Module discretization and consolidation of a modular morphing wing

2015 ◽  
Vol 61 (2) ◽  
pp. 36-50
Author(s):  
Ryan Perera ◽  
Prakash Paudel ◽  
John Kamel ◽  
Fengfeng Xi ◽  
Paul Walsh
Keyword(s):  
Morphing Wing

Withdrawal: A Study on the Aerodynamic Performance of a Morphing Wing during Pitching Motion

2020 ◽  
Author(s):  
Manoj Prabakar Sargunaraj ◽  
Dibya Raj R. Adhikari ◽  
Carlos E. Soto ◽  
Samik Bhattacharya
Keyword(s):  
Aerodynamic Performance ◽  
Morphing Wing ◽  
Pitching Motion

scholarly journals Sensing, Actuation, and Control of the SmartX Prototype Morphing Wing in the Wind Tunnel

Actuators ◽  
2021 ◽  
Vol 10 (6) ◽  
pp. 107
Author(s):  
Nakash Nazeer ◽  
Xuerui Wang ◽  
Roger M. Groves
Keyword(s):  
Wind Tunnel ◽  
Optical Fibers ◽  
Fiber Optic ◽  
Experimental Testing ◽  
Single Mode ◽  
Fiber Optic Sensor ◽  
Sensor Data ◽  
Random Errors ◽  
Morphing Wing ◽  
Actuator Dynamics

This paper presents a study on trailing edge deflection estimation for the SmartX camber morphing wing demonstrator. This demonstrator integrates the technologies of smart sensing, smart actuation and smart controls using a six module distributed morphing concept. The morphing sequence is brought about by two actuators present at both ends of each of the morphing modules. The deflection estimation is carried out by interrogating optical fibers that are bonded on to the wing’s inner surface. A novel application is demonstrated using this method that utilizes the least amount of sensors for load monitoring purposes. The fiber optic sensor data is used to measure the deflections of the modules in the wind tunnel using a multi-modal fiber optic sensing approach and is compared to the deflections estimated by the actuators. Each module is probed by single-mode optical fibers that contain just four grating sensors and consider both bending and torsional deformations. The fiber optic method in this work combines the principles of hybrid interferometry and FBG spectral sensing. The analysis involves an initial calibration procedure outside the wind tunnel followed by experimental testing in the wind tunnel. This method is shown to experimentally achieve an accuracy of 2.8 mm deflection with an error of 9%. The error sources, including actuator dynamics, random errors, and nonlinear mechanical backlash, are identified and discussed.

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 Digital Morphing Wing: Active Wing Shaping Concept Using Composite Lattice-Based Cellular Structures

Soft Robotics ◽  
2017 ◽  
Vol 4 (1) ◽  
pp. 33-48 ◽  
Author(s):  
Benjamin Jenett ◽  
Sam Calisch ◽  
Daniel Cellucci ◽  
Nick Cramer ◽  
Neil Gershenfeld ◽  
...  
Keyword(s):  
Cellular Structures ◽  
Morphing Wing ◽  
Composite Lattice

Mapping and selection of profiles for morphing wing of a flapping foil

2021 ◽  
Vol 43 (2) ◽  
Author(s):  
Guilherme Amaral do Prado Campos ◽  
Luciano Santos Constantin Raptopoulos ◽  
Max Suell Dutra
Keyword(s):  
Morphing Wing ◽  
Flapping Foil ◽  
Selection Of

Flight State Monitoring of a Morphing Wing using Multimodal Distributed Sensors-informed Prediction Models

2022 ◽  
Author(s):  
Tanay Topac ◽  
Sung Yeon Sara Ha ◽  
Xiyuan Chen ◽  
Lawren L. Gamble ◽  
Daniel J. Inman ◽  
...  
Keyword(s):  
Prediction Models ◽  
Morphing Wing ◽  
State Monitoring ◽  
Distributed Sensors

Impact of N-Shaped Wing Morphing on Solar-Powered Aircraft

2020 ◽  
pp. 1-12
Author(s):  
Mostafa E. El-Salamony ◽  
Mohamed A. Aziz
Keyword(s):  
Solar Energy ◽  
Lift Coefficient ◽  
Morphing Wing ◽  
Aerial Vehicles ◽  
Aircraft Performance ◽  
Aerial Vehicle ◽  
Solar Powered ◽  
Two Parameters ◽  
Wing Morphing ◽  
The Impact

Generally, unmanned aerial vehicles and micro aerial vehicles depend on batteries or conventional fuel as a source of energy. These sources of energy have limited flight time, relatively high cost, and also a certain level of pollutants. Solar energy applied to aerial vehicles is an excellent alternative way to overcome other sources of energy’s disadvantage. This study aimed to design a solar-powered aerial vehicle to achieve continuous flight on Earth. The efficiency of the solar system is related to the absorbed sun rays. The concept of an anti-symmetric N-shaped morphing wing is a good idea to increase the collected solar energy during the daily sun path. But this comes with the penalty of side forces and moments due to the anti-symmetry of the wing. This paper introduces a study for two parameters that strongly affect the aerodynamics of the N-shaped morphing wing; the dihedral part angle and the dihedral part length. The impact of the dihedral angle decreases the lift coefficient and increases the drag coefficient. The impact of the morphing wing on the aircraft performance is also considered.

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