
S Sriram ◽  
VM Sreehari
Keyword(s):  
Structural Analysis ◽  
Aircraft Wing ◽  
Wing Structure ◽  
Solar Powered

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.

ARAMID ORGANOPLASTICS FOR INCREASING THE BIRD RESISTANCE OF ELEMENTS OF AIRCRAFT STRUCTURES

2021 ◽  
pp. 77-84
Author(s):  
A.Ch. Kan ◽  
◽  
G.F. Zhelezina ◽  
N.A. Solovieva ◽  
◽  
...  
Keyword(s):  
Carbon Fiber ◽  
Aircraft Wing ◽  
Aircraft Structures ◽  
Optimal Ratio ◽  
External Contour ◽  
Impact Tests ◽  
Protective Screen

The possibility of using protective screens made of aramid organoplastics to ensure the bird resistance of carbon fiber wing flaps is investigated. Aramid organoplastics were selected for the production of a protective screen, taking into account the main requirements for the materials of external contour of the aircraft wing. The result of impact tests simulating the collision of a bird with carbon fiber flaps that are not protected and protected by organoplastics are presented. The optimal ratio of aramid organoplastics as part of the protective screen for carbon fiber wing flaps is presented.

How flight feathers stick together to form a continuous morphing wing

Science ◽  
2020 ◽  
Vol 367 (6475) ◽  
pp. 293-297 ◽  
Author(s):  
Laura Y. Matloff ◽  
Eric Chang ◽  
Teresa J. Feo ◽  
Lindsie Jeffries ◽  
Amanda K. Stowers ◽  
...  
Keyword(s):  
Connective Tissue ◽  
Bird Species ◽  
Elastic Compliance ◽  
Morphing Wing ◽  
Morphing Aircraft ◽  
Morphing Wings ◽  
Aerial Robot

Variable feather overlap enables birds to morph their wings, unlike aircraft. They accomplish this feat by means of elastic compliance of connective tissue, which passively redistributes the overlapping flight feathers when the skeleton moves to morph the wing planform. Distinctive microstructures form “directional Velcro,” such that when adjacent feathers slide apart during extension, thousands of lobate cilia on the underlapping feathers lock probabilistically with hooked rami of overlapping feathers to prevent gaps. These structures unlock automatically during flexion. Using a feathered biohybrid aerial robot, we demonstrate how both passive mechanisms make morphing wings robust to turbulence. We found that the hooked microstructures fasten feathers across bird species except silent fliers, whose feathers also lack the associated Velcro-like noise. These findings could inspire innovative directional fasteners and morphing aircraft.

Pitching Dynamic Response of Variable Sweep Wing Aircraft

2012 ◽  
Vol 197 ◽  
pp. 159-163 ◽  
Author(s):  
Lai Bin Xu ◽  
Shu Xing Yang ◽  
Bo Mo
Keyword(s):  
Dynamic Response ◽  
Flight Control ◽  
Equations Of Motion ◽  
Center Of Gravity ◽  
Moment Of Inertia ◽  
Morphing Wing ◽  
Wing Morphing

The dynamic response of Variable Sweep Wing Aircraft (VSWA) with the wing sweeping is presented. The center of gravity (cg) of the aircraft, location of each wing partition , and moment of inertia alter significantly due to the wing morphing, resulting in considerably change of the dynamics of the aircraft. The extended equations of motion (EOMs) suitable for morphing wing aircraft are derived. Compared with the traditional EOMs, there are 4 additional forces and moments exhibiting in the extended EOMs due to the wing morphing. The results show that the additional forces and moments can affect the flight control considerably.

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