scholarly journals Adhesive bonding in composite structures for aerospace applications

2006 ◽  
Author(s):  
Bhushan Kumar Shashi
Keyword(s):  
Composite Structures ◽  
Adhesive Bonding ◽  
Aerospace Applications

scholarly journals Defects and uncertainties of adhesively bonded composite joints

2021 ◽  
Vol 3 (9) ◽  
Author(s):  
Sadik Omairey ◽  
Nithin Jayasree ◽  
Mihalis Kazilas
Keyword(s):  
Composite Materials ◽  
Composite Structures ◽  
Production Efficiency ◽  
Adhesive Bonding ◽  
Detection Methods ◽  
Bonded Joints ◽  
Adhesively Bonded ◽  
Adhesively Bonded Joints ◽  
Wide Range ◽  
Bonded Composite

AbstractThe increasing use of fibre reinforced polymer composite materials in a wide range of applications increases the use of similar and dissimilar joints. Traditional joining methods such as welding, mechanical fastening and riveting are challenging in composites due to their material properties, heterogeneous nature, and layup configuration. Adhesive bonding allows flexibility in materials selection and offers improved production efficiency from product design and manufacture to final assembly, enabling cost reduction. However, the performance of adhesively bonded composite structures cannot be fully verified by inspection and testing due to the unforeseen nature of defects and manufacturing uncertainties presented in this joining method. These uncertainties can manifest as kissing bonds, porosity and voids in the adhesive. As a result, the use of adhesively bonded joints is often constrained by conservative certification requirements, limiting the potential of composite materials in weight reduction, cost-saving, and performance. There is a need to identify these uncertainties and understand their effect when designing these adhesively bonded joints. This article aims to report and categorise these uncertainties, offering the reader a reliable and inclusive source to conduct further research, such as the development of probabilistic reliability-based design optimisation, sensitivity analysis, defect detection methods and process development.

Durability of nano-reinforced polyimide adhesive bonding of titanium nitride deposited aluminium for aerospace applications

2019 ◽  
Vol 6 (9) ◽  
pp. 0965c7 ◽  
Author(s):  
Kavi Kerusiha ◽  
Swathi ◽  
K Thayalan ◽  
Sabbir Ahmed ◽  
Mohan Kumar Pitchan ◽  
...  
Keyword(s):  
Titanium Nitride ◽  
Adhesive Bonding ◽  
Aerospace Applications

Challenges and Opportunities in Multifunctional Nanocomposite Structures for Aerospace Applications

MRS Bulletin ◽  
2007 ◽  
Vol 32 (4) ◽  
pp. 328-334 ◽  
Author(s):  
Jeff Baur ◽  
Edward Silverman
Keyword(s):  
Composite Structures ◽  
Reinforced Composites ◽  
Aerospace Applications ◽  
Structural Applications ◽  
Challenges And Opportunities ◽  
The Status ◽  
Hierarchical Composites ◽  
Easy Integration ◽  
Nanocomposite Structures ◽  
Made In

AbstractOne important application of nanocomposites is their use in engineered structural composites. Among the wide variety of structural applications, fiber-reinforced composites for aerospace structures have some of the most demanding physical, chemical, electrical, thermal, and mechanical property requirements. Nanocomposites offer tremendous po tential to improve the properties of advanced engineered composites with modest additional weight and easy integration into current proc essing schemes. Sig nificant progress has been made in fulfilling this vision. In particular, nanocomposites have been applied at numerous locations within hierarchical composites to improve specific properties and optimize the multifunctional properties of the overall structure. Within this ar ticle, we review the status of nanocomposite incorporation into aerospace composite structures and the need for continued development.

Distributed Strain Monitoring for Damage Evolution in CFRP Bolted Structures with Embedded Optical Fibers

2013 ◽  
Vol 558 ◽  
pp. 252-259 ◽  
Author(s):  
Nobuo Takeda ◽  
Shu Minakuchi ◽  
Takeyuki Nadabe
Keyword(s):  
Optical Fibers ◽  
Composite Structures ◽  
Large Scale ◽  
Permanent Deformation ◽  
Bolted Joints ◽  
Element Analysis ◽  
Internal Damage ◽  
Aerospace Applications ◽  
Strain Change ◽  
Distributed Strain

The authors proposed fiber-optic-based damage monitoring of carbon fiber reinforced plastic (CFRP) bolted joints. Optical fibers were embedded along bolt holes and strain change along the optical fiber induced by internal damage was measured by a Brillouin Optical Correlation Domain Analysis (BOCDA), which is a high spatial resolution distributed strain sensing system. This study began by investigating damage modes of CFRP bolted joints after bearing failure. Effective embedding positions of optical fibers were then proposed and their feasibility was evaluated by finite element analysis simulating the damage propagation in the bolted joint and consequent strain change. Finally, verification tests were conducted using specimens with embedded optical fibers at various positions. It was clearly shown that damage could be detected using residual strain due to fiber-microbuckling (kinking) damage or permanent deformation of neighboring plies. Furthermore, damage size and direction could be estimated from the change in the strain distribution. The system developed is quite useful for a first inspection of large-scale composite structures in aerospace applications.

Structural Design of Hybrid Processing Unit Chassis for Airborne Electronic Systems

2018 ◽  
Author(s):  
Daniele Santoro ◽  
Umberto Lecci ◽  
Fabrizio Quadrini ◽  
Loredana Santo
Keyword(s):  
Composite Structures ◽  
Load Condition ◽  
Element Model ◽  
Numerical Approach ◽  
Processing Unit ◽  
Harmonic Load ◽  
Nominal Data ◽  
Aerospace Applications ◽  
Load Factors ◽  
Definition Of

Defence&Aerospace applications greatly benefit from the weight reduction of their payloads. On one hand, a reduced weight leads to lower fuel consumption and thus a greater flight range. On the other, higher load factors reduce the overall flight envelope. In the case of mast mounted naval or terrestrial units (e.g shelters), mass budgets are strongly limit. The need of producing very light structures leads to the use of composite materials but drawbacks arise from the definition of a robust design methodology. The present work aims at defying an integrated experimental-numerical approach to design complex composite structures. The unit chassis of a hybrid processing unit for airborne application is taken as case study. Material properties are extracted from laboratory tests and integrated with nominal data. A finite element model is calibrated and used to predict the behavior of a chassis wall under harmonic load condition.

Enhancement of Surface Integrity of Titanium Alloy With Copper by Means of Laser Metal Deposition Process

2020 ◽  
pp. 245-270
Author(s):  
Mutiu F. Erinosho ◽  
Esther T. Akinlabi ◽  
Sisa Pityana
Keyword(s):  
Titanium Alloy ◽  
Surface Integrity ◽  
Adhesive Bonding ◽  
Sea Water ◽  
Laser System ◽  
Research Work ◽  
Deposition Process ◽  
Metal Deposition ◽  
Laser Metal Deposition ◽  
Aerospace Applications

The laser metal deposition process possesses the combination of metallic powder and laser beam respectively. However, these combinations create an adhesive bonding that permanently solidifies the laser-enhanced-deposited powders. Titanium alloys (Ti6Al4V) Grade 5 have been regarded as the most used alloys for the aerospace applications, due to their lightweight properties and marine application due to their excellent corrosion resistance. The improvements in the surface integrity of the alloy have been achieved successively with the addition of Cu through the use of Ytterbium laser system powered at maximum of 2000 Watts. The motivation for this research work can be attributed to the dilapidation of the surface of titanium alloy, when exposed to marine or sea water for a longer period of time. This chapter provides the surface modification of titanium alloy with the addition of percentage range of Cu within its lattices; and the results obtained from the characterizations conducted on the laser deposited Ti6Al4V/Cu alloys have been improved.

Characteristics of In-Plane Waves in Composite Plates

2019 ◽  
Vol 24 (3) ◽  
pp. 458-466
Author(s):  
K. Renji ◽  
S. Josephine Kelvina Florence ◽  
Sameer Deshpande
Keyword(s):  
Composite Structures ◽  
Plane Waves ◽  
Phase Speed ◽  
Composite Plates ◽  
Laminated Plates ◽  
Composite Panel ◽  
Plane Shear ◽  
Aerospace Applications ◽  
Bending Waves ◽  
Isotropic Plates

The high frequency dynamic excitations generate both in-plane as well as bending waves in structures. In aerospace applications, many of these structures are made of composite materials. There are two types of in-plane motions, longitudinal and in-plane shear. Although these motions are uncoupled in isotropic materials, composite structures show coupled behaviour. The works reported on in-plane waves in composite structures assume that two in-plane motions are uncoupled as in isotropic plates. In this work, characteristics of the in-plane waves in composite laminated plates are investigated. Expressions for wavenumber, phase speed and group speed are derived. It is seen that in composite plates the two in-plane waves are coupled in longitudinal and shear propagations and are non-dispersive. The phase speeds of in-plane waves in composite plates can be much different from those determined using the expressions for isotropic plates where the waves are uncoupled. To validate the expressions derived the phase speeds of in-plane waves in a typical composite panel are determined experimentally. It is seen that the experimentally obtained phase speeds match well with the theoretical results.

scholarly journals Isogeometric analysis for simulation of progressive damage in composite laminates

2018 ◽  
Vol 52 (25) ◽  
pp. 3471-3489 ◽  
Author(s):  
Marco S. Pigazzini ◽  
Yuri Bazilevs ◽  
Andrew Ellison ◽  
Hyonny Kim
Keyword(s):  
Composite Laminates ◽  
Isogeometric Analysis ◽  
Composite Structures ◽  
Low Velocity Impact ◽  
Stiffened Panel ◽  
Progressive Damage ◽  
Low Velocity ◽  
New Class ◽  
Aerospace Applications ◽  
Post Impact

The increasing popularity of composite materials in aerospace applications is creating the need for a new class of predictive methods and tools for the simulation of progressive damage in laminated fiber-reinforced composite structures. The unique challenges associated with modeling damage in these structures may be addressed by means of thin-shell formulations which are naturally developed in the context of Isogeometric Analysis. In this paper, we further validate our recently developed Isogeometric Analysis-based multi-layer shell model for progressive damage simulations using experimental data for low-velocity impact on a 24-ply flat panel. The validation includes a careful comparison of delamination and matrix damage patterns predicted by the Isogeometric Analysis-based simulation and those obtained from post-impact non-destructive evaluation of the damaged coupon. The Isogeometric Analysis-based formulation is then deployed on two additional examples: a stiffened panel and a full-scale UAV wing, to demonstrate its suitability for, and ease of application to, typical aerospace composite structures.

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