The strain rosette used to measure failure strains at a point yielded the following ratio between
the strains in the lamina coordinate axes:
&1= n₂/₁2=0
E2
The lamina was loaded by tensile stresses and ₂.
Compare the results obtained by the maximum stress, Tsai-Hill and Tsai-Wu criteria to
determine the failure stress. Which of these criteria prescribed the safest stress combination?
&c
Eb
60°
Y
60°
30°
QU
X
45⁰
Figure 1. Typical strain gauge rosettes (eFunda.com).
(a)/nNotes:
The ratio of strains: See Table 1 for your variant.
Material: See Tables 2 and 3 for your variant.
Table 1. The strain ratio measured in the lamina at failure.
Variant 1
n
Variant 10
1.3
n
1.5
Variant 19
1.4
n
2
1.1
11
1.6
20
0.75
3
1.2
12
1.15
4
0.8
13
0.7
5
2.0
14
0.5
6
1.7
15
1.5
7
0.6
16
1.2
8
0.9
17
0.4
9
0.75
18
1.6
1/nTable 2: Material in Problem 1 (see Table 3 for properties)
Var.
1
Material 1
Var.
10
Material 1
Var.
Material
19
1
2
1
11
1
20
1
3
1
12
1
4
2
13
2
5
2
14
2
6
2
15
2
7
3
16
3
8
3
17
3
9
3
18
3/nTable 3. Composite materials for problems 1 and 2 (material number in your variant refers to the
material in Table 1.1 below)
From
Table 1.1 Typical properties of unidirectional composites
E.J. Barbero, "Introduction to Composite Materials"
Density (
Longitudinal Model E
Tven Mode GP
Inplane Shear Modulus G₁ GP
P's Radio
Longitudinal Tessile Strength F₁, [MPa]
Transverse Tensile Strength PMP
Inplane Shear Strength (MP
Longitudinal Compressive Strength F₁, [MPa]
Transverse Compressive Strength F (MP)
elaminar Shear Strength (For Fy) [MPa]
Longitudinal Tessile Strain 3, 1963
Longitudinal CTE o [10/C)
Transverse CTE [10/
Longitudinal moisture
Transserse mistare expansice P
Fiber Volume Fract V
Void Content V. []
Fiber Misalignment
Material number
E-Glass S-Class
Epoxy Epoxy
2.076
12
55
30
0
55
16
0.2
60
82-85SBASERE
0.19 0.28
10:20 1630
40
60
630
140
60
23
37
Jalalalalalalal
16
60
6.90
140
80
29
32
02
60
2
*** 982-30*****338-3822M
E-Glas Kevlar
Epery
ophtal
Polyester
1.85
113
40
40
357
24
6.5
3.53
1.380
75.8
5.5
934
13800
34.5
441
586.0
138.0
48.69
1.8
-1.0
60
0.01
02
60
4
Carbo Carbon/ Carbon Carbon
Epoxy Epoxy Epey
ASA/35-6 T80/1960-2 1551 ASAPCE
PEEK
1.58
142
10.3
7.2
0.27
1830
57
71
1096
228
1.29
-49
27
0
02
60
n
1558
19
5.14
0.3
2608
168
0.0095
0.321
151
9.0
5.6
0.3
L64
57.3
DI
1.6
138
102
5.7
0.3
2000
85
186
1360
400
150
1.45
0.5
30
61
6
2
Carbo
Polid
ASU
Avi
Note: Carbon/epoxy, Kevlar/epoxy and boron/epoxy (to a smaller extent) are used in aerospace
applications, while less expensive glass/epoxy and glass/polyester are preferred by shipbuilders
and in civil engineering.
110
83
37
63
1000
0.5
Fig: 1
Fig: 2
Fig: 3
Fig: 4
Questión 4:For a bronze alloy, the stress at which plastic deformation begins is 275 MPa and the modulus of elasticity is 115 GPa. (6 marks – 3 marks each part) (a) What is the maximum load that may be applied to a specimen with a cross-sectional area of 325 mm without plastic deformation? (b) If the original specimen length is 115 mm, what is the maximum length to which it may be stretched without causing plastic deformation?
*16-68. Knowing that angular velocity of link AB is WAB = 4 rad/s, determine the velocity of the collar at C and the angular velocity of link CB at the instant shown. Link CB is horizontal at this instant.
16-107. At a given instant the roller A on the bar has the velocity and acceleration shown. Determine the velocity and acceleration of the roller B, and the bar's angular velocity and angular acceleration at this instant.
16-57. At the instant shown the boomerang has an angular velocity o = 4 rad/s, and its mass center G has a velocity vG = 6 in./s. Determine the velocity of point B at this instant.
A [0/+60/-60]s laminate with the ply properties listed in the table below is to be subjected to a temperature change from its initial temperature of 75°F. This temperature change can be expressed as a linear temperature change through the thickness of the laminate, with the temperature at the top of the six-ply laminate set at 225°F and the temperature at the bottom of the six-ply laminate set to -75°F. Therefore, for the temperature distribution defined by the equation AT(2) = AT+T'z, with ATh2=225°F - 75°F = 150°F and AT-2=-75°F-75°F=-150°F, AT. =(AT1/2+AT-1/2)/2= [150+(-150)]/2=0°F and T'=(AT12-AT-1/2)/h=(150-(-150))/6(0.0052) = 9,615.4°F/inch we obtain the distribution expression a) Determine the stresses in the lamina coordinate system at both the top and bottom in each of the 0°, +60° and -60° plies. b) Given the lamina strengths in the table below, determine if the laminate subjected to this temperature change distribution could be expected to survive with no excessive lamina stresses and therefore with no damage to the laminate. c) Assuming the same initial stress-free temperature of 75°F and by subjecting this same [0/+60/-60]s laminate separately to (i) a uniform temperature of 225°F and (ii) a uniform temperature of -75°F, answer the question "Is the through thickness temperature gradient more stressing on the laminate than either the uniform through thickness temperature of 225°F or the uniform through thickness temperature of -75°F?" Property E₁ E₂ G12 V12 α₁ (-200°F to 200°F) α₂ (-200°F to 200°F) 01 0 AT(2) AT+T'z = 9,615.4°F/inch*z TL cu OL σχετι Ply thickness Lamina Value 25 x 10º psi 1.7 x 106 psi 1.3 x 10º psi 0.3 -0.3 x 10 in/in/°F 19.5 x 10 in/in/°F 110 x 10³ psi 4.0 x 10³ psi 9.0 x 10³ psi 110 x 10³ psi 20 x 10³ psi 0.0052 inch
FORMULAS Emax = VƒEƒ + (1 - Vj) Em 1 = gel [r+rs(f-2)]¹/2/nQ6 A cylindrical pressure vessel with closed ends has a radius R = 1 m and thickness t = 40 mm and is subjected to internal pressure p. The vessel must be designed safely against failure by yielding (according to the von Mises yield criterion) and fracture. Three steels with the following values of yield stress oy and fracture toughness Kic are available for constructing the vessel. Steel Kic(MPa √/m A: 4340 100 B: 4335 70 C: 350 Maraging 55 Fracture of the vessel is caused by a long axial surface crack of depth a. The vessel should be designed with a factor of safety S = 2 against yielding and fracture. (a) By considering equilibrium along the longitudinal (axial) and circumferential (hoop) di- rections determine expressions for the hoop stress and axial stress in terms of the internal pressure, p, the radius, R and the thickness, t. dy (MPa) 860 1300 1550 (4 marks) (b) For the three steels, find the maximum pressure the vessel can withstand without failure by yielding. Note, your calculation should include the factor of safety, S. (4 marks) (c) The fracture toughness for a long axial surface crack of depth a is given by Kic 1.12000 √na. Hence determine an expression for the maximum pressure as a function of crack length a and fracture toughness. Note, your calculation should again include the factor of safety, S. (3 marks) (d) Plot the maximum permissable pressure pe versus crack depth a, for the three steels. (3 marks) (e) Calculate the maximum permissable crack depth a for an operating pressure p = 12 MPa. (3 marks) (f) Calculate the failure pressure p, for a maximum detectable crack depth a = 1 mm. (3 marks)
Today most turbo charged car engines have their rotors made of silicon nitride (Si3N4)rather than the traditional nickel alloy (Figure 1). i)Justify this material switch from metals to ceramics by comparing FOUR relevant material properties of silicon nitride with that of the previously used nickel alloy. ii)Draw a flow chart to outline the main process steps of the Si3N4 ceramic turbocharger rotor manufacture and assembly, and discuss two micro structural features that must be controlled to within strict limits during manufacture.
FORMULAS Emax = V₁E+ (1-V₁) Em Ogel 1 [r+rs(f-2)]¹/2/nQ5 The fuel rods of a nuclear reactor consist of solid uranium cylinders of diameter 70 mm. During operation, a typical rod experiences a temperature distribution approximated by the equation T(r) = 600 -0.1² °C, where r is the radius in mm. The properties of uranium are E = 172 GPa, v = 0.28, and a = 11 x 10-6 per °C. (a) Find the maximum tensile, compressive and shear stresses in the fuel rod if the outer surface is traction-free and plane strain conditions can be assumed. (14 marks) (b) If the fuel rod is now permitted to expand axially, determine the maximum tensile, com- pressive and shear stresses. (6 marks) [You may assume that the radial and hoop stresses in an axi-symmetric disk in a state of plane strain are Orr 000 = (3-2v)p²r² 8(1-v) (1+2v)p²,² 8(1-v) with the corresponding radial displacement + Ea (1-0)² /rTdr +/ Ea (1-v)r² afr rTdr _ ( 1-20)/(1+1) ²²³³ + 0(1+1) [T rTdr + 8E(1-v) (1-v)r where the symbols have their usual meanings] A+ EaT (1-v) B + A A(12v)(1+ v)r E B (1 + v) B Er
FORMULAS Emax = VjEj + (1 - V₁) Em 1 [r+rs(f − 2)]¹/2 Olgel/nQ2 You are a composites engineer in a company that is currently producing carbon fibre reinforced composites using a blend of a tetrafunctional epoxy and an aromatic diamine with the following characteristics: functionality of the crosslinking groups, f = 4, molar ratio of the epoxy groups to amine hydrogen atoms, r= 1, and the fraction of the amine hydrogen atoms in the reactants, s = 1. The matrix is predicted to undergo gelation at agel of 0.577 (around 58%). (a) Unfortunately, there has been an error in procurement and your materials supplier has provided a trifunctional epoxy for use with the same diamine. You can assume that the fraction of amine hydrogen atoms in the reactant formulation remains the same. Show, using Flory-Stockmayer theory, the polymer conversion at which your new matrix for- mulation reaches gelation. The polymer undergoes a change from a rubbery material to a cross-linked polymer, what do we call this? If you keep the other processing conditions the same, what effect will this have on the manufacturing time for the composite? (5 marks) (b) Fortunately, you realise the mistake before processing the composite, but you have to proceed using the same trifunctional epoxy and diamine. What two steps could you take to shorten the time to reach gelation? Justify your answer by showing the effect on Orgel- (5 marks) (c) A Time-Temperature-Transformation (TTT) diagram for your trifunctional epoxy and diamine blend is shown in Figure Q2. Sketch the TTT diagram and annotate on the dia- gram the isothermal processing temperature that you would propose to get the best ma- terial properties from your resin. Justify your reasoning by describing how your choice influences the manufacturing process. (5 marks) (d) Your cured epoxy resin develops a Young's modulus of 3.4 GPa and is combined with intermediate modulus carbon fibres (250 GPa). If the target fibre volume fraction for your composite is 55%, what is the maximum stiffness (Emaz) that you would expect along the fibre direction in each ply? Sketch a diagram to represent relative stiffness of the laminate against ply angle to show what Emax becomes in: (i) a unidirectional laminate, (ii) a cross-ply laminate, (iii) a quasi-isotropic laminate./nCure temperature (°C) Tg gel To Tso Gelled rubber gelation Liquid Oxidation Log time (min) Figure Q2 Tg Gelled glass Ungelled glass
Q1 Section A Complete both questions in this section in the BLUE answer booklet You are using an AISI 4340 (Fe-0.4wt% C+ alloying additions) steel to produce forged/machined ground anchors for a large mobile phone mast. (a) The steel is supplied in the normalised condition. What fraction of the steel do you expect to be austenite, martensite and pearlite? Justify each answer. (5 marks) (b) Upon examination you find the steel is mostly bainite and martensite with a small amount of proeutectoid ferrite. Determine the range of possible cooling rates this material might have experienced? Would the presence of these microconstituents cause you any concern considering the steel will be hot-forged? (5 marks) (c) The steel needs to be processed in the following manner: (i) Hot forge to the basic shape. (ii) Substantial machining to create threads. (iii) Heat treatment and cooling to create a 100% martensite microstructure. (iv) Tempering to modify the toughness. Sketch a time-temperature history that you would use for this process. Focus on specify- ing the temperatures and the required cooling rates for each stage. Clearly indicate where you have had to use your judgement to estimate a value. (5 marks) (d) You decide that the forging should be a dual-phase steel consisting of 50% ferrite and 50% martensite in order to improve the damage resistance of the anchor. What single change could be made to the above process to produce this desired microstructure? Fully explain your reasoning. (5 marks)/n8-iron (BCC) Temperature, T (°C) Ferrite a (BCC) 1600 1400 1200 1000 800 600 400 200 0 Melting point /of pure Fe 1534°C L+8 Peritectic point 0 Fe Austenite Y (FCC) 910°C 0.8 α+Y 0.035 1 L+Y Liquid, L 2.1 Eutectoid point 2 Eutectic point 3 Ferrite, & + Fe,C Austenite. Y + Fe₂C 723°C 4.3 wt% C 4 1147°C Compound, Cementite Fe₂C 5 6 7/nTemperature (C) 900 800 700 600 500 400 300 200 100 0 10⁰ M₂ M₁ B. Rate (C/s) 20 8 10¹ 10² 10³ time (s) Figure Q1 4 AISI 4340 0.33 0.08 0.023 0.006 104 105/nFORMULAS Emax = VjEj + (1 - V₁) Em 1 [r+rs(f − 2)]¹/2 - agel