Advances in the Bonded Composite Repair o f Metallic Aircraft Structure phần 2 potx

... 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 ... for the composite are for through-thickness deformation, (c) critical strain refers to failing strain for the composites and yield strain for the metals, (d) fatigue strain refers to approximate ... Sections 2. 1 and 2. 2 for a complete discussion of the issues and in this section a summary of the main points is given referring to the four main repair materials and some of the main design...

Advances in the Bonded Composite Repair o f Metallic Aircraft Structure phần 1 potx

... method 10.4. 10.5. 10.6. xvii 21 2 21 5 22 7 22 9 23 I 23 3 23 6 23 8 24 0 24 1 24 2 24 3 24 5 25 1 25 6 25 8 26 2 26 4 26 6 26 9 26 9 27 0 27 1 27 1 27 2 27 2 27 3 27 4 27 5 27 6 27 7 ... 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 viability of this fleet. The...

Advances in the Bonded Composite Repair o f Metallic Aircraft Structure phần 3 pptx

... 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 plies of the composite. Obviously the failure ... strain response to various cyclic loads for one of the strain gauges. The initiation load for this specimen was 24 .2kN using the definition above. Since the strain gauge was installed very close...

Advances in the Bonded Composite Repair o f Metallic Aircraft Structure phần 4 docx

... 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 ... first-order solution ignoring the load attraction effect of composite 178 Advances in the bonded composite repair of metallic aircraft structure by new analyses that account for both patch material ... reinforcement can be determined using the conventional theory of cylindrical bending of plates, i.e. we shall assume that the bending deformation of the reinforced portion satisfies the usual...

Advances in the Bonded Composite Repair o f Metallic Aircraft Structure phần 5 pdf

... 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 pivot fitting of FlllC aircraft ... consider the effect that the difference between the coefficients of thermal expansion of the boron patch and the aluminium alloy wing skin has on the residual stresses left in the skin after the patch ... When allowing for the stiffeners using the stiffener correction factor (SCF), i.e. Eq. (9 .29 ) the approximate formulae was accurate, for all (20 0+) test cases, to within 5%. To confirm the...

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

... tt-' is the height for step k. 28 0 Advances in the bonded composite repair of metallic aircraft structure Table 10.1 Geometric details for patch on one side of plate for non- uniform ... 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 stresses in the repaired component. ... at the strut end of the reinforcement, the non-uniform stepping was only applied to this end of the reinforcement. The region at the lug end of the reinforcement has low stresses, and hence the...

Advances in the Bonded Composite Repair o f Metallic Aircraft Structure phần 7 pdf

... (referring to Chapter 13 for more details). In the following, we will focus our attention on the influence of thermal residual stress only. For an orthotropic composite patch bonded to an isotropic ... 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. The following equations ... the joint, B = +(ta/2q COS X1 /2) /X3 and x = k 1 12 corresponds to the ends of the joint. 3 62 Advances in the bonded composite repair of metallic aircraft structure (a) (b) (c) Fig....

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 ... either from a static calibration or in flight. (d) From a knowledge of the external aerodynamic loads and the availability of a full F- E model of the aircraft and local region to estimate internal ... influence of an increasing cure temperature on the decreasing shear strain in the GLARE 2 patch, while the strains in the bond line of the boron/epoxy patch remain above the design limit for...

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 ... is done for the purpose of increasing the fatigue life of the joint. In service, environmental degradation may cause this bond to become ineffective, and corrosion of the mating skins could ... exposure to aircraft oils and fluids, etc. The doubler locations were chosen on the following criteria: Fig. 16 .26 . Boeing 727 lap joint repair. 460 Advances in the bonded composite repair...

Advances in the Bonded Composite Repair o f Metallic Aircraft Structure phần 10 docx

... 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. (20 01). Commercial application of composite doublers for DC-IO fuselage repairs, Int’l. SAMPE Synzp. on Composites in ... for loss-of-adhesion flaws to initiate and grow in the composite doubler installation. Disbonds can occur between the composite doubler and the aluminum skin while delaminations can develop...

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