Advances in the Bonded Composite Repair o f Metallic Aircraft Structure phần 9 pptx

... Advances in the bonded composite repair of metallic uircraft structure Following the development of a bonded- composite repair for MSD in the fuselage lap-joint of wide bodied transport aircraft ... the final configuration of the defects. In some cases the defects only remained on one side of the hole, the other being removed by the tool. Foll...

Ngày tải lên: 08/08/2014, 11:21

... Advances in the bonded composite repair of metallic aircraft structure 4.5.4. Fickean diffusion coeflcients for moisture absorption Althof [24] gives the following data for the diffusion coefficients ... The adhesive to metal or composite interface 0 The adhesive to primer interface 0 The surface matrix resin of the composite 0 The near-surface pli...

Ngày tải lên: 08/08/2014, 11:21

... mm from the centre of the lower lug and continued to the end of the “horizontal” section around the lug, as indicated in Figure 10.24. The first ply of the boron/epoxy reinforcement was then ... function by transferring some portion of the load from the reinforced component through the adhesive bond layer, thereby reducing the range and mean of the cyclic stre...

Ngày tải lên: 08/08/2014, 11:21

... determine the economic life of the airframe. Unfortunately, management of corrosion by the setting of inspection intervals is not always effective since the location of corrosion and its rate of ... use of this technology. The application for the solution of the problem of cracking in the fuel drain holes in wing of the C-141 is credited with maintaining the viab...

Ngày tải lên: 08/08/2014, 11:21

... Keeping void contents low is a matter of recognising the origins of the voids and ensuring that appropriate procedures are used. If the 64 Advances in the bonded composite repair of metallic aircraft ... Advances in the bonded composite repair of metallic aircraft structure current understanding and the complexity of the bonded joint, there is...

Ngày tải lên: 08/08/2014, 11:21

... practice, however, structures to be reinforced may be finite in size or constrained by the surrounding structure. To quantify the effect of this constraint, consider the configuration shown in Figure ... simulating finite size effect. only the solution for an isotropic patch with a coefficient of thermal expansion a~, (7 .99 ) The above solution applies strictly for an...

Ngày tải lên: 08/08/2014, 11:21

... linearly to zero at the free surface of the skin (or plane of symmetry in the case of a patch on both sides of the skin). This results in the matrix D having the form: D =fO [ '1 ... When allowing for the stiffeners using the stiffener correction factor (SCF), i.e. Eq. (9. 29) the approximate formulae was accurate, for all (200+) test cases, to within...

Ngày tải lên: 08/08/2014, 11:21

... the first being the isotropic solution and the second the orthotropic solution. Application of a closed form solution to the repair of an aircraft wing requires an assumption of the value of ... Application of analysis to large repairs of aircraft wings The object of this section is to determine the applicability of a closed form solution to the large repair o...

Ngày tải lên: 08/08/2014, 11:21

... strains in the bond line of the boron/epoxy patch remain above the design limit for typical operating loads. Figure 14 .9 shows the influence of the operating temperature on the most significant ... DERA research on bonded composite patch repair of aluminium alloy structures; it contains nine main sections covering repair of thin skin components, repair of...

Ngày tải lên: 08/08/2014, 11:21

... assessment of bonded composite doubler repairs 491 Application of impact damage to composite coupons Following the composite doubler installation and prior to environmental conditioning, ... performed in- situ to eliminate the removal of the specimens from the tension test machine following each fatigue interval. 5. Static strain measurements were acquired at th...

Ngày tải lên: 08/08/2014, 11:21