scholarly journals Finite element analysis for composite wing structure of the maritime surveillance unmanned aerial vehicle

2020 ◽  
Author(s):  
Fajar Ari Wandono ◽  
Mohammad Adhitya
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Unmanned Aerial Vehicle ◽  
Element Analysis ◽  
Maritime Surveillance ◽  
Aerial Vehicle ◽  
Wing Structure ◽  
Composite Wing

Structural Design and Finite Element Analysis of Unfolding Process for All Composite Folding Wing of UAV

2010 ◽  
Vol 163-167 ◽  
pp. 2328-2332 ◽  
Author(s):  
Peng Lv ◽  
Sheng Li Lv ◽  
Guang Jun Yang ◽  
Qing Na Zeng ◽  
Xiao Yan Tong
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Structural Design ◽  
Third Order ◽  
Element Analysis ◽  
Impact Action ◽  
Flutter Analysis ◽  
Folding Wing ◽  
Overall Performance ◽  
Composite Wing

This paper discusses the unfolding form of the folding wing and its application to special UAV. The main investigations involve aspects such as unfolding process of the special UAV’s folding wing, contour structure of the complete unfolding, the choice of composite materials for the folding wing and its overall performance parameters. Modeling and dynamics analysis are made for all-composite wing through finite element analysis and calculating software. The unfolding process is also simulated. The result shows that the wing’s first-order frequency is low, second-order frequency and third-order frequency are close at different sweep angles. The wings are apt to happen flutter coupling in flutter analysis. With the continued folding of the wing, the wing’s natural frequency decreases significantly at different orders. The conclusions can provide effective basis for the study of wing rotational rate, unfolding time and impact action.

scholarly journals Evaluation of Mechanical Strength Characteristics of Double Ducted Unmanned Amphibious Aerial Vehicle using Finite Element Analysis

2019 ◽  
Vol 4 (2) ◽  
pp. 420-431 ◽  
Author(s):  
Gokul Raj P. ◽  
Balasubramanian Esakki ◽  
Surendar Ganesan
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Land Surface ◽  
Water Surface ◽  
Structural Strength ◽  
Strength Characteristics ◽  
Element Analysis ◽  
Vehicle Structure ◽  
Payload Capacity ◽  
Aerial Vehicle

Unmanned Aerial Vehicles are extensively exploited for diverse applications importantly surveillance, defence and military, photography. Development of unmanned amphibious vehicle with integrating features of hovercraft principles and multirotor to navigate along and above the water surface, land surface and flying in the air is challenging demand. This article presents conceptual design of amphibious vehicle for the payload capacity of 7 kg with an endurance of 20 minutes and provision for mounting water sampler to collect water samples in remote water bodies. Structural strength characteristics of each part of the amphibious vehicle and integrity of same are analysed by Finite Element Analysis. FEA results indicated that the designed amphibious vehicle structure is well within the stress limit and minimal displacement is obtained. Based on structural analysis materials for various parts of the amphibious vehicle are determined and integrated structure is analysed.

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

Development of Sensor Integrated Composite Wing Structure

2010 ◽  
Vol 123-125 ◽  
pp. 903-906 ◽  
Author(s):  
Mi Jin Choi ◽  
Jin Seong Kim ◽  
Young Kyu Kim ◽  
Jong Hoon Kim ◽  
Ko Woon Choi ◽  
...  
Keyword(s):  
Health Monitoring ◽  
Failure Modes ◽  
Fatigue Tests ◽  
Optimal Number ◽  
Sensor System ◽  
Element Analysis ◽  
Vehicle Performance ◽  
Aerial Vehicle ◽  
Wing Structure ◽  
Composite Wing

Demands for improved aerial vehicle performance have led to the increasing use of composite materials. However, the mechanical behavior and failure modes of composites are not characterized as well as metals, and damages may be more difficult to detect. To overcome this, there is a demand to develop a structural health monitoring (SHM) system for composite aerial vehicles. This paper presents the development of sensor integrated composite wing structure, which is an essential part of SHM system. The composite wing structure was manufactured using an autoclave process, and Fiber Bragg Grating (FBG) optical sensor and piezoelectric (PZT) sensor were installed. The optimal number and location of each sensor system are determined based on the experimental results and Finite Element Analysis (FEA). Installation procedures for FBG and PZT sensor system are developed and validated using tension-tension fatigue tests over 106 cycles.

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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