Analysis Of Bars Of Varying Section
Sekiranya ada 3 besi yang berlainan kawasan luas persilangan sahaja
Length increase = , NaN
Load = , NaN
Length of Bar 1 (Original Length)= , NaN
Young Modules 1 = , NaN
Area Crossection 1 (Original Area)= , NaN
Length of Bar 2 (Original Length)= , NaN
Young Modules 2 = , NaN
Area Crossection 2 (Original Area)= , NaN
Length of Bar 3 (Original Length)= , NaN
Young Modules 3 = , NaN
Area Crossection 3 (Original Area)= , NaN
Analysis Of Uniformly Tapering Circular Rod==Mungkin perlu edit balik gambar
Check (4)Total Extension For 1 Rod With Same Diameter
Total Extension = , NaN
Load = , NaN
Length of bar= , NaN
Young Modules = , NaN
Diameter = , NaN
(5)Total Extension For 1 Rod With Different Diameter
Total Extension = , NaN
Load = , NaN
Length of bar = , NaN
Young Modules = , NaN
Diameter at 0cm = , NaN
Diameter at lastcm = , NaN
(6) Extension At Certain Length
k = NaN
Extension at certain length = , NaN
Load, NaN
Young Modules, NaN
Largest Diameter, NaN
Smallest Diameter, NaN
Length of the Rod, NaN
Length of the Rod from largest diameter, NaN
Thickness of the certain length =, NaN
Analysis Of Uniformly Tapering Rectangular Bar(Perlu Check balik sebab at certain length mungkin ada salah/silap tgk)
(7) Extension At Certain Length
k = NaN
Extension =, NaN
Load =, NaN
Young Modules =, NaN
Thickness of the bar =, NaN
Width at the bigger end =, NaN
width at the smaller end =, NaN
Length of the Rod =, NaN
Certain length of the Rod from largest diameter =
(8) Total Extension
Extension , NaN
Load, NaN
Young Modules, NaN
Thickness of the bar, NaN
Width at the bigger end, NaN
width at the smaller end, NaN
Length of the Rod, NaN
Analysis Of Bars Of Composite Sections
(9) Pressure For BArs of Composite Section
Load or Force = 0
Stress at Rod 1NaN
Crossection Area at Rod 1NaN
Stress at Rod 2 NaN
Crossection Area at Rod 1NaN
(10) Modular Ration
Modular Ratio = NaN
Young Modulus for Rod 1 = 0
Young Modulus for Rod 2 = NaN
Thermal Stress
(11) Thermal Strain
Temperature Changes = 0
Compressive Strain = 0
Stress = 0
Load = 0
Coefficient of linear expansion =
Initial Temperature = 0
Final Temperature = 0
Young Modules =
Area =
Thermal Stress Actual
Actual Stress = NaN
Actual Strain = NaN
Coefficient of linear expansion = NaN
Initial Temperature = NaN
Final Temperature = NaN
Original Length = NaN
Yield Length = NaN
Young Modules = NaN
Thermal Stress in Composite Bars
Actual Expansion of steel A and B Is The Same
Free Expansion of steel A = 0
Free Expansion of steel B = 0
Tensile Strain = NaN
Compressive Strain = NaN
Young Modulus A (Bigger) = NaN
Young Modulus B (Smaller)= NaN
Coefficient of linear expansion Steel A = NaN
Coefficient of linear expansion Steel B = NaN
Final Temperature =
Initial Temperature =
Stress of Steel A = NaN
Stress of Steel B = NaN
Elongation Of Bar Due To Its Own Weight
Total Elongation at 0= NaN
Weight = NaN
Length of Bar= NaN
Young Modules= NaN
(Tambah Gambar Check)Analysis Of Bar Of Uniform Strength
(14)Area at Upper End= NaN
Specific weight =
Length of Bar=
Area of lower bar end=
Stress=
(1) Poisson Ratio = NaN
Lateral Strain =0
Longitudinal Strain =NaN
Lateral Strain
(2) lateral Strain = -0
Poisson Ratio
Longitudinal Strain
Volumetric Strain
(3) Volumetric Strain = NaN
Change In length0
Original LengthNaN
Poisson RatioNaN
Volumetric Strain Of A Rectangular Bar Subjected To Three Forces Which Are Mutually Perpendicular
(4) Volumetric Strain = NaN
Young Modules = NaN
Stress in X-direction0
Stress in Y-direction0
Stress in Z-direction0
Poisson RatioNaN
Volumetric Strain Of A Cylindrical Rod
(5) Volumetric Strain = NaN
Change in Length(Increase/Decrease) = NaN
Original LengthNaN
Change in Diameter(Increase/Decrease)NaN
Original DiameterNaN
Bulk Modulus
(6) Bulk Modulus = NaN
Direct Stress =
Volumetric Strain
Expression For Young's Modulus In Terms Of Bulk Modulus
(7) Young Modulus = 0
Poisson Ratio =
Bulk Modulus =
(8)Principle Of Complementary Shear Stress *Note that shear stress occur the same as it other surface in when it is 90 degree
Stresses On Inclined Sections When The Element Is Subjected To Simple Shear Stresses
Normal Stress = 0
Tangential Stress = 0
Shear Stress =
Angle/Degree =
(8a)Diagonal Stresses Produced By Simple Shear On A Square Block
Normal Stress in 0 = 0
Tangential Stress in 0 = 0
Shear stress =
Angle/Degree =
Direct(Tensile And Compressive) Strains Of The Diagonals
Total Tensile/Compressive Strain = NaN
Young Modules =
Poisson Ratio =
Shear Stress =
Normal Stress= 0
Tangential Stress= 0
Stress =
Angle/Degree =
(2) A member Subjected to like Direct Stress in two mutually Perpendicular Direction
Normal Pressure or Load = 0
Tangential Pressure or Load = 0
Normal Stresses = 0
Tangential Stresses = 0
Stress normal to the surface =
Area of Crossection(Adjacent to the angle) =
Angle/Degree =
Stress tangential to the surface =
Area of Crossection(opposite to the angle) =
(3)Obliquity
Obliquity = NaN
Tangential stress =
Normal stress =
(4)Maximum Shear Stress
Maximum shear stress = 0
Stress normal to the surface =
Stress tangential to the surface =
Principal Plane
(5)A member subjected to a simple shear stress
X(Normal) Force or Load depend on angle = 0
Y(Tangential) Force or Load depend on angle= 0
X(Normal) Stress or Load = 0
Force x Direction = 0
Force y Direction = 0
Y(Tangential) Stress or Load = 0
Shear Force =
Area of crossection of x direction =
Area of crossection of y direction =
Angel/Degree =
(6)A member subjected to direct stress in two mutually Perpendicular Direction accompanied by a simple shear stress
Total Normal Force
Total Tangent force
Total Normal Force = 0
Total Tangential Force = 0
X(Normal) Force or Load depend on angle due to shear = 0
Y(Tangential) Force or Load depend on angle dues to shear Q2= 0
X(Normal) Stress or Load = 0
Force x Direction due to shear P1= 0
Force y Direction due to shear P2= 0
Y(Tangential) Stress or Load = 0
Shear Force =
Area of crossection of x direction =
Area of crossection of y direction =
Angel/Degree =
Stress X Direction =
Stress Y Direction =
Normal stress Accross FC
(7)Tangential stress Accross FC
Normal Stresses = 0
Tangential Stresses = 0
Shear Force =
Stress normal to the surface =
Angle/Degree =
Stress tangential to the surface =
(8)Position of principle plane
Stress at Principle Plane = Max, 0 Min = 0
Shear Force =
Stress normal to the surface =
Stress tangential to the surface =
Major principles stress
Major Principle Stress = 0
Minor principles stress
Minor Principle Stress = 0
Maximum shear stress
Maximum Shear Stress = +- 0
Strain Enery Stored = NaN
volume of the body =
Young Modulus =
Stress =
Modulus Of Resilience
Strain Enery Stored = NaN
Young Modulus =
Stress =
Expression for strain energy stored in A body when the load is applied with direct impact *Note, that use strain = stress/young modulus
Stress = NaN
Pressure or Load =
Area =
Young Modulus =
height of the dropped =
Length of the rod =
Expression for strain energy stored in a body due to shear stress
Work Done or Strain Energy = NaN
Shear =
Volume Of The Block =
Modulus Of Rigidity =
negatif(-) indicate it is downward weight or load or force
Bending moment at distance 0 from free end = 0
Shear force = 0
Weigth = KG
distance from free end =
Shear force and bending moment diagram for a cantilever with a Uniformly distributed load
negatif(-) indicate bending moment is clockwise
Shear force at 0= 0
Bending Moment 0= 0
Weigth =
distance from free end =
Shear force and bending moment diagram for a cantilever carrying a gradually varying load
Shear Force = NaN
Bending Moment = NaN
Weigth =
distance from free end =
Total Length of the bar =
Shear force and bending moment diagram for a simply supported beam with a point load at mid-point
Shear Force/Resultant Force = 0
Bending Moment = 0
Weigth =
Total Length of the bar =
Shear force and bending moment diagram for a simply supported beam with an eccentric point load
Shear Force/Resultant Force at A= NaN
Shear Force/Resultant Force at B= NaN
Bending Moment = NaN
Weigth =
Length of the bar from side A =
Length of the bar from side A =
Total Length of the bar =
Shear force and bending moment diagram for a simply supported beam carrying a uniformly distributed load
Shear Force/Resultant Force = 0
Bending Moment = 0
Weigth =
Total Length of the bar =
Shear force and bending moment diagram for a simply supported beam carrying a uniformly distributed load from zero at each end to w per unit length at the centre
Shear Force/Resultant Force = 0
Bending Moment = 0
Weigth =
Total Length of the bar =
Shear force and bending moment diagram for a simply supported beam carrying a uniformly distributed load from zero at each end to w per unit length at the other end
Shear Force/Resultant Force at zero load= 0
Shear Force/Resultant Force at max load= 0
Bending Moment at length from zero load = NaN
Maximum Bending Moment = 0
Weigth =
Length of the bar from zero load =
Total Length of the bar =
Strain or Increase of layer in bending= NaN
Stress from neutral axis=
Radius of the bending rod from the centre of its force =
Stress Variation
Stress along the center of Rod= NaN
Young Modulus =
Radius of the bending rod from the centre of its force =
Stress from neutral axis=
Neutral Axis and Moment of Resistance
Force on the layer=NaN
Area of layer (depend on the circumference shape of the rod or bar)=
Young Modulus =
Radius of the bending rod from the centre of its force =
Stress from neutral axis=
Moment of Resistance or Moment of the forces on the section of the beam
Moment=NaN
Moment of inertia =0
Force on the layer=NaN
Area of layer (depend on the circumference shape of the rod or bar)=
Young Modulus =
Radius of the bending rod from the centre of its force =
Stress from neutral axis=
Section Modulus
Section of Modulus=NaN
Moment of inertia =0
Area of layer (depend on the circumference shape of the rod or bar)=
Stress from neutral axis=
Length from outer most layer from neutral axis=
Section Modulus For Various Shapes or Beam Section
i) Rectangular Section
Section of Modulus = 0
Moment of Inertia = 0
Breadth or width=
Depth=
ii) Rectangular hollow Section
Moment of Inertia = 0
Section Modulus = NaN
Breadth or width Outer=
Depth Outer=
Breadth or width internal=
Depth internal=
iii) CIRCULAR SECTIONS
Section Modulus = 0
Moment Of Inertia = 0
Diameter or Depth =
iV) Circular hollow Sections
Section Modulus = NaN
Moment Of Inertia = 0
Diameter or depth internal=
Diameter or depth Outer=
Composite Beam (Flitched Beam)
Moment(M) = NaN
Modular Ratio(m) = NaN
Moment of Inertia Outer Steel = 0
Moment of Inertia Inner Steel = 0
Stress (follow outer surface direction) =
Stress distance from neutral axis=
Young Modulus Inner steel=
Young Modulus Outer Steel=
Diameter internal=
Diameter Outer=
Shear along the beam = NaN
Moment of Inertia = 0
Area of cross section above the shear stress region from the neutral axis= 0
Breadth or width of the beam from force untill shear region from the neutral axis=
Depth of the beam from force untill shear region from the neutral axis=
Downward Force=
Distance Center of Gravity of the area above the shear stress from the neautral axis=
Shear Stress Distribution for Different Sectioni) Rectangular Section
Shear Stress at 0 from the neutral axis and above= NaN
Shear Stress at Neutral Axis = NaN
Moment of Inertia = 0
Force =
Breadth =
Depth =
Shortest distance of the shear stress region from neutral axis =
Circular Section
E in the formula is actually 3Shear Stress at 0 from the neutral axis and above= NaN
Moment of Inertia = 0
Force =
Diameter or depth Outer =
Shortest distance of the shear stress region from neutral axis =
I Section Shear Stress Distribution in the flange
Shear Stress at 0 from the neutral axis and above= NaN
Moment of Inertia = 0
Force =
Depth Outer (D) =
Depth Inner from neutral axis (Y)Please Refer The Picture Above=
Breadth Outer (B) =
Breadth Inner (b) total =
Shear Stress Distribution in the web
Shear Stress at 0 from the neutral axis and above= NaN
Maximum Shear Stress = NaN
Moment of Inertia = 0
Force =
Depth Outer (D) =
Depth Inner from neutral axis (Y)Please Refer The Picture Above=
Breadth Outer (B) =
Breadth Inner (b) total =
Direct Stress = NaN
Load or Pressure =
Area =
Resultant Stress When A CoLumn Of Rectangular Section Is Subjected To An Eccantric Load
Bending Stress = +NaN for left side of neutral axis and -NaN for right side of neutral axis
Distance of the load from neutral Y axis =
Distance of the load from neutral X axis =
Depth =
Breadth =
Maximum Stress or Right Side of Neutral Axis = NaN
Minimum Stress Left Side Of Neutral axis = NaN
Resultant Stress When A CoLumn of Rectangular Section is subjected to a load which is subjected to eccentric both axes
Direct Stress = NaN
Moment of Load About X-X axis = 0
Moment of Load About Y-Y axis = 0
Load or Pressure =
Distance from Neutral X axis =
Distance from Neutral Y axis =
Area =
Moment Of Inertia Ixx = 0
Moment Of Inertia Iyy = 0
Bending Moment for Moment X = NaN
Bending Moment for Moment Y = NaN
Breadth =
Depth =
Stress at Quadrant I = NaN
Stress at Quadrant II = NaN
Stress at Quadrant III = NaN
Stress at Quadrant IV = NaN
Middle Third Rule For Rectangular Section ( i.e Kernal Of Section)
This is for when the force is acting any place on the neutral axisStress (Negative mean Tensile Positive Mean Compresive) = NaN
Load or Pressure =
Area =
Breadth =
Depth =
Distance of force from Neutral axis =
The Shaded region is call core section, maening it will not have tensile stress.Distance from centre from x axis is 0 at upper side and 0 at lower side
Distance from centre from y axis is 0 at left side and 0 at right side
Middle Quarter Rule For Circular Section ( i.e Kernal Of Section)
The Shaded region is call core section, maening it will not have tensile stress.Distance from centre is 0
Load =
Radius of the force from centre =
Diameter =
Direct Stress = NaN
Bending Stress = +NaN or -NaN
Minimum Stress = NaN
Kernel of hollow circular section (or value of eccentricity for hollow circular section)
Circular Area = 0
Direct Stress = NaN
Section modulus , Z = NaN
moment of Inertia= 0
Bending Stress = NaN
Load or Pressure =
Diameter internal =
Diameter Outer =
Diameter from the force =
Diameter of Kernal = NaN
Kernel of hollow rectangular section (or value of eccentricity for hollow rectangular section)
Area = 0
Moment of inertia Ixx = 0
Distance from neutral X axis =
Depth Outer =
Breadth Outer =
Depth Internal =
Breadth Internal =
Section Of Modulus, Z = NaN
Force = 0
Volume = 0
liquid density
Breadth =
Height from the surface =
Length =
If only want at a point of the pressure, make Length = 1
Force or Weight= 0
Volume = 0
Dam density
Breadth =
Height from the bottom =
Length =
If only want at a point of the pressure, make Length = 1
Resultant Force = 0
Angle = NaN
Distance from neutral Y-axis that cut the base = NaN
Stress across section of Rectangular Dam
Distance From The Surface To The Point Where It Cutt The Base
Distance From The Surface To The Point Where It Cutt The Base = NaN
Distance of eccentricity(Distance from neutral axis) =NaN
Bending Stress at eccentricity of NaN is NaN but depend on location
Bending Stress near A , -NaN near B = +NaN
Total Stress near A= NaN
Total Stress near B= NaN
Trapezoidal Dam Having Water Face Vertical
Force Exerted By Water At Center Of Gravity = 0
Distance From neutral Y-axis to water =NaN
Distance From Water to cutt base = NaN
Eccenticity = NaN
Breadth Top =
Breadth bottom =
Distance x(Centroid to Point that cutt the base) =
Base Length =
Trapezoidal Dam Having Water Declined
Above Picture mean AE=AF/cos
AE(refer Picture) Distance = 0
Distance of AF =
Degree =
Force due to water = 0
Volume of water =
Force in X direction = 0
Force in Y direction = 0
Stability of A Dam
0 X 0 = NaN X 0
Rankine Theory of Earth Pressure //Yang ni aku perlu sah kan apa beza pressure P ni.
Pressure or Load = 0
Degree =
Pressure or Load = 0
Degree =
Volume =
Heigth =
Chimney
Force = 0
Coefficient
Intensity Wind Pressure =
area of exposed =
Bending Moment = 0
Height Of Chimney =
Deflection of beam = NaN
Length of the beam=
Moment of Inertia of the beam(Calculate Yourself. Depends on the shape of the beam) =
Moment (Calculate Yourself. Depends on the shape of the beam) =
Young Modulus =
sin Theta or Theta in radian=NaN
Relationship between slope, deflection, and radius of curvature
Need to Draw in graph so that the derivative can be calculate (error)
Need to Draw in graph so that the derivative can be calculate (error)
Need to Draw in graph so that the derivative can be calculate (error)
Need to Draw in graph so that the derivative can be calculate (error)
Deflection of simply supported beam carrying a point load at the center
Need to Draw in graph so that the derivative can be calculate (error)
Need to Draw in graph so that the derivative can be calculate (error)
Need to Draw in graph so that the derivative can be calculate (error)
Need to Draw in graph so that the derivative can be calculate (error)
Deflection of simply supported beam with an eccentric point load
Deflection of simply supported beam with a uniformly distributed load
Macaulay Method
Moment Area Method
Deflection of a cantilever with a point load at a Distance A from the fixed end
Deflection of a cantilever with a uniformly distributed load
Deflection of a cantilever with a uniformly distributed load A from the fixed end
Deflection of a cantilever with a gradually varying load
Deflection and slope of a cantilever by moment area method.
Cantilever carrying a Uniformly distributed load
Cantilever carrying a Uniformly distributed load upto a length A from fixed end
Strain for bending moment = NaN
Length of the beam=
Moment of Inertia of the beam(Calculate Yourself. Depends on the shape of the beam) =
Load =
Young Modulus =
Simply supported beam carrying an eccentric load
1
2
Deflection and slope of a cantilever with a point load at the free end
Propped cantilever and beam
S.F and B.M diagram for a propped cantilever carrying a Uniformly distributed load and propped at the free end
S.F and B.M diagram for a simply supported beam with a uniformly distributed load and propped at the free end.
Maximum torque transmited by circular solid shaft
Maximum torque transmited by a hollow circular shaft
Power transmitted by shaft
Polar Modulus
Strength of shaft and torsional rigidity
Flanged Coupling
Expression for strain energy stored in a body due to torsion
Total strain energy in the hollow shaft due to torsion
Torsion of tappering shaft
Laminated or spring leaf
Expression for Central deflection of the leaf spring
Closed coil helical spring
Expression For Circumferential Stress Or Hoop Stress
Expression For Longitudinal Stress
Effect of the internal pressue on the dimension on a thin cylindrical shell
Wire Winding Of Thin Cylinder
Thin Spherical Shells
Change in Dimension of a Thin Sperical Shell due to an Internal Pressure
Volumetric Strain
Rotational Stress in Thin Cylinder
End conditions for long columns
Expression for crippling load when the both end of the column are hinged
Expression for crippling load when the end of the column are hinged and others are free
Expression for crippling load when the both end of the column are fixed
Expression for crippling load when the end of the column are fixed and others are hinged or pin
Crippling stress in terms of effective length and radius if gyration
Slenderness of ratio
Limitation of Euler Formula
Rankine formula
Straight Line Formula
Columns with ecentric load
Maximum stress
Column with initials curvature
Maximum deflection
Maximum stress
Strut with lateral load(Or Beam Columns)
Strut subjected to compressive axial load or axial trust and a transverse uniformly distributed load Of internsity w per unit length. Both end are pinned
Butt joints
Chain Riveted Join
Diamond Riveted Join
Failure of Riveted Join
Failure due to tearing of the plate between rivets of a row
Failure due to shearing of rivet
Failure due to crushing (or bearing) of Rivet or plate
Strength of Riveted Join
Design of a riveted join
Analysis of Unsymmetrical welded section which are loaded axially
Axial Load in terms of shear stress
Maximum Shear Stress Theory
Maximum Strain Energy Theory
Maximum Shear Strain Energy Theory
