Showing posts with label strength of material. Show all posts
Showing posts with label strength of material. Show all posts

Wednesday, 21 March 2018

Springs

Springs are energy absorbing units and used to store energy and to release it slowly or rapidly depending on application.

Closed Coiled Helical Spring under axial pull:


Consider one half turn of helical spring as shown   

Every cross section would be under torsion F*R

thus, maximum stress by torsion theory:
\[\tau_{max} = \frac{16 T}{\pi d^3}\]
\[\boxed{\tau_{max} = \frac{8FD}{\pi d^3}}\]
where D = 2*R = diameter of coil
d = diameter of spring wire 

If one cross section twists angle θ relative to other then:
\[θ = \frac{TL}{GJ} = \frac{FR(\pi R)}{GJ}\]
\[\delta' = Rθ = \frac{\pi F R^3}{GJ}\]

Total deflection \( \delta = 2N* \delta' = \frac{2N F \pi R^3}{GJ} = \frac{8NF D^3}{G d^4}\)

Spring Stiffness(K) :
\[\boxed{K = \frac{F}{\delta} = \frac{G d^4}{8 N D^3}}\]
where, N : number of turns
                  G : Modulus of rigidity 

NOTE: Stiffness is inversely proportional to the number of coils, therefore when a spring cut into half its stiffness becomes double for each part.

Wahl's correction factor( $k_w$ )

The simple torsion theory gives inappropriate results, thus for accurate result multiply by Wahl's factor.
\[\tau_{max} = \frac{k_w 8FD}{\pi d^3}\]
Wahl's correction factor is defined as:
\[k_w = \frac{4C-1}{4C-4} + \frac{0.615}{C}\]
where C is spring index = D/d

  

Springs in series:


When different stiffness springs joined such that shares common load, said to be in series. 

Total deflection \( \delta = \frac{F}{K_{eq}} = \delta_1 + \delta_2 + ..... + \delta_n = \frac{F}{K_1} + \frac{F}{K_2} + .....+ \frac{F}{K_n}\)
\[\boxed{\frac{1}{K_{eq}} =  \frac{1}{K_1} + \frac{1}{K_2} + .....+ \frac{1}{K_n}}\]

Springs in parallel: 


When different stiffness springs joined such that shares common deflection, said to be in parallel. 


\[ \delta = \frac{F}{K_{eq}} = \delta_1 = \delta_2 = ..... = \delta_n = \frac{F_1}{K_1} = \frac{F_2}{K_2} = .....= \frac{F_n}{K_n}\]
Total load \(F = F_1 + F_2 + ..... + F_n\)
\[\boxed{K_{eq} = K_1 + K_2 + ...... + K_3}\]


Spiral Spring


Consider a rectangular cross sectional (breadth B and thickness t) spiral spring is given by following equation:  
\[ r = \frac{b}{2} + \frac{a-b}{4 \pi N}θ \]
Springs will be subjected to uniform bending due to action of central moment which tends to reduce the radius of curvature at all points.

When winding couple M is applied to the spindle, resisting force F will be set up at the pin such that 
M = F * R

Now, Consider two small elements of length dl at distance x each side of center. 

For small deflection change in slope is = $\frac{M dl}{EI}$.

for left side element change in slope,
\[dθ_1 = \frac{F(R+x) dl}{EI}\]
for right side element change in the slope,
\[dθ_2 = \frac{F(R-x) dl}{EI}\]
sum of these two slopes = $dθ_1 + dθ_2 = \frac{2FR dl}{EI}$

Total angle of twist = $\frac{1}{2} \int_{0}^{L} \frac{2FR}{EI}dl = \frac{FRL}{EI} = \frac{ML}{EI}$

Length of spiral $ L = \frac{\pi N}{2}(a+b) $

We get wind up angle of spiral spring is :
\[θ = \frac{M}{EI} \Bigg[ \frac{\pi N}{2} (a+b) \Bigg] \]

Maximum Bending moment = F*a

Maximum bending stress = $\frac{M y}{I}$
\[ \sigma_{max} = \frac{F a(t/2)}{Bt^3/12}\]
\[ \sigma_{max} = \frac{6 F a}{Bt^2}\]



Saturday, 10 March 2018

Pressure Vessels


When the thickness of the wall of the shell in less than $\frac{1}{10}$ to $\frac{1}{15}$ of its diameter, then shell is called thin shell.
\[t < \frac{D}{10} \quad to \quad \frac{D}{15}\]
When the thickness of the wall of the shell in greater than $\frac{1}{10}$ to $\frac{1}{15}$ of its diameter, then shell is called thick shell.
\[t > \frac{D}{10} \quad to \quad \frac{D}{15}\]

Thin Cylinders



Say L length, diameter d and t thickness of cylinder is subjected to internal pressure P. Due to this pressure, three type of stresses are developed at any point on the wall of cylinder -
  1. Hoop Stress / Circumferential stress ($\sigma_h$) will be tensile in nature.
  2. Longitudinal stress / Axial stress ($\sigma_L$) will be tensile in nature.
  3. Radial stress ($\sigma_R$) will be compressive in nature. 

Analysis of thin cylinder

  • It is assumed that stresses are uniformly distributed through the thickness of the wall.
  • Radial stress varies from P at inner surface to atmospheric pressure at the outside of surface.
  • If the internal pressure is very low, radial stress is negligible compared to axial and hoop stress. 

1. Hoop or circumferential stress ($\sigma_h$):


This stress is directed along to the tangent to the circumference of the cylinder. It resist the bursting effect due to internal pressure. 


At the equilibrium,

$P*(dL) = σ_h*(2tL)$

Hoop stress,                                       $\boxed{σ_h = \frac{Pd}{2t}}$

2. Longitudinal Stress ($\sigma_L$):


This stress is directed along the length of the cylinder and it tends to increase the length. 


At the equilibrium,
\(P*(\frac{\pi d^2}{4}) = σ_L*(\pi dt)\)

Longitudinal stress                  \(\boxed{σ_L = \frac{Pd}{4t}}\)

3. Longitudinal strain


\[ε_L = \frac{σ_L}{E} - μ\frac{σ_h}{E}\]
\[\boxed{ε_L = \frac{Pd}{4tE}(1 - 2μ)}\]

4. Hoop Strain

\[ε_h = \frac{σ_h}{E} - μ\frac{σ_L}{E}\]
\[\boxed{ε_h = \frac{Pd}{4tE}(2 - μ)}\]

5. Volumetric Strain


Volumetric strain = Longitudinal strain + 2*hoop strain
\[\boxed{ε_v = \frac{Pd}{4tE}(5 - 4μ)}\]

Thin Sphere


Hoop Stress/ Longitudinal Stress  
\[σ_h = σ_L = \frac{Pd}{4t}\]
Hoop Strain/ Longitudinal Strain
\[ε_h = ε_L = \frac{Pd}{4tE}(1 - μ)\]
Volumetric Strain
                                            \(ε_v = 3*ε_L = \frac{3Pd}{4tE}(1 - μ)\)



Thick Cylinders


  • Radial stress in thin cylinder is neglected but it is of significant magnitude in case of thick cylinders.
  • Tangential stresses assumed uniformly distributed over the wall in thin cylinder while it changes gradually from inner surface to outer surface in case of thick cylinders.  

  • Axial Stress \( \sigma_z = \frac{P_i r_i^2}{r_o^2 - r_i^2}\)

  • Radial Stress \(\sigma_r = A - \frac{B}{r^2}\)

  • Circumferential or hoop stress   \(\sigma_h = A + \frac{B}{r^2}\)

A and B are constant which can be determine by boundary conditions:

$\sigma_r = - P_i$  at $r = r_i$

$\sigma_r = - P_o$  at $r = r_o$







Friday, 9 March 2018

Columns: Buckling Failure


STRUT: A structural member which carries an axial compressive load.

COLUMN: A vertical strut is known as column.

A long column becomes unstable when its axial compressive load reaches a limit called critical buckling load. Its lateral deflection called buckling.

Load carrying capacity of columns in depend upon -

  • Material
  • End connections
  • dimension or slenderness ratio

Euler's Theory


Assumptions:
  • Column is perfectly straight and uniform cross section.
  • Applied compressive load is perfectly axially.
  • Stresses are within elastic limit.
  • The material is homogenous and isotropic.
Maximum allowable buckling load or Euler's critical load is given by:
\[\boxed{P_e = \frac{{\pi}^2EI_{min}}{L_e^2}}\]
where, $I_{min}$ = Moment of inertia about centroids axis
Le = Effective length                            



NOTE: This formula doesn't take account the axial stress. It is applicable for long columns where effect of crushing is neglected. 

Slenderness ratio (S)

Slenderness ratio is defined as the ratio of its effective length to least radius of gyration. 
\[S = \frac{L_e}{k}\]
\[ K = \sqrt{\frac{I_{min}}{A}}\]
\[Buckling \quad Stress \quad \sigma_b = \frac{P_e}{A} = \frac{{\pi}^2EI_{min}}{A L_e^2} = \frac{{\pi}^2E}{S^2}\]

Rankine's Theory


\[\frac{1}{P_R} = \frac{1}{P_C} + \frac{1}{P_e}\]

$P_R$ = Rankine Load or Crippling load
$P_C$ = crushing load = $\sigma_C$
$P_e$ = Buckling Load
\[P_R = \frac{\sigma_c A}{1 + K'(\frac{L_e}{k})^2}\]
K' = Rankkine's constant = $\frac{\sigma_c}{\pi^2E}$

  • Effect of crushing and buckling considered in this formula.
  • This formula is applicable to any column.


Wednesday, 7 March 2018

Theories of Failure


  1. Maximum Principal Stress theory (RANKINE’S THEORY)
  2. Maximum Shear Stress theory (GUEST AND TRESCA’S THEORY)
  3. Maximum Principal Strain theory (St. VENANT’S THEORY)
  4. Total Strain Energy theory (HAIGH’S THEORY)
  5. Maximum Distortion Energy theory (VONMISES AND HENCKY’S THEORY)

Maximum Principal Stress Theory (MPST)


According to MPST, failure occurs when the value of maximum principal stress is equal to that of yield point stress. 

Condition for failure is,
Maximum principal stress ($\sigma$) > failure stresses (Syt)

Condition for safe design,
Maximum principal stress  ≤  Permissible stress 
where, permissible stress = failure stress / Factor of Safety =\( \frac{Syt}{N}\)

\[\boxed{\sigma ≤  \frac{Syt}{N}}\]


NOTE:
  • This theory is suitable for brittle materials under all loading conditions (bi axial, tri axial etc.) because brittle materials are weak in tension.
  • This theory is not suitable for ductile materials because ductile materials are weak in shear.
  • This theory can be suitable for ductile materials when state of stress condition such that maximum shear stress is less than or equal to maximum principal stress i.e. 
  1. Uniaxial state of stress( $τ_{max} = \frac{\sigma}{2}$)
  2. Biaxial loading when principal stresses are like in nature. ( $τ_{max} = \frac{\sigma}{2}$)
  3. Under hydrostatic stress condition (shear stress in all the planes is zero).

Maximum Shear Stress Theory (MSST)


According to this theory, failure occurs when maximum shear stress at any point reaches the yield strength. 

Condition for safe design,

\(\boxed{\tau_{max} ≤  \frac{Sys}{N} = \frac{Syt}{2N}}\)

For tri-axial state of stress,
Max{\(|\frac{σ_1 - σ_2}{2}|, |\frac{σ_2 - σ_3}{2}|, |\frac{σ_3 - σ_1}{2}|\)} ≤  $\frac{Syt}{2N}$

For bi-axial state of stress,
Max{\(|\frac{σ_1 - σ_2}{2}|, |\frac{σ_2}{2}|, |\frac{σ_1}{2}|\)} ≤  $\frac{Syt}{2N}$




NOTE:
  • This theory is well suitable for ductile materials.
  • MSST and MPST will give same results for ductile materials under uniaxial state of stress and biaxial state of stress when principal stresses are like in nature.
  • MSST is not suitable for hydrostatic loading.

Maximum Principal Strain theory (M P St T)


According to this theory, failure occurs when maximum principal strain reaches strain at which yielding occurs in simple tension.


Condition for safe design,

 \(\boxed{ε_1 ≤  \frac{Syt}{EN}}\)

\(\frac{1}{E}[σ_1 - μ(σ_2 + σ_3)] ≤  \frac{Syt}{EN} \)

for biaxial state of stress, $σ_3$ = 0

\(σ_1 - μ(σ_2) ≤  \frac{Syt}{N} \)





Total Strain Energy theory (T St E T)


According to this theory, failure occurs when total strain energy per volume is equal to strain energy per volume at yield point in simple tension.

Condition for safe design,
 Total Strain Energy per unit volume  ≤  Strain energy per unit volume at yield point under tension test.

 Total Strain Energy per unit volume = $\frac{1}{2}σ_1ε_1$ + $\frac{1}{2}σ_2ε_2$ + $\frac{1}{2}σ_3ε_3$ 

$ε_1 = \frac{1}{E}[σ_1 - μ(σ_2 + σ_3)]$
$ε_2 = \frac{1}{E}[σ_2 - μ(σ_1 + σ_3)]$
$ε_3 = \frac{1}{E}[σ_3 - μ(σ_2 + σ_1)]$

we get,
\[\frac{TSE}{Vol} = \frac{1}{2E}[σ_1^2 + σ_2^2 + σ_3^2 - 2μ(σ_1σ_2 + σ_2σ_3 + σ_3σ_1)]\]
\[\frac{TSE}{Vol}\Bigg]_{Y.P.} = \frac{1}{2E}(\frac{Syt}{N})^2 \]
\[[σ_1^2 + σ_2^2 + σ_3^2 - 2μ(σ_1σ_2 + σ_2σ_3 + σ_3σ_1)] ≤ (\frac{Syt}{N})^2 \]
for bi axial case $σ_3 = 0$,

\(σ_1^2 + σ_2^2 - 2μσ_1σ_2  ≤ (\frac{Syt}{N})^2 \)

Above Equation is an equation of ellipse whose semi major axis is $\frac{Syt}{\sqrt{1-μ}}$ and minor axis is $\frac{Syt}{\sqrt{1+μ}}$


NOTE: This theory is suitable for hydrostatic stress condition.


Maximum Distortion Energy Theory (M D E T)


According to this theory, failure occurs when strain energy of distortion per volume is equal to strain energy of distortion per unit volume at yield point in simple tension.

Total strain energy/Vol = Volumetric strain energy/vol + distortion energy / volume

Volumetric Strain Eenrgy /vol = $\frac{1}{2}$ (average stress)(Volumetric strain)
\[Vol SE/Vol = \frac{1}{2}\frac{σ_1 + σ_2+ σ_3}{3}[\frac{1-2μ}{E}(σ_1 + σ_2+ σ_3)] = \frac{1-2μ}{6E}(σ_1 + σ_2+ σ_3)^2 \]
DE/vol = TSE/vol - Vol SE/vol
\[\boxed{DE/vol =  \frac{1 + μ}{6E}[(σ_1 - σ_2)^2 + (σ_2 - σ_3)^2 + (σ_3 - σ_1)^2]}\]
\[DE/vol]_{YP} =  \frac{1 + μ}{6E}[2(\frac{Syt}{N})^2]\]
Condition for safe design,
$DE/vol  ≤  DE/vol]_{YP}$
\[[(σ_1 - σ_2)^2 + (σ_2 - σ_3)^2 + (σ_3 - σ_1)^2] ≤  2(\frac{Syt}{N})^2\]
for bi axial case $σ_3 = 0$,

\(σ_1^2 + σ_2^2 - σ_1σ_2  ≤ (\frac{Syt}{N})^2 \)

This Equation is an equation of ellipse whose semi major axis is $\sqrt{2}Syt$ and minor axis is $\sqrt{2/3}Syt$


NOTE:

  • This theory is best for ductile materials.
  • It can not be applied materials under hydrostatic stress condition. 

Comparison among the different failure theories


Comparison of different failure theories



Monday, 5 March 2018

Deflection Of Beams

The deflection is measured from original neutral surface of the beam to neutral surface of deformed beam. The configuration of neutral surface of deformed beam is known as elastic curve of beam.

Differential Equation of Elastic Curve for the loaded beam


Assumptions:
  • Stress is proportional to strain i.e. hooks law applies.
  • Small deflection
  • pure bending or Any deflection resulting from the shear deformation of the material or shear stresses is neglected.

from analytic geometry, curvature of line is given by,
\[k = \frac{1}{R} = \frac{\frac{d^2y}{dx^2}}{\Big[1 + \frac{d^2y}{dx^2}\Big]^{3/2}} \approx \frac{d^2y}{dx^2}\]
from simple bending theory equation,
\[\frac{σ}{y} = \frac{M}{I} = \frac{E}{R} \quad or \quad \frac{1}{R} = \frac{M}{EI}\]
So basic differential equation governing deflection of beam is
\[\boxed{M = EI \frac{d^2y}{dx^2}}\]
since shear force is \(\frac{dM}{dx}\) thus,
\[\boxed{Slope = \frac{dy}{dx}}\]
\[\boxed{Bending \quad Moment = EI\frac{d^2y}{dx^2}}\]
\[\boxed{Shear \quad Force = EI\frac{d^3y}{dx^3}}\]
\[\boxed{Load \quad Distribution = EI\frac{d^4y}{dx^4}}\]

Deflection for Common Loadings


1. Moment load at the free end of cantilever beam



  • Maximum Bending Moment       M = -M   
  • Slop at end     \(θ = \frac{ML}{EI}\)
  • Maximum deflection (at end)     \(δ = \frac{ML^2}{2EI}\)
  • Deflection Equation    \(EI y = -\frac{Mx^2}{2}\)

2. Concentrated load at the free end of cantilever beam


  • Maximum Bending Moment       M = -PL   
  • Slop at end     \(θ = \frac{PL^2}{2EI}\)
  • Maximum deflection (at end)     \(δ = \frac{PL^3}{3EI}\)
  • Deflection Equation    \(EI y = -\frac{Px^2}{6}(3L-x)\)



3. Cantilever Beam subjected to a Uniformly distributed load


  • Maximum Bending Moment       \(M = -\frac{qL^2}{2}\)   
  • Slop at end     \(θ = \frac{qL^3}{6EI}\)
  • Maximum deflection (at end)     \(δ = \frac{qL^4}{8EI}\)
  • Deflection Equation    \(EI y = -\frac{qx^2}{120L}(6L^2 -4Lx + x^2)\)




4. Cantilever Beam subjected to a Uniformly Triangular distributed load


  • Maximum Bending Moment       \(M = -\frac{q_oL^2}{6}\)   
  • Slop at end     \(θ = \frac{q_oL^3}{24EI}\)
  • Maximum deflection (at end)     \(δ = \frac{q_oL^4}{30EI}\)
  • Deflection Equation    \(EI y = -\frac{q_ox^2}{120L}(10L^3 -10L^2x + 5Lx^2 - x^3)\)

5. Concentrated load at the mid-span of simply supported beam


  • Maximum Bending Moment       \(M = -\frac{PL}{4}\)   
  • Slop at end     \(θ_A = θ_B = θ = \frac{PL^32}{16EI}\)
  • Maximum deflection (at midspan)     \(δ = \frac{PL^3}{48EI}\)
  • Deflection Equation (for 0 < x < L/2) \(EI y = -\frac{Px}{48}(3L^2 - 4x^2)\)

6. Uniformly distributed load of simply supported beam


  • Maximum Bending Moment       \(M = -\frac{qL^2}{8}\)   
  • Slop at end     \(θ_A = θ_B = θ = \frac{qL^3}{24EI}\)
  • Maximum deflection (at mid span)     \(δ = \frac{5qL^4}{384EI}\)
  • Deflection Equation    \(EI y = -\frac{qx}{24}(L^3 -2Lx^2 + x^3)\)



Strain Energy Method (Castigliano’s Theorem)


Castigliano’s Theorem states that the partial derivative of the strain energy with respect to an applied force is equal to the displacement of the force along its line of action.

\[\boxed{δ = \frac{\partial U}{\partial P}}\]
The strain energy is given by
\[U = \int\limits_{0}^{L} \frac{M^2}{2EI} dx\]

\[\boxed{δ = \int\limits_{0}^{L} \frac{\partial M}{\partial P}\frac{M}{EI} dx}\]

Example : Take a cantilever beam subjected to concentrated load P at free end

M = P(L - x)
\(δ = \int\limits_{0}^{L} \frac{\partial M}{\partial P}\frac{M}{EI} dx\)
\(δ = \int\limits_{0}^{L} (L - x)\frac{P(L-x)}{EI} dx\)

\(δ = \frac{PL^3}{3EI}\)


Friday, 23 February 2018

Bending and Torsion

Pure Bending


Assumptions:
  • Beam is initially straight and constant cross section.
  • Beam material is homogeneous and isotropic.
  • The material is elastic, Obeys Hook's law (stress in elastic limit).
  • Plane transverse sections remains plane after bending. 
  • Constant B.M along the length of the beam.

Pure Bending


The surface described by the lines which do not extend or contract in the process of bending is called neutral surface and the line of intersection between the neutral surface and the transverse exploratory section is called the neutral axis.

Bending equation is
\[\boxed{\frac{σ}{y} = \frac{M}{I} = \frac{E}{R}}\]
where σ = Bending Stress              
M = Bending moment
E = Modulus of elasticity
I = Moment of inertia = \(\frac{\pi D^4}{64}\) for solid circular shaft
R = Radius of curvature 
y = Distance from Neutral axis

\[\boxed{σ = \frac{My}{I} = \frac{M}{\frac{I}{y}}}\]

  • Section modulus is defined as \(Z = \frac{I}{y}\). Higher the Z lower the stress.
  • For same cross section area Z for non-circular cross section is higher than circular sections.
  • Maximum Bending stress occurs at where y is maximum (either at the top or bottom of the bar depending on the actual direction of the moment). 

Torsion


Torsion means twisting of a structural member when it is loaded by couple that produce rotation about longitudinal axis. 

Equation of Torsion


Assumptions:
  • The material is homogeneous and isotropic.
  • The material is elastic, Obeys Hook's law (stress in elastic limit).
  • Cross sections remains plane. 
  • Cross-sections rotate as if rigid, i.e. every diameter rotates through the same angle

\[\boxed{\frac{T}{J} = \frac{τ}{r} = \frac{Gθ}{L}}\]

where,     T = Torsion or applied torque 
J = Polar moment of inertia 
τ = Shear stress induced due to torsion
R = shaft radius
L = Shaft length
G = modulus of rigidity
θ = Angle of twist
$ϕ = \frac{rθ}{L}$  = Shear strain for any plane from fixed end.


Shear stress Distribution in torsion
  • Torsional stiffness $ k = \frac{T}{θ} = \frac{GJ}{L}$   
.
  • Polar section modulus $ Z_p = \frac{J}{r}$
  • Shear stress is maximum when r = R.

Polar moment of inertia


  • For solid circular shaft 
\[J = \frac{\pi d^4}{32}\]
  • For hollow shaft (Outer dia D and inter dia d)
\[J = \frac{\pi}{32}(D^4 - d^4)\]

Connections of shafts


  • Series connection        
Torque (T) will be same in all sections.

Total angle of twist at free end will be equal to the sum of each section's angle of twist.
        θ = θ1 + θ2 + θ3
\[θ = T \bigg[ \frac{L1}{G1J1} + \frac{L2}{G2J2} + \frac{L3}{G3J3}\bigg]\]



  • Parallel connection 
Angle of twist will be same for both shaft.    
       θ1 =  θ2 = θ
Total torque will be equal to sum of torque acting on both shafts.
       T  = T1 + T2
\[θ = \frac{TL}{G1J1 + G2J2}\]



Combined Bending and Torsion


For a solid shaft (dia D) subjected to bending moment M and torque T
Combined Bending & Torsion


Bending stress \(σ = \frac{32 M}{\pi D^3}\)

shear stress due to torsion \( τ = \frac{16 T}{\pi D^3}\)


Maximum principal stress $σ_{max}$ and maximum shear stress $τ_{max}$
\[σ_{max} = \frac{16}{\pi D^3}(M + \sqrt{M^2 + T^2})\]
\[τ_{max} = \frac{16}{\pi D^3}\sqrt{M^2 + T^2}\]

Thus equivalent bending moment (Me) alone would produce the same maximum stresses by combination of M and T:
\[M_e = \frac{1}{2}\Big[M + \sqrt{M^2 + T^2}\Big]\]

And equivalent torque (Te) alone would produce the same maximum shear stress:
\[T_e =  \sqrt{M^2 + T^2}\]


NOTE: Equivalent torque and equivalent bending moment should not be used for other purposes like the calculation of power transmission by the shaft, power transmitted depends solely on the torque T carried by the shaft not on Te.


Tuesday, 20 February 2018

Principal Stress and Principal Strain

Sign Conventions

  • Tensile normal stress is considered positive ans compressive normal stress is considered negative.
  • Shear stress acting on a positive face is considered positive if it acts in positive direction and negative if in negative direction.

Transformation of plane stress


The stress system is known in coordinate system xy. We want to find stress in coordinate system x1y1 which is rotated θ degree in anti clockwise direction. 



Transformation Equations are:
\[σ_{x1} = \frac{σ_x + σ_y}{2} + \frac{σ_x - σ_y}{2}cos2θ + τ_{xy}sin2θ\]
\[σ_{y1} = \frac{σ_x + σ_y}{2} - \frac{σ_x - σ_y}{2}cos2θ - τ_{xy}sin2θ\]
\[τ_{x1y1} = - \frac{σ_x - σ_y}{2}sin2θ + τ_{xy}cos2θ\]

Note:
  • $σ_x + σ_y  = σ_{x1} + σ_{y1}$

Principal Stresses and Principal Plane

  • The maximum or minimum of normal stresses (σ 1 and σ 2) are known as the principal stresses.
  • The plane on which principal stresses act is called principal plane.
  • The shear stresses are zero on the principal plane.
To find the principal stresses, differentiate the transform equations and we get,  
\[\boxed{tan2θ_p = \frac{2τ_{xy}}{σ_x - σ_y}}\]
$θ_p$ is angle of principal plane.

Principal Stresses are:
\[\boxed{σ_{1,2} = \frac{σ_x + σ_y}{2} ± \sqrt{(\frac{σ_x - σ_y}{2})^2 + (τ_{xy})^2}}\]


Maximum Shear Stress


Say $θ_s$ is angle of plane where shear stress is maximum then,
\[tan2θ_s = - \bigg(\frac{σ_x - σ_y}{2τ_{xy}}\bigg)\]
\[τ_{max} = \sqrt{(\frac{σ_x - σ_y}{2})^2 + (τ_{xy})^2} \quad \quad τ_{min} = -τ_{max}\]


Relation between Maximum shear stress and Principal Stress :
         \[θ_s = θ_p ± 45°\]
 \[τ_{max} = \frac{σ_1 - σ_2}{2}\]


Principal Strains and Principal Angles


All the equations based on stress transformation can be converted to equations of strain by substitute as follows:
\[ ε _x \iff σ_x\]
\[ ε _y \iff σ_y\]
\[\frac{γ_{xy}}{2} \iff τ_{xy}\]

 
  • Plane stress doesn't lead to plane strains.



Sunday, 11 February 2018

Shear Forces and Bending Moment

Members with support loadings applied perpendicular to their longitudinal axis are called beams. Beams classified according to the way they are supported.

Types of Beam

  • Simply supported beam

If the ends of a beam are made to rest freely on supports, it is called simply supported beam.

Simply supported beam

  • Fixed Beam

If both ends of a beam are fixed, it is called fixed beam.

Fixed Beam

  • Cantilever Beam

If beam is fixed at one end and another end is free, it is called cantilever beam.

Cantilever Beam

  • Continuous Beam

It more than two supports are provided to a beam, it is called continuous beam.


Continuous Beam


Shear Force And Bending Moment


It is an internal force acting tangentially to the section which is normal to longitudinal direction. Bending moment at any section is internal reaction due to all the transverse force either from left side or right.


where w = load per unit length (N/m), V = shear force, M = bending moment

Note:
  • At a hinge bending moment will be zero.
  • Bending moment will be maximum or minimum where shear force is zero.
  • A point of contraflexture / point of inflexion is a point where the curvature of beam changes sign. It occurs points on the beam where bending moment changes sign i.e. BM is zero.


Shear force and Bending Moment diagram for an applied moment(Fd)



Elastic Constant, Strain Energy

Hook's Law


The Stress is directly proportional to strain.
Hook's Law

Elastic constants are those factor which determine the deformation produced by given a stress acting on a material.

  • Modulus of elasticity(E)  = Normal stress / Normal strain
  • Modulus of rigity (G)  =    Shear Stress / Shear Strain
  • Bulk Modulus (K)  = Direct stress / Volumetric strain

Poisson’s Ratio (µ)

µ   =      - (Transverse Strain) / (Axial Strain)

  • µ = 0 to 0.5 under uni-axial loading
  • µ = 0 for cork
  • µ = 0.5 for perfectly plastic 
  • -1 < µ < 0.5

Volumetric Strain (ev)

Here,  sx , syand sz  are stress in x, y, and z- direction.

ev  = ex + ey + ez



   e= (sx + sy + sz)(1 - 2µ) / E     

If sx = sy = sz = s, 

   e= 3s(1 - 2µ) / E     

  • Volumetric strain of cylinder bar = longitudinal strain + (2 x diametric strain)
  • Volumetric strain of sphere = 3 x diametric strain

Relation Between E, G, K, µ 





      Material          Number of independent Elastic constant     
Homogeneous & Isotropic                           2 
  Orthotropic                           9 
  Anistropic                          21 

Axial elongation of a prismatic bar due to external load



Equivalent young's modulus of parallel composite bar



Strain Energy

It is the ability of material to absorb energy when it is strained.

U = Pxδ / 2   = Txϴ / 2 

Where P = Applied load
           δ = Elongation due to applied load
          T = Applied Torque
           ϴ  = Angle of twist due to applied torque

Resilience

Ability of a material to absorb energy in the elastic region when it is strained.

Resilience  = Area under P- δ curve = Pxδ / 2  

The maximum strain energy that can be stored in a material is known as proof resilience.

Modulus of Resilience (u) = Strain energy / Volume

                                     

Thermal Stress and Strain

Stress which is induced in a body due to change in the temperature is known as thermal stress and the corresponding strain is called thermal strain.



T is the Temperature change.

  • When bar is free to expand, there will be no thermal stress due to temperature change.
  • airon = 11.8 µm/m·K
  • aAluminium > aBrass  > a Copper > airon 


Saturday, 10 February 2018

Mechanical Properties of Metals, Stress and Strain

Stress


When a material is subjected to an external force, a resisting force induced. The internal resistance force per unit area is called stress.

Unit :    $N/m^2$

Type of stress:

  • Normal Stress

  • Shear Stress
          
  • Bulk Stress
      


Strain

Deformation per unit length in the direction of deformation is known as strain. It is dimensionless quantity.

Types of Strain

  • Normal Strain
    

  • Shear Strain


  • Bulk Strain
    


True Stress and True Strain


True stress is defined as the ratio of load to the instantaneous area. 



Where σ and ε is the engineering stress and engineering strain respectively.

The true strain is defined as


Stress-Strain Curve





NOTE:

  • Limit of Proportionality: It is the stress at which the stress-strain curve is straight line(OA).
  • Hook's law is valid upto proportionality limit.
  • Elastic limit: point in the stress-strain curve upto which the material remains elastic. There is no permanent deformation upto this point.
  • Plastic Range: Region between elastic limit and point of fracture.
  • Yeild Point: The point just beyond the elastic limit, at which material goes increase in length without further increase in the load.

Properties of Materials

Elasticity

Elasticity is the property by virtue of which a material is deformed under the load and is enabled to return to it original dimension when the load is removed.

Plasticity

The characteristic of the material by which it undergoes inelastic strains beyond those at elastic limit is known as plasticity.

Ductility

Ducitility is the characteristic which permits a material to be drawn out longitudinally to a reduced section, under the action of a tensile force. A ductile material possess a high degree of plasticity strength.

Brittleness

A material is said to be brittle when it cannot be drawn out by tension to smaller section. e.g. glass, ceramic etc
In brittle material failure takes place under load without significant deformation.

Malleability

It is a property of a material which permits the material to be extended in all directions without rapture. A malleable material possess a high degree of plasticity, but not necessarily great strength.

Toughness

It is the property of a material which enable it to absorb energy without fracture. It is desirable in materials which is subject to cyclic or shock loading.
Bend test used for common comparative test for toughness.


Hardness

Hardness is the ability of a material to resist indentation or surface abrasion. Brinell hardness test is used to check hardness. 

Brinell Hardness Number (BHN)   

where, P = Standard load,
                         D = Diameter of steel ball 
                                 d = Diameter of the indent (mm)

Strength

The property enables material to resist fracture under load.
Load required to cause fracture, divided by area of specimen is known as ultimate strength.


Behavior of Various Material

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