Structural Analysis and Testing of an Ultralight Unmanned-Aerial-Vehicle Carbon-Composite Wing

2009 ◽  
Vol 46 (3) ◽  
pp. 814-820 ◽  
Author(s):  
R. Warsi Sullivan ◽  
Y. Hwang ◽  
M. Rais-Rohani ◽  
T. Lacy
Keyword(s):  
Structural Analysis ◽  
Unmanned Aerial Vehicle ◽  
Carbon Composite ◽  
Aerial Vehicle ◽  
Composite Wing

scholarly journals Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle

2019 ◽  
Vol 8 (5) ◽  
pp. 4374-4386
Author(s):  
Ernnie Illyani Basri ◽  
Faizal Mustapha ◽  
Mohamed Thariq Hameed Sultan ◽  
Adi Azriff Basri ◽  
Mohd Firdaus Abas ◽  
...  
Keyword(s):  
Finite Element ◽  
Conceptual Design ◽  
Unmanned Aerial Vehicle ◽  
Leading Edge ◽  
Simulation Validation ◽  
Aerial Vehicle ◽  
Composite Wing

Fiber Bragg Grating Strains to Obtain Structural Response of a Carbon Composite Wing

2013 ◽  
Author(s):  
Matthew J. Nicolas ◽  
Rani W. Sullivan ◽  
W. Lance Richards
Keyword(s):  
Fiber Bragg Grating ◽  
Large Scale ◽  
Structural Response ◽  
Carbon Composite ◽  
Wing Shape ◽  
Strain Sensors ◽  
Bragg Grating ◽  
Out Of Plane ◽  
Aerial Vehicle ◽  
Composite Wing

The objective of this study was to determine the deflected wing shape and the out-of-plane loads of a large-scale carbon-composite wing of an ultralight aerial vehicle using Fiber Bragg Grating (FBG) technology. The composite wing, subjected to concentrated and distributed loads, was instrumented with an optical fiber on its top and bottom surfaces positioned over the main spar, resulting in approximately 780 strain sensors bonded to the wings. The in-plane strains from the FBG sensors were used to obtain the out-of-plane loads as well as the wing shape at various load levels using NASA-developed real-time load and displacement algorithms. The calculated out-of-plane displacements and loads were generally within 4% of the measured data.

scholarly journals Analysis by UAV Digital Photogrammetry of Folds and Related Fractures in the Monte Antola Flysch Formation (Ponte Organasco, Italy)

Geosciences ◽  
2018 ◽  
Vol 8 (8) ◽  
pp. 299 ◽  
Author(s):  
Niccolò Menegoni ◽  
Claudia Meisina ◽  
Cesare Perotti ◽  
Matteo Crozi
Keyword(s):  
Structural Analysis ◽  
Unmanned Aerial Vehicle ◽  
Northern Apennines ◽  
Digital Photogrammetry ◽  
Rock Outcrops ◽  
Deformation Structures ◽  
Structural Measures ◽  
Aerial Vehicle ◽  
Points Of View ◽  
Digital Outcrop

The deformation structures (folds and fractures) affecting Monte Antola flysch formation in the area of Ponte Organasco (Northern Apennines-Italy) were analyzed by Unmanned Aerial Vehicle Digital Photogrammetry (UAVDP). This technique allowed the realization of Digital Outcrop Models (DOMs) interpreted in a stereoscopic environment by collecting a large number of digital structural measures (strata, fractures and successively fold axes and axial planes). In particular, by UAVDP was possible to analyze the relationships between folds and fractures all along the study structures. The structural analysis revealed the presence of a series of NE-vergent folds characterized by a typical Apenninic trend and affected by four main sets of fractures. Fractures are always sub-orthogonal to the bedding, maintains constant angular relationships with the bedding and seems linked to the folding deformation. The study shows that the UAVDP technique can overcome the main limitations of field structural analysis such as the scarce presence and the inaccessibility (total or partial) of rock outcrops and allows for acquiring images of rock outcrops at a detailed scale from user-inaccessible positions and different points of view and analyze inaccessible parts of outcrops.

scholarly journals Structural Optimization of Frame of the Multi-Rotor Unmanned Aerial Vehicle through Computational Structural Analysis

2021 ◽  
Vol 1849 (1) ◽  
pp. 012004
Author(s):  
V Aswin Kumar ◽  
M Sivaguru ◽  
B Rohini Janaki ◽  
K S Sumanth Eswar ◽  
P Kiran ◽  
...  
Keyword(s):  
Structural Analysis ◽  
Structural Optimization ◽  
Unmanned Aerial Vehicle ◽  
Aerial Vehicle

scholarly journals Parametric Optimization of Load Bearing Elements for Composite Wing of an Unmanned Aerial Vehicle

2021 ◽  
Vol 346 ◽  
pp. 03093
Author(s):  
Naing Lin Aung ◽  
Oleg Tatarnikov ◽  
Phyo Wai Aung
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Safety Factor ◽  
Structural Elements ◽  
Ansys Software ◽  
Load Bearing ◽  
Aerial Vehicle ◽  
Wing Structure ◽  
Wing Skin ◽  
Composite Wing ◽  
The Ideal

This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pareto set method of the “ideal center” basing on four criteria: minimum mass, deflection, normal stress, and maximum safety factor of the wing. Verification calculations were carried out to determine the safety factor of the load-bearing wing structure using a geometrically nonlinear model in FEMAP software.

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