Advances in the Bonded Composite Repair o f Metallic Aircraft Structure phần 8 ppsx

... DERA research on bonded composite patch repair of aluminium alloy structures; it contains nine main sections covering repair of thin skin components, repair of thick sections, gr/ep versus ... used to predict the effect of increasing the size of the initial bondline defect. Table 15.4 shows that, for a crack length of 15mm, AKP/AKu increased from 0.24 in the abs...

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 ... 26 Advances in the bonded composite repair of metallic aircraft structure composites are very abrasive and diamond tipped tools are normally used f...

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

... 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 ... with the first-order approximation given by Eq. (7.14). It can be seen that the first-order solution ignoring the load attraction effect of composite 1 78 Advance...

Ngày tải lên: 08/08/2014, 11:21

... 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 having the form: D =fO ... to design several complex repair schemes, such as the repair of fatigue cracks in the lower skin of Mirage aircraft [2], and cracks on the upper surface of the wing pi...

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 ... 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-...

Ngày tải lên: 08/08/2014, 11:21

... of a1. The coefficients of thermal expansion, a1 and a2, are the effective coefficients of thermal expansion for a unidirectional laminate. For a 3D laminate the out of plane coefficient ... stresses. In a bonded joint in which two materials are bonded together, thermal stresses may develop as a result of the difference in thermal coefficients of expansion. Th...

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 ... is done for the purpose of increasing the fatigue life of the joint. In service, environmental degradation may cause this bond to become ineffective,...

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 the...

Ngày tải lên: 08/08/2014, 11:21