Damage tolerance and durability testing for F/A-18 E/F composite materials structures

Author(s):  
Harlan Ashton
2011 ◽  
Vol 465 ◽  
pp. 535-538 ◽  
Author(s):  
Milad Hajikhani ◽  
Amir Refahi Oskouei ◽  
Mehdi Ahmadi Najaf Abadi ◽  
Amir Sharifi ◽  
Mohammad Heidari

Glass/polyester and glass/epoxy laminated composites widely used in structures and have very near properties. These composite laminates have poor inter-laminar fracture resistance and suffer extensive damage by delamination cracking when subjected to out of plane loading and hence are vulnerable to delamination. The presence of delamination in the composite material may reduce the overall stiffness. Structural design and nondestructive test techniques have evolved as increased emphasis has been placed on the durability and damage tolerance of these materials. There are several methods used to investigate damages of composite materials. Acoustic emission is one of these. In this work the effect of delamination propagation on acoustic emission (AE) events in glass/polyester and glass/epoxy composites is obtained also Fracture surface examinations were conducted using a scanning electron microscope (SEM) and results in these two common composites compared. Consequently, revealed that the AE technique is a practicable and effective tool for identifying and separating kinds of cracks in these composites.


2015 ◽  
Vol 6 (6) ◽  
pp. 787-798 ◽  
Author(s):  
Nikolai Kashaev ◽  
Stefan Riekehr ◽  
Kay Erdmann ◽  
Alexandre Amorim Carvalho ◽  
Maxim Nurgaliev ◽  
...  

Purpose – Composite materials and metallic structures already compete for the next generation of single-aisle aircraft. Despite the good mechanical properties of composite materials metallic structures offer challenging properties and high cost effectiveness via the automation in manufacturing, especially when metallic structures will be welded. In this domain, metallic aircraft structures will require weight savings of approximately 20 per cent to increase the efficiency and reduce the CO2 emission by the same amount. Laser beam welding of high-strength Al-Li alloy AA2198 represents a promising method of providing a breakthrough response to the challenges of lightweight design in aircraft applications. The key factor for the application of laser-welded AA2198 structures is the availability of reliable data for the assessment of their damage tolerance behaviour. The paper aims to discuss these issues. Design/methodology/approach – In the presented research, the mechanical properties concerning the quasi-static tensile and fracture toughness (R-curve) of laser beam-welded AA2198 butt joints are investigated. In the next step, a systematic analysis to clarify the deformation and fracture behaviour of the laser beam-welded AA2198 four-stringer panels is conducted. Findings – AA2198 offers better resistance against fracture than the well-known AA2024 alloy. It is possible to weld AA2198 with good results, and the welds also exhibit a higher fracture resistance than AA2024 base material (BM). Welded AA2198 four-stringer panels exhibit a residual strength behaviour superior to that of the flat BM panel. Originality/value – The present study is undertaken on the third-generation airframe-quality Al-Li alloy AA2198 with the main emphasis to investigate the mechanical fracture behaviour of AA2198 BMs, laser beam-welded joints and laser beam-welded integral structures. Studies investigating the damage tolerance of welded integral structures of Al-Li alloys are scarce.


2010 ◽  
pp. 177-191

Abstract The second-generation composite materials were added to increase the strain to failure of the primary phase and/or create a dispersed second phase, thereby enhancing the fracture toughness of the thermosetting matrix. These matrices offered novel design capabilities for composites in a variety of aircraft applications. To improve the damage tolerance of composite materials even further, an engineering approach to toughening was used to modify the highly stressed interlayer with either a tougher material or through the use of preformed particles, leading to the third generation of composite materials. This chapter discusses the development, processes, application, advantages, and disadvantages of dispersed-phase toughening of thermoset matrices. Information on the processes of particle interlayer toughening of composite materials is also included.


Materials ◽  
2005 ◽  
Author(s):  
K. Sairam ◽  
K. A. Jagadeesh ◽  
M. Senthilkumar

In the present scenario, strength of the structures has been the main focus of automobile manufacturers. The suspension leaf spring is one of the potential items for higher strength in automobiles as it accounts more than two times stronger than the conventional steel leaf spring. This helps in achieving more damping capacity, less fuel consumption and resistance against impact loads in the vehicle. The introduction of composite materials made it possible to avoid catastrophic damage due to sudden impact loads that are transferred to the chassis of light passenger vehicle through the leaf spring. In this work, an attempt has been made in replacing the design of a conventional multileaf leaf spring by a composite multileaf leaf spring based on strength ratio without any modification of the existing design of a light passenger vehicle. The materials adopted in the analysis of composite multileaf leaf spring are glass/epoxy, glass jute /epoxy, carbon jute/epoxy. The optimum material combination is determined based on the maximum induced bending stress, material availability and the contact pressure generated between each and every laminate which will influence the unsprung weight of the light passenger vehicle. Due to impact loads acting on the multileaf leaf spring damage tolerance work is also carried out in the composite material that has minimum contact pressure by creating artificial hemispherical damage for varying proportions. The optimum composite multileaf leaf spring is fabricated using filament winding technique. Modeling and contact analysis were carried out for both conventional and composite materials using ANSYS 8.1 software. From the investigations undergone, it is well proved that composite multileaf leaf spring made of glass/epoxy is found to be of higher strength comparing strength ratio, induced bending stress, contact pressure as well as with respect to cost, than the conventional leaf spring and the optimum damage radius due to sudden impact loads is also predicted in the composite multileaf leaf spring.


2010 ◽  
Vol 129-131 ◽  
pp. 1238-1243 ◽  
Author(s):  
Wei Gou Dong ◽  
Hai Ling Song

Two forms of perform were prepared by a Glass fiber/Polypropylene fiber commingled yarn. One was a three-dimensional woven fabric with an angle-interlock structure, and another was a two-dimensional plain woven fabric laminate. The three-dimensional woven fabric reinforced thermoplastic composites(3-DWRC) and two-dimensional woven fabric reinforced thermoplastic composites(2-DWRC) were fabricated by hot-press process. The Impact and tensile performances of both 3-DWRC and 2-DWRC were examined. Compared to the 2-DWRC, the 3-DWRC have better impact properties, the energy required to initiate cracks, the threshold force of the first oscillation and maximum load increased by 41.90%, 54.41%, 38.75% respectively under the low-energy impact conditions. The tensile tests shown that the 3-DWRC presented batter fracture toughness than the 2-DWRC. The use of thermoplastic composites is growing rapidly because of their excellent properties, a high toughness and damage tolerance, short processing cycles, and the ability to be reprocessed. But thermoplastic materials usually have a difficulty to impregnate between reinforcing fibers, due to high melt polymer viscosity. It is a technology innovation that the commingled yarns composed of reinforced fibers and thermoplastic fibers are used as prepreg for thermoplastic composite materials. Because thermoplastic fiber and reinforced fiber are closely combined, which reduces distances of resin’s infiltration, this can effectively overcome the difficulties of resin’s impregnation. The commingled yarns can be woven and knitted, and can facilitate the processing of complex structural composites. Three-dimensional fabrics reinforced composites are ideal materials with excellent integrity because it is linked with yarns between layers. Its shearing strength between layers, damage tolerance and reliability are better than the two-dimensional fabric laminated composites. At present, the researches of thermoplastic materials with two-dimensional fabric reinforced structure made from commingled yarns are much more, such as manufacturing technology, material properties ,effects of process conditions on properties, relationship between structures and properties, and so on [1-8]. However, only a few studies appear in literature on the structure-property relationships of three-dimensional fabric reinforced thermoplastic composite materials made of commingled yarns [9-10]. Byun, Hyung Joon et al. [9] undertook the impact test and the tensile test on 3-D woven thermoplastic composite materials and 2-D plain woven laminate which is made by CF/PEEK mixed yarn. Dong Weiguo and Huang Gu[10] studied the porosity, tensile and bending properties on 3-D woven thermoplastic composites which make from core-spun yarn containing glass fibers and polypropylene fibers. The aim of this study was to investigate the impact behavior of and tensile properties of 3-D woven fabric thermoplastic composites made by a GF/PP commingled yarns. Attempts was made to identify the damage mode of the 3-D woven fabric thermoplastic composites under the low energy impact and tensile conditions.


1993 ◽  
Vol 1993 (173) ◽  
pp. 359-366
Author(s):  
Kazuro Kageyama ◽  
Isao Kimpara ◽  
Toshio Suzuki ◽  
Isamu Ohsawa ◽  
Shigenori Kabashima

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