Digitally Adjustable Tooling Technology for Manufacturing of Aircraft Panels

2010 ◽  
Author(s):  
Liu Chunguo ◽  
Li Mingzhe ◽  
Cai Zhongyi ◽  
Yan Aimin ◽  
Su Shizhong
Keyword(s):  
Tooling Technology ◽  
Aircraft Panels

Increased Productivity in Hot Aluminum Extrusion by Using Extrusion Dies with Inner Cooling Channels Manufactured by Rapid Tooling

2014 ◽  
Vol 611-612 ◽  
pp. 981-988 ◽  
Author(s):  
Ramona Hölker ◽  
Matthias Haase ◽  
Nooman Ben Khalifa ◽  
A. Erman Tekkaya
Keyword(s):  
Surface Defects ◽  
Experimental Investigations ◽  
Extrusion Force ◽  
Aluminum Extrusion ◽  
Thermally Induced ◽  
Manufacturing Method ◽  
Cooling Channels ◽  
Extrusion Dies ◽  
Exit Temperature ◽  
Tooling Technology

The influence of local inner die cooling on the heat balance in hot aluminum extrusion was investigated. For the manufacturing of the die with cooling channels close to the forming zone, the layer-laminated manufacturing method was applied. The new tooling technology was applied in order to decrease the profiles exit temperature and to avoid thermally induced surface defects with the aim to raise the productivity in hot aluminum extrusion processes. Numerical and experimental investigations revealed that, while maintaining the exit temperature of the extrudate, a distinct increase of the production speed up to 300% can be realized, while the extrusion force increases only slightly. An effect on the profiles microstructure was also detected. By applying die cooling, grain coarsening can be significantly limited or even be avoided.

Use of Computational Intelligence for Corrosion Damage Assessment of Aging Aircraft Panels

2001 ◽  
Author(s):  
M. J. Palakal ◽  
J. Huang ◽  
R. M. Pidaparti ◽  
D. T. Peeler ◽  
S. Rebbapragada
Keyword(s):  
Air Force ◽  
Computational Intelligence ◽  
Multivariate Data Analysis ◽  
Damage Assessment ◽  
Corrosion Damage ◽  
Nondestructive Inspection ◽  
Material Loss ◽  
Aging Aircraft ◽  
Extent Of Damage ◽  
Aircraft Panels

Abstract This paper describes computational methods that have been developed to automatically detect and quantify corrosion on images of aircraft panels obtained using nondestructive inspection (NDI) techniques. Images obtained from NDI techniques are not directly suitable for corrosion analysis. We propose a multi-resolution wavelet analysis to segment the NDI images to isolate the corroded regions from the undamaged regions. Wavelet coefficients were extracted from each segment and subjected to a multivariate data analysis to obtain the most relevant features. These features are then used to identify the corroded region on the images and also to estimate the extent of damage, in terms of material loss, using backpropagation neural networks. Experiments were conducted to test the developed modules on images obtained from the Air Force Research Lab in Dayton, Ohio. The results obtained prove the feasibility and robustness of our approach in detecting the damaged regions and for estimating the material loss due to corrosion.

Tooling Technology

2021 ◽  
pp. 177-202
Author(s):  
Hauke Lengsfeld ◽  
Hilmar Apmann
Keyword(s):  
Tooling Technology

Mathematical Modeling and Fuzzy Analysis of Hot Runner in Comparison to Cold Runner in Injection Moulding

2019 ◽  
Vol 18 (04) ◽  
pp. 657-676
Author(s):  
Sandeep Mathur ◽  
Ravinder Kumar ◽  
Vipul Mathur
Keyword(s):  
Mass Production ◽  
Weight Ratio ◽  
Production Environment ◽  
Slight Improvement ◽  
Decision Making Problem ◽  
Cycle Time Reduction ◽  
Index Value ◽  
Tooling Technology ◽  
Material Utilization ◽  
Insight Into

In a mass production environment of supply chains where volume of production runs into millions of parts per month where even the slight improvement in the manufacturing process through cycle time reduction or better material utilization has the potential to produce huge savings and productivity to match customer tact time, the paper serves a useful insight into appropriate tooling technology for moulding processes. Though there have been several studies on hot runner technology in injection molding processes vis a vis conventional cold runner technology, ultimate manufacturer still has to conduct trials and calculate ROIs, initial investment, quality and maintainability aspect to conclude if the manufacturer can go for hot runner or not. The paper lends a scientific expression to this decision making problem and offers a mathematical model with variables like Gross weight to Net Weight ratio, machine tonnage, volume involved. The user only has to put in the values to get an index value with a threshold number to decide if hot runner is viable for the component in hand or not.

scholarly journals Assembly Variation Analysis of Aircraft Panels under Part-to-part Locating Scheme

2019 ◽  
Vol 2019 ◽  
pp. 1-15 ◽  
Author(s):  
Xia Liu ◽  
Luling An ◽  
Zhiguo Wang ◽  
Changbai Tan ◽  
Xiaoping Wang ◽  
...  
Keyword(s):  
Elastic Deformation ◽  
Assembly Process ◽  
Variation Analysis ◽  
Kinematic Theory ◽  
Statistical Variation ◽  
Variation Propagation ◽  
Fixed Part ◽  
Compliant Parts ◽  
Aircraft Panels

A typical aircraft panel is the assembly consisting of a multitude of thin and lightweight compliant parts. In panel assembly process, part-to-part locating scheme has been widely adopted in order to reduce fixtures. By this locating scheme, a part is located onto the pre-fixed part/subassembly by determinant assembly (DA) holes, and temporary fasteners (e.g., spring pin) are used for joining these DA hole-hole pairs. The temporary fasteners can fasten DA hole-hole pairs in the axial and radial directions of DA holes. The fastening in the radial directions is realized by the expansion of temporary fasteners. Although the usage of temporary fasteners helps reduce the positional differences between hole-hole pairs, their clamping forces thereby may lead to elastic deformation of compliant parts/subassemblies. Limited research has been conducted on such elastic deformation produced by temporary fastener and its influence on assembly dimensional quality. This paper proposes a novel rigid-compliant variation analysis method for aircraft panel assembly, incorporating the deformation in part-to-part locating process. Based on the kinematic theory and linear elasticity deformation assumption, the variation propagation through the locating process, as well as the entire assembly process of an aircraft panel, is formulated. Then, the statistical variation analysis is performed with Monte Carlo (MC) simulation. Finally, the proposed method is validated by a case study. The result shows the deformation in the part-to-part locating process significantly impacts the assembly variations, and our method can provide a more accurate and reliable prediction.

scholarly journals Non-Destructive Inspection of Impact Damage in Composite Aircraft Panels by Ultrasonic Guided Waves and Statistical Processing

Materials ◽  
2017 ◽  
Vol 10 (6) ◽  
pp. 616 ◽  
Author(s):  
Margherita Capriotti ◽  
Hyungsuk E. Kim ◽  
Francesco Lanza di Scalea ◽  
Hyonny Kim
Keyword(s):  
Guided Waves ◽  
Impact Damage ◽  
Statistical Processing ◽  
Ultrasonic Guided Waves ◽  
Non Destructive ◽  
Aircraft Panels
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