Aluminium Design and Construction John Dwight

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Table 11.7 Properties of six two-component epoxy adhesives Notes. 1 The table is based on data supplied by Ciba Speciality Chemicals of Duxford, Cambridge, UK, who manufacture the Araldite range of adhesives. 2. Pot-life is the useable time after mixing for 100 g of adhesive held at 25°C. 3. Columns 3 and 4 give the room temperature curing time to achieve �=1 and �=10 N/mm 2 , when tested at 23°C. 4. Columns 5 and 6 give typical average strengths when tested at 23°C and 80°C, after curing as follows: first figure, 7 days/23°C; second figure (in brackets), 24 h/23°C+30 min/80°C. 5. Column 7 refers to testing at 23°C after the specimen has been immersed in water at 23°C for 60 days. 16 h/40°C cure. Copyright 1999 by Taylor & Francis Group. All Rights Reserved.
Table 11.7 and Figure 11.17 provide data on six selected two-component adhesives (Araldite 2010 to 2015). The quoted cure times to achieve a shear strength � of 1 N/mm 2 indicate how soon an assembled component can be handled. Table 11.8 and Figure 11.18 give equivalent data for a useful one-component adhesive, namely Araldite AV119. All the quoted strengths, which are typical (not minima), are based on short-term tests using the standard lap specimen. The information was provided by Ciba, the strength figures being unaffected by the alloy of the connected parts. It should be assumed that the given values refer to specimens having an ideal glue-line thickness, i.e. less than 0.3 and 0.6 mm respectively for the non-toughened and the toughened adhesives (Section 11.4.9). Manufacturers are usually able to provide values of percentage elongation to fracture, as obtained from a bulk tension type of specimen (Section 11.4.8). For all but one of the listed adhesives, the elongation is low (1–4%). The exception is Araldite 2011, which is reported as reaching a strain of nearly 5% at maximum tensile stress, with 20% elongation at fracture (at a reduced stress). With 2011, therefore, there will be redistribution of the stress in a bonded shear-joint before final collapse occurs. Figure 11.17 Curing times (t) for six selected two-component Araldite adhesives, to achieve shear strengths of 1 and 10 N/mm 2 . T c =curing temperature. Copyright 1999 by Taylor & Francis Group. All Rights Reserved.
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Aluminium Design and Construction C
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First published 1999 by E & FN Spon
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2.2.1 Rolling mill practice 2.2.2 P
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5 Limit state design and limiting s
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8.2.6 Use of interpolation for semi
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10.3.2 Inertias for a section with
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Preface Aluminium is easily the sec
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List of symbols The following symbo
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uu, vv principal axes w effective s
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1.1.3 The industrial metal It is on
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where A is the section area (mm 2 )
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1.3.1. The good points about alumin
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Deflection Because of the lower mod
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1.4.4 Establishment of the alloys I
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1.5.2 New technology Most of alumin
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large span, where self-weight is a
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These tend to be in all-aluminium c
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Close-up of the M-dec system, which
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Aluminium glazing system for commer
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Nat West Media Centre, Lords Cricke
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The main requirements for the produ
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in which t and w are in mm. These a
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Figure 2.1 Extrusion process (direc
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Figure 2.2 Typical extrusion die. t
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Figure 2.6 ‘Semi-hollow’ profil
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especially the stronger alloys in t
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Figure 2.9 Conventional profiles. 2
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2.4 TUBES By tubes we mean hollow s
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CHAPTER 3 Fabrication 3.1 PREPARATI
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Figure 3.1 Alternative designs for
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Figure 3.2 Thread insert. a coil-sp
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3.3 ARC WELDING 3.3.1 Use of arc we
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adjusted. The technique is claimed
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For welds of minimum or fatigue qua
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Figure 3.5 Friction-stir welding: s
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are, and the designer/fabricator mu
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cartridge, and mixing takes place a
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3.7.4 Painting Alloys having durabi
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Where a range is given, as for the
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will be only slightly above that fo
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heating the metal to a temperature
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Table 4.4 Characteristics of differ
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softening in the heat-affected zone
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60 alloys, are: BSEN.485 plate and
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Firure 4.3 Nominal composition and
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popular alloys in the series are: 6
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Figure 4.6 Variation of tensile str
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undercarriages of aircraft. They ar
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Figure 4.11 Minimum stress-strain c
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AC.51400 This is another non-heat-t
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times that of the actual pits) prod
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The severity of bimetallic corrosio
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Nominal loading. Nominal loads are
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2. Material factor (� m ). In the
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design does not, because stress at
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Table 5.2 Summary of limiting stres
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Figure 5.4 Plastic strain at workin
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example, a reduced value might be t
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The parameter � depends purely on
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CHAPTER 6 Heat-affected zone soften
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area of softening. With 7xxx-type m
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Figure 6.3 Typical hardness plots a
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6.4 SEVERITY OF HAZ SOFTENING 6.4.1
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Figure 6.6 Categories of welded joi
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Figure 6.10 One-inch rule, extent o
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e allowed for in design by replacin
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Figure 6.13 Predicted area (A z ) o
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Figure 6.15 Overlapping HAZs. nomin
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In determining A zp , an appropriat
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failure plane in the HAZ, close to
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With MIG welding, an electrode-posi
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CHAPTER 7 Plate elements in compres
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(a) Compression member elements The
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Table 7.1 Classification of element
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Figure 7.4 Slender internal element
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Figure 7.7 shows curves of � ° p
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(7.9a) (7.9b) The strain gradient c
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(through the centroid) for ß S . F
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Figure 7.13 Outstands under strain-
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Figure 7.15 Reinforced elements. Th
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Figure 7.18 Stiffener location for
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Figure 7.20 Slender reinforced inte
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CHAPTER 8 Beams 8.1 GENERAL APPROAC
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8.2.2 Section classification The di
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that for the gross section. It woul
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the usual manner. Line 1 in the fig
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1. Fully compact sections. The limi
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Figure 8.8 Transverse and longitudi
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8.3.4 Shear resistance of bars and
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Figure 8.12 Tension-field action. i
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Figure 8.14 Moment/shear interactio
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depending on the estimated degree o
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where a is the stiffener spacing an
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plates (if fitted), p v =limiting m
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ending moment diagram. Two cases ar
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Figure 8.23 Sections covered in Tab
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where: I yy , I vv =inertia about m
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post (Section 8.6.4) or by some oth
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Figure 8.26 Components of deflectio
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9.1.2 Classification of the cross-s
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hole. Alternatively, it might fail
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Figure 9.2 Limiting stress p b for
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The determination of l involves a c
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Figure 9.6 Monosymmetric section. I
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Figure 9.9 Limiting stress p b for
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where s=� s /� t s =slenderness
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Figure 9.11 Type-R sections covered
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Figure 9.14 Four standardized profi
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9.7.2 Secondary bending in trusses
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Table 9.5 Necessary checks for memb
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Figure 9.18 Axial load with biaxial
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1. Tension members. The localized f
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Figure 10.1 Symmetric plastic bendi
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Page 233 and 234: 10.3.3 Product of inertia The produ
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Page 237 and 238: Table 10.2 Torsion constant. Factor
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Page 243 and 244: 10.5.3 Evaluation of warping When t
Page 245 and 246: For sections where the position of
Page 247 and 248: (10.31) where: e=distance that S li
Page 249 and 250: 10.5.9 Asymmetric sections Before s
Page 251 and 252: CHAPTER 11 Joints This chapter cons
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Page 259 and 260: k in order to give a fair compariso
Page 261 and 262: 3. The design is satisfactory if fo
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Page 265 and 266: 11.3.3 Weld force arising In many c
Page 267 and 268: Table 11.6 Limiting stress p w (N/m
Page 269 and 270: where p a =limiting stress for unwe
Page 271 and 272: Figure 11.11 Interaction diagram fo
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Page 275 and 276: 11.4.6 Creep Shear strength figures
Page 277: Figure 11.15 Effect of glue-line th
Page 281 and 282: 11.4.11 Resistance calculations for
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Page 287 and 288: For example: The loading spectrum i
Page 289 and 290: act on the structure. However, BS.8
Page 291 and 292: Figure 12.4 Crack propagation: (a)
Page 293 and 294: 12.5 CLASSIFICATION OF DETAILS 12.5
Page 295 and 296: i.e. a joint extending in the same
Page 297 and 298: when the design life is low or when
Page 299 and 300: Methods (2) and (3) are difficult t
Page 301: it reverts to line 1. The slope s o
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Aluminium Design and Construction John Dwight

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