Bonded Repair of Aircraft StructuresA. Baker, Jones The conventional approach to through-life-support for aircraft structures can be divided into the following phases: (i) detection of defects, (ii) diagnosis of their nature and significance, (iii) forecasting future behaviour-prognosis, and (iv) pre scription and implementation of remedial measures including repairs. Considerable scientific effort has been devoted to developing the science and technology base for the first three phases. Of particular note is the development of fracture mechanics as a major analytical tool for metals, for predicting residual strength in the presence of cracks ( damage tolerance) and rate of crack propagation under service loading. Intensive effort is currently being devoted to developing similar approaches for fibre composite structures, particularly to assess damage tolerance and durability in the presence of delamination damage. Until recently there has been no major attempt to develop a science and tech nology base for the last phase, particularly with respect to the development of repairs. Approaches are required which will allow assessment of the type and magnitude of defects amenable to repair and the influence of the repair on the stress intensity factor (or some related parameter). Approaches are also required for the development and design of optimum repairs and for assessment of their durability. |
Contents
1 | 4 |
1 | 11 |
1 | 17 |
4 | 23 |
Design and analysis of bonded repairs for metal aircraft | 31 |
5 | 35 |
6 | 45 |
4 | 57 |
Partial reinforcement | 99 |
8 | 105 |
22222 2 | 108 |
3 | 111 |
29 | 122 |
5 | 133 |
6 | 151 |
31 | 158 |
7 | 63 |
Residual strength of flawed or damaged bonded joints | 70 |
9 | 73 |
19 | 76 |
5 | 86 |
7 | 162 |
22222223 | 164 |
Repair of composite aircraft | 175 |
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Common terms and phrases
adherends adhesive AF126 adhesive bonding adhesive cure adhesive layer adhesive shear stress adhesive-bonded aluminium alloy analysis analytical anodise anodize application approach b/ep behaviour bending correction bolted bond flaws bonded joints bonded repairs bonded structure boron composite patch configuration crack growth crack length crack tip crack-patching cycles cyclic loading damage disbond displacement durability effective epoxy equation estimate experimental failure fastener fatigue crack fatigue tests finite element fracture fracture mechanics gr/ep grit-blasting hole K₁ kN/m laminate load transfer materials maximum mechanical Mirage III moisture overlap joint panel parameters patched specimen peel phosphoric acid plate Plots Poisson's ratio precured procedure ratio reduced reinforcing patch residual stress residual-stress resin rivet shear modulus shear strain shear stress sheet shown in Figure silane stiffness strength stress intensity factor surface preparation surface-treatment Table temperature tensile tensile stress thermal thickness titanium unpatched wing skin