Deflection in Eccentric Loading Solution

STEP 0: Pre-Calculation Summary
Formula Used
Deflection in Eccentric Loading = (4*Eccentricity of Load*Axial Load/Critical Buckling Load)/(pi*(1-Axial Load/Critical Buckling Load))
δ = (4*eload*P/Pc)/(pi*(1-P/Pc))
This formula uses 1 Constants, 4 Variables
Constants Used
pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288
Variables Used
Deflection in Eccentric Loading - (Measured in Millimeter) - Deflection in Eccentric Loading the degree to which a structural element is displaced under a load (due to its deformation).
Eccentricity of Load - (Measured in Millimeter) - Eccentricity of Load is the distance from the center of gravity of the column section to the center of gravity of the applied load.
Axial Load - (Measured in Kilonewton) - Axial Load is defined as applying a force on a structure directly along an axis of the structure.
Critical Buckling Load - (Measured in Kilonewton) - Critical Buckling Load is defined as the greatest load that will not cause lateral deflection.
STEP 1: Convert Input(s) to Base Unit
Eccentricity of Load: 2.5 Millimeter --> 2.5 Millimeter No Conversion Required
Axial Load: 9.99 Kilonewton --> 9.99 Kilonewton No Conversion Required
Critical Buckling Load: 53 Kilonewton --> 53 Kilonewton No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
δ = (4*eload*P/Pc)/(pi*(1-P/Pc)) --> (4*2.5*9.99/53)/(pi*(1-9.99/53))
Evaluating ... ...
δ = 0.739343353400621
STEP 3: Convert Result to Output's Unit
0.000739343353400621 Meter -->0.739343353400621 Millimeter (Check conversion here)
FINAL ANSWER
0.739343353400621 0.739343 Millimeter <-- Deflection in Eccentric Loading
(Calculation completed in 00.004 seconds)

Credits

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Osmania University (OU), Hyderabad
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18 Eccentric Loading Calculators

Cross-Sectional Area given Total Stress is where Load doesn't lie on Plane
Go Cross-Sectional Area = Axial Load/(Total Stress-(((Eccentricity with respect to Principal Axis YY*Axial Load*Distance from YY to Outermost Fiber)/(Moment of Inertia about Y-Axis))+((Eccentricity with respect to Principal Axis XX*Axial Load*Distance from XX to Outermost Fiber)/(Moment of Inertia about X-Axis))))
Distance from YY to outermost fiber given Total Stress where Load doesn't lie on Plane
Go Distance from YY to Outermost Fiber = (Total Stress-((Axial Load/Cross-Sectional Area)+((Eccentricity with respect to Principal Axis XX*Axial Load*Distance from XX to Outermost Fiber)/(Moment of Inertia about X-Axis))))*Moment of Inertia about Y-Axis/(Eccentricity with respect to Principal Axis YY*Axial Load)
Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane
Go Distance from XX to Outermost Fiber = ((Total Stress-(Axial Load/Cross-Sectional Area)-((Eccentricity with respect to Principal Axis YY*Axial Load*Distance from YY to Outermost Fiber)/(Moment of Inertia about Y-Axis)))*Moment of Inertia about X-Axis)/(Axial Load*Eccentricity with respect to Principal Axis XX)
Eccentricity w.r.t axis XX given Total Stress where Load doesn't lie on Plane
Go Eccentricity with respect to Principal Axis XX = ((Total Stress-(Axial Load/Cross-Sectional Area)-((Eccentricity with respect to Principal Axis YY*Axial Load*Distance from YY to Outermost Fiber)/(Moment of Inertia about Y-Axis)))*Moment of Inertia about X-Axis)/(Axial Load*Distance from XX to Outermost Fiber)
Total Stress in Eccentric Loading when Load doesn't lie on Plane
Go Total Stress = (Axial Load/Cross-Sectional Area)+((Eccentricity with respect to Principal Axis YY*Axial Load*Distance from YY to Outermost Fiber)/(Moment of Inertia about Y-Axis))+((Eccentricity with respect to Principal Axis XX*Axial Load*Distance from XX to Outermost Fiber)/(Moment of Inertia about X-Axis))
Moment of Inertia about XX given Total Stress where Load doesn't lie on Plane
Go Moment of Inertia about X-Axis = (Eccentricity with respect to Principal Axis XX*Axial Load*Distance from XX to Outermost Fiber)/(Total Stress-((Axial Load/Cross-Sectional Area)+((Eccentricity with respect to Principal Axis YY*Axial Load*Distance from YY to Outermost Fiber)/Moment of Inertia about Y-Axis)))
Moment of Inertia about YY given Total Stress where Load doesn't lie on Plane
Go Moment of Inertia about Y-Axis = (Eccentricity with respect to Principal Axis YY*Axial Load*Distance from YY to Outermost Fiber)/(Total Stress-((Axial Load/Cross-Sectional Area)+((Eccentricity with respect to Principal Axis XX*Axial Load*Distance from XX to Outermost Fiber)/Moment of Inertia about X-Axis)))
Eccentricity wrt axis YY given Total Stress where Load doesn't lie on Plane
Go Eccentricity with respect to Principal Axis YY = ((Total Stress-(Axial Load/Cross-Sectional Area)-(Eccentricity with respect to Principal Axis XX*Axial Load*Distance from XX to Outermost Fiber)/(Moment of Inertia about X-Axis))*Moment of Inertia about Y-Axis)/(Axial Load*Distance from YY to Outermost Fiber)
Moment of Inertia of Cross-Section given Total Unit Stress in Eccentric Loading
Go Moment of Inertia about Neutral Axis = (Axial Load*Outermost Fiber Distance*Distance from Load applied)/(Total Unit Stress-(Axial Load/Cross-Sectional Area))
Cross-Sectional Area given Total Unit Stress in Eccentric Loading
Go Cross-Sectional Area = Axial Load/(Total Unit Stress-((Axial Load*Outermost Fiber Distance*Distance from Load applied/Moment of Inertia about Neutral Axis)))
Total Unit Stress in Eccentric Loading
Go Total Unit Stress = (Axial Load/Cross-Sectional Area)+(Axial Load*Outermost Fiber Distance*Distance from Load applied/Moment of Inertia about Neutral Axis)
Critical Buckling Load given Deflection in Eccentric Loading
Go Critical Buckling Load = (Axial Load*(4*Eccentricity of Load+pi*Deflection in Eccentric Loading))/(Deflection in Eccentric Loading*pi)
Eccentricity given Deflection in Eccentric Loading
Go Eccentricity of Load = (pi*(1-Axial Load/Critical Buckling Load))*Deflection in Eccentric Loading/(4*Axial Load/Critical Buckling Load)
Deflection in Eccentric Loading
Go Deflection in Eccentric Loading = (4*Eccentricity of Load*Axial Load/Critical Buckling Load)/(pi*(1-Axial Load/Critical Buckling Load))
Load for Deflection in Eccentric Loading
Go Axial Load = (Critical Buckling Load*Deflection in Eccentric Loading*pi)/(4*Eccentricity of Load+pi*Deflection in Eccentric Loading)
Radius of Gyration in Eccentric Loading
Go Radius of Gyration = sqrt(Moment of Inertia/Cross-Sectional Area)
Cross-Sectional Area given Radius of Gyration in Eccentric Loading
Go Cross-Sectional Area = Moment of Inertia/(Radius of Gyration^2)
Moment of Inertia given Radius of Gyration in Eccentric Loading
Go Moment of Inertia = (Radius of Gyration^2)*Cross-Sectional Area

Deflection in Eccentric Loading Formula

Deflection in Eccentric Loading = (4*Eccentricity of Load*Axial Load/Critical Buckling Load)/(pi*(1-Axial Load/Critical Buckling Load))
δ = (4*eload*P/Pc)/(pi*(1-P/Pc))

Define Eccentric loading

The eccentric load is basically defined as the load whose line of action does not pass through the axis of the column, but also a line of action of load passes through a point away from the axis of the column. In the case of eccentric loading, there will be produced direct stress as well as bending stress in the column.

How to Calculate Deflection in Eccentric Loading?

Deflection in Eccentric Loading calculator uses Deflection in Eccentric Loading = (4*Eccentricity of Load*Axial Load/Critical Buckling Load)/(pi*(1-Axial Load/Critical Buckling Load)) to calculate the Deflection in Eccentric Loading, The Deflection in Eccentric Loading formula is defined as the degree to which an element of structure changes shape when a load is applied. Deflection in Eccentric Loading is denoted by δ symbol.

How to calculate Deflection in Eccentric Loading using this online calculator? To use this online calculator for Deflection in Eccentric Loading, enter Eccentricity of Load (eload), Axial Load (P) & Critical Buckling Load (Pc) and hit the calculate button. Here is how the Deflection in Eccentric Loading calculation can be explained with given input values -> 739.3434 = (4*0.0025*9990/53000)/(pi*(1-9990/53000)).

FAQ

What is Deflection in Eccentric Loading?
The Deflection in Eccentric Loading formula is defined as the degree to which an element of structure changes shape when a load is applied and is represented as δ = (4*eload*P/Pc)/(pi*(1-P/Pc)) or Deflection in Eccentric Loading = (4*Eccentricity of Load*Axial Load/Critical Buckling Load)/(pi*(1-Axial Load/Critical Buckling Load)). Eccentricity of Load is the distance from the center of gravity of the column section to the center of gravity of the applied load, Axial Load is defined as applying a force on a structure directly along an axis of the structure & Critical Buckling Load is defined as the greatest load that will not cause lateral deflection.
How to calculate Deflection in Eccentric Loading?
The Deflection in Eccentric Loading formula is defined as the degree to which an element of structure changes shape when a load is applied is calculated using Deflection in Eccentric Loading = (4*Eccentricity of Load*Axial Load/Critical Buckling Load)/(pi*(1-Axial Load/Critical Buckling Load)). To calculate Deflection in Eccentric Loading, you need Eccentricity of Load (eload), Axial Load (P) & Critical Buckling Load (Pc). With our tool, you need to enter the respective value for Eccentricity of Load, Axial Load & Critical Buckling Load and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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