# 7.4 The Elementary Beam Theory

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1 7.4 The Elementary Beam Theory In this section, problems involving long and slender beams are addressed. s with pressure vessels, the geometry of the beam, and the specific type of loading which will be considered, allows for approimations to be made to the full three-dimensional linear elastic stress-strain relations. The beam theory is used in the design and analysis of a wide range of structures, from buildings to bridges to the load-bearing bones of the human body The Beam The term beam has a very specific meaning in engineering mechanics: it is a component that is designed to support transverse loads, that is, loads that act perpendicular to the longitudinal ais of the beam, Fig The beam supports the load by bending only. Other mechanisms, for eample twisting of the beam, are not allowed for in this theory. applied force applied pressure roller support pin support cross section Figure 7.4.: supported beam loaded by a force and a distribution of pressure It is convenient to show a two-dimensional cross-section of the three-dimensional beam together with the beam cross section, as in Fig The beam can be supported in various ways, for eample by roller supports or pin supports (see section..). The cross section of this beam happens to be rectangular but it can be any of many possible shapes. It will assumed that the beam has a longitudinal plane of symmetry, with the cross section symmetric about this plane, as shown in Fig Further, it will be assumed that the loading and supports are also symmetric about this plane. With these conditions, the beam has no tendency to twist and will undergo bending only. longitudinal plane of symmetry Figure 7.4.: The longitudinal plane of symmetry of a beam certain very special cases, where there is not a plane of symmetry for geometry and/or loading, can lead also to bending with no twist, but these are not considered here 94

2 Imagine now that the beam consists of many fibres aligned longitudinally, as in Fig When the beam is bent by the action of downward transverse loads, the fibres near the top of the beam contract in length whereas the fibres near the bottom of the beam etend. Somewhere in between, there will be a plane where the fibres do not change length. This is called the neutral surface. The intersection of the longitudinal plane of symmetry and the neutral surface is called the ais of the beam, and the deformed ais is called the deflection curve. y fibres contracting z neutral surface fibres etending Figure 7.4.: the neutral surface of a beam conventional coordinate system is attached to the beam in Fig The ais coincides with the (longitudinal) ais of the beam, the y ais is in the transverse direction and the longitudinal plane of symmetry is in the y plane, also called the plane of bending oments and Forces in a Beam Normal and shear stresses act over any cross section of a beam, as shown in Fig The normal and shear stresses acting on each side of the cross section are equal and opposite for equilibrium, Fig b. The normal stresses will vary over a section during bending. Referring again to Fig. 7.4., over one part of the section the stress will be tensile, leading to etension of material fibres, whereas over the other part the stresses will be compressive, leading to contraction of material fibres. This distribution of normal stress results in a moment acting on the section, as illustrated in Fig c. Similarly, shear stresses act over a section and these result in a shear force. The beams of Fig and Fig show the normal stress and deflection one would epect when a beam bends downward. There are situations when parts of a beam bend upwards, and in these cases the signs of the normal stresses will be opposite to those shown in Fig However, the moments (and shear forces) shown in Fig will be regarded as positive. This sign convention to be used is shown in Fig

3 (a) cross-section in beam (b) (c) Figure 7.4.4: stresses and moments acting over a cross-section of a beam; (a) a crosssection, (b) normal and shear stresses acting over the cross-section, (c) the moment and shear force resultant of the normal and shear stresses positive bending positive shearing ( a) ( b) (c) Figure 7.4.5: sign convention for moments and shear forces Note that the sign convention for the shear stress conventionally used the beam theory conflicts with the sign convention for shear stress used in the rest of mechanics, introduced in Chapter. This is shown in Fig y echanics (in general) Beam Theory Figure 7.4.6: sign convention for shear stress in beam theory The moments and forces acting within a beam can in many simple problems be evaluated from equilibrium considerations alone. Some eamples are given net. 96

4 Eample Consider the simply supported beam in Fig From the loading, one would epect the beam to deflect something like as indicated by the deflection curve drawn. The reaction at the roller support, end, and the vertical reaction at the pin support, end B, can be evaluated from the equations of equilibrium, Eqns...: R y P /, R P / (7.4.) By l / P deflection curve B l Ry RBy Figure 7.4.7: a simply supported beam The moments and forces acting within the beam can be evaluated by taking free-body diagrams of sections of the beam. There are clearly two distinct regions in this beam, to the left and right of the load. Fig a shows an arbitrary portion of beam representing the left-hand side. coordinate system has been introduced, with measured from. n unknown moment and shear force act at the end. positive moment and force have been drawn in Fig a. From the equilibrium equations, one finds that the shear force is constant but that the moment varies linearly along the beam: P P l, ( ) (7.4.) l / P P / P / ( a) (b) Figure 7.4.8: free body diagrams of sections of a beam the horizontal reaction at the pin is zero since there are no applied forces in this direction; the beam theory does not consider such types of (aial) load; further, one does not have a pin at each support, since this would prevent movement in the horizontal direction which in turn would give rise to forces in the horizontal direction hence the pin at one end and the roller support at the other end the coordinate can be measured from any point in the beam; in this eample it is convenient to measure it from point 97

5 Cutting the beam to the right of the load, Fig b, leads to P, P l l ( l ) (7.4.) The shear force is negative, so acts in the direction opposite to that initially assumed in Fig b. The results of the analysis can be displayed in what are known as a shear force diagram and a bending moment diagram, Fig Note that there is a jump in the shear force at l / equal to the applied force, and in this eample the bending moment is everywhere positive. P Pl 9 P l l / l ( a) (b) Figure 7.4.9: results of analysis; (a) shear force diagram, (b) bending moment diagram Eample Fig shows a cantilever, that is, a beam supported by clamping one end (refer to Fig...8). The cantilever is loaded by a force at its mid-point and a (negative) moment at its end. 5 kn m m 4 knm Figure 7.4.: a cantilevered beam loaded by a force and moment gain, positive unknown reactions and are considered at the support. From the equilibrium equations, one finds that 98

6 knm, 5 kn (7.4.4) s in the previous eample, there are two distinct regions along the beam, to the left and to the right of the applied concentrated force. gain, a coordinate is introduced and the beam is sectioned as in Fig The unknown moment and shear force can then be evaluated from the equilibrium equations: 5kN,, 5 knm 4 knm 6 (7.4.5) m 5kN 5 5 ( a) (b) Figure 7.4.: free body diagrams of sections of a beam The results are summarized in the shear force and bending moment diagrams of Fig m m ( a) (b) Figure 7.4.: results of analysis; (a) shear force diagram, (b) bending moment diagram In this eample the beam eperiences negative bending moment over most of its length. Eample 99

7 Fig shows a simply supported beam subjected to a distributed load (force per unit length). The load is uniformly distributed over half the length of the beam, with a triangular distribution over the remainder. 4 N/m 6m B 6m C Figure 7.4.: a beam subjected to a distributed load The unknown reactions can be determined by replacing the distributed load with statically equivalent forces as in Fig (see..). The equilibrium equations then give R N, R 4 N (7.4.6) C 4 N N m m m 4m R RC Figure 7.4.4: equivalent forces acting on the beam of Fig Referring again to Fig. 7.4., there are two distinct regions in the beam, that under the uniform load and that under the triangular distribution of load. The first case is considered in Fig N/m Figure 7.4.5: free body diagram of a section of a beam The equilibrium equations give 4, 6 (7.4.7)

8 The region beneath the triangular distribution is shown in Fig Two possible approaches are illustrated: in Fig a, the free body diagram consists of the complete length of beam to the left of the cross-section under consideration; in Fig b, only the portion to the right is considered, with distance measured from the right hand end, as. The problem is easier to solve using the second option; from Fig b then, with the equilibrium equations, one finds that 4 ( ) /, 4( ) ( ) / 9 6 (7.4.8) 4 Figure 7.4.6: free body diagrams of sections of a beam The results are summarized in the shear force and bending moment diagrams of Fig ( a) (b) 6 4 6m 6m 6m 6m ( a) (b) Figure 7.4.7: results of analysis; (a) shear force diagram, (b) bending moment diagram 7.4. The Relationship between oads, Shear Forces and Bending oments Relationships between the applied loads and the internal shear force and bending moment in a beam can be established by considering a small beam element, of width, and

9 subjected to a distributed load p () which varies along the section of beam, and which is positive upward, Fig () p() () ( ) p ( ) Figure 7.4.8: forces and moments acting on a small element of beam t the left-hand end of the free body, at position, the shear force, moment and distributed load have values ( ), () and p () respectively. On the right-hand end, at position, their values are slightly different: ( ), ( ) and p( ). Since the element is very small, the distributed load, even if it is varying, can be approimated by a linear variation over the element. The distributed load can therefore be considered to be a uniform distribution of intensity p () over the length together with a triangular distribution, at and p say, a small value, at. Equilibrium of vertical forces then gives ( ) p( ) p ( ) ( ) ( ) p( ) p (7.4.9) Now let the size of the element decrease towards zero. The left-hand side of Eqn is then the definition of the derivative, and the second term on the right-hand side tends to zero, so d p() (7.4.) d This relation can be seen to hold in Eqn and Fig a, where the shear force over 6 has a slope of 4 and the pressure distribution is uniform, of intensity 4 N/m. Similarly, over 6, the pressure decreases linearly and so does the slope in the shear force diagram, reaching zero slope at the end of the beam. It also follows from 7.4. that the change in shear along a beam is equal to the area under the distributed load curve: p( ) d ) (7.4.) (

10 Consider now moment equilibrium, by taking moments about the point in Fig : ( ) ( ) ( ) p( ) p ( ) ( ) ( ) p( ) p 6 (7.4.) gain, as the size of the element decreases towards zero, the left-hand side becomes a derivative and the second and third terms on the right-hand side tend to zero, so that d () (7.4.) d This relation can be seen to hold in Eqns , and It also follows from Eqn that the change in moment along a beam is equal to the area under the shear force curve: ( ) d ) (7.4.4) ( Deformation and Fleural Stresses in Beams The moment at any given cross-section of a beam is due to a distribution of normal stress, or fleural stress (or bending stress) across the section (see Fig ). s mentioned, the stresses to one side of the neutral ais are tensile whereas on the other side of the neutral ais they are compressive. To determine the distribution of normal stress over the section, one must determine the precise location of the neutral ais, and to do this one must consider the deformation of the beam. part from the assumption of there being a longitudinal plane of symmetry and a neutral ais along which material fibres do not etend, the following two assumptions will be made concerning the deformation of a beam:. Cross-sections which are plane and are perpendicular to the ais of the undeformed beam remain plane and remain perpendicular to the deflection curve of the deformed beam. In short: plane sections remain plane. This is illustrated in Fig It will be seen later that this assumption is a valid one provided the beam is sufficiently long and slender.. Deformation in the vertical direction, i.e. the transverse strain yy, may be neglected in deriving an epression for the longitudinal strain. This assumption is summarised in the deformation shown in Fig. 7.4., which shows an element of length l and height h undergoing transverse and longitudinal strain.

11 y plane in deformed beam remains perpendicular to the deflection curve deflection curve Figure 7.4.9: plane sections remain plane in the elementary beam theory dh h dl dh, yy l h l dl Figure 7.4.: transverse strain is neglected in the elementary beam theory With these assumptions, consider now the element of beam shown in Fig Here, two material fibres ab and pq, of length in the undeformed beam, deform to a b and p q. The deflection curve has a radius of curvature R. The above two assumptions imply that, referring to the figure: p ab abq / (assumption ) ap ap, bq bq (assumption ) (7.4.5) Since the fibre ab is on the neutral ais, by definition a b pq, a distance y from the neutral ais, etends in length from longitudinal strain for this fibre is ab. However the fibre to length. The ( R y) R R y R (7.4.6) s one would epect, this relation implies that a small R (large curvature) is related to a large strain and a large R (small curvature) is related to a small strain. Further, for y (above the neutral ais), the strain is negative, whereas if y (below the neutral ais), the strain is positive 4, and the variation across the cross-section is linear. 4 this is under the assumption that R is positive, which means that the beam is concave up; a negative R implies that the centre of curvature is below the beam 4

12 R p a b q y p a q b y before after Figure 7.4.: deformation of material fibres in an element of beam To relate this deformation to the stresses arising in the beam, it is necessary to postulate the stress-strain law for the material out of which the beam is made. Here, it is assumed that the beam is isotropic linear elastic 5. The beam is a three-dimensional object, and so will in general eperience a fairly comple three-dimensional stress state. We will show in what follows that a simple onedimensional approimation, E, whilst disregarding all other stresses and strains, will be sufficiently accurate for our purposes. Since there are no forces acting in the z direction, the beam is in a state of plane stress, and the stress-strain equations are (see Eqns. 6..) yy zz y yy E yy E yy E y, E z yz (7.4.7) Yet another assumption is now made, that the transverse normal stresses, neglected in comparison with the fleural stresses yy, may be. This is similar to the above assumption # concerning the deformation, where the transverse normal strain was neglected in comparison with the longitudinal strain. It might seem strange at first that the transverse stress is neglected, since all loads are in the transverse direction. However, 5 the beam theory can be etended to incorporate more comple material models (constitutive equations) 5

13 just as the tangential stresses are much larger than the radial stresses in the pressure vessel, it is found that the longitudinal stresses in a beam are very much greater than the transverse stresses. With this assumption, the first of Eqn reduces to a onedimensional equation: E (7.4.8) / and, from Eqn , dropping the subscripts on, E y (7.4.9) R Finally, the resultant force of the normal stress distribution over the cross-section must be zero, and the resultant moment of the distribution is, leading to the conditions d E R yd E R yd y d y y d (7.4.) and the integration is over the complete cross-sectional area. The minus sign in the second of these equations arises because a positive moment and a positive y imply a compressive (negative) stress (see Fig ). The quantity y d is the first moment of area about the neutral ais, and is equal to y, where y is the centroid of the section (see, for eample,..). Note that the horizontal component ( in-out of the page ) of the centroid will always be at the centre of the beam due to the symmetry of the beam about the plane of bending. Since the first moment of area is zero, it follows that y : the neutral ais passes through the centroid of the cross-section. The quantity y d is called the second moment of area or the moment of inertia about the neutral ais, and is denoted by the symbol I. It follows that the fleural stress is related to the moment through y Fleural stress in a beam (7.4.) I This is one of the most famous and useful formulas in mechanics. The oment of Inertia The moment of inertia depends on the shape of a beam s cross-section. Consider the important case of a rectangular cross section. Before determining the moment of inertia one must locate the centroid (neutral ais). Due to symmetry, the neutral ais runs 6

14 through the centre of the cross-section. To evaluate I for a rectangle of height h and width b, consider a small strip of height dy at location y, Fig Then I h / bh y d b y dy h / (7.4.) This relation shows that the taller the cross-section, the larger the moment of inertia, something which holds generally for I. Further, the larger is I, the smaller is the fleural stress, which is always desirable. h y dy y centroid b Figure 7.4.: Evaluation of the moment of inertia for a rectangular cross-section For a circular cross-section with radius R, consider Fig The moment of inertia is then R 4 R (7.4.) I y d r sin drd 4 r y d rdrd Figure 7..: oment of inertia for a circular cross-section Eample Consider the beam shown in Fig It is loaded symmetrically by two concentrated forces each of magnitude N and has a circular cross-section of radius mm. The reactions at the two supports are found to be N. Sectioning the beam to the left of the forces, and then to the right of the first force, one finds that,, l/ (7.4.4) 7

15 where l is the length of the beam. 5 mm 5 mm r mm Figure 7.4.4: a loaded beam with circular cross-section The maimum tensile stress is then ma ( yma ) 5r ma.8 Pa (7.4.5) 4 I r / 4 and occurs at all sections between the two loads (at the base of the beam) Shear Stresses in Beams In the derivation of the fleural stress formula, Eqn. 7.4., it was assumed that plane sections remain plane. This implies that there is no shear strain and, for an isotropic elastic material, no shear stress, as indicated in Fig before deformation shear stresses would produce an angle change Figure 7.4.5: a section of beam before and after deformation This fact will now be ignored, and an epression for the shear stress within a beam will be developed. It is implicitly assumed that this shear stress has little effect on the (calculation of the) fleural stress. s in Fig , consider the equilibrium of a thin section of beam, as shown in Fig The beam has rectangular cross-section (although the theory developed here is strictly for rectangular cross sections only, it can be used to give approimate shear stress values in any beam with a plane of symmetry). Consider the equilibrium of a section of this section, at the upper surface of the beam, shown hatched in Fig The stresses acting on this section are as shown. gain, the normal stress is compressive at the surface, consistent with the sign convention for a positive moment. Note that there are no shear stresses acting at the surface there may be distributed normal loads or forces acting at the surface but, for clarity, these are not shown, and they are not necessary for the following calculation. 8

16 From equilibrium of forces in the horizontal direction of the surface section: d d b (7.4.6) The third term on the left here assumes that the shear stress is uniform over the section this is similar to the calculations of 7.4. for a very small section, the variation in stress is a small term and may be neglected. Using the bending stress formula, Eqn. 7.4., and, with Eqn. 7.4., as, ( ) ( ) y d I b (7.4.7) Q Shear stress in a beam (7.4.8) Ib where Q is the first moment of area y d of the surface section of the cross-section. h b () () ( ) ( ) Figure 7.4.6: stresses and forces acting on a small section of material at the surface of a beam s mentioned, this formula can be used as an approimation of the shear stress in a beam of arbitrary cross-section, in which case b can be regarded as the depth of the beam at that section. For the rectangular beam, one has Q b h / y b h ydy 4 y (7.4.9) so that 9

17 6 h y (7.4.) bh 4 The maimum shear stress in the cross-section arises at the neutral surface: ma (7.4.) bh and the shear stress dies away towards the upper and lower surfaces. Note that the average shear stress over the cross-section is / and the maimum shear stress is 5% of this value. Finally, since the shear stress on a vertical cross-section has been evaluated, the shear stress on a longitudinal section has been evaluated, since the shear stresses on all four sides of an element are the same, as in Fig Eample Consider the simply supported beam loaded by a concentrated force shown in Fig The cross-section is rectangular with height mm and width 5 mm. The reactions at the supports are 5 kn and 5 kn. To the left of the load, one has 5kN and 5 knm. To the right of the load, one has 5kN and 5 knm. The maimum shear stress will occur along the neutral ais and will clearly occur where is largest, so anywhere to the right of the load: ma ma 4.5 Pa (7.4.).5m kn.5m Figure 7.4.7: a simply supported beam s an eample of general shear stress evaluation, the shear stress at a point 5 mm below the top surface and m in from the left-hand end is, from Eqn 7.4.,.5Pa. The shear stresses acting on an element at this location are shown in Fig

18 m.5 Pa Figure 7.4.8: shear stresses acting at a point in the beam pproimate nature of the beam theory The beam theory is only an approimate theory, with a number of simplifications made to the full equations of elasticity. more advanced (and eact) mechanics treatment of the beam problem would not make any assumptions regarding plane sections remaining plane, etc. The accuracy of the beam theory can be eplored by comparing the beam theory results with the results of the more eact theory. When a beam is in pure bending, that is when the shear force is everywhere zero, the full elasticity solution shows that plane sections do actually remain plane and the beam theory is eact. For more comple loadings, plane sections do actually deform. For eample, it can be shown that the initially plane sections of a cantilever subjected to an end force, Fig , do not remain plane. Nevertheless, the beam theory prediction for normal and shear stress is eact in this simple case. deformed section not plane Figure 7.4.9: a cantilevered beam loaded by a force and moment Consider net a cantilevered beam of length l and rectangular cross section, height h and width b, subjected to a uniformly distributed load p. With measured from the cantilevered end, the shear force and moment are given by p( l ) and ( pl / ) / l ( / l ). The shear stress is 6 p h y l bh (7.4.) 4 and the fleural stresses at the cantilevered end, at the upper surface, are p 4 l h (7.4.4)

19 The solution for shear stress, Eqn 7.4., turns out to be eact; however, the eact solution corresponding to Eqn is p 4 l h 5 (7.4.5) It can be seen that the beam theory is a good approimation for the case when large, in which case the term /5 is negligible. l / h is Following this type of analysis, a general rule of thumb is this: for most configurations, the elementary beam theory formulae for fleural stress and transverse shear stress are accurate to within about % for beams whose length-to-height ratio is greater than about Beam Deflection Consider the deflection curve of a beam. The displacement of the neutral ais is denoted by v, positive upwards, as in Fig The slope at any point is then given by the first derivative, dv / d. For any type of material, provided the slope of the deflection curve is small, it can be shown that the radius of curvature R is related to the second derivative d v / d through (see the ppendi to this section, 7.4.) d v d R (7.4.6) and for this reason d v / d is called the curvature of the beam. Using Eqn , Ey / R, and the fleural stress epression, Eqn. 7.4., y / I, one has the moment-curvature equation d v ( ) EI moment-curvature equation (7.4.7) d v Figure 7.4.: the deflection of a beam With the moment known, this differential equation can be integrated twice to obtain the deflection. Boundary conditions must be supplied to obtain constants of integration.

20 Eample Consider the cantilevered beam of length shown in Fig. 7.4., subjected to an endforce F and end-moment. The moment is found to be ( ) F( ), with measured from the clamped end. The moment-curvature equation is then EI d v ( F ) d dv EI ( F d EIv ( F F ) F C ) F C C 6 (7.4.8) The boundary conditions are that the displacement and slope are both zero at the clamped end, from which the two constant of integration can be obtained: v() v() C C (7.4.9) F Figure 7.4.: a cantilevered beam loaded by an end-force and moment The slope and deflection are therefore dv v ( F ) F, ( F ) F EI 6 d EI (7.4.4) The maimum deflection occurs at the end, where v ( ) F EI (7.4.4) The term EI in Eqns is called the fleural rigidity, since it is a measure of the resistance of the beam to deflection. Eample Consider the simply supported beam of length shown in Fig. 7.4., subjected to a uniformly distributed load p over half its length. In this case, the moment is given by

21 p p 8 ( ) p( ) 8 p (7.4.4) / / Figure 7.4.: a simply supported beam subjected to a uniformly distributed load over half its length It is necessary to apply the moment-curvature equation to each of the two regions / and / separately, since the epressions for the moment in these regions differ. Thus there will be four constants of integration: d v EI p p d 8 dv EI p p C d EIv p p C C 48 4 d v EI p p d 8 8 dv EI p p d 8 6 EIv p p 6 48 D D D (7.4.4) The boundary conditions are: (i) no deflection at roller support, v ( ), from which one finds that C, and (ii) no deflection at pin support, v ( ), from which one finds that D p 4 / 4 D. The other two necessary conditions are the continuity conditions where the two solutions meet. These are that (i) the deflection of both solutions agree at / and (ii) the slope of both solutions agree at /. Using these conditions, one finds that C 9 p 7 p, C (7.4.44) so that 4 w EI v 4 w EI 4 (7.4.45) 4

22 The deflection is shown in Fig Note that the maimum deflection occurs in / ; it can be located by setting dv / d there and solving. / EI v 4 p Figure 7.4.: deflection of a beam Statically Indeterminate Beams Consider the beam shown in Fig It is cantilevered at one end and supported by a roller at its other end. moment is applied at its centre. There are three unknown reactions in this problem, the reaction force at the roller and the reaction force and moment at the built-in end. There are only two equilibrium equations with which to determine these three unknowns and so it is not possible to solve the problem from equilibrium considerations alone. The beam is therefore statically indeterminate (see the end of section..). Figure 7.4.4: a cantilevered beam supported also by a roller ore eamples of statically indeterminate beam problems are shown in Fig To solve such problems, one must consider the deformation of the beam. The following eample illustrates how this can be achieved. 5

23 Figure 7.4.5: eamples of statically indeterminate beams Eample Consider the beam of length shown in Fig , cantilevered at end and supported by a roller at end B. moment is applied at B. B Figure 7.4.6: a statically indeterminate beam The moment along the beam can be epressed in terms of the unknown reaction force at end B: ( ) RB ( ). s before, one can integrate the moment-curvature equation: d v EI R d dv EI d EIv B ( ) R B 6 RB RB C C R B C (7.4.46) There are three boundary conditions, two to determine the constants of integration and one can be used to determine the unknown reaction R B. The boundary conditions are (i) v ( ) C, (ii) dv / d() C and (iii) v ( ) from which one finds that R B /. The slope and deflection are therefore 6

24 v dv d B 4EI B 4EI (7.4.47) One can now return to the equilibrium equations to find the remaining reactions acting on the beam, which are R RB and RB The Three-point Bending Test The -point bending test is a very useful eperimental procedure. It is used to gather data on materials which are subjected to bending in service. It can also be used to get the Young s odulus of a material for which it might be more difficult to get via a tension or other test. mouse bone is shown in the standard -point bend test apparatus in Fig a. The idealised beam theory model of this test is shown in Fig b. The central load is F, so the reactions at the supports are F /. The moment is zero at the supports, varying linearly to a maimum F /4 at the centre. F / / v ma (a) (b) Figure 7.4.7: the three-point bend test; (a) a mouse bone specimen, (b) idealised model The maimum fleural stress then occurs at the outer fibres at the centre of the beam: for a circular cross-section, ma F / R. Integrating the moment-curvature equation, and using the fact that the deflection is zero at the supports and, from symmetry, the slope 4 is zero at the centre, the maimum deflection is seen to be vma F / R E. If one plots the load F against the deflection v ma, one will see a straight line (initially, before the elastic limit is reached); let the slope of this line be Ê. The Young s modulus can then be evaluated through E Eˆ (7.4.48) 4 R 7

25 With E, the maimum strain is ma F / ER Rvma /. By carrying the test on beyond the elastic limit, the strength of the material at failure can be determined Problems. The simply supported beam shown below carries a vertical load that increases uniformly from zero at the left end to a maimum value of 9 kn/m at the right end. Draw the shearing force and bending moment diagrams 9kN/m 6 m. The beam shown below is imply supported at two points and overhangs the supports at each end. It is subjected to a uniformly distributed load of 4 kn/m as well as a couple of magnitude 8 kn m applied to the centre. Draw the shearing force and bending moment diagrams 8kN m 4 kn/m m m m m. Evaluate the centroid of the beam cross-section shown below (all measurements in mm) Determine the maimum tensile and compressive stresses in the following beam (it has a rectangular cross-section with height 75 mm and depth 5 mm) 8

26 kn 5 m 5. Consider the cantilever beam shown below. Determine the maimum shearing stress in the beam and determine the shearing stress 5 mm from the top surface of the beam at a section adjacent to the supporting wall. The cross-section is the T shape shown, for which I 4 6 mm 4. [note: use the shear stress formula derived for rectangular cross-sections as mentioned above, in this formula, b is the thickness of the beam at the point where the shear stress is being evaluated] 5 kn 5 5 m 5 6. Obtain an epression for the maimum deflection of the simply supported beam shown here, subject to a uniformly distributed load of w N/m. w N/m 7. Determine the equation of the deflection curve for the cantilever beam loaded by a concentrated force P as shown below. a P 8. Determine the reactions for the following uniformly loaded beam clamped at both ends. 9

27 w N/m 7.4. ppendi to 7.4 Curvature of the deflection curve Consider a deflection curve with deflection v () and radius of curvature R (), as shown in the figure below. Here, deflection is the transverse displacement (in the y direction) of the points that lie along the ais of the beam. relationship between v () and R () is derived in what follows. y, v( ) R() v() First, consider a curve (arc) s. The tangent to some point p makes an angle with the ais, as shown below. s one move along the arc, changes. y p ds dy d Define the curvature of the curve to be the rate at which increases relative to s, d ds Thus if the curve is very curved, is changing rapidly as one moves along the curve (as one increase s) and the curvature will be large.

28 From the above figure, so that tan ( d) ( dy) dy ds, ( dy / d), d d d d d d d arctan dy / d ds d ds d d y / d dy / d / d ds dy / d d y d d ds Finally, it will be shown that the curvature is simply the reciprocal of the radius of curvature. Draw a circle to the point p with radius R. rbitrarily measure the arc length s from the point c, which is a point on the circle such that cop. Then arc length s R, so that d ds R o c R p o d R ds d Thus R d v d dv d If one assumes now that the slopes of the deflection curve are small, then dv / d and R d v d Images used:.

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