Aircraft Structures for Engineering Students-Solutions 7th. Edition by T.H.G. Megson | 9780128228685 | 0128228687 | Holooly

Aircraft Design

Aircraft Structures for Engineering Students-Solutions

1 SOLVED PROBLEMS

287 SOLVED PROBLEMS

Question: p.21.1

A wing spar has the dimensions shown in Fig. P.21.1 and carries a uniformly distributed load of 15 kN/m along its complete length. Each flange has a cross-sectional area of 500 mm² with the top flange being horizontal. If the flanges are assumed to resist all direct loads while the spar web is ...

Verified Answer:

Referring to Fig. P.21.1 the bending moment at sec...

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Question: 24.3

A three-flange wing section is stiffened by the wing rib shown in Fig. P.24.3. If the rib flanges and stiffeners carry all the direct loads while the rib panels are effective only in shear, calculate the shear flows in the panels and the direct loads in the rib flanges and stiffeners. ...

Verified Answer:

A three-flange wing section is statically determin...

Question: 24.2

Calculate the shear flows in the web panels and direct load in the flanges and stiffeners of the beam shown in Fig. P.24.2 if the web panels resist shear stresses only. ...

Verified Answer:

Referring to Fig. P.24.2 and considering the verti...

Question: 24.1

The beam shown in Fig. P.24.1 is simply supported at each end and carries a load of 6000 N. If all direct stresses are resisted by the flanges and stiffeners and the web panels are effective only in shear, calculate the distribution of axial load in the flange ABC, the stiffener BE, and the shear ...

Verified Answer:

From the overall equilibrium of the beam in Fig. S...

Question: 20.7

A rectangular section thin-walled beam of length L and breadth 3b, depth b, and wall thickness t is built-in at one end (Fig. P.20.7). The upper surface of the beam is subjected to a pressure which varies linearly across the breadth from a value p0 at edge AB to zero at edge CD. Note that the ...

Verified Answer:

The pressure loading is equivalent to a shear forc...

Question: 20.6

A cantilever, length L, has a hollow cross-section in the form of a doubly symmetric wedge, as shown in Fig. P.20.6. The chord line is of length c, wedge thickness is t, the length of a sloping side is a/2, and the wall thickness is constant and equal to t0. Uniform pressure distributions of the ...

Verified Answer:

At any section of the beam the applied loading is ...

Question: 21.4

If the vertical plane of symmetry in the beam of P.21.3 is swept back by 25° as shown in plan in Fig. P.21.4, the span of 3 m is retained and the 40 kN load is applied as in P.21.3, calculate the flange and stringer loads and the shear flow distribution at a section 1.5 m from the built-in end. ...

Verified Answer:

As in S.21.3 and referring to Figs. P.21.4, S.21.4...

Question: 29.5

The rectangular wing shown in Fig. P.29.5 has a constant torsional rigidity GJ and an aileron of constant chord. The aerodynamic center of the wing is at a constant distance ec ahead of the flexural axis, while the additional lift due to operation of the aileron acts along a line a distance hc aft ...

Verified Answer:

Since the additional lift due to operation of the ...

Question: 26.14

Determine the axial force in the flanges and web of the channel section shown in Fig. P.26.14 when it is subjected to a total axial force of 40 kN. The ply properties are El=140, 000 N/mm², Et=10,000 N/mm², Glt=5000 N/mm², and nlt=0.3. ...

Verified Answer:

The ply properties are identical to those of P.26....

Question: 27.13

Figure P.27.13 shows a portion of the undersurface of a wing comprising two outer longerons, two central stringers, and skin panels. The wing includes a cut-out for the undercarriage bay and may be assumed to be attached to a rigid bulkhead at its left-hand end. Aerodynamic calculations show that ...

Verified Answer:

Referring to Fig.S.27.13(a), the panel is symmetri...

Question: 27.12

The idealized cantilever beam shown in Fig. P.27.12 carries a uniformly distributed load of intensity w. Assuming that all direct stresses are carried by the booms while the panels are effective only in shear, determine the distribution of direct load in the central boom in the top cover. Young’s ...

Verified Answer:

The forces acting on the top cover of the box are ...

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