Advances in the Bonded Composite Repair o f Metallic Aircraft Structure phần 6 pptx

... 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 ... in the bonded composite repair of metallic aircraft structure ioo.0 Fig. 10.22. Typical auxiliary model used in the shape optimisation procedure for F/ A-1...

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

... 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...

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... 76 1 76 1 762 762 763 764 765 766 766 767 FOREWORD The introduction of the technology for bonded composite repairs of metallic airframe structures could not have come at a more ... have also benefited from the 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...

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 ... even though the load transfer through the bonded joint around the periphery of the patch is not instantaneous in the manner of the inclusion model, it is s...

Ngày tải lên: 08/08/2014, 11:21

... program, reported in reference [I6], have confirmed this need. Indeed, the tendency for the centroid of the skin/patch combination to align itself with the plane of action of the remote load ... then decay 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 hav...

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... 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

... aluminium alloy structures; it contains nine main sections covering repair of thin skin components, repair of thick sections, gr/ep versus b/ep patches, effect of bondline defects, effect of impact ... cycles .oo x IO6 .75 x IO6 .25 x IO6 50 x IO6 .88 x IO6 Fig. 15.4. Development of debond during FALSTAFF loading (specimen 16/ 17P). Chapter 13. Boronlepoxy pat...

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, ... bonded composite repair of metallic aircraft structure 21. Roach, D.P. (2001). Commercial application of composite doublers for DC-IO fuselage repairs, Int’l. SAMPE Sy...

Ngày tải lên: 08/08/2014, 11:21