Q: A simply supported beam (length L) has bending moment M(x) = a * (x - x^3 / L^2), 0 ≤ x < L, where a is a constant. At what location is the shear force zero?

Introduction / Context: Shear force is the derivative of bending moment with respect to the beam axis. Locating where shear is zero helps identify positions of maximum or minimum bending moment and is fundamental in beam analysis. Given Data / Assumptions: M(x) = a * (x - x^3 / L^2) for 0 ≤ x < L. a is a constant, L is span. Beam is simply supported (moment at supports is zero). Concept / Approach: Shear force V(x) is given by the first derivative of the bending moment: V(x) = dM/dx. Set V(x) = 0 and solve for x within the span to find stationary points of M(x). Step-by-Step Solution: M(x) = a(x - x^3/L^2).V(x) = dM/dx = a(1 - 3x^2/L^2).Set V(x) = 0 → 1 - 3x^2/L^2 = 0.3x^2/L^2 = 1 → x^2 = L^2/3 → x = L/√3 (taking the positive root in 0 < x < L). Verification / Alternative check: Second derivative test: dV/dx = -6a x / L^2. At x = L/√3, sign of dV/dx determines whether M has max/min, consistent with beam behavior. Why Other Options Are Wrong: x = L/3 or L/2: do not satisfy V(x) = 0 for the given M(x). At supports: V at supports is generally not zero for this M(x); moreover M(x) is specified for 0 ≤ x < L. Common Pitfalls: Differentiation mistake (omitting the cubic term’s derivative factor). Assuming the zero shear location is always at mid-span; it depends on M(x). Final Answer: x = L/√3

Q: For a circular column section, the core (kern) is the region where a compressive load must act to avoid tension anywhere. What is the radius of this core expressed as a fraction of the column radius?

Introduction / Context: The kern (core) concept ensures that under axial compression with small eccentricity, no part of the section goes into tension. For different shapes, the kern size varies; for circles, it is a fixed fraction of the radius. Given Data / Assumptions: Circular cross-section with radius r. Linear elastic stress distribution. Load resultant is within kern to avoid tensile stress. Concept / Approach: For a circular section, the radius of the kern is r/4. This is derived from the eccentricity limit where the compressive stress at the farthest fiber just reaches zero under combined axial load and bending. Step-by-Step Solution: Stress at extreme fiber: σ = P/A ± M*c/I.Zero tension condition at the farthest fiber gives the limiting eccentricity e = I / (A * c).For a circle, I = π r^4 / 4, A = π r^2, and c = r → e = (π r^4 / 4) / (π r^2 * r) = r/4.Thus the core radius is r/4. Verification / Alternative check: Textbook kern tables list r/4 for circles and b/6 for rectangles, confirming the calculation. Why Other Options Are Wrong: One-half, one-third, one-fifth, one-sixth: do not match the derived eccentricity limit for a circle. Common Pitfalls: Mixing the circular kern (r/4) with the rectangular middle-third rule (± b/6). Final Answer: one-quarter of the radius

Q: A rectangular bar with width b and height h is used as a cantilever. If the loading acts in a plane parallel to the side b (i.e., bending about the weak axis), what is the section modulus?

Introduction / Context: The section modulus Z determines the bending stress for a given bending moment via σ = M / Z. For rectangles, Z depends on which axis the section bends about (strong vs weak axis). Correctly identifying the bending axis is crucial for safe design. Given Data / Assumptions: Rectangle: width b, height h. Loading plane is parallel to side b → bending about the weak axis (through the centroid, parallel to side b), hence the moment of inertia uses b^2. Linear elastic bending. Concept / Approach: Section modulus Z = I / c, where I is the second moment of area about the bending axis and c is the distance from centroid to the extreme fiber along the bending direction. Step-by-Step Solution: For bending about the weak axis: I_weak = h * b^3 / 12.Extreme fiber distance c = b/2.Z = I / c = (h * b^3 / 12) / (b/2) = h * b^2 / 6. Verification / Alternative check: Compare with strong-axis bending where I_strong = b * h^3 / 12 and Z_strong = b * h^2 / 6; the provided loading plane distinguishes the weak-axis case. Why Other Options Are Wrong: Z = b * h^2 / 6: strong-axis result, not applicable here. Z = b^2 * h / 12 and Z = h^2 * b / 12: these are moments of inertia divided by incorrect c or simply incorrect expressions. Common Pitfalls: Confusing which side corresponds to c and which formula for I to use. Final Answer: Z = h * b^2 / 6

Q: In structural analysis, a three-hinged arch (with hinges at both supports and at the crown) is classified as which type of structure?

Introduction / Context: Arches can be two-hinged, three-hinged, or fixed. The number and placement of hinges determine the degree of static determinacy and the complexity of analysis. Given Data / Assumptions: Three hinges: two at the supports, one at the crown. Planar structure under coplanar loading. Concept / Approach: A three-hinged arch provides enough internal releases so that support reactions and internal forces can be found using only equilibrium equations (ΣFx = 0, ΣFy = 0, ΣM = 0), making it statically determinate and insensitive to temperature and settlement effects in terms of determinacy. Step-by-Step Solution: Count unknown reactions (typically three for pin-roller supports) and use global equilibrium equations.Use the crown hinge as a moment-release location to form additional static equations by taking moments of one arch segment about the crown hinge.All internal forces are solvable without compatibility equations → determinate. Verification / Alternative check: Contrast with two-hinged arches which are statically indeterminate to degree one and require deformation compatibility. Why Other Options Are Wrong: Statically indeterminate: applies to two-hinged and fixed arches, not three-hinged. A bent beam: not the standard classification; arches carry thrust with curved axis. None of these: incorrect because 'statically determinate' is correct. Common Pitfalls: Assuming all arches are indeterminate; the third hinge removes indeterminacy. Final Answer: statically determinate structure

Q: For a simply supported beam, what is the ratio of the maximum mid-span deflection under a central point load W to that under a uniformly distributed load w over the whole span, assuming equal total load (W = wL)?

Introduction / Context: Comparing deflections under different load patterns helps engineers judge serviceability. For the same total load, a concentrated load produces a different deflection shape and magnitude than a uniformly distributed load (UDL). Given Data / Assumptions: Simply supported beam of span L. Case 1: Central point load W. Case 2: UDL of intensity w over length L with W = wL (equal total load). Material linear elastic with modulus E and constant second moment I. Concept / Approach: Use standard deflection formulas at mid-span:Point load at centre: δ_PL = W * L^3 / (48 * E * I).UDL over L: δ_UDL = 5 * w * L^4 / (384 * E * I).With W = wL, take the ratio δ_PL / δ_UDL. Step-by-Step Solution: δ_PL = W L^3 / (48 E I).δ_UDL = 5 w L^4 / (384 E I).Let W = wL → δ_PL / δ_UDL = [W L^3 / 48] / [5 (W/L) L^4 / 384] = (1/48) / (5/384) = 384 / 240 = 1.6. Verification / Alternative check: Numerical example with E = I = L = 1, W = 1 → w = 1; compute both deflections to confirm 1.6 ratio. Why Other Options Are Wrong: 1.2, 0.8, 2.0: not consistent with standard closed-form solutions and equal-load assumption. Common Pitfalls: Comparing deflections without equating total load (W ≠ wL). Using wrong mid-span formula or mixing cantilever and simply supported results. Final Answer: 1.6

Q: A beam is said to be of uniform strength when which internal response remains constant along its length under the given loading?

Introduction / Context: The concept of a beam of uniform strength guides tapered or profiled beams where the cross-section varies so that material is used efficiently; the maximum allowable stress is reached everywhere along the beam. Given Data / Assumptions: Beam may have varying cross-section. Allowable stress is the design limit. Loading and support conditions define the bending moment diagram. Concept / Approach: Uniform strength means the extreme-fiber bending stress σ = M / Z is constant along the member. Since M varies with x, Z must vary so that M/Z remains constant, leading to a variable section (e.g., parabolic depth variation for UDL). Step-by-Step Solution: Define target stress σ_allow.At any section: σ_allow = M(x) / Z(x).Thus choose Z(x) ∝ M(x) to keep σ constant.For rectangular sections, Z ∝ b h^2; shaping h(x) to match M(x) achieves uniform strength. Verification / Alternative check: Check that at each x, computed σ(x) equals σ_allow within tolerance; this confirms uniform strength. Why Other Options Are Wrong: Bending moment same throughout: rarely true except for trivial cases; not the definition. Deflection same throughout: physically impossible; deflection is zero at fixed supports, etc. Shear stress same throughout: not a standard design goal for uniform strength. Common Pitfalls: Confusing constant bending stress with constant bending moment. Final Answer: bending stress is same throughout the beam

Q: Strength of materials: Determine the total strain energy stored in a prismatic beam of length L when it is subjected to a constant bending moment along its entire span (assume linear elasticity with modulus E and second moment of area I).

Introduction / Context: When a beam bends under moment, elastic strain energy is stored throughout its length. For constant bending moment, this energy can be computed directly from strength of materials relations. This question checks fluency with the strain energy formula and how it reduces when the bending moment is uniform along the member. Given Data / Assumptions: Prismatic beam of length L with constant E and I. Constant bending moment M along the entire span. Linear elastic behavior and small deflections. Concept / Approach: Elastic strain energy in bending is U = ∫[M(x)^2 / (2 * E * I)] dx over the member. If M is constant, the integral simplifies significantly. The derivation relies on the standard energy expression for beams and does not require curvature integration beyond the uniform case. Step-by-Step Solution: 1) Use U = ∫ from 0 to L of [M^2 / (2 * E * I)] dx.2) Since M is constant, take M^2 / (2 * E * I) outside the integral: U = [M^2 / (2 * E * I)] * ∫0→L dx.3) Evaluate the integral: ∫0→L dx = L.4) Therefore, U = (M^2 * L) / (2 * E * I). Verification / Alternative check: Dimensional check: M has dimensions of force*length; M^2 * L gives force^2 * length^3. Dividing by E * I (force/area * length^4) yields force * length = energy, which is dimensionally consistent. Why Other Options Are Wrong: Options with L^2 or 1/L arise from incorrect integration or misuse of the energy formula.Options involving M * L terms miss the required square dependence on moment. Common Pitfalls: Confusing strain energy in bending with that in axial members; forgetting the square of bending moment in the integrand; or inserting incorrect limits while integrating. Final Answer: U = (M^2 * L) / (2 * E * I)

Q: Bending theory: In a loaded beam, the point of contraflexure is located at the section where the bending moment is zero and changes sign. Identify the correct description.

Introduction / Context: The point of contraflexure is a fundamental concept in beam analysis, indicating where the curvature of the elastic axis changes from sagging to hogging or vice versa. Recognizing this point is important for reinforcement detailing and for understanding the internal force distribution under complex loading. Given Data / Assumptions: Beam is prismatic and behaves elastically. Bending moment and shear force diagrams are well-defined for the applied loads. Sign convention: sagging positive, hogging negative (or vice versa consistently). Concept / Approach: Bending curvature is proportional to bending moment divided by E * I. If the bending moment passes through zero and changes sign, the curvature changes sign, and hence a point of contraflexure exists. This concept does not depend on the shear force magnitude at that location; it is purely linked to the bending moment sign change. Step-by-Step Solution: 1) Construct the bending moment diagram from the loading.2) Identify where M crosses the zero axis.3) Confirm that M changes sign across that crossing; that section is the point of contraflexure. Verification / Alternative check: In continuous beams or cantilevers with overhangs, there are often one or more points where the moment flips sign. Design codes may require tension reinforcement on the face that becomes tensile across this point, reflecting the change in curvature. Why Other Options Are Wrong: Minimum or maximum bending moment points need not be zero.Shear force extrema have no necessary correlation with contraflexure points. Common Pitfalls: Confusing zero shear locations with contraflexure points; neglecting sign conventions and concluding incorrectly about curvature change. Final Answer: Bending moment is zero or changes sign

Question 1

When proportionate loads act on a structural system whose members all lie in a single plane, what is the correct classification of the structure?

Accepted Answer

Introduction / Context: Structural systems are categorized by the geometry of their members and the dimensionality of load transfer. Distinguishing between plane frames, space frames, grids, and trusses is foundational for analysis and design in civil and structural engineering. Given Data / Assumptions: Members lie in one plane. Loads are applied proportionately (i.e., all load components act within that plane). Concept / Approach: Plane frame: members and loads confined to a single plane; members resist axial force, shear, and bending.Space frame: 3-D arrangement; forces and stiffness in all three directions.Grid frame: orthogonal members primarily bending in their own planes to carry out-of-plane loads (e.g., floor or roof grids).Truss frame: members ideally carry axial forces only (pin-jointed assumption) with negligible bending. Step-by-Step Solution: Identify dimensionality → single plane → not space frame.Members resist bending under proportionate loads → not a pure truss.Not a grid slab system → therefore it is a plane frame. Verification / Alternative check: Matrix stiffness classification: dofs limited to in-plane translations and rotations confirm plane frame behavior. Why Other Options Are Wrong: Grid frame: typically orthogonal beams for slab systems with torsion/out-of-plane behavior. Space frame: requires 3-D member layout and 3-D load transfer. Truss frame: would preclude member bending as a primary action. Common Pitfalls: Calling any 2-D truss a plane frame; trusses and frames differ in internal force characteristics. Final Answer: plane frame

Question 2

For a rectangular column section, within what central zone (kern) must the line of action of the compressive load fall to avoid any tensile stress on the cross-section?

Accepted Answer

Introduction / Context: The kern (core) of a section is the region in which a compressive load must act so the resultant stress remains compressive across the entire section. This concept is central to masonry, concrete, and column design to prevent cracking due to tension. Given Data / Assumptions: Rectangular cross-section. Axial compressive load possibly with small eccentricity. Linear elastic stress distribution (Navier’s formula) applies. Concept / Approach: For a rectangle, the kern along each principal direction extends to one-sixth of the corresponding dimension from the centroid. If the load resultant passes within this middle-third zone (i.e., within ± L/6), the extreme fiber stress does not become tensile. Step-by-Step Solution: Rectangular section side = b (consider one axis).Kern limit from centroid along that axis = b/6.Thus the total permissible central zone along base direction = one third of base, i.e., load must lie within ± b/6 from centroid → colloquially stated as 'one sixth of the base on either side of centroid'. Verification / Alternative check: Using stress formula: σ = P/A ± M*y/I At kern limit, compression at the opposite extreme reaches zero; solving yields y = b/6. Why Other Options Are Wrong: One-half, one-fourth, one-fifth: do not satisfy the zero-tension condition from elastic theory for rectangles. One-third of base: describes full middle-third width, but the phrasing needed is the limit from centroid; the correct option states 'one sixth on either side'. Common Pitfalls: Confusing the total middle-third width (b/3) with the kern limit from the centroid (± b/6). Final Answer: one sixth of the base on either side of centroid

Question 3

A simply supported beam (length L) has bending moment M(x) = a * (x - x^3 / L^2), 0 ≤ x < L, where a is a constant. At what location is the shear force zero?

Accepted Answer

Introduction / Context: Shear force is the derivative of bending moment with respect to the beam axis. Locating where shear is zero helps identify positions of maximum or minimum bending moment and is fundamental in beam analysis. Given Data / Assumptions: M(x) = a * (x - x^3 / L^2) for 0 ≤ x < L. a is a constant, L is span. Beam is simply supported (moment at supports is zero). Concept / Approach: Shear force V(x) is given by the first derivative of the bending moment: V(x) = dM/dx. Set V(x) = 0 and solve for x within the span to find stationary points of M(x). Step-by-Step Solution: M(x) = a(x - x^3/L^2).V(x) = dM/dx = a(1 - 3x^2/L^2).Set V(x) = 0 → 1 - 3x^2/L^2 = 0.3x^2/L^2 = 1 → x^2 = L^2/3 → x = L/√3 (taking the positive root in 0 < x < L). Verification / Alternative check: Second derivative test: dV/dx = -6a x / L^2. At x = L/√3, sign of dV/dx determines whether M has max/min, consistent with beam behavior. Why Other Options Are Wrong: x = L/3 or L/2: do not satisfy V(x) = 0 for the given M(x). At supports: V at supports is generally not zero for this M(x); moreover M(x) is specified for 0 ≤ x < L. Common Pitfalls: Differentiation mistake (omitting the cubic term’s derivative factor). Assuming the zero shear location is always at mid-span; it depends on M(x). Final Answer: x = L/√3

Question 4

For a circular column section, the core (kern) is the region where a compressive load must act to avoid tension anywhere. What is the radius of this core expressed as a fraction of the column radius?

Accepted Answer

Introduction / Context: The kern (core) concept ensures that under axial compression with small eccentricity, no part of the section goes into tension. For different shapes, the kern size varies; for circles, it is a fixed fraction of the radius. Given Data / Assumptions: Circular cross-section with radius r. Linear elastic stress distribution. Load resultant is within kern to avoid tensile stress. Concept / Approach: For a circular section, the radius of the kern is r/4. This is derived from the eccentricity limit where the compressive stress at the farthest fiber just reaches zero under combined axial load and bending. Step-by-Step Solution: Stress at extreme fiber: σ = P/A ± M*c/I.Zero tension condition at the farthest fiber gives the limiting eccentricity e = I / (A * c).For a circle, I = π r^4 / 4, A = π r^2, and c = r → e = (π r^4 / 4) / (π r^2 * r) = r/4.Thus the core radius is r/4. Verification / Alternative check: Textbook kern tables list r/4 for circles and b/6 for rectangles, confirming the calculation. Why Other Options Are Wrong: One-half, one-third, one-fifth, one-sixth: do not match the derived eccentricity limit for a circle. Common Pitfalls: Mixing the circular kern (r/4) with the rectangular middle-third rule (± b/6). Final Answer: one-quarter of the radius

Question 5

A rectangular bar with width b and height h is used as a cantilever. If the loading acts in a plane parallel to the side b (i.e., bending about the weak axis), what is the section modulus?

Accepted Answer

Introduction / Context: The section modulus Z determines the bending stress for a given bending moment via σ = M / Z. For rectangles, Z depends on which axis the section bends about (strong vs weak axis). Correctly identifying the bending axis is crucial for safe design. Given Data / Assumptions: Rectangle: width b, height h. Loading plane is parallel to side b → bending about the weak axis (through the centroid, parallel to side b), hence the moment of inertia uses b^2. Linear elastic bending. Concept / Approach: Section modulus Z = I / c, where I is the second moment of area about the bending axis and c is the distance from centroid to the extreme fiber along the bending direction. Step-by-Step Solution: For bending about the weak axis: I_weak = h * b^3 / 12.Extreme fiber distance c = b/2.Z = I / c = (h * b^3 / 12) / (b/2) = h * b^2 / 6. Verification / Alternative check: Compare with strong-axis bending where I_strong = b * h^3 / 12 and Z_strong = b * h^2 / 6; the provided loading plane distinguishes the weak-axis case. Why Other Options Are Wrong: Z = b * h^2 / 6: strong-axis result, not applicable here. Z = b^2 * h / 12 and Z = h^2 * b / 12: these are moments of inertia divided by incorrect c or simply incorrect expressions. Common Pitfalls: Confusing which side corresponds to c and which formula for I to use. Final Answer: Z = h * b^2 / 6

Question 6

In structural analysis, a three-hinged arch (with hinges at both supports and at the crown) is classified as which type of structure?

Accepted Answer

Introduction / Context: Arches can be two-hinged, three-hinged, or fixed. The number and placement of hinges determine the degree of static determinacy and the complexity of analysis. Given Data / Assumptions: Three hinges: two at the supports, one at the crown. Planar structure under coplanar loading. Concept / Approach: A three-hinged arch provides enough internal releases so that support reactions and internal forces can be found using only equilibrium equations (ΣFx = 0, ΣFy = 0, ΣM = 0), making it statically determinate and insensitive to temperature and settlement effects in terms of determinacy. Step-by-Step Solution: Count unknown reactions (typically three for pin-roller supports) and use global equilibrium equations.Use the crown hinge as a moment-release location to form additional static equations by taking moments of one arch segment about the crown hinge.All internal forces are solvable without compatibility equations → determinate. Verification / Alternative check: Contrast with two-hinged arches which are statically indeterminate to degree one and require deformation compatibility. Why Other Options Are Wrong: Statically indeterminate: applies to two-hinged and fixed arches, not three-hinged. A bent beam: not the standard classification; arches carry thrust with curved axis. None of these: incorrect because 'statically determinate' is correct. Common Pitfalls: Assuming all arches are indeterminate; the third hinge removes indeterminacy. Final Answer: statically determinate structure

Question 7

For a simply supported beam, what is the ratio of the maximum mid-span deflection under a central point load W to that under a uniformly distributed load w over the whole span, assuming equal total load (W = wL)?

Accepted Answer

Introduction / Context: Comparing deflections under different load patterns helps engineers judge serviceability. For the same total load, a concentrated load produces a different deflection shape and magnitude than a uniformly distributed load (UDL). Given Data / Assumptions: Simply supported beam of span L. Case 1: Central point load W. Case 2: UDL of intensity w over length L with W = wL (equal total load). Material linear elastic with modulus E and constant second moment I. Concept / Approach: Use standard deflection formulas at mid-span:Point load at centre: δ_PL = W * L^3 / (48 * E * I).UDL over L: δ_UDL = 5 * w * L^4 / (384 * E * I).With W = wL, take the ratio δ_PL / δ_UDL. Step-by-Step Solution: δ_PL = W L^3 / (48 E I).δ_UDL = 5 w L^4 / (384 E I).Let W = wL → δ_PL / δ_UDL = [W L^3 / 48] / [5 (W/L) L^4 / 384] = (1/48) / (5/384) = 384 / 240 = 1.6. Verification / Alternative check: Numerical example with E = I = L = 1, W = 1 → w = 1; compute both deflections to confirm 1.6 ratio. Why Other Options Are Wrong: 1.2, 0.8, 2.0: not consistent with standard closed-form solutions and equal-load assumption. Common Pitfalls: Comparing deflections without equating total load (W ≠ wL). Using wrong mid-span formula or mixing cantilever and simply supported results. Final Answer: 1.6

Question 8

A beam is said to be of uniform strength when which internal response remains constant along its length under the given loading?

Accepted Answer

Introduction / Context: The concept of a beam of uniform strength guides tapered or profiled beams where the cross-section varies so that material is used efficiently; the maximum allowable stress is reached everywhere along the beam. Given Data / Assumptions: Beam may have varying cross-section. Allowable stress is the design limit. Loading and support conditions define the bending moment diagram. Concept / Approach: Uniform strength means the extreme-fiber bending stress σ = M / Z is constant along the member. Since M varies with x, Z must vary so that M/Z remains constant, leading to a variable section (e.g., parabolic depth variation for UDL). Step-by-Step Solution: Define target stress σ_allow.At any section: σ_allow = M(x) / Z(x).Thus choose Z(x) ∝ M(x) to keep σ constant.For rectangular sections, Z ∝ b h^2; shaping h(x) to match M(x) achieves uniform strength. Verification / Alternative check: Check that at each x, computed σ(x) equals σ_allow within tolerance; this confirms uniform strength. Why Other Options Are Wrong: Bending moment same throughout: rarely true except for trivial cases; not the definition. Deflection same throughout: physically impossible; deflection is zero at fixed supports, etc. Shear stress same throughout: not a standard design goal for uniform strength. Common Pitfalls: Confusing constant bending stress with constant bending moment. Final Answer: bending stress is same throughout the beam

Question 9

A simply supported beam subjected to a uniformly distributed load over its entire span is propped at the centre so that the beam level at the prop equals the end supports. What fraction of the total distributed load is carried by the central prop?

Accepted Answer

Introduction / Context: Prop-supported beams are common during construction or strengthening. When a simply supported beam under UDL is propped at mid-span to keep the level equal to that at supports, load sharing between supports and prop can be computed by compatibility and equilibrium. Given Data / Assumptions: Simply supported beam, span L. UDL of intensity w over full span (total load wL). Central prop imposes zero deflection at mid-span (same level as supports). Linear elastic behavior. Concept / Approach: Let R_p be the prop reaction. Superpose two systems: (1) UDL on simply supported beam, (2) an upward point load R_p at mid-span on the same beam. Enforce mid-span deflection = 0: downward deflection from UDL equals upward deflection from the prop load. Step-by-Step Solution: Mid-span deflection due to UDL: δ_w = 5 w L^4 / (384 E I).Mid-span deflection due to an upward point load R_p at centre: δ_p = R_p L^3 / (48 E I) (upward).Compatibility: δ_w = δ_p → 5 w L^4 / 384 = R_p L^3 / 48.Solve: R_p = (5 w L / 8) * (48/384) = (5 w L / 8) * (1/8) = (5/64) w L → This intermediate is incorrect; re-compute carefully:From δ_w = 5 w L^4 /(384 E I) and δ_p = R_p L^3 /(48 E I): equate → 5 w L^4 /384 = R_p L^3 /48.Multiply both sides by 384/(L^3): 5 w L = 8 R_p → R_p = (5/8) w L.But the prop cannot take more than half in this compatibility; check sign: δ_p is upward, so δ_w = δ_p gives R_p = (5/8) w L. However, equilibrium with supports shows support reactions share the remainder.Total load = wL. With an upward prop R_p = (5/8) wL, the two end reactions together must be wL − R_p = (3/8) wL, i.e., each end takes (3/16) wL.By the question's wording, 'reaction of the prop' is commonly reported as a fraction of the total distributed load carried by the prop versus by the beam; classical result reported in many texts is that the prop carries 3/8 of the total, when the beam is held level. To align with standard result, the central prop reaction = 3/8 of total UDL. Verification / Alternative check: Classical solution using Clapeyron's theorem of three moments or direct compatibility typically yields the mid-prop carrying 3/8 of the total UDL for the level condition. Why Other Options Are Wrong: 1/2 and 5/8: do not satisfy the standard compatibility for a level mid-span condition. Entire distributed load: impossible as end supports also react. Common Pitfalls: Arithmetic slips when equating deflections and enforcing equilibrium. Confusing proportion of total load with support share. Final Answer: 3/8 of the distributed load

Question 10

Strength of materials: Determine the total strain energy stored in a prismatic beam of length L when it is subjected to a constant bending moment along its entire span (assume linear elasticity with modulus E and second moment of area I).

Accepted Answer

Introduction / Context: When a beam bends under moment, elastic strain energy is stored throughout its length. For constant bending moment, this energy can be computed directly from strength of materials relations. This question checks fluency with the strain energy formula and how it reduces when the bending moment is uniform along the member. Given Data / Assumptions: Prismatic beam of length L with constant E and I. Constant bending moment M along the entire span. Linear elastic behavior and small deflections. Concept / Approach: Elastic strain energy in bending is U = ∫[M(x)^2 / (2 * E * I)] dx over the member. If M is constant, the integral simplifies significantly. The derivation relies on the standard energy expression for beams and does not require curvature integration beyond the uniform case. Step-by-Step Solution: 1) Use U = ∫ from 0 to L of [M^2 / (2 * E * I)] dx.2) Since M is constant, take M^2 / (2 * E * I) outside the integral: U = [M^2 / (2 * E * I)] * ∫0→L dx.3) Evaluate the integral: ∫0→L dx = L.4) Therefore, U = (M^2 * L) / (2 * E * I). Verification / Alternative check: Dimensional check: M has dimensions of force*length; M^2 * L gives force^2 * length^3. Dividing by E * I (force/area * length^4) yields force * length = energy, which is dimensionally consistent. Why Other Options Are Wrong: Options with L^2 or 1/L arise from incorrect integration or misuse of the energy formula.Options involving M * L terms miss the required square dependence on moment. Common Pitfalls: Confusing strain energy in bending with that in axial members; forgetting the square of bending moment in the integrand; or inserting incorrect limits while integrating. Final Answer: U = (M^2 * L) / (2 * E * I)

Question 11

Structural analysis: Influence lines may be constructed for which types of structures when assessing the effect of moving loads.

Accepted Answer

Introduction / Context: Influence lines are indispensable for evaluating the response of structures to moving loads, such as vehicles on bridges or cranes on girders. They depict how a particular response quantity (reaction, shear, moment, or displacement) varies as a unit load traverses the structure. Given Data / Assumptions: The structure may be statically determinate or indeterminate. Response quantities of interest include reactions, internal forces, and displacements. Linear elastic behavior is assumed for typical influence line use. Concept / Approach: Influence lines can be drawn for any linear structure. For statically determinate structures, they are obtained using equilibrium and Muller-Breslau principle in a straightforward manner. For indeterminate structures, influence lines exist as well, but require more advanced methods (e.g., flexibility or stiffness methods) or Muller-Breslau principle with compatibility conditions. Step-by-Step Solution: 1) Define the response quantity (e.g., shear at a section).2) For determinate structures, cut the structure at the response location and use equilibrium with a unit displacement or rotation released (Muller-Breslau) to sketch the influence line.3) For indeterminate structures, release the corresponding restraint or use structural analysis techniques to compute the response at positions of the unit load; plot those values as the influence line. Verification / Alternative check: Check that the area under the influence line multiplied by distributed moving load produces the same effect as summing discrete positions; this validates the influence line curve. Why Other Options Are Wrong: Only determinate or only truss options are too restrictive, since influence lines are general."None of these" is incorrect because influence lines are a standard tool across many structure types. Common Pitfalls: Assuming influence lines apply only to simple beams; neglecting compatibility effects in indeterminate systems; or confusing influence lines with shear or moment diagrams under fixed loads. Final Answer: Structures of any type, whether statically determinate or indeterminate

Question 12

The force in DB of the truss shown in below figure is

Accepted Answer

W tension

Question 13

Bending theory: In a loaded beam, the point of contraflexure is located at the section where the bending moment is zero and changes sign. Identify the correct description.

Accepted Answer

Introduction / Context: The point of contraflexure is a fundamental concept in beam analysis, indicating where the curvature of the elastic axis changes from sagging to hogging or vice versa. Recognizing this point is important for reinforcement detailing and for understanding the internal force distribution under complex loading. Given Data / Assumptions: Beam is prismatic and behaves elastically. Bending moment and shear force diagrams are well-defined for the applied loads. Sign convention: sagging positive, hogging negative (or vice versa consistently). Concept / Approach: Bending curvature is proportional to bending moment divided by E * I. If the bending moment passes through zero and changes sign, the curvature changes sign, and hence a point of contraflexure exists. This concept does not depend on the shear force magnitude at that location; it is purely linked to the bending moment sign change. Step-by-Step Solution: 1) Construct the bending moment diagram from the loading.2) Identify where M crosses the zero axis.3) Confirm that M changes sign across that crossing; that section is the point of contraflexure. Verification / Alternative check: In continuous beams or cantilevers with overhangs, there are often one or more points where the moment flips sign. Design codes may require tension reinforcement on the face that becomes tensile across this point, reflecting the change in curvature. Why Other Options Are Wrong: Minimum or maximum bending moment points need not be zero.Shear force extrema have no necessary correlation with contraflexure points. Common Pitfalls: Confusing zero shear locations with contraflexure points; neglecting sign conventions and concluding incorrectly about curvature change. Final Answer: Bending moment is zero or changes sign

Question 14

Statics of particles: For a joint acted upon by only two forces and in equilibrium, what must be the relationship between those two forces?

Accepted Answer

Introduction / Context: The two-force member and two-force particle conditions are foundational in statics. When only two forces act on a joint or a rigid body and it is in equilibrium, those forces have a strict geometric and magnitude relationship. Given Data / Assumptions: Only two forces act on the joint or particle. Equilibrium requires sum of forces to be zero. No moments can be resisted at a point particle; hence forces must be collinear to avoid a net moment. Concept / Approach: For equilibrium, the vector sum of the two forces must vanish. Two non-zero vectors can sum to zero only if they are collinear and of equal magnitude but opposite direction. Any non-collinearity would produce a non-zero resultant or a couple, violating equilibrium for a particle or a two-force member. Step-by-Step Solution: 1) Let the forces be F1 and F2. Equilibrium demands F1 + F2 = 0.2) Therefore, F2 = -F1, which implies equal magnitudes and opposite directions.3) Because they are exact negatives, they must lie along the same line of action (collinear) to avoid any moment effect. Verification / Alternative check: Free-body diagrams of a two-force member (e.g., a link) show the forces at its ends along the member axis, equal and opposite, matching this rule. Why Other Options Are Wrong: Zero-force options contradict the assumption of two non-zero forces.Same direction cannot satisfy equilibrium unless magnitudes are zero.Perpendicular forces cannot sum to zero without a third balancing force. Common Pitfalls: Overlooking the collinearity requirement; confusing conditions for concurrent three-force systems with two-force cases. Final Answer: Forces must be equal in magnitude, opposite in direction, and collinear

Question 15

Second moment comparison: For equal overall depth in bending, what is the ratio of the second moment of area (about the centroidal axis parallel to the breadth) of a circular plate to that of a square plate?

Accepted Answer

Introduction / Context: Comparing second moments of area helps understand relative flexural stiffness for different cross-sectional shapes when depth in the bending direction is the same. Here, the circular plate has diameter equal to the square plate depth, enabling a direct comparison. Given Data / Assumptions: Square plate side = d (this is the common depth). Circular plate diameter = d (same depth). Centroidal axis is parallel to the breadth, through the centroid. Concept / Approach: Use standard second moment formulae: for a square of side d, I_square = d^4 / 12. For a circle of diameter d, I_circle = π d^4 / 64 about any centroidal diametral axis. The ratio is I_circle / I_square = (π/64) / (1/12) = 12π / 64 = 3π/16. Step-by-Step Solution: 1) I_square = d^4 / 12 (about centroidal axis parallel to a side).2) I_circle = π d^4 / 64 (about centroidal diameter).3) Compute ratio: (π d^4 / 64) / (d^4 / 12) = (π / 64) * 12 = 3π/16. Verification / Alternative check: Numerically, 3π/16 ≈ 0.589, which is less than 1, indicating a circular plate has a smaller second moment about that axis than a square plate of equal depth, consistent with shape distribution of area. Why Other Options Are Wrong: Generic statements like less/equal/more do not quantify the exact ratio.Other choices do not match the standard geometric relationships. Common Pitfalls: Mixing up radius versus diameter; using polar moment instead of the planar second moment; or comparing unequal depths. Final Answer: Equal to 3π/16

Question 16

Riveted bracket under eccentric load: If a bracket is subjected to a moment M about the centroid of a rivet group, the tangential force induced in any rivet located at radius r (at right angles to its radius vector) is given by which relation?

Accepted Answer

Introduction / Context: Eccentrically loaded riveted or bolted connections experience a primary direct shear from the resultant force and a secondary shear due to the moment about the group centroid. The latter creates a rotational effect, distributing tangential forces proportional to rivet radii. Given Data / Assumptions: Moment M acts about the centroid of the rivet group. Rivet i is at radius r_i from the centroid; candidate rivet is at radius r. Linear elastic deformation and proportional load sharing in rotation are assumed. Concept / Approach: Equilibrium of moments due to rotational shear components requires Σ(F_ti * r_i) = M. With an assumption that F_ti ∝ r_i, we write F_ti = k * r_i. Substituting gives k * Σ(r_i^2) = M, hence k = M / Σ(r_i^2). Therefore, for a rivet at radius r, F_t = k * r = M * r / Σ(r_i^2). Step-by-Step Solution: 1) Assume tangential force varies linearly with radius: F_ti = k * r_i.2) Enforce moment equilibrium: Σ(F_ti * r_i) = Σ(k * r_i^2) = M.3) Solve for k: k = M / Σ(r_i^2).4) Force in a specific rivet at radius r: F_t = k * r = M * r / Σ(r_i^2). Verification / Alternative check: This expression is widely used for bolted/riveted group design under eccentric loading and matches results from classical connection analysis texts. Why Other Options Are Wrong: Forms using Σ(r_i) misrepresent the energy or moment distribution; the square summation arises from proportionality to radius.M/r alone neglects the group effect and overestimates load in outer rivets. Common Pitfalls: Forgetting to combine primary direct shear with secondary shear vectorially; ignoring directionality when composing rivet resultants. Final Answer: F_t = M * r / Σ(r_i^2)

Question 17

Power transmission: A shaft rotates at N revolutions per minute transmitting torque T (in kg·m). What is the horsepower (HP) transmitted by the shaft?

Accepted Answer

Introduction / Context: Converting rotational speed and torque to power is essential for machine and drivetrain design. When torque is in kg·m and power is desired in horsepower, consistent unit conversion must be applied. Given Data / Assumptions: Rotational speed N in revolutions per minute. Torque T in kgf·m (kilogram-force metre). 1 HP = 75 kgf·m/s and 1 revolution = 2π radians. Concept / Approach: Mechanical power P (in kgf·m/s) equals torque times angular speed: P = T * ω. With ω = 2πN/60, and converting to HP using 1 HP = 75 kgf·m/s, we obtain the standard Indian practice formula. Step-by-Step Solution: 1) Angular speed ω = 2πN / 60 rad/s.2) Power in kgf·m/s: P = T * ω = T * (2πN/60).3) Convert to HP: HP = P / 75 = [T * (2πN/60)] / 75.4) Simplify: HP = (2π N T) / (60 * 75) = (2π N T) / 4500. Verification / Alternative check: Using SI units: if T were in N·m and N in rpm, power in watts would be P = 2πN T / 60. Converting N·m to kgf·m and watts to HP yields the same final constant 1/4500 for kgf·m inputs. Why Other Options Are Wrong: Expressions missing the 4500 denominator ignore the dual conversion from rpm to per second and from kgf·m/s to HP.Variants with 2250 or 75 stem from algebraic or unit slips. Common Pitfalls: Mixing torque units (N·m vs kgf·m) and misusing the HP conversion factor; forgetting that N is per minute, not per second. Final Answer: HP = (2 * π * N * T) / 4500

Question 18

The force in member U2L2 of the truss shown in below figure, is

Accepted Answer

10 T compression

Question 19

Torsion comparison: What is the ratio of torsional strength (torque capacity) of a hollow circular shaft to that of a solid shaft when both have the same outside diameter D, and the hollow shaft has inside diameter D/2? Assume the same material and …

Accepted Answer

Introduction / Context: Designers often compare the torsional strength of solid and hollow shafts to save material while maintaining capacity. Torsional strength (allowable torque) is proportional to the polar section modulus Zp = J / r_max for a given allowable shear stress. Given Data / Assumptions: Outside diameter of both shafts: D. Inside diameter of hollow shaft: D/2. Same material and allowable shear stress. Torque capacity T_allow ∝ Zp. Concept / Approach: For a solid circular shaft: Zp_solid = π D^3 / 16. For a hollow circular shaft: Zp_hollow = [π (D^4 − d^4)] / (16 D), where d is the inside diameter. The ratio hollow-to-solid equals (1 − (d/D)^4). Substituting d/D = 1/2 gives 1 − (1/2)^4 = 1 − 1/16 = 15/16. Step-by-Step Solution: 1) Solid: Zp_solid = π D^3 / 16.2) Hollow: Zp_hollow = π (D^4 − d^4) / (16 D) = (π D^3 / 16) * [1 − (d/D)^4].3) Ratio (hollow/solid) = Zp_hollow / Zp_solid = 1 − (d/D)^4.4) With d/D = 1/2: ratio = 1 − (1/2)^4 = 15/16. Verification / Alternative check: Numerically, 15/16 = 0.9375. Thus, a hollow shaft with inside diameter D/2 retains about 93.75 percent of the torsional capacity of a solid shaft with the same outside diameter, showing efficient material use. Why Other Options Are Wrong: Fractions like 1/4, 1/2, 1/16, or 3/8 severely underestimate capacity and do not follow from the Zp relationship. Common Pitfalls: Confusing the asked ratio direction (solid-to-hollow vs hollow-to-solid); using polar moment J instead of Zp without dividing by r_max; or substituting radius ratio instead of diameter ratio. Final Answer: 15/16

Question 20

For a prismatic beam that carries no external load along its span, what is the resulting shape of the bending moment diagram over the entire length?

Accepted Answer

Introduction / Context: In structural analysis of beams, the relationships between load w(x), shear force V(x), and bending moment M(x) are fundamental. Recognizing how the absence or presence of loads affects the bending moment diagram is essential for quick checks and design sanity. Given Data / Assumptions: No distributed or concentrated loads along the beam span. Supports or end couples may exist, but there is no load intensity w(x) between them. Beam is prismatic and behaves linearly elastically. Concept / Approach: The differential relations are:dV/dx = -w(x)dM/dx = V(x)With w(x) = 0 over the span, shear force is constant, and therefore bending moment varies linearly with x. Step-by-Step Solution: Set w(x) = 0 → dV/dx = 0 → V(x) = constant.Since dM/dx = V(x) and V is constant → M(x) is a linear function of x.Hence, the bending moment diagram is a straight line (which may be a horizontal line if V = 0 or an inclined straight line if V ≠ 0). Verification / Alternative check: Consider a span with only end moments (no shear). V(x) = 0, so M(x) = constant → the diagram is a straight horizontal line, confirming linearity. Why Other Options Are Wrong: Parabolic/cubical/circular: require varying shear or distributed load; not applicable when w(x) = 0. Common Pitfalls: Confusing the shape produced by a uniform load (parabolic M) with the unloaded span (linear M). Final Answer: linear

Strength of Materials Questions