Shape prediction of a composite wing panel under the action of an SMA wire and an MFC bimorph

2019 ◽  
Author(s):  
Aghna Mukherjee ◽  
Shaikh Faruque Ali ◽  
Arockiarajan Arunachalakasi
Keyword(s):  
Shape Prediction ◽  
Wing Panel ◽  
Composite Wing

Weight optimization of a composite wing-panel with flutter stability constraints by ply-drop

2020 ◽  
Vol 62 (4) ◽  
pp. 2181-2195
Author(s):  
Sachin Shrivastava ◽  
Hitesh Tilala ◽  
P. M. Mohite ◽  
M. D. Limaye
Keyword(s):  
Weight Optimization ◽  
Wing Panel ◽  
Composite Wing

Impact Damage Detection in a Stiffened Composite Wing Panel Using Digital Shearography and Thermosonics

2011 ◽  
Vol 471-472 ◽  
pp. 904-909 ◽  
Author(s):  
Giovanni De Angelis ◽  
Michele Meo ◽  
D.P. Almond ◽  
S.G. Pickering ◽  
U. Polimeno
Keyword(s):  
Infrared Imaging ◽  
Impact Damage ◽  
Flaw Detection ◽  
Low Velocity ◽  
Number Of Factors ◽  
Resonance Frequencies ◽  
Operations And Maintenance ◽  
Optimization Methodology ◽  
Wing Panel ◽  
Composite Wing

There has been a growing interest in the use of composites especially in structural application ranging from aerospace to automotive and marine sectors. However, their performances under impact loading represent one of the major concerns as impacts may occur during manufacture, normal operations and maintenance. This paper presents two novel NDT techniques, thermosonics and digital shearography (DISH) to detect and assess barely visible impact damage (BVID) produced on a stiffened composite wing panel by unknown low energy impacts. Thermosonics is based on synchronized infrared imaging and ultrasonic excitation. Despite the apparent simplicity of the experimental setup, thermosonics involves a number of factors, e.g. acoustic horn location, horn crack proximity, horn-sample coupling etc., that significantly tend to influence both the degree and the period of the excitation. Then, a numerical-experimental procedure for the assessment of the size and depth of delamination by digital shearography (DISH) is proposed. The flaw detection capabilities of DISH have been evaluated by measuring the dynamic response of the delaminated area to applied stresses. The shearographic methodology is based on the recognition of the (0 1) resonance mode per defect. A simplified model of thin circular plate, idealized above each impacted area, is used to calculate the natural frequency of vibrating delamination. The numerical difference between experimental resonance frequencies and those computationally obtained is minimized using an unconstrained optimization algorithm in order to calculate the delamination depth. The results showed that thermosonics is a quick and effective method to detect and localize BVID damage while the combined shearography and optimization methodology was able to size and localize delamination due to low velocity impacts.

Out-of-autoclave Process and Automation: A Successful Path to Highly Integrated and Cost Efficient Composite Wing Moveables

2019 ◽  
Author(s):  
Thibault de Lumley ◽  
François Mathieu ◽  
Didier Cornet ◽  
Dimitri Gueuning ◽  
Nicolas Van Hille
Keyword(s):  
Autoclave Process ◽  
Cost Efficient ◽  
Out Of Autoclave ◽  
Composite Wing

DESIGN AND MANUFACTURING PROCESS OF A UAV COMPOSITE WING SPAR

2018 ◽  
Author(s):  
Pablo M. N. Araujo ◽  
Thiago R. Costa ◽  
Eduardo C. Silva
Keyword(s):  
Manufacturing Process ◽  
Design And Manufacturing ◽  
Wing Spar ◽  
Composite Wing

scholarly journals Shape Prediction of Large Deployable Antenna Structure on Orbit

2012 ◽  
Vol 10 (ists28) ◽  
pp. Pc_35-Pc_40 ◽  
Author(s):  
Kosei ISHIMURA ◽  
Tsuneo KII ◽  
Keiji KOMATSU ◽  
Ken GOTO ◽  
Ken HIGUCHI ◽  
...  
Keyword(s):  
Antenna Structure ◽  
Shape Prediction

Research on trajectory planning of non-developable surface for automated tape placement processing of composite

2017 ◽  
Vol 24 (6) ◽  
pp. 929-936
Author(s):  
Lin Liu ◽  
Jun Xiao ◽  
Yong Li
Keyword(s):  
Trajectory Planning ◽  
Local Stress ◽  
Developable Surface ◽  
Software Environment ◽  
Quantitative Characterization ◽  
Large Size ◽  
Variable Step ◽  
The Cost ◽  
Wing Panel

AbstractTape placement manufacturing process, as one of the automated forming technologies for composite material, not only substantially improves the productivity of composite component and reduces the cost of production significantly but also raises the reliability and stability of composite structure. Automated tape placement technology is mainly applied for manufacturing the fuselage and wing panel of airplane characterized by small curvature and large size. For these kinds of structural components with a non-developable surface, trajectory planning by “natural path” method could reduce the internal stress and improve the quality of composite products to a certain extent but not be optimized by quantitative characterization. On the basis of preliminary work, the theoretical model of “unnatural degree” (UD) is introduced in the first step, which could characterize the tensile and shear strain of the laying tape quantitatively. Secondly, by adjusting the iterative step and laying direction to diminish the UD, local stress could be softened in order to optimize the laying track. Ultimately, the simulation model of the non-developable surface is established under the Matlab software environment, and the “variable step-angle” algorithm is adopted to verify the adjustment effect of the tape-laying track.

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