scholarly journals STRUCTURE ANALYSIS AND MANUFACTURING OF WINGS TRAINER-5774

Vortex ◽  
2021 ◽  
Vol 1 (2) ◽  
pp. 107
Author(s):  
Suciari Dewi Triani ◽  
Moh Ardi Cahyono ◽  
Lazuardy Rahendra Pinandhita
Keyword(s):  
Remote Control ◽  
Structure Analysis ◽  
Structural Design ◽  
Manufacturing Process ◽  
Aircraft Wing ◽  
Margin Of Safety ◽  
Wing Structure ◽  
Aircraft Loads

Unmanned Aerial Vechicle (UAV) is one of the types an aircraft. Trainer is part of an airplane where the aircraft is controlled by a remote control for its flight. One of the things that must be considred in design an airplane is strength and and resistance of the wing structure in accepting distributed aircraft loads. In addition to the structural design and load, the material to be used can have an effect. The process is starting from modification of the aircraft wing using CATIA V5R20 which is then carried out analysis of the wing structure by being given the aircraft load using ANSYS 19. The largest structural value is in the Joiner section of 7,967 with manuvering load and smallest value is 0,026 on the Spar section. Margin of safety smallest value in the spar when its manuver. After analysis it is continued with the manufacturing process according to the design that has been made.

scholarly journals New biomimetic approach to the aircraft wing structural design based on aeroelastic analysis

2017 ◽  
Vol 65 (5) ◽  
pp. 741-750
Author(s):  
D. Gawel ◽  
M. Nowak ◽  
H. Hausa ◽  
R. Roszak
Keyword(s):  
Structural Design ◽  
Interaction Analysis ◽  
Load Case ◽  
Aircraft Wing ◽  
And Topology ◽  
Aeroelastic Analysis ◽  
Biomimetic Approach ◽  
Wing Structure ◽  
Multiple Load Case ◽  
Multiple Load

Abstract This paper presents a new biomimetic approach to the structural design. For the purpose of aircraft wing design the numerical environment combining simultaneous structural size, shape, and topology optimization based on aeroelastic analysis was developed. For the design of aircraft elements the optimization process must be treated as a multi-load case task, because during the fluid structure interaction analysis each step represents a different structural load case. Also, considering different angles of attack, during the CFD computation each result is considered. The method-specific features (such as domain independence, functional configurations during the process of optimization, and multiple load case solution implemented in the optimization scenario) enable the optimal structural form. To illustrate the algorithm functionality, the problem of determining the optimal internal wing structure was presented. The optimal internal wing structure resulting from aeroelastic computation with different angles of attack has been presented.

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

Joint fixity effect on structural design of a box wing aircraft

2012 ◽  
Vol 116 (1178) ◽  
pp. 363-372
Author(s):  
P. O. Jemitola ◽  
J. Fielding ◽  
P. Stocking
Keyword(s):  
Finite Element ◽  
Structural Design ◽  
Vortex Lattice ◽  
Computational Study ◽  
Requirements Analysis ◽  
Stress Distributions ◽  
Box Models ◽  
Wing Structure

Abstract A computational study was performed to compare the stress distributions in finite element torsion box models of a box wing structure that result from employing four different wing/end fin joint fixities. All considered wings were trimmed in pitch. The joint fixities refer to the type of attachment that connects the tip of the fore and aft wings to the end fin. Using loads from a vortex lattice tool, the analysis determined the best wing-joint fixity of a statically loaded idealised box wing configuration by comparing the stress distributions resulting from the different wing joints in addition to other essential aerodynamic requirements. Analysis of the wing joint fixity indicates that the rigid joint is the most suitable.

A Discussion about Finite Element Analysis of Aircraft Wing Structure

2012 ◽  
Vol 532-533 ◽  
pp. 427-430
Author(s):  
Wei Tao Zhao ◽  
Tian Jun Yu ◽  
Yi Yang
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Aircraft Design ◽  
Element Model ◽  
Aircraft Wing ◽  
Element Analysis ◽  
Actual Structure ◽  
Shear Plate ◽  
Wing Structure ◽  
Lifting Surfaces

One of the most significant components of aircraft design is the wing, the wings are the main lifting surfaces that support the airplane in flight. The structures of wings must have enough strength and rigidity to ensure the safe of the aircraft. Usually, the displacements of the structures are calculated by using finite element method. But it is very difficult to select a reasonable finite element model to approximate the actual structure. In this study, two models are adopted to calculate the displacements of the wing structure. The first is a model of rod and shear plate, the second is a model of beam and shell. The disadvantages and advantages of two models are discussed. As seen from the comparison with the test date, two models proposed are both feasible to analyze the wing structure.

Structure Analysis of Electron Gun Deflection Coil Based on ProE and ANSYS

2011 ◽  
Vol 201-203 ◽  
pp. 1352-1355
Author(s):  
Hai Lang Liu ◽  
Rui Bin Zhang ◽  
Yi Ping Huang
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Structure Analysis ◽  
Structural Design ◽  
Electron Gun ◽  
Structure Modeling ◽  
Element Analysis ◽  
The Finite Element Analysis ◽  
Coil Size

Through the example of the electron gun deflection coil, this paper implements the structure modeling with ProE and makes the finite element analysis with ANSYS .The structure analysis is performed by the combination of the advantages of two softwares. The reasonableness of the design is verified. This method helps to optimize the structural design of the coil. The production of precision of the coil was improved, and coil size can effectively control and reduce material waste.

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