Q: In a beam, if the shear force at a given section is zero, what does this imply about the bending moment at that section?

Introduction / Context: Shear force V(x) and bending moment M(x) are linked by calculus. Identifying where V(x) = 0 helps locate extrema of M(x), which is critical for design because maximum moment controls required section modulus. Given Data / Assumptions: V(x) = dM/dx. Beam is smooth and loading is well-behaved so derivatives exist. Concept / Approach: If V(x) = 0 at a section, then dM/dx = 0 there, meaning M(x) has a stationary value (extremum). In most practical beam problems, this stationary value corresponds to a maximum (occasionally a minimum or point of inflection depending on load distribution). Step-by-Step Solution: Start from dM/dx = V.Set V = 0 → dM/dx = 0 → M is extremal at that section.Under common downward loading, the stationary point between supports is typically the maximum positive bending moment. Verification / Alternative check: Second derivative test: d²M/dx² = dV/dx = -w(x). For downward w(x) > 0, the stationary point is a local maximum of M. Why Other Options Are Wrong: Zero: requires a specific boundary condition, not implied by V = 0. Minimum or average: possible in special cases, but the standard implication in loaded spans is a maximum. Common Pitfalls: Forgetting the sign convention connecting w, V, and M. Final Answer: maximum

Question 1

For a hollow circular shaft with internal-to-external diameter ratio n = d_i / d_o, what is the ratio of the weight of the hollow shaft to that of a solid shaft of the same torsional strength (same allowable shear stress)?

Accepted Answer

Introduction / Context: Weight efficiency comparisons between solid and hollow shafts are common in machine design. For equal torsional strength (same maximum shear stress), we compare the required sizes and then the cross-sectional areas (and hence weights) of the two shafts. Given Data / Assumptions: Hollow shaft: outside diameter d_o, inside diameter d_i, with n = d_i/d_o. Solid shaft: diameter d_s provides the same torsional strength. Same allowable shear stress and material density for both shafts. Concept / Approach: Torsional strength ∝ polar section modulus Z_p. For a circle:Z_p(solid) = (π/16) * d_s^3Z_p(hollow) = (π/16) * (d_o^4 - d_i^4) / d_oEquate strengths to relate d_s and d_o, then form the weight ratio using areas. Step-by-Step Solution: Equal strength → (d_o^4 - d_i^4)/d_o = d_s^3.Put d_i = n d_o → d_s = d_o * (1 - n^4)^(1/3).Areas (∝ weight): A_h = (π/4)(d_o^2 - d_i^2) = (π/4)d_o^2(1 - n^2).A_s = (π/4)d_s^2 = (π/4)d_o^2 (1 - n^4)^{2/3}.Weight ratio = A_h / A_s = (1 - n^2) / (1 - n^4)^(2/3). Verification / Alternative check: Boundary checks: n = 0 (solid) → ratio 1; n → 1 (very thin tube) → ratio → 0, both physically consistent. Why Other Options Are Wrong: Other expressions do not follow from equating Z_p and simplifying areas; they fail dimensional and limit checks. Common Pitfalls: Using J instead of Z_p or forgetting the d in the denominator for hollow Z_p. Final Answer: (1 - n^2) / (1 - n^4)^(2/3)

Question 2

A simply supported rectangular beam 10 cm × 18 cm with span 400 cm carries a uniformly distributed load that induces a maximum bending stress of 100 kg/cm². What is the intensity of the load per metre length?

Accepted Answer

Introduction / Context: This problem links bending stress limits to allowable loading on a simply supported beam under a uniformly distributed load (UDL). It tests the use of bending stress formula with section properties and the maximum moment under UDL. Given Data / Assumptions: Section: b = 10 cm, h = 18 cm. Span: L = 400 cm (4 m). Max bending stress σ_max = 100 kg/cm². Loading: UDL of intensity w (kg/cm) along the span; simply supported. Concept / Approach: UseM_max(UDL) = w * L^2 / 8and the flexure formulaσ_max = M_max * c / Iwith c = h/2 and I = b * h^3 / 12. Step-by-Step Solution: I = b h^3 / 12 = 10 * 18^3 / 12 = 4860 cm^4.c = h/2 = 9 cm.M_max = σ_max * I / c = 100 * 4860 / 9 = 54000 kg·cm.Equate to UDL moment: w L^2 / 8 = 54000 → w = 54000 * 8 / 400^2 = 432000 / 160000 = 2.7 kg/cm.Convert to per metre: w_per_m = 2.7 * 100 = 270 kg/m. Verification / Alternative check: Back-calculate σ using w = 270 kg/m to confirm M_max and σ_max match 100 kg/cm². Why Other Options Are Wrong: 240, 250, 260, 280 kg/m do not reproduce σ_max = 100 kg/cm² for the given geometry and span. Common Pitfalls: Forgetting to convert w between kg/cm and kg/m consistently. Using c = h instead of h/2 in the flexure formula. Final Answer: 270 kg/m

Question 3

A beam of span L is pin-supported at both ends and subjected to a pure bending couple of magnitude M applied at mid-span. What is the maximum bending moment in the beam?

Accepted Answer

Introduction / Context: Beams under applied moments (couples) behave differently from beams under transverse loads. Understanding how a concentrated couple influences reactions, shear, and bending moment is key to correct analysis. Given Data / Assumptions: Simply supported (pin–pin) beam of length L. A pure couple of magnitude M applied at mid-span. Linear elastic behavior. Concept / Approach: A couple has no net force; the end reactions must form an equal and opposite couple to maintain equilibrium. Let left reaction be +R and right reaction be −R so that ΣF = 0 and the couple R*L balances M. Step-by-Step Solution: Global moment balance → R * L = M → R = M / L.Left span shear V = +R; right span shear V = −R.Bending moment for 0 < x < L/2: M(x) = R x → at x = L/2: M = (M/L)*(L/2) = M/2.Across the applied couple, internal M has a jump of magnitude M; immediately to the right of mid-span, M = M/2 − M = −M/2.Thus the maximum absolute bending moment in the beam is M/2. Verification / Alternative check: Shear is piecewise constant, so M(x) is linear on each side, peaking in magnitude at mid-span with value ±M/2. Why Other Options Are Wrong: M: would require zero reactions or fixed ends; not applicable here. M/3, ML/2: do not satisfy equilibrium with pin supports under a mid-span couple. Common Pitfalls: Assuming a couple creates zero internal moments everywhere; it induces linear M with a jump at the application point. Final Answer: M/2

Question 4

In a beam, if the shear force at a given section is zero, what does this imply about the bending moment at that section?

Accepted Answer

Introduction / Context: Shear force V(x) and bending moment M(x) are linked by calculus. Identifying where V(x) = 0 helps locate extrema of M(x), which is critical for design because maximum moment controls required section modulus. Given Data / Assumptions: V(x) = dM/dx. Beam is smooth and loading is well-behaved so derivatives exist. Concept / Approach: If V(x) = 0 at a section, then dM/dx = 0 there, meaning M(x) has a stationary value (extremum). In most practical beam problems, this stationary value corresponds to a maximum (occasionally a minimum or point of inflection depending on load distribution). Step-by-Step Solution: Start from dM/dx = V.Set V = 0 → dM/dx = 0 → M is extremal at that section.Under common downward loading, the stationary point between supports is typically the maximum positive bending moment. Verification / Alternative check: Second derivative test: d²M/dx² = dV/dx = -w(x). For downward w(x) > 0, the stationary point is a local maximum of M. Why Other Options Are Wrong: Zero: requires a specific boundary condition, not implied by V = 0. Minimum or average: possible in special cases, but the standard implication in loaded spans is a maximum. Common Pitfalls: Forgetting the sign convention connecting w, V, and M. Final Answer: maximum

Question 5

A simply supported uniform beam under a full-length uniformly distributed load is propped at mid-span to keep the level there equal to the end supports. What is the net bending moment at the centre after propping?

Accepted Answer

Introduction / Context: Propping a simply supported beam at mid-span changes internal force distribution. Using superposition and compatibility, we can determine the central reaction and the resulting bending moment at the centre. Given Data / Assumptions: Span L, UDL intensity w over entire length. Prop at mid-span enforces zero deflection at the mid-point (same level as supports). Linear elastic behavior; superposition valid. Concept / Approach: Superpose two systems: (1) simply supported beam under UDL, (2) same beam under an upward point load R_p at mid-span (the prop reaction). Choose R_p such that net mid-span deflection is zero, then compute the net central moment. Step-by-Step Solution: Mid-span deflection due to UDL: δ_w = 5 w L^4 / (384 E I).Mid-span deflection due to upward point load R_p: δ_p = R_p L^3 / (48 E I) upward.Compatibility: δ_w = δ_p → R_p = (5/8) w L.Central bending moment due to UDL alone: M_w = w L^2 / 8.Central bending moment due to R_p (upward) alone: M_p = - R_p * L / 4 = - (5/8) w L * L / 4 = - 5 w L^2 / 32.Net M_center = M_w + M_p = w L^2 / 8 - 5 w L^2 / 32 = w L^2 / 32. Verification / Alternative check: Sign and magnitude are consistent with a reduced but non-zero sagging moment at the centre after propping. Why Other Options Are Wrong: wL^2/8 is the unpropped moment; others do not follow from the compatibility-based reaction. Common Pitfalls: Mistakes in the deflection formulas or forgetting the negative sign for the upward point load contribution. Final Answer: w L^2 / 32

Question 6

Which of the following statements about welded joints is incorrect from a practical fabrication perspective?

Accepted Answer

Introduction / Context: Comparing welded and riveted (or bolted) joints is fundamental in steel construction. The modern industry largely favors welding for speed, rigidity, and aesthetics, though execution quality and inspection are crucial. Given Data / Assumptions: Shop and site welding are performed with qualified procedures. Riveting is considered a legacy method; bolting is the common alternative today. Concept / Approach: Evaluate each statement against standard practice. Welding typically reduces fabrication and erection time for equivalent strength because it avoids hole-making, multiple fasteners, and fit-up complexities associated with riveting. Step-by-Step Solution: Rigidity and finish: Welds create continuous connections with good appearance → correct statements.Effective area: In properly designed welds, the member cross-section is not perforated by holes, preserving area → correct.Strength: Full-strength groove welds can match parent metal strength with proper consumables and procedures → broadly correct as a capability statement.Time comparison: Welding usually requires less time than riveting for comparable connections, hence the claim that welding takes more time is incorrect. Verification / Alternative check: Industry codes and handbooks (e.g., steel construction manuals) emphasize welding efficiency compared to riveting. Why Other Options Are Wrong: Options a–d reflect accepted advantages/capabilities of welding; they are not incorrect in general practice. Common Pitfalls: Assuming all welds are automatically full-strength; weld design and QA/QC matter. Final Answer: Welding takes more time than riveting

Question 7

In a uniaxial tension test with yield stress σ = 300 kg/cm², what is the octahedral shear stress at yield?

Accepted Answer

Introduction / Context: Octahedral shear stress is used in energy-based yield criteria and provides a scalar shear measure derived from principal stresses. It is frequently used when discussing von Mises type theories. Given Data / Assumptions: Uniaxial tension at yield: principal stresses are σ1 = σ, σ2 = 0, σ3 = 0 with σ = 300 kg/cm². Use the standard octahedral shear stress relation consistent with many textbooks. Concept / Approach: One common expression for octahedral shear stress is:τ_oct = (1/3) * sqrt[ ( (σ1 - σ2)^2 + (σ2 - σ3)^2 + (σ3 - σ1)^2 ) ]Apply this to the uniaxial state. Step-by-Step Solution: Differences: (σ1 - σ2) = σ, (σ2 - σ3) = 0, (σ3 - σ1) = -σ.Sum of squares = σ^2 + 0 + σ^2 = 2 σ^2.τ_oct = (1/3) * sqrt(2 σ^2) = (σ √2)/3.With σ = 300 kg/cm² → τ_oct = 300 √2 / 3 = 100 √2 kg/cm². Verification / Alternative check: Relate to von Mises stress: σ_vm = sqrt( ( (σ1 - σ2)^2 + (σ2 - σ3)^2 + (σ3 - σ1)^2 ) / 2 ) = σ. Then τ_oct = σ_vm / √3 = σ/√3 ≈ 0.577σ, which differs numerically from the chosen textbook convention here; this problem’s options correspond to the (σ√2)/3 form, giving 100√2. Why Other Options Are Wrong: 150√2, 200√2, 250√2 kg/cm² do not result from substituting σ = 300 kg/cm² into the adopted formula. Common Pitfalls: Mixing different definitions of τ_oct; always align with the convention implied by the choices. Final Answer: 100√2 kg/cm²

Question 8

A solid circular shaft runs at 150 rpm and transmits a steady torque of 150 kg·m. What is the horsepower (HP) transmitted?

Accepted Answer

Introduction / Context: Power transmitted by a rotating shaft is directly related to torque and angular speed. Converting to horsepower in engineering units requires careful use of consistent unit systems. Given Data / Assumptions: Torque T = 150 kg·m (kilogram-force metre). Speed N = 150 rpm. Use metric engineering relation between torque, speed, and HP. Concept / Approach: Power P (in HP) for torque in kg·m and speed in rpm is:P_HP = (2 * π * N * T) / 4500This follows from P (kgf·m/s) = 2π N T / 60 and 1 HP = 75 kgf·m/s. Step-by-Step Solution: P_HP = (2 * π * 150 * 150) / 4500.Compute numerator: 2 * π * 22500 = 45000 π.Divide by 4500 → P_HP = 10 π. Verification / Alternative check: Convert to watts using 1 HP ≈ 735.5 W if needed; numeric value 10π HP ≈ 31.416 HP, consistent with P = τ ω. Why Other Options Are Wrong: π, π², 1/π are not consistent with the torque–speed product and HP conversion factor. Common Pitfalls: Using N in rad/s without converting units, or mixing N·m with kg·m. Final Answer: 10 π

Question 9

Steel design and detailing: What is the minimum number of rivets required to connect a member to a gusset plate so that a safe, non-rotational connection is achieved in civil/structural engineering practice?

Accepted Answer

Introduction / Context: In steel structures, members such as truss bars, bracing angles, or plates are commonly connected to a gusset plate using rivets (or bolts in modern practice). The minimum fastener count is a fundamental detailing rule because it governs the connection’s ability to resist rotation and carry axial force safely. Given Data / Assumptions: The connection is between a structural member and a gusset plate. Only riveted (or similarly behaving bolted) shear connections are considered. Connection must be safe against unintended rotation and slip under service actions. Concept / Approach: A single fastener provides a point support, which does not prevent rotation of the connected member about the fastener’s center. To prevent this free rotation and to provide a statically reliable transfer of axial force, at least two fasteners are placed with spacing. Two fasteners create a couple arm that resists rotational tendencies and improves redundancy and slip resistance. Step-by-Step Solution: Connection with 1 rivet: allows rotation about the rivet center, which is undesirable and unsafe for axial members.Connection with 2 rivets: provides a line of action with spacing, enabling resistance to rotation and ensuring a determinate transfer path.Codes and standard practice: traditional riveted/bolted detailing guides require a minimum of two fasteners for primary member-to-gusset connections. Verification / Alternative check: Review of free-body diagrams shows that a single fastener connection cannot equilibrate an axial force without allowing rotation. Two fasteners separated by a pitch distance provide moment resistance against rotation via couple action under small slips. Why Other Options Are Wrong: '1': rotationally unstable and non-redundant.'3' or '4': acceptable but not the minimum; the question asks for the minimum number. Common Pitfalls: Confusing temporary erection pins with permanent fasteners; assuming a single fastener is acceptable because the member is laterally braced elsewhere; neglecting torsional effects in truss joints. Final Answer: 2

Question 10

Deflection sensitivity: A simply supported rectangular beam carries a central point load. If the beam's width is doubled (depth unchanged), by what factor does the midspan deflection change?

Accepted Answer

Introduction / Context: Understanding how geometric changes affect beam deflection is central to structural stiffness tuning. For a simply supported beam with a central point load, deflection depends on span, material (E), and the section's second moment of area (I). This question isolates the effect of width, keeping depth constant. Given Data / Assumptions: Beam is simply supported, rectangular cross-section. Central concentrated load P acts at midspan. Material modulus E and depth d remain constant. Only width b is doubled. Concept / Approach: For a simply supported beam with a midspan point load, the maximum deflection is δ = (P * L^3) / (48 * E * I). For a rectangle, I = b * d^3 / 12 about the neutral axis. Thus, δ ∝ 1/I ∝ 1/b when depth d is unchanged. Doubling b halves δ. Step-by-Step Solution: Start: δ1 = (P * L^3) / (48 * E * (b * d^3 / 12)) = (P * L^3) / (4 * E * b * d^3).Change: b → 2b, new I = 2b * d^3 / 12, so δ2 = (P * L^3) / (4 * E * (2b) * d^3) = (1/2) * δ1.Therefore, the deflection reduces to half: factor = 1/2. Verification / Alternative check: Dimensional consistency holds. Also, from stiffness k_bending ∝ E * I / L^3, doubling b doubles I and hence doubles stiffness, which halves deflection for the same load. Why Other Options Are Wrong: '1/8': would require I to increase eightfold (e.g., doubling depth, not width).'2', '4', '8': imply deflection increases, which contradicts δ ∝ 1/b for fixed depth. Common Pitfalls: Confusing effects of width and depth; using I ∝ d^3 incorrectly with b; forgetting the 1/I dependence of deflection. Final Answer: 1/2

Question 11

Beam deflection trends: For a simply supported rectangular beam, which proportionality best characterizes how midspan deflection varies with section dimensions and span?

Accepted Answer

Introduction / Context: Qualitative proportionalities are frequently examined in structural analysis to anticipate stiffness changes without full calculations. For a simply supported beam under standard loads, deflection depends on E, span L, and the second moment of area I of the cross-section. For a rectangular section, I is highly sensitive to depth. Given Data / Assumptions: Simply supported beam, rectangular section. Linear elasticity (E constant). Comparisons concern geometric influence, not changes in load magnitude. Concept / Approach: Take the classic case of a central point load where δ ∝ L^3/(EI). For a rectangle, I = bd^3/12. Holding width b constant, δ ∝ 1/d^3. This sharp dependence makes depth the dominant stiffness driver in beams. Step-by-Step Solution: Use δ ∝ 1/I and I ∝ d^3 ⇒ δ ∝ 1/d^3.Thus, doubling depth reduces deflection by 2^3 = 8 times.Other proportionalities (to width or length) exist, but the question seeks the most characteristic statement highlighting depth sensitivity. Verification / Alternative check: For a uniformly distributed load, δ_max ∝ L^4/(E*I); the inverse cube dependence on depth remains because I still includes d^3. Why Other Options Are Wrong: 'Directly proportional to its weight': weight is not a defining variable unless using self-weight loading specifically.'Inversely proportional to its width': true if depth fixed, but the depth-cube dependence is more defining; the standard single best choice emphasizes depth.'Directly proportional to the cube of its length': only for a specific loading; generalized wording can mislead. Common Pitfalls: Assuming linear dependence on depth; ignoring that I scales with d^3 for rectangles; mixing load type effects. Final Answer: Inversely proportional to the cube of its depth

Question 12

Bending fundamentals: In an elastic, homogeneous beam under pure bending, which statement about the neutral plane (neutral axis in section) is correct?

Accepted Answer

Introduction / Context: The neutral plane (and its intersection with a section—the neutral axis) is the locus of zero longitudinal strain in bending. Identifying its location is essential for stress distribution and reinforcement detailing in beams. Given Data / Assumptions: Beam is homogeneous, isotropic, prismatic. Plane sections remain plane (Bernoulli–Euler hypothesis). Pure bending or bending-dominant behavior without significant shear warping. Concept / Approach: For homogeneous sections in pure bending, the neutral axis passes through the centroid of the section and is perpendicular to the plane of bending. This follows from the linear strain distribution and the zero resultant axial force condition, which places the NA at the centroid. Step-by-Step Solution: Zero axial resultant requires ∫σ dA = 0 with σ = E * κ * y, where y is measured from the NA.Setting the reference so that ∫y dA = 0 places the NA through the centroid by definition of centroidal axis.Thus the correct statement is that the neutral plane passes through the C.G. of the cross-section. Verification / Alternative check: For composite or non-homogeneous sections, the elastic neutral axis passes through the transformed-section centroid; for homogeneous sections it is the geometric centroid. Why Other Options Are Wrong: 'May be its centre': vague and not general; the NA is at the centroid for homogeneous sections.'Does not change during deformation': its orientation/location is fixed for a given section and bending plane, but this statement is ambiguous and not the standard defining property. Common Pitfalls: Confusing geometric centre with centroid for non-uniform sections; applying composite-section logic to homogeneous beams. Final Answer: It passes through the centroid (C.G.) of the cross-sectional area

Question 13

Strength of materials (simple bending theory): In the common beam assumptions, “the material is isotropic” means which of the following?

Accepted Answer

Introduction / Context: Classical bending theory relies on simplifying assumptions about material behavior and geometry. One key assumption is isotropy, which impacts how stress and strain relate in different directions when a beam bends. Given Data / Assumptions: Homogeneous, linearly elastic material. Plane sections remain plane and normal to the neutral axis after bending. Small deformations and a straight prismatic member. Concept / Approach: Isotropic materials have identical mechanical properties in all directions at a point. Practically, constants such as Young’s modulus E and shear modulus G are direction-independent. This ensures that the linear stress distribution from bending is valid irrespective of orientation, provided other assumptions hold. Step-by-Step Solution: State bending relation: sigma = My / I for linear elastic isotropic material.Because E is uniform and direction independent, strain compatibility leads to linear stress variation across depth.The neutral axis passes through the centroid for symmetrical sections with isotropic materials.Results such as curvature k = M / (EI) use a single E due to isotropy. Verification / Alternative check: Compare with orthotropic materials (e.g., composites); E differs by direction, violating isotropy and changing bending response. Why Other Options Are Wrong: Normal stress constant in all directions: not a definition of isotropy and not true in bending. Normal stress varies linearly: that is a bending result, not the definition of isotropy. Elastic constants vary linearly: contradicts isotropy; that would be inhomogeneity. Common Pitfalls: Equating isotropy with homogeneity; they are related but distinct—homogeneity means properties are the same at every point, isotropy that they are direction independent at a point. Final Answer: Elastic constants are the same in all directions

Question 14

Welding vs riveted joints: Compared to an equivalent riveted joint, a properly designed welded joint has what relative strength under static loading?

Accepted Answer

Introduction / Context: Permanent joints connect machine or structural elements. Riveted joints were once standard, but welding often replaces them due to weight savings, strength, and fabrication speed. Knowing the comparative strength guides design choices. Given Data / Assumptions: Joints are designed to good practice (adequate weld size, correct electrode/procedure, quality control). Static loading comparison; fatigue and inspection concerns are considered separately. Parent material properties are compatible with the weld process. Concept / Approach: Welding creates near-continuous joints that distribute load across the entire faying surface. Riveting introduces holes that reduce net section and create stress concentrations. Thus, for similar geometry and materials, a welded joint can achieve higher net static strength at lower weight. Step-by-Step Solution: Note that riveted plates have reduced net area A_net = bt − nd*t due to holes.Welded joints maintain gross area and can be sized (throat thickness) to develop parent-metal strength.Under static tension or shear, the effective capacity of a proper weld typically exceeds that of comparable riveted patterns.Result: “More” strength for welded joints under the stated conditions. Verification / Alternative check: Historical transitions in bridges/boilers/shipbuilding from rivets to welding were driven by higher strength-to-weight and lower fabrication time. Why Other Options Are Wrong: Same: ignores net-section loss in riveted joints. Less: only true if welding is defective; not an inherent limitation. Common Pitfalls: Confusing static strength with fatigue performance; weld toes can be fatigue-critical if not designed properly. Final Answer: More

Question 15

Mohr’s circle / stress transformation: A body is subjected to two mutually perpendicular normal stresses of 20 kN/m² (tension) and 10 kN/m² (compression). What is the maximum shear stress?

Accepted Answer

Introduction / Context: When plane stress involves two perpendicular normal stresses with no shear on the reference planes, principal and maximum shear stresses can be computed directly. This is a core application of Mohr’s circle and stress transformation equations. Given Data / Assumptions: Sigma_x = +20 kN/m² (tensile). Sigma_y = −10 kN/m² (compressive). Tau_xy on the reference planes = 0. Concept / Approach: For plane stress with perpendicular normal stresses: maximum shear stress tau_max equals half the difference between the principal stresses. With sigma_1 and sigma_2 as the principal stresses, tau_max = (sigma_1 − sigma_2) / 2. Here, sigma_1 = +20 and sigma_2 = −10. Step-by-Step Solution: Identify principal stresses: sigma_1 = +20, sigma_2 = −10.Compute difference: sigma_1 − sigma_2 = 20 − (−10) = 30 kN/m².Compute maximum shear: tau_max = 30 / 2 = 15 kN/m².Report the result with correct units. Verification / Alternative check: Draw Mohr’s circle: center at (sigma_avg, 0) where sigma_avg = (20 − 10)/2 = 5; radius R = 15. Tau_max equals the radius, confirming 15 kN/m². Why Other Options Are Wrong: 5 or 10 kN/m²: result from taking half the absolute values incorrectly or from using sigma_avg. 20 kN/m²: corresponds to the larger principal stress, not the shear radius. Common Pitfalls: Forgetting the sign of compressive stress; using absolute values without considering direction; mixing up average normal stress with shear magnitude. Final Answer: 15 kN/m²

Question 16

Beam bending (cantilever with end load): When a cantilever beam is loaded at its free end by a downward force, where does the maximum compressive bending stress occur at the fixed support cross-section?

Accepted Answer

Introduction / Context: Bending stress distribution in beams depends on load type and support conditions. For cantilevers, identifying the fibres in tension versus compression is key for safe design and detailing (e.g., reinforcement placement in concrete). Given Data / Assumptions: Prismatic cantilever beam fixed at one end and free at the other. Downward point load applied at the free end. Linear elastic behavior; small deflections. Concept / Approach: Under a downward end load, the cantilever deflects downward, producing a sagging curvature (concave upward). In sagging, the top fibres are in compression and bottom fibres are in tension. Bending stress magnitude at a section is sigma = My / I, largest at extreme fibres (maximum y). Step-by-Step Solution: Compute bending moment at a distance x from the free end: M(x) = Px; maximum at the fixed end where x = L.At the fixed end, extreme fibres carry the largest stress magnitude.With sagging curvature from downward loading, top fibres are compressive, bottom tensile.Therefore the maximum compressive stress is at the top fibre at the fixed support. Verification / Alternative check: Draw a qualitative bending moment diagram: a triangle from zero at free end to maximum at the fixed end; check sign conventions—sagging indicates compression at the top for a horizontal beam with downward load. Why Other Options Are Wrong: Bottom fibre: carries maximum tension, not compression. Neutral axis: zero bending stress by definition. Centre of gravity: coincides with neutral axis for symmetric sections; stress is zero there. Common Pitfalls: Confusing sign conventions for sagging/hogging; assuming the same behaviour as simply supported beams at midspan without considering boundary conditions. Final Answer: Top fibre

Question 17

Design concept: A beam of “uniform strength” is characterised by which of the following conditions along its length under a given bending moment distribution?

Accepted Answer

Introduction / Context: The idea of a “beam of uniform strength” is used to design lightweight members by varying the cross-section so that allowable stress is reached everywhere, fully utilising material while avoiding overdesign. Given Data / Assumptions: Bending stress formula applies: sigma = M*y / I. Material is linearly elastic with allowable stress sigma_allow. Geometry can vary along the length (e.g., variable depth or width). Concept / Approach: Uniform strength means the maximum fibre stress equals the allowable stress at every section. Because bending moment M varies along the span, the section modulus Z = I / y must be varied so that sigma = M / Z = constant (equal to sigma_allow). This yields tapered or cut-out sections that are lighter than prismatic beams. Step-by-Step Solution: Start from sigma = M / Z.Impose sigma = sigma_allow (constant) along the length.Conclude Z(x) = M(x) / sigma_allow: increase Z where M is high; reduce Z where M is low.Translate Z(x) into geometric dimensions (depth/width) for a chosen profile. Verification / Alternative check: For a cantilever with end load, M rises linearly to the fixed end; a triangular (tapered) depth keeping Z proportional to M provides near-uniform stress along the length. Why Other Options Are Wrong: Same cross-section: defines a prismatic beam, not uniform strength under varying moments. Same bending moment: depends on loading, not a design property of the section. Same shear stress: not the principle behind uniform strength; shear varies differently and usually governs near supports in deep webs. Common Pitfalls: Ignoring stress concentrations and local buckling when tapering; confusing section modulus with second moment of area alone. Final Answer: Same bending stress at every section

Question 18

On the standard engineering stress–strain curve for mild steel under tension, what is the nature of the stress at point D (the peak of the curve before necking begins)?

Accepted Answer

Introduction / Context: In materials testing for mechanical engineering, the tensile test produces a characteristic stress–strain curve. Recognising key points on this curve—proportional limit, yield points, ultimate tensile stress, and fracture—is essential for safe design and failure prevention. Given Data / Assumptions: A standard tensile test on a ductile (mild steel–like) specimen. Engineering stress–strain curve is considered (load divided by original area). Point D is the highest point on the curve before the final drop to fracture. Concept / Approach: The curve starts linear (Hooke’s law), then yields (upper/lower yield), then strain hardening increases stress until a maximum is reached (ultimate tensile stress). After this peak, local necking causes a reduction in load-carrying cross-section and the measured engineering stress drops until fracture. Step-by-Step Solution: Identify the linear region ending at proportional limit and elastic limit.Locate yield region (upper and lower yield points) for low-carbon steel.Observe strain hardening region leading to a peak stress value.Recognise that the highest stress reached (point D) is the ultimate tensile stress.Note the subsequent drop due to necking, ending at fracture stress. Verification / Alternative check: The ultimate tensile stress is always the maximum engineering stress recorded in the test; fracture stress is lower for ductile metals due to necking. Why Other Options Are Wrong: Yield point stress: occurs earlier, before strain hardening.Breaking stress: occurs at the end, after necking and load drop.Elastic limit: much earlier in the curve; end of purely elastic behaviour. Common Pitfalls: Confusing ultimate tensile stress with fracture stress; mixing engineering and true stress where the true stress can still rise after necking. Final Answer: Ultimate tensile stress

Question 19

Two shafts of the same material: Shaft A is solid with diameter D; Shaft B is hollow with outer diameter D and inner diameter D/2. Comparing torsional strength (torque capacity at the same allowable shear stress), the hollow shaft is what fraction o…

Accepted Answer

Introduction / Context: Torsion design often favours hollow shafts because material is more effective away from the centre. This question compares the torsional strength (torque for a given maximum shear stress) of a solid versus a hollow circular shaft with the same outer diameter and material. Given Data / Assumptions: Material and allowable shear stress are the same. Outer diameter for both shafts is D; hollow shaft has inner diameter D/2. Strength comparison is based on torque at the same maximum shear stress. Concept / Approach: For circular shafts, torsional strength T is related to polar section modulus Zp: T = τ_max * Zp. For a solid shaft, Zp_solid = (π/16) * D^3. For a hollow shaft, Zp_hollow = J/R = [(π/32) * (D^4 − d^4)] / (D/2). Step-by-Step Solution: Let d = D/2 → d^4 = (D/2)^4 = D^4 / 16.Compute J_hollow = (π/32) * (D^4 − D^4/16) = (π/32) * (15/16) * D^4.Compute Zp_hollow = J_hollow / (D/2) = (π/16) * (15/16) * D^3.Compute Zp_solid = (π/16) * D^3.Strength ratio = Zp_hollow / Zp_solid = 15/16. Verification / Alternative check: Because most torque resistance comes from outer fibres, removing the core barely reduces strength: 15/16 ≈ 0.9375, confirming high efficiency of hollow sections. Why Other Options Are Wrong: 1/16, 1/8, 1/4 drastically underestimate strength; they ignore the outer-radius dominance in torsion. Common Pitfalls: Comparing polar moments J (stiffness-related) instead of polar modulus Zp (strength-related); forgetting to divide J by outer radius for strength. Final Answer: 15/16

Question 20

Mohr’s circle interpretation: The endpoints of any diameter on Mohr’s circle represent stresses on which planes?

Accepted Answer

Introduction / Context: Mohr’s circle is a powerful graphical tool for transforming plane stresses. Correctly reading what points and diameters represent is key to finding stresses on inclined planes without laborious algebra. Given Data / Assumptions: State of plane stress is represented by a Mohr’s circle. A diameter is drawn through the circle with endpoints on the circumference. We relate these endpoints to stresses on real (physical) planes in the body. Concept / Approach: Each point on Mohr’s circle corresponds to the pair (σ_n, τ_nt) acting on some plane through a point. Two points connected by a diameter correspond to two orthogonal (mutually perpendicular) physical planes. Principal stresses are a special case where τ = 0 (points at horizontal intercepts). Step-by-Step Solution: Select any reference plane; find its stress point on Mohr’s circle.Construct the diameter through the circle’s centre to the opposite point.Interpretation: the two endpoints give (σ, τ) for two perpendicular planes in the material.Recognise that rotating the physical plane by θ rotates the Mohr’s radius by 2θ. Verification / Alternative check: Transformations show that stress components on orthogonal planes are located 180° apart on Mohr’s circle, i.e., at endpoints of a diameter. Why Other Options Are Wrong: Principal stresses only: only true at τ = 0 intercepts.Options limited to “45° planes”: too restrictive; a diameter is general. Common Pitfalls: Mistaking principal points for arbitrary diameter endpoints; forgetting the 2θ relationship between physical and Mohr rotations. Final Answer: The normal and shear stresses on two mutually perpendicular physical planes

Strength of Materials Questions